ML20141L972
| ML20141L972 | |
| Person / Time | |
|---|---|
| Site: | Farley  |
| Issue date: | 05/25/1971 |
| From: | BECHTEL CORP. |
| To: | |
| Shared Package | |
| ML19317C318 | List: |
| References | |
| NUDOCS 9706030275 | |
| Download: ML20141L972 (4) | |
Text
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D: sign BIsis for Tornado-GIntrated Missiles
- Joseph M. Fart:;y Nuclear Plant
, Enclosure - Attachment 4 Page 1 of 3 I
CTVIL A.4D STRI: Cit!RAL DESIGN CRITT.RTA
. *MfH M.l TAPLE'i tWCLEAR FLANT tartt 1 4,13Ik 2 AIAP.AMA PNER COMPANY BECHTEL CORPORATION i GAIT 1ER$RURC. MARY!AND
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Preps, red by: /'*
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i Mechtel Corporation, Engineer
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Approved by: ( 8L[Lt.u YI
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- nechtel C rporitten, Crneir $ .
Approvea,h : ,
M Hechtel Corporation. Project Esigid
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, Approved by i._ /. m t. . . J. -
Rechtel Corporationg*Chkf Engineer
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. . l R_EVIS T&*S t ,
WO. DATE DE.Sc1tIPTION ST unv -
O I - E -1*'lO ISSUED FOR DESIGN
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AAV' pp i <, 2 - i rio aevisv.D FOR PSAR AMENDMt.N73 GM AAV.i j 9M 5 25 i".71 REVIS"D FOR P! aR N/.ENDuENTS DSM AAVldi p$
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4 9706030275 970528 PDR ADOCK 05000348 9 PDR
. 1l l Drsign B: sis for Tornado G:n:rtted Missiles '
Joseph M. Fari:y Nucl:ar Plant !
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Enclosure - Attachment 4 :
Page 2 of 3 ge.rne.tures prot.ecting Cl-ns 1 equipetit uhtch asyrter a
expaseil to torn.ido minell. e util be of aut(tatens, ,
l thickness te preve nt missila penetration. The . depth -te
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i vhich .i given tornado missile 9f11 peneteate a senarety J
t watt may be calculated by use of the modified Petry 'formitsj as prencated la Nav Docks ?-31.
I This foruuta is gi, vee _: g i
Section 5.1.4.11 of the PSAR. Where required by.2aS1Fetjidg the inside surfaces of structures will be coveredMthW doch to contain any soelied pieces of concrete.sai@WM i
sult due to missile impact.
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l Except for Local crushtag at the etselle impses;aseaMahGst14lu adic stresses to restat the effects of tornahuil,N 1
i cent of the yleid of the reinforcing steel and ,$Spg the ultimate strength of the concrete.
I When cone'derlast load combinations and fastersi,the;WM i
factor is always equal to 1.0. ;
l
! se t ss te t.oad s, l AEC Puhilcation 7th 7024, " Nucle.1r Reactors and Earthquakas" se amplifiedhge13, j shaLl be used as the basic design zuide for satssic analysia. Serisestalidatantei accelerattan in one direction and vertical setanic acceleraties shall be'sensM 'l h act,gtmuttaneously. j
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4.3.1 Dedian of clails 1 St.ructures se amic Destan for sLL major Cinns 'l structures will be perfeemedintil,ising l ~ 1 dynamic analysin techniques. .[ ]
nriaretine Re ef 9 F,1r thena be (Fig. A-1. page 19)
Ilnrttanta L 'nroun,I acceteratton: 05m vertical remnul arceleration: .0333
-10
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D: sign BIsis for Torn:do-Gsnsrated Missiles i Jossph M. Fertsy Nucirr PI:nt Enclosure - Attachment 4 l
I Page S of 3 ,
j 4.2.i r.ru d.
All structures housing critical equipenest requires as assate.
j .a,e shutd s .f the re..t.r .haii ,e .esi .d for. m l
1eading (not coincident with accident er earthquaka) en.tne l .
! following basis: I i
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(a) Differential pressure will be applied as e 3 pet positiveE i !
-~ l (bursting) pressure securring in three seeendst l i
(b) Lateral force en the contaissneat wt11 be asamedidsjtisej j i
' force caused by a tornado funnel having a peripherai; tea @dit(R j
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wel-it7 of =0 h e4 .ger-rd ,regr u. . . ;s ,
- .ppitcable porti u hf wtad deetyn mothed deoerised
- mag l l
} reper so. 3269 vf.11 he used, particularly for;shapej g i i
i the previsiems for gust fastere and veristies'M.wthd.' l l veleesty with height will not' apply.
I l 'the average tormede design dypeste wind. Pressure is,,130; pes i
l based on an average wind veteetty of 300 mph. .' The;4yeasiqr
. wind pressure is satsulated from the fe11ewf.ag,equattegyf
. q = 0.002550 Y2 where.- g - pressure la psf I
.- ,. .tw .re.a is .,6 l
s (c) A tornade drives missile equivalest to a 11 feet long. pg of weed & Laches to diameter trave 11ag end.ee et a:spe4}M4 1
300 mph over the tutt hetsh: ofthestructure/erad000*
i-pound passenger auto, with a sostact area of 40 ft ',,eartM 1
at a speed of 50 mph not more ~ than 25 feet a@ greend,liisu 3 inch dtometer (!D) pipe 10 feet.long traveling end-en at LOO sph over the futi height of the structure'.
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Desiga B: sis f:r Tern do-G:n:rcted Missiles Joseph M. Farley Nuclear Plant Enclosure ATTACHMENT 5 O
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j Design Bcsis for Torntdo-Gen: rated Missiles ,
j Joseph M. Farisy Nuct:ar Plint l j ,
Enclosure - Attachment 5 i Page 1 of 65 ,
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- BC-TOP-3-A REVISION 3 l .
AUGUST 1974 I
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l, TORNADO AND EXTREME WIND ll i
DESIGN CRITERIA FOR l
!'; NUCLEAR POWER PLANTS ,
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BECHTEL POWER CORPORATION SAN FRANCISCO, CAllFORNIA i
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DIsign Basis for Tornado-G:nsrtted Missiles Joseph M. Ftrisy Nucirr Plant i gg,igcipure- Attachment 5 {
Page 2 of 65 i i
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.3 CAWLT: THIS REPORT RAS BERN PREPAJtED AND POR THE USE OF BECHTEL PONER CORPORATION AND ITS RELATED ENTITIES. ITS USE55Y OTNERS IS PERMITTED ONLY ON THE UNDERSTANDING
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p THAT THERE ARE NO REPRESENTATIONS OR ;
WARRANTIES, EXPRESSED OR IMPLIED, AS TO !
THE VALIDITY OF TIM INFORMATI0 '
CONCLUSIONSCONTAINEDHEREIN.f.OR h
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'I Orsign Basis for Tomado-Grntrated Missiles
- Jossph M. Farity Nucl
- ar Plant
' Enclosure - Attachment 5 4
Page 3 of 65 TOPICAL REPORT BC-TOP-3-A REVISION 3 i.
3 TORNADO AMD EXTREME WIND
'i naszam CazTzaIA Poa NUCLEAa POWER PIANTS i
Prepared by 1
J. V.. Rots l
G. C. K. Yeh W. Bertwell I
'l Approved by:
N. W. Wahl .
- chief Civil Engineer Thermal Power Organization !
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i Bechtel Power Corporation Issue Date: ' August 3 f 74 J
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!^ Drsign Bisis for Tomado-Gtntrated Missiles i Joseph M. Ferlsy Nucir r PI:nt Enclosure - Attachment 5 f Page 4 of 65 UNITED STATES l .
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skD - 1 ATOMIC' ENERGY COMMISSION
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! Mr, ohn V. Motowski ;
i Vi esident-Engineering' Power Corporation j 7 Seala Street s anciseo, California 94119 i
. Morouskis i The Regulatory staff has completed its zweiser of Bechtel Power
- corporation's Topical Report. DC6 TOP-3, Revision 3 dated August i 1974 and Nuclear entitled Power " Tornado *and Estress Wind Desism Criteria for Planta".
{ We conclude that the design criteria and l procedures described by this report are acceptable to the Regulatory
- staff and that 3C-Top-3, havision 3, is acceptable by reference in i applications for construction permits and operating licenses. A i summary of our evaluation is enclosed.
i j BC-TOP-3 does not provide all of the partinent tornado and estreme
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wind infornscion required by the Regulatory staff in its review of
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specific applications. Therafere, the suppleasatary infosmetion identiftad in the Regulatory Position of the enclosed Topical Raport Evaluation will have to be provided La individnal Safety Analysis Raports.
{
The staff does not intend to repeat its review of BC-TOF-3, Revision 3, when it appears as a reference in a particular license application.
- should maplatory criteria or reguistians change, such that our c.caciusions concerning BC- -3, Revisian 3, are invalidated, you will be notified and given opportunity to revise and resubmit your topical report for re sw, should you ao desire.
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D: sign B: sis for Tornido-G:n: rated Missiles i
Joseph M. Farley Nuciser Plant Enclosure- Attachment 5 Page 5 of 65 i Mr. John V. Morowski 4; p i
I We request that you reissue BC-TOP-3, Revision 3, dated August 1974 l l in accordance with the provistoms of the "Elemente of the Regulatory i : . Staff Topical Report Review Progr a" which was forwarded to you ca
- August 26, 1974. If you have any questions in this regard, please j ! Ist us know.
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Sincerely, i
f,,
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' L W. Elecker. TecAmical Ceardinator for Light Water Emestors Group 1 -
l ii Directorate of Licensing i '
Enclosure:
Topical Report Evaluation
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] D: sign Basis for Tornado-Gsnzrated Missiles '
- Joseph M. Farlay Nucisir Plint Enclosure Attachment 5 Page 6 of 65 a
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10PICAL REPORT EVALUATION '
1
- Report No.: BC-TOP-3 Rev. 3
! Report
Title:
Tornado and Extreme Wind Design Criteria for Nuclear
. p.ower Plants l l Report Date: August Ig74 '
,! Originating Organization: Bechtel Power Corporation t Reviewed by: Structural Engineering Branch Site Analysis Branch
! and Auxiliary Power and Conversion System Branch, all l of Directorate of Licensing. September 1974 l 3M MARY OF REPORT l, This report contains criteria for design of nuclear power plant i
!l . structures for extreme winds and tornado effects. Extreme wind criteria cover wind velocities up to and including hurricanes. The '
l extreme wind velocities specified herein, are identical to those i defined by wind speed map of ANSI Building Code requirements A58.
l 1-1972. The velocities defined correspond to a mean recurrence j interval of 100 years.
i l i-Extreme wind loading is applied to structures using methods and i
procedures consistent with the ANSI Code. The wind load previsions of i the ANSI code, as modified herein, are an essential part of'these '
[ criteria. C6mbinations of extreme wind loads with other loads
! and maxiom allowable values of stress and strain are not included ;
f in the report. This information will be specified in individual
! plant SAR.
For the parameters defining tornado size, intensity loading.de-j pressurization characteristics and others, the report refers to the
! plant SAR.
1 I. Velocity pressures resulting from tornado winds are applied using procedures paralleling those for extreme winds, the primary differ-ences being the treatment of the tornado horizontal and vertical
'el
- pressure profiles as opposed to those considered in extreme wind j design. To facilitate use of the material contained in the ANSI l Code, parallel definitions of velocity pressures for determining j ; wil loading local loading and internal pressures have been i ! d.
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1 Design Basis for Tornado-Gensrated Missiles l Jossph M. Farlay Nuclear Plant '- }
Enclosure - Attachrnent 5 1 Page 7 of 05 l
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, In addition to velocity pressure loadt.ng, methods and procedures t
for detemining'the magnitude and combined effects of atmosp ric
- pressure change' and tornado missile ispect are included i .
! For the load combinations inwplying tornado effects, and associated design allowables the report refers to individual plant i
SAR. For structures with no openings, differential pressures'due
! to full and partial effects of. atmospheric pressure change are on-
- j. sideired in design. For structures with openings (vested) the' differ- '
3 i
ential pressure loading is calculated using techtel camputer program CE Sgg.
Differential pressures on exterior walls calculated by the i
i code .(one dimensional analysis) are to be multiplied by a 1.20 factor j of safety to account for possible non-conservatism due to the three-l dimansional flow effects.
A cross-reference listing of items in this report related to Atomic Energy Coenission Safety Analysis Report format is pmvided in Appendix A. Symbols and notations that are generally consistent with those
) adopted by the ANSI Code are contained in Appendix B. Development of
{ supporting tornado. criteria is included in Agendix C. Appendix D i describes a one dimensional computer program for calculating building
{
depressurization effects and references am contained in Appendix E. I l l SlftiARY OF THE REGtA.ATORY EVALUATION ll The Structural Engineering. Site Analysis and Auxiliary power and
{~ I,~ Conversion Systems Branches of the Directorate of Licensing have l reviewed the sub, ject report, including Appendices A. B. C and D.
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The procedures covend by this report with augmentation of pertinent l information that is referred to and to be provided in plant SAR.
l are judged to represent the pmsent " state of the art" in the field l j of desian of structures against wind and tornado loadings. If properly ut1112cJ in nuclear power plant structural design work, the i
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. Design Basis for Tomido-Gener:ted Missiles l Joseph M, Ferity Nuclair Pirnt -
i Enclosure - Attachment 5 l Page 8 of 65 i ->.
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procedures and criteria contained in the report should pmvide conservative and acceptable bases,.for design of nuclear power j plant structures. > '
W TORY POSITION j j
j The design criteria and precadures described by this report are acceptable to the Regulatory Staff. The report may be referen,ced l
- in future casa applications pmvided that the following specific
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l fnfbreation reviewed and accepted' by 'the Regulatory Staff is I i included in individual SAR:
l a. Parameters that define tornado loading, such as.translational j and maximus tornado wind velocities. rate of depressurization, radius of maximum tornado wind velocity and amplitude of maxismi pressum drop, etc.
- b. Applicable wind velocities higher than those shown in Fig. 2 of the report as required by uniq've site conditions.
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- c. Combinatio' ns of extreme wind 1 pads W. with other. loads and maximum allowable stress and strain.
- d. A list of Category I and non-Category I structures, systems and components to which extreme wind design criteria are applied.
- e. A list of all safety-related structures that are to be designed to resist the effects of tornadoes.
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- sign Basis for Tornido-Gzntrated Missiles Joseph M. Fa'1:;y Nucistr Ptint{!
j Revisiogn$sure - Attachment 51, Page 9 of 65
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j TOPI f REPORT g i
1 BC-TOP-3
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TORNADO AND EXTREME WIND t
[' DESIGN' CRITERIA FOR
! NUCLEAR POWER PIANTS '
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- ' ABSTRACT * '
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! This report contains nuclear power plant design criteria j for tornadocs and extreme. winds. It includes data, formu-lation and procedures for determining maxiJous wind loading on j structures and parts of structures.
- Sztreme wind loading is applied to structures using methods
! and procedures consistent with the ANSI Building Code require- ,
! ments A58.1-1972 (Ref. 1). The basic design wind-velocities 3 !
j are defined by the wind speed map, Fig. 2-1 (from hof. 1, l l Fig. 2) for 100-year mean recurrence interval winds. l i Tornado wind loading is applied to structures using procedures i paralleling those for extreme winds with additional criteria j' resulting from the atmospheric pressure change accompanying.
i tornadoes and tornado missile impact effects. ,
j Parameters (velocities, pressure drop a.nd geometry) defining i i the magnitude of the tornado upon which plant design is based 3 l
!I cre specified in the plant Safety Analysis Report (SAR) . 1 i
i} A cross reference listing of items in this report related to Atomic Energy Commission Safety Analysis Report format is pro-l3 l vided in Appendia A. Development supporting tornado criteria
- is included in Appendix C and Appendix D. l3 I
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- sign Basis fra Tornedo-G2n: rated Missiles Jc,seph I A. FarlIy Nucleir Plint F Attachment 5 Revi,ggggurg Page 10 of 6 T OF CONTENTS
- Section 1 1 Page l i
j h 1.O INTRODUCTION
! 1-l I 2.0 EXTREME WINDS l 2.1 2-1
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Extreme Wind Phenomena- 2-1 2.2 Basic Wind Velocities 4
2.3 General Provisions 2-1
! i 2.4 Special Considerations 2-1
, 2.5 Load Combinations 2-2 ,
- 2-2 3.0 TORtIADOES
- 3.1 Tornado Phencuena 3-1
- ; 3.2 General Provisions 3-1 t 3.3 Tornado. Design Parameters. 3-2 5
3.3.1 3-2 Maximum Wind Velocities 3-2
! 3.3.2 Atmospheric Pressure Change 3-3
} 3.3.3 Tornado Missiles 3-3 i 3.4 Load Combinetions 4 3-3 3.5 Load Determination 3-3
! 3.5.1 V61ocity Pressure Loading 3.5.1.1 Velocity Pressures 3-3 l 3-4 i 3.5.2 Atmospheric Pressure Change Loading i 3.5.3 3-5 Missile Impact Effects 3-6 3.6 Special Considerations 3-6
- 3.6.1 Differential Pressures On Internal Components 3-6
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3.6.2 Protection of Exterior Openings 3-6 j i 3.6.3 Special Shapes 3-6
! 3.6.4 Dynamic Excitation 3-7 i 3.6.5 Limited Damage 3-7 1
3.6.5.1 Missile Damage 3-7 3.6.5.2 Loss of Shcathing 3-7 3.6.5.3 Cranes 3-8 3 3.6.5.4 Other Structurea 3-8 j 3.6.6 Exposed Category I Bodies of Water t
3-8
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I 4.0 EXA89LES AND ILLUSTRATIONS 4-1 4.1 Velocity Pressure coefficients 4-1
, 4.2 Extreme Wind Velocity Pressures 4-1 l i 4.3 Tornado Pressure Imading 4-2 4.3.1 Velocity Pressures 4-2 j 4.3.2 Velocity Pressure coefficients 4-3 i 4.3.3 Atmospheric Differential Pressures 4-4 1 4.4 Frame With Detached Sheathing 4-4 i ~
4.5 Structure With Blowout Panel 4-4
) 4.6 Partially Vented Structure 4-5
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- g Design Basis for Tomido-Gen rated Missiles
- Jos:ph M. Ferley Nuctur Ptnt t
- i sN " '
e 11 ot 65 I
s APPEN7 ICES b
Appendix'A
- Cross Reference Listing To ABC Format Appendix B
~ Notation I
Appendix C Supporting Derivations For Tornado Design Criteria 1
1 Appendix D
! Computer Prpgram For Building Depressurization Bechtel Corporation Program CE 899 l
Appendix E R4ferences k *
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3 Dzsign BIsis for Tomido-Gensrited Missiles i Joseph M. Ftrisy Nuctsar PI:nt
{ Enclosure - Attachment 5 t
Revision 3 Page 12 of 65 l
LIST OF FIGURES
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l 2-1 Basic Wind Velocity, V30 (uph) - 100-Year hean
{ Recurrence Interval (from Ref. 1) 3-1 Idealized Atmospheric Pressure Change Vs. Time Function j 3-2 Velocity Pressure variation with Radius frasa Center of Tornado
- 3-3 i
SizeCoefficient,Ce[forAverageTornadoVelocity Pressure Loading e
! 4-1 j Local with Gabled Pressure RoofCoefficients for Sectangular Building' 1
,4-2 Local Pressures on Rectangular Building with Plat Roof I
4-3
- Velocity Pressure Distribution - Cylinders and Spheres
) 4-4 Drag Coefficient vs. Aspect Ratio - Suspended Rectangular
! Members j 4-5 j Extreme Wind Velocity Pressure Distribution on Typical nuilding
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} 4-6 Tornado velocity Pressure Loading on Steel Frame with j Detached Sheathing 4-7 !
i Typical Sheathing Failure Pattern (3-span Sheathing) 4-8 Pressures on Structure Before Blowout Panel Releases and at Maximum wind velocity (psf) 4-9 Illustration during Building of Pressure DepressurizationDistribution and Flow Pattern i
4-10 Illustration of a Structure Depressurization Model 4-11 Differential Pressure Time History for Compartments ,
1 and 3 Cl-1 Atmospheric Pressure Change Variations with Radius and Time iii
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I i Dssign Basis for Tornado-Gen: rated Missibs Joseph M. Farisy Nucisar PIInt 3evis$$8T'p e"[oy' t
j 1.O INTRODUCTION j i
This report contains criteria for design of nuclear i
power plant structures for extreme winda and torando {
effacts.
i Extreme wind critaria cover wind velocities up to and including hurricanes. The extresa wind j,
velocities specified here'in (defined by wind speed map, Fig.' 2-1 from hNSI Building Code requirements A58.1-1972, Fig. 2, Ref.1) correspond to a mean 3 i
1 recurrence interval of 100 years.
i Extreme wind loading is applied to structures using 4
methods and procedures consistent with Ref. 1. The j
wind load provisions of Ref. 1, as modified herein, 3 are an essential part of these critaria. Although '
j it is assumed in this report that the reader (or user) i .
is thoroughly familiar with the provisions contained in -
l Ref. 1, additional data and explanatory material are q included to facilitate application of these provisions.
I j
Parameters defining tornado loading are specified in
.the plant SAR.
, 3 l Velocity pressures resulting from torntdo winds are applied using procedures paralleling those for extreme winds, the primary differences being the treatment of the tornado horizontal and vertical pressure profiles
! as opposed to those considered in extreme wind design.
j To facilitate use of the material contained in Anf. 1, j parallel definitions of velocity pressures for deter-j mining overall loading, local loading and internal j pressures have been developed. ;
l In addi. tion to velocity pressure loading, methods and i procedures for determining the magnitude and coubined offacts of atmospheric pressure change and tornado missile impact are included along with special consider- i ations peculiar to nuclear power plant facilities.
A cross-reference listing of items in this report related l3 to AtcsLic Energy Cosatission Safety Analysis Report for-mat is provided in Appendix A. Symbols and notation con-sistent with this report and Ref. 1 are contained in Appendix B. Development supporting tornado criteria is included in Appendix C. Appendix D describes a computer progran for calculating building depressurisation and references are contained in Appendix E.
1-1
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- i Dssign Basis for Tomido-G:nsrated Missil:s 3
Josrph M. Fartsy Nuctsar Plint >
Enclosure - Attachment 5 '
Revision 3 Page 14 of 65 2.0 EXTREME WINDS l 2.1 Extreme Wind Phenomena '
Extreme winds are defined for the Purpose of this document as winds with a vertical gradient, occurr-ing over a wide area, and having velocities up to l3 and including hurricane intensity.
The 100 year mean recurrence interval extreme winds in these design criteria (Fig. 2-1) are based on the data in " Climatological Data, National Summaries
- from the U. 8. weather Bureau. If local canditions indi- 3
, cate higher wind velocities than shown in Fig. 2-1, such velocities will be addressed in the SAR. Local -
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conditions, if more severe, shall govern.
2.2 Basic Wind velocitie_s The basic design wind speeds are shown in Fig. 2-1.
Criteria for surburban areas and cities are generally less severe, but are not used in the design of nuclear 3 plants regardless of plant location.
l 2.3 General Provisions Extreme wind design criteria are applied to Category l l
I and non-Category I structures, systems, and components '
as defined in Ref. 4 and listed in the plant SAR.
l These structures are designed for the basic wind vo-
- locities shown by Fig. 2-1. Except as otherwise i noted herein, the provisions of Ref. 1 for Buyosure c (flat, open terrain) shall be followed in applying l3 extreme wind loads.
Other structures are designed in accordance with l3 local or regional governing building codes, if so provided in the project design critaria, or in compli- l3 ance with Ref. 1, whichever is the more severe.
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i D: sign Basis for Tornado-Generated Missiles
! Joseph M. Farlay Nuctsar Plant Revisiogn@sure - Attachment 5 i -
Page 15 of 65 i
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i 2.4 Soecial Considerations The effective velocity pressures given in Table 5 of maf. I take into account the dynamic response to gusts 1
of ordinary buildings and structures in a direction l
parallel to the wind and should be considered minimum.
Design of structures subject to dynamic excitation, such as vortex shedding from chf =na detailed dynamic investigation.ys, shall be based on a i
1 Appendix A of RWf.1,and Raf. 5. )tese Section 6.3.4.1 of 3 4
2.5- Load combinations 4
combinations of extreme wind loads, W, with other loads, and =mwh= allowable values of strees and strain, are ,
- . specified in the plant safety Analysis moport (SAR) . !
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Drsign BIsis for Tornido-Gtnzrated Missiles 4
Jos:ph M. Fart:y Nuclear Pl!.nt i
if-Enclosure . Attachment 5 Page 16 of 65 i
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! i l Design Basis for Tornado-Generated Missiles ! Joseph M. Farlay Nuclear Plank i t Enclosure - Attachment 5 l
, Revision 3 Page 17 of 65 l f
i
-l I 3.O TORNADOES "l 3.1 Tornado Phenomena Tornadoes are highly localized wind storms character-ized by high velocity winds varying in intensity with the radial distance from the center or axis of the tornado.
For developing structural design criteria, a single vortex tognado is considered. Maximum wind velocity l occurs at:a distance from the center of the tornado, l called the radius of ===i== wind, m e. Wind veloeity increases with distance from the center to the radius - of maxisma wind, beyond which velocitydecreases, varying j3 inversely with the radius. *This results in a horisontal velocity pressure profile peaking at the radius of maximum wind. Wind velocity also varies with height, but to a much lesser degree than the horizontal varia-tion with radius. The vertical velocity pressure pro-file is as'sumed to be uniform. Design velocity pres-sure loading from tornado winds (We) is therefore based on the horizontal pressure pr8 file. 1 The rotational motion of the air mass about the center of a tornado produces a pronounced eh==ge in atmospheric pressure which can, in the case of closed or partially vented-structures, produce additional direct differen-(We),isasminimalthe tornado passes over l l tial pressure loading a atructure. This change at the outer peri- ! phary of the tornado and reaches a maximum at its center. l l l Tornado-resistant structures must also be designed to resist missile impact effects.from airborne objects and
- debris (from failed or damaged atruetures and ecruipment) which are transported by tornado winds. Due to the i
rotary motion of the tornado winds, missiles tend to be e$ected frca the tornado and generally reach marina velocities in the vicinity of or beyond the radius of maximum wind. For design purposes, tornado missile impact effects are therefore considered separately or l concurrent with velocity pressure and atmospheric ( pressure change effects at the radius of maximum wind. 1 Tornadoes vary in size, configuration, intensity and frequency of occurrence depending on local and regional . meteorological and topographical conditions. The largest number and most severe tornadoes occur in the eastern portion of the United States. Smaller and less savare
- u j pe p ,,
j C - _ -t e z - 3-1
l Design Basis for Tomado-Generated Missilts Joseph M. Farley Nuclear Pig RevisionESciosure Attachment 5 Page 18 of 65 tornadoes have occurred infrequently in isolated por-tions of the western coastal states. Present stora data are insufficient to deteznine which areas are not susceptible to tornadoes. Therefore, in the ab-sence of a detailed meteorological investigation for a particular plant location, tornadoes are assumed to occur anywhere within.the 48 contiguous United States. Parameters. defining the tornado size, intensity, , and characteristics are defined in the SAR for each 3 plant. 3.2 General Provisions All eafety-related structures that are to be designed to resist the effects of tornadoes will be listed in 3 the plant SAR. All safety-related equipment systems and components shall either be designed to sustain l tornado effects without loss of function or shall be l protected by' a tornado-resistant structure. Other structures and plant equipment shall also be designed ; or protected so that they will not jeopardize the i ! integrity or function of Category I structural systems j l or components or safety-related equipennt by virtue l3 1 l of collapse or detachment of component parts. ' 3.3 Tornado Design Parameters 3.3.1 Maximum Wind velocities ! l Due to rapid developments in tornado technology, parameters defining nazisum win $ velocities and 3 geometrical features of the design basis tornado model will be specified in the SAR. ! 3.3.2 Atmospheric Pressure Change The maximum magnitude and rate of atmospheric pressure change are specified in the plant SAR. l3 For determining the differential pressure loading resulting from atmospheric pressure change, the idealized pressure-time function shown in Fig. 3-1 can be used in lieu of the more representative for-mulae contained .in Appendix C. Bowever, use of the formulation in Appendix C is preferred where e 3 putational difficulties are not a factor. 1
.- cs . . . . r .:
. ? d ; *.ig ( . .! *-
A *., v .: L 3u4 IOCit*/ pre .m a: 3-2 l
1 Design BIsis for Tornido-G:n: rated Missilis i Joseph M. Ftrisy Nuctsar Pirnt 9 i E Revision 3 closure Attachment 5 Page 19 0f 65 1 3.3.3 Tornado Missiles The tornado missiles to1be considered in plant de-
- sign are identified. andicharacterised in the plant i SAR. I I 3.4 Load Combinations l The load combinations involving tornado effects, We, and associated design allowables are specified in the
- plant SAR. -
j - W, is further defined by the following load equations: 1-W g =W g, (sq. 3-1) { l Ng =W g, (Eq. 3-2) l W, = W ,, . (sq. 3-n l W, = Wg, + 0.5 W,, (Eq. 3-4) l W g *W gg + W,, (Eq. 3-5) ; l 4 W-W e et + 0.5 Wtp + u to (sq. 3-6) 1 \ j W gg = Velocity pressure effects 'l Wg , = Atmospheric pressure change offacts ' ! Calculated differential pressnres (using pro- - ! cedures described in Appendix D) on exterior 3 1, walls shall be multiplied by a factor of 1.2. j W,, = Missile impact effects i
- For discussion and derivations supporting these load j combinations, see Wadix C.
l 3.5 Load Determination i j 3.5.1 velocity Pressure Loadinq ! is determined using j Velocity the methods pressure and procedures loading,con W,,tained , in maf. I with the following exceptions: i 1 1. Velocity and velocity pressure are assumed not i to vary with height. l j 2. Velocity and velocity pressure vary with hori- { zontal distance from the center of the tornado. j FoWfic.ition of horizontal pressure pr file,
' 3 j sr. -2.
- .? . .., u,, ,
..y i 3., vai ca tl assures gy, gP, and qu are dt. :
l mined in cecordance with Section 3.5.1.1 3-3 i. w---
f
- Drsign Basis for Tomido-Gensrated Missiles Joseph M. Fartsy Nuctsar Plint -
Enclosure - Attachment 5 \
' Revision 3 Page 20 of 65 ,
- 4. Criteria for determining. velocity pressures for parts and portions (par. 6.3.4.2 of mer. 1) l are not applicable.
i i
- 5. Gust factor is taken as unity.
3.5.1.1 velocity Pressures , 5 Velocity pressures are determined by multiply- ! ing the velocity pressure, P i of maxisma wind, by the sizecoefficient, . , at the radius C
' defined see Appendix C).
in Fig. 3-3 (for development of Fig.,. 3 -3 l3 l A q = C,7 ,,, (Eq. 3-7) e = e,, e, or e,
- q, = Velocity pressure for overall structural
- res - se <,sf) . -
~4 q, = Velocity pressure for parts and portions { 4 (psf) j q, = Velocity pressure for calculating inter-4 nal pressures (psf) P ( *** = Velocity pressure at the radius of i maximum wind (psf) Smax."0.00256Va _ , a (Eq. 3-8) v*** = MaxiJWWs OSSign wind Velocity as de= i termined by Section 3.3.1 (mph) ) For qF ""d I'O P s is determined as follows: i j 1. Determine the load distribution length, L, of the structure or structural element. l Length L is the plan distance perpendicular to the direction of the wind over which the l wind load can be distributed, (such as by 4 j beam, truss, or horizontal diaphragm action) j or the mean horisontal extent of the tribu-tary area perpendicular to the direction of the wind. j,
- 2. Determine the ratio of length, L, to radius of maximum wind, Re. (The value of Rm is 3
] specified in the plant SAR.)
] 3. Enter M r3 3-3 with L/R and read value of 'g l C,. .am d . s .
j u./2WL :6W. 24" '- t- y>- ~
- t. .
3-4
f Dssign B: sis for Tornido-Gsnsrated MissilIs 3 1 Joseph M. Farlsy Nucl:ar Planl* j Revisanelotre - Attachment 5 Page 21 of 65 The internal velocity pressure, qu, depands on the location and distribution of openings. When the size and distribution of openings are relatively uniform around the periphery of the 3 structure, qu is determined from Eq. 3-7 using a value of L equal-to the plan dimension of the structure perpendicular to the wind and the same procedure as for external velocity pressures. For unequal size and distribution of openings, Su is determined from Eq. 3-7 using the follow-sag weighted average technique to determine C .
- 1. Imcate structure within the pressure profile for maximum total wind load by determining the valuaa of rg and r2 which satisfy Sq. 3-9:
# Its 1
y=7 (3q. 3-9) ' e 2 L=r 2
~#
1 (*** 'I* ~' L = Plan dimension of structure perpen-dicular to wind direction
- 2. Determine velocity pressure factor C, from Fig. 3-2 for each exposed opening.
- 3. Determine Ce from Eq. 3-10. [3 N
EA C g oi gi C, = , <>. 3-1o> 3A oi 1 A,g = Area of opening at location i C 9g = Velocity pressure factor at loca-tion i n e Number of openings 3.5.2 Atmospheric Pressure Change Loading - For structures with no openings (unvented), differ-ential pressures due to atmospheric pressure change are applied in accordence with Eqs. 3-2, 3-4, and 3-6 with the atmosph? + A Uferential prersure , tending to force exts ,.: ?s): / faces outward.
> $ %i5s s '
3-5
4 l Dssign Basis for Tomado-Gensratzd Missiles - f t Jg . F*.rlay Nuctstr Plant . lodare - Attachment 5 ' Page 22 of 65 ' i i t{ j [ For structures with openings (vented) the differen-a e tial pressurs loading is calculated using a pres- - i sure-time function as described in Section 3.3.2. i , Bechtel computer program CE 899 described in Appendix D can be utilized for performing these calculations. 3 . j i Structures with a vent area to compartment voluna ratio greater than that of a structure sustaining i ' a maximum differential pressure of 10 psf during the n assumed tornado can be considered fully vented. t o ' Differential pressures on exterior walls calculated ! by procedures contained in Appendix D (CE 899) are 3 j . multiplied by a factor of 1.2. ! "3.5.3 Miseile Impact Effacts Missile impact effects are evaluated using the me-thods and procedures contained in Esf. 3. i l 3.6 Special considerations 3.6.1 Differential Pressures On Internal O m ents j Internal components (such as tankage, ventilation ! ducts and equipment, walls, floors, partitions, etc.) j must be provided with adequate venting or must be j designed for differential pressures resulting from j __ building pressurisation and depressurisation. Vents and openings must be located and sised such that exit and entrance velocities will not :leopar-l dise the functional capability of other internal { safety-related equipment and components. 3.6.2 Protection Of Exterior Openinos Exterior openings and vents in structures required to provide missile protection shall be designed such as to preclude entrance of tornado missiles. ! 3.6.3 special Shapes j Lift, drag and/or pressure coefficients for struc-tures or structural elements whose shape and geo-3 metry differ appreciably from those of regular buildings and components such as covered in Ref. 1 j may be based on well-documented data such as those j contained in Ref. 2. For example, Fig. 4-3, based j on Table 4 (f) of Ref. 2 can be used to determine l3 1 wind loads and pressure distribution on containment j structures. 8 j .n ,a na A. ! Where such data are not avaM.J.?!O .'? cannot be as-4 veloped analytically, specis1%EJ Wre required. i t
- 3-6
i ! Design Basis for Tornido-Gsnerated Missilts ! JapohsMdigrity Nuclear Plint l l Enclosure- Attachment 5:
)
Page 23 of 65 ' I 3.6.4 Dynamic Excitation ,. I j Design of wind sensitive structures as defined in mo f. I and structures subject to dynamic excita-l tion, such as frou flutter, gallop and vortex j shedding, shall be based on a dynamic investiga-tion such as outlined 2.n Section A6.3.4.1 of Ref. 1 3 ll l and papers listed in Ref. 1. j) 3.G.5 .Q mi,u,d_D_ama g -
- i n i structures may sustgin limited ' damage if such da- ,I l mage does not hazar$ the integrity or functional .
j capability of Categ try I structures or equipment. l! i i l 3.6.5.1 Missile Damsgo - 4 l Tornado resistaqk structures may 3 i sustain local missile damage such as partial i penetration and local cracking and/or perma-l nent deformation provided that structural in-tegrity is maintained, perforation is preclud-j ed and conta Category I equipment is not I j subjected to d go by secondary missiles, such as from e ete spalling. l3 ;
.l 3.6.5.2 Loss of sheathing '
l i Exterior cheath and nonstructural walls and i partitions of a tures not required to pro-tect interior sy ens and components from tor-l nado effects as be considered expendable and , allowed to beconja detached or fail during a ! tornado, provided such detar$naat or failure J does not constitute a more serious missile 4 hazard than that of the tornado design missiles specified in tho'SAR. The structural frame of such structures shall be designed to sustain 1.5 times the pressure at which the sheathing is expected to fail. This loading need not exceed the full pressure load-ing. These structures shall also be designed for tornado winds acting on the projected area of exposed members and equipment, assuming (for conventional three-span sheathing) one- ; third of the sheathing remains on the windward t portion of the building. Sheathing which is supported by more than four girts or purlins 3 will be treated on a special case basis.*
- Previous analyses and obscrvationr1 have indi-cated no significant difference b. ' ' 'oad on frames where special sheathing hL - . 'ed. 3 However, this check shall be made 'ra the adequacy of the structure.
3-7
i i Design Basis for Tornado-Gsnerated Missiles ' i Joseph M. Fariny Nuclear Pl:nt Enclosure - Ntachment 5 l Revision 3 Page 24 of 65 ! The tributary load froe expendable interior non- i structural walls and partitions shall be taken as i 1.5 times the pressure loading at which they are j
- expected to fail, but need not exceed full tornado l velocity pressure loading.
3.6.5.3 Cranes t Cranes exposed to tornado winds by virtue of loss
- of expendable sheathing may sustain functional i damage but shall be designed to remain on the run-way girders so as not'to hasard tornado-resistant l
- structures or category I systems and components. l l
. -3. 6. 5. 4 other 8,t_r gturee 1
l The design or location of other structures not j l designated as tornado-resistant structures shall ' he such as not to hazard tornado-resistant struc-1 ' j i tures or protected equipment by virtue of collapse or generation of missiles (more severe than those specified in the SAR) from detached portions or i contained equipment. ! 3.6.6 Exposed category I Bodies of Water ) Design of small exposed category I bodies of water j (such as the fuel pool) shall consider a water loss 3 l amounting to a change in water level of two feet. i i Larger exposed bodies of water (such as spray s) 3 ! shall be designed such that water can be suppl I i from an alternative source on an as-needed basis or j shall be tied in with redundant facilities to main- l l tain functional
- capability. This interim provision
- will be followed until further investigation enables
- a closer evaluation of potential water loss, water i transport by tornadoes is discussed in Refs. 7, 8 and j 9.
i I 1 l I i 1 k i 4 i l i
; 3-8 i i 4
_l
i Dssign Basis for Tornido-Gsn: rat:d Missilts Jos:ph M. Farisy Nuclear Pitnt Enclosure - Attachment 5 l Page 25 of 65 ' \ \ l ) i l Rm VW
~
= .
il - 4'. 4
=
4 Time 3 l Note: Trapescidal Appromination of the Theoretical 2 Curve Derived fros a Combined Rankine Vortes Velocity Pressure Profile (see Fig. Cl-1). For notation see Appendia B. I FIGURE 3-1 Idealized Atmospheric Pressure Change Vs. Time Function
.w- -r ~ , a, ,--
._ _ ..-. .~ -- -~~ - -
1 -
' 1.0 _ -
i.9 - 0.8 . 0.7 .
- F e
0.6 cr ' ( 0.5 = ' E O.4 ' tT [ 0.3 t 02 0.1 - m%
- e e.
- cn l =
ri e ! L-1 i 1 1 1 i i i i i i i g ,8 0.2 0.4 0.6 0.8 1.0 1.2 1.4 i 4g 1.6 1.8 2.0 2.2 2.4 2.6 2.8 3.0 r o '! E' fa s ye b 6 FIGURE 3-2 Velocity Pressure Variation With Radius Fross Center Of Tornado es. y[z g EE$$ N R *g3 i g a .! E-S ui a 3 ~ _ , _ _ - . . . - _ _ _ _ _ _ -__- _-_. . . _ - - . . - - . - - - _ - . . - - - _ . - _ _ . _ . . . _ _ - _ - - - - - . . _ - - - - - _ _ _ _ _ . -- _ _ _- -
i 1 ai .. n . I Plan View * '
' Stneture or , ,,,,,,,,,,,,,,,,,,,,, i Elenent M l J' d '
i E = m 1.0
- in,'% ,'",v,,o "
Melocity h , i , t Presure i n ofile ' e.9 - ' l P v'I,d I's,,,=,, u 3y t r O.8 - \ 3 . r3 g r2 6
!h 0.7 _
\ A Velocity i'i
i 3l i
pygggy , h m
- \ y, '
u N & 0.6 - N* 3 E1 % E2 j N I N ' 0.5 N N-
" o
% 3
% % 6 s
t i B' ! I 0.4 a a a a a a o . . . . . . . . 5- t
,_, s e s
- W r e ~s. c- !
F u s oR i V i a e a u 0.2 0.4 0.6 0.8 1.0 1.2 1.4 g , T.'6' 1.,8 2.0 @#
}
m :r B L
~ EFEo
% Om0 E, =2 PIGURE 3-3 Size Coefficient, C. , For Average Tornado Velocity Pressure Loading y 74$ !
- o. .ag Nf" i w w 8;;a?:h n !
l l Dssign Basis for Tornado Gsnsrated Missilis Jossph M. Farisy Nucixr Pirnt Revisiggdgsure- Attachment 5 Page 28 of 65 4.0 EZAMPLES AND ILI/JSTRATIONS 4.1 Velocity Pressyre Coefficients velocity pressare coefficients a applicable to both extream winds and tornado winds, igs. 4-1 and 4-2 illustrate applications of local ternal pressure coefficients C forwaps roofa (asf. 1). Local increased loads are applied individually, and not simultaneously with the not e eru l pressures when computing overall loads, nor ianaltaneously with . 1 overlapping local increased' loads s at eaves and i eave intersections. . An illustration of pressures ac on an overhanging ! eave is shown in Fig. 4-2. Where the walls extend : upward above the roof as parapets 'C for the outer parapet face .shall be the same as' foI the wall, and Cp - for the inner face of the parapet shall be -2.4. The width of strips subjected to local increased loads need not exceed 12 feet. Figure 4-3 illustrates the external pressure distri-bution on cylinders and spheres (Ref. 2) which can be used in the analysis of wind loads on con + min ==nt structures. Figure 4-4 illustrates the variation of drag coefficient, Cn, with aspect ratio (ratio of length to width). this figure is applicable to sus- I
' 3 pended rectangular asabers (such as structural shapes).
If flow around the ends of a asaber is inhihited such as by other framing members, the length is considered infinite and a drag coefficient of 2 is used. 4.2 Extreme Wind Velocity Pressures Pigure 4-5 illustrates application of extreme wind velocity pressures on a typical building. Pressure coefficients, C, and C,g, correspond to a structure with uniformly Sistribbted openings and height-to-width and height-to-length ratios less than 2.5. The variation of velocity pressure with height is also shown schematically. The corresponiing varia-
- tion of internal pressures assumes negligible verti- ;
cal venting between floors. t w. 4-1 ' i
. ._ . _ . _ . _ _ _l
. - - . - .. - -.-. - - - .._. . - .. - - - - - - - - - _ . - -. , - . - . - - . - ~ -
0: sign Basis for Tomido-Gsnzrated Missil::s Joseph M. Ftrisy Nuclatr Plant ; l, y,,ggurgPageAttachment 29 of 655 lj 4.3 Tornado Pressure Loading The following example illustrates determination of tornado pressure loading. The steel f,rame structure shown below is subjected to a tornado with winds from either direction, A or B. only, R , V ,, v , and APFor illustrative' purposes 275 ft., have been assumed to be 3 l 365 mph,g50mphan$432 pef,respectively.* l l
>d y
- s y
v MY - N , Ansaoropenne e umorra umLL AREA
- 30,o00r78 The structure has a horizontal roof truss system, which transmits wind loads to bracing in the side and and walls. Purline are parallel to the side walls, roof girders span the struauture in the ahort direction and bay spacing is 25 feet.
4.3.1 Velocity Pressures The following effective veloc. tty pressures, gy, q 13 1 and qu for the various structural components and s,ys-tems were determined using the criteria'in Section 3.5.1.1 and Fig. 3-3. 3
*The values of R , Vaan. Ver, and APa to be used in design shall be obtained from the plant SAR. 3
- a. r, -
+ i a
4, p ., 42 - l l 4-2 I
D sign Basis for Tornido-Generated Missiles Joseph M. Farty Nucbir Plint , i Re. vision 3 Enclosure - Attachm Page 30 of 65 i I Wind Effective l3 Direction 1 yetoetry For internal , s Ce Pressure Presourc A 5 (ft) (psf) ~ 200 .73 3 100 qu = 240
.83 qg = 275 i
- , For Sbsathing A&E '
O 1.00 gy = 330 soof Truss A 200 .73 gy - 240 a B 100 .83 qy = 275 100' W11 Bracing A 200 .73 1 gy = 240 1 200' W11
- Bracing 3 j L 100 .83 e
gy = 275 ' Roof Cirders A j 25 .96 B 100 gy = 315
.83 gy = 275 Purlins A j 25 .96 2 0 gy = 315 1.00 gy - 330 I
200' Wall j, Cirts & Columns A 25 j .96 gy = 315 B > 0 i 1.00 gy = 330 100' Wall Girts & Columns A 0 1.00 gy = 330 1 3 25 .96 qy = 315 4.3.2 Velocity Pressure Coefficient l Velocity pressure coefficients (based on height-widt.h and height-length ratios less than 2.5) are sunusarised as follows: External Pressure Coefficients, Cp i Wlad Direction g 100' Walls A .7 5 Raf. 1. "Table 7
+. 8 , .5 200' Salls A +. 8 , .5 "
l 3 .7 "
.: .w Raof .[3,'];p pc. _A c., , . , -. 9 ,
-B
. .7
.7 a
n ;- - 1, Par. 6.5.3.2.1 4-3
)
j j' Design Basis for Tornado-Gsnerated Missilis Joszph M. Fartsy Nuclear Plant i Attachment 5 Revi5Tbrgug Page 31 of 6 f ! Local Pressure Coefficients i Wind C Dirsetion P local-k Wall Corners 1 ut -2.0 Ref. 1, Par. 6.5.3.1 Eaves MB -2.4 Eaf.1, Table 10 } Ecof Corners ME -5.0 " l Internal Pressure Coefficients 1,000
- a = 30,000 < 0.3 and evenly distributed
, Raf. 1, Table 11' 4.3.3 Atacaphoric Differential Pressures Using the idealized pressure-time function shown in Fig. 3-1 and Bechtel computer program CE 399 resulted in a maximam differential pressure of 9 paf. There- 3 fore, the structure can be considered fully vented (Section 3.5.2) and W,, can be taken as zero. ,
4.4 Frame With Detached Sheathing Figure 4-6 illustrates-loading on a frame with sheath-
~ ~ing par _tially ah. One-third of the sheathing on the windward portion of the structure is assumed to 4-7). remain in place (for three-span sheathing, see Fig. l3
- A drag coefficient of 2 is used for exposed steel by other members framingsince members. flow around the ends is ' restricted The sheathing failure pattern will result la a low aspect ratio for remain-ing sheathing for which a drag coefficient of 1.2 is appropriate (see Fig. 4-4) .
4.5 Structure With Blowout Panels Blowout panels are installed in some structures to Prevent (or minimise) differential pressure loading resulting from atmospheric pressure chknge. Figure 4-8 shows the pressure loading on a 100 ft. square structure just prior to blowout panel release and when tha structure is subjected to maximum winds 3 (Veer = 360 mph). The panels are designed to release at a pressure of 100 psf and each has sufficient area to provide full venting. As the tornado ap-proacheF~the building, negative velocity prc r:ure builds;t" 1rra cAe leeward wal.L. At the sama M"'e differoAL31: masure from atmospheric prer: u ol r 'igs
&w .r . c.t
... i 4-4
4 I i Design Basis for Tornado-Gansrcted MissilIs ! l Jos:rph M. Farlsy Nuclear Plant j
, ReviE&desut - Attachment 5 - i Page 32 of 65 i
1 builds up, tanding to force the walls outward. When i I the sum of these pressures reaches 100 psf, the lee- l ward panel releases. 'The pressures just prior to i panel release'are obtained as follows: 1. Detamine the value of r/R, for a combined pres-
- sure, Per, of 100 psf (from Eq. Cl-9b) for l Va = 290 Imph (for AP = 432 pst from Eq. Cl-7a)
C = 0.5 i. 360 K = g a 1.24 , 1 l ' h=1.95 s ! 2. Determine corresponding values of P qr 1 Eqs. cl-5b and Cl-7b. . and Par froen ; j P,, = $6.4 psf laternal pressure l P r = 43.6 psf leeward wall Pq , = 61.1 psf roof and side walls P = 69.9 psf windward wall i d i 1 The pressures before release reflect a value of C, = 1 (uniform pressure distribution assumed). A value of L C e 1 was also used for internal velocity pressures sInce the plan' dimension of the blowout panel is small. Mari=um equal to 100 ft. external pressures correspond to a value of L - i The othar panel is assumed not to release (due to ini-tial inward velocity pressure) unless the direction of the wind reverses and the sum of the internal and ex-i tornal of 100 psf. velocitypressures caused a not outward pressure i 4.6 Partially Vented Structures Figure 4-9 illustrates the. flow pattera and difforential j pressure zation. variations in a building undergoing depressuri-
- Differential pressure calculation is facilitated by a first making a depressurisation model for the building such as that shown in Fig. 4-10. Using this model and the pressure-time function shown in Fig. 3-1, the dif-forential pressure-time functions between compartmente
' one and three r 1 W ; pean compartment 3 and outside. et- 3 mosphere were Ld.ict& Owl (using Bechtel computer p;o-gram CE 999 as-5:.cee.i5cd in Appendix D) . The resulb l3 ing pressure-time functions are shown in Fig. 4-11.
4-5
- l. C, g,,,g . ( g,ge .g.0 ) # 5 30' I C p loses = t o. le. 5.0 ) # 530*
- C ,;,,,g . 1.0 4 750' Op g,,,e . 2.0 e > 30*
R. C ,no,eg . .g.4 e S age asp g,,,q . 3,4 E C , go , ,3 . . f. 7 + > 30' 3 Cp tecel = . R.0 ; 3 C p go ,g . . R. O i
, a I t
g f V g g
., i i
i h w& v.a - 3
- wx
/ w E
RECTANGULAR Sull.DIgle WITH GASLED It00F W fWOTANGULAR BUILDING WITM GASLED ROOF 5 WIND PERPEfSICULAR TO R10SE WIND PARALLEL 19 RIDet IT$
$o m=a i FIGURE 4-1 I,ocal Pressure Coefficients For Rectangular Building With Gabled Roof 8 F E.
in , AR*$ meha b U gk$ S. g 3 G. 3 E. 5 5
i:!i! .! ! . I;! ;4 i! ,il! .. ' , ); !
.i4 _
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' r
.s] .:
. ] :: _
'Y \
F - k a , (l . Dl 4\ -
- _ .
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Design Basis for Tornado-Generattd Missil:s Josrph M. Fartsy NuclJar Pirnt Enclosure - Attachment 5 Page 35 of 65 os 30* 40* eo* to* ico* iso
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- ANSLE FROM 5134NAT10N PolNT +
FIGURE 4-3 Velocity Pressure Distributic.* - Cylinders and Spheres a
..-. _. - . . . . . - . . - . . - - - . - . . _ . . - . - - . . - _ . - - ~ _ . - - . . . - . - - _ . . . - - . - . - - - . . . _ ,
4 t . ! DIsign Basis for Tomado-Gsn: rated MissilIs Jos ph M. Farlsy Nuclear Pirnt
- i. Enclosure - Attachment 5 Page 36 of 65 i
. \
I i ? I i i 1 1 i i j r- -- -- 4 - l _ . . . . . . f i k j i , I : f' i I
). i
-. . 1 t _
a s' 3 sals
/
, p i E l'
/ J e aM T L.J J.
E a = shbrt dimension jgo , . -- . normal to wind ; 1 = long dimension 1 poraal to wJnd 1 1 i l j . i I i i e f ' } 8.0 18 Le 4.8 Le 1.0 1.1 1.4 DRAS COEFFICIENT 1 1 1 FJCukP. 4-4 Drag Coefficient vs. Aapoet lutio - Susoended RecOngular Mcabers C
'. ilj:3il 5i :,i l)i l $: !;; l:IIl 4f>!!! ;
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_ = = ~- __
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i I I I Es. t f I. , 1 1 I - I I 1 I ; i t i f - I 1 I l i f ' T 1 i t f t i t T n.a .= [ ' s 1 , I i f t f i v v "f f Aa1( I ' t v a f - i
. f t
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QXNssq\sN\\ ' N lT N \ s 'N N 5\\N ss D \ .
,[85g 8 sg >14 ,5 D
e 5: 2. g: ! s gi n B a si s
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- 9. !. E hrn nMa
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4, ; ! !ll;
. . . - . . _ . _ _ . . . ~ . . . . ~ . . . . - - . - . . . . . - - . . - . . - - - . - - . - . . . . - - . - . . - - . . . . . . .
Dssign Basis for Tornado-Gensrated Missil:s Josrph M. Fartsy Nucisar Plant Enclosure - Attachment 5 Page 38 of 65 i 8
- v. .
3kmf: g
- 2A er (_ t g o l'
f -, L_ _ .I . t [ : ]y 1
/
gN i
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'l ing l
- I -
I i I Imeward I I l columns: % I
/ I F
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~~"I H! ;
I Ag = Area of bare stmel l I d = Bay spacing l l h=*W l L. l , 1 F l ' 1 I f
- r P
= 1 HI I
_I r l IEag COSfficiWital W steel CD = 2.0 nummining sheathing pc = 1.2 FIGUP2 4-6 Tornado Velocity Pressure Loading On Steel Frame With Detachod Sheathing l I
- = -
Design Basis for Tornado-G:n: rated Missiles Joseph M. Farley Nucisar Plant Enclosure- Attachment 5 Page 39 of 65 f I l i TYP, GET
- i. /.
! T y i I
, C2iGINAl. SIDING BEPORE TORNADO
, I i
! l
- < r 1
r - L 3-S' PAN SIDING - WIND ' IN PLACE AFTER l g li. TORNADO l
- t. ,
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)
3 I
', g [ ENDS OF. SIDING l
i I JL i, i (' i
# I d = TYP. GIRT SPACING g 1
- t a
' I l[ l l
1 FIGURE 4-7 Typical Sheathing Failure Pattern (3-!$ pan Sheathing) l3 l
t Design Basis for Tornado-Generated Missil;s ! l g Jos:ph M. Farley Nuclear Ptint !
, Enclosure - Attachrnent 5 l Page 40 0f 65 l
,n ' r; i
i f- [ l l ' i n i I 4 (- i - .i H 61.1 i
- o a o
{ = g 4 3
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- DimetienD 69.9 "* I 56.4 "* 43.6
{ 56.4 . 5,y < s i i % 4 N8 /
'lcWout B panel-i e d
! Pressures justprior to hlet j panel rel - i 194 l T
._ - . _ _"_.-.i , ,
e ,
'I %
! k l e 4 j 100 l
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e n \ 8 " ! Wind 220 -* Id -* 100 100 e.- -
--e 140
- Direction" j l .
* * +
- l
.e -t j Pressures at maximum wind !
velocity . e FIGURE 4-8 Pressures on Structure Before Blowout Panel Releases and at Maximum Wind velocity (psf) l i e 0 i
f Design Basis for Tornado-Generated Missiles j Josepg M. Farley Nuclear Plant 15nclosure - Attachment 5 i Page 41 of 65
~
t i ! PORT (OPEN TO ATMO5PHERE) s j na easssesuttttttM"" 'y jyj{" MF Mf C ECTIVITY r, p ui i n a
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////////////////////////////
t i i j FICURE 4-9 Illustration of Pressure Distribution and 3 j Flow Patt.crn During Ntilding Depressurization , r i . i i
-. . . - _ _ . . - - ~ - . . - - - . - . . . . - . . . . - . - - - . . _ . . _ ~ - . . . - - . . _ - . . _ . - . - .
i 4 Dssign Basis for Tornido-Gsntrated Missil:4 i
- Josrph M. Farlsy Nuclear Plant >
j ! Enclosure. Attachment 5 Page 42 of 65 4 i 4: ij - ,i : t
! A = 2250 FT2 o i
j h ' COEP. 3 _ PORT 1 [ V = [94700 FT* 3 ! ' #@ A = 24 FE y- A = 21 FT2 j A = M FT2f COMP. 1 v iss,000 n' 4 . a rT2 V"*'""3 (Cow. 2 hW , i i s = 63 n 2 : 2 s A,= 294 PT 4 i A = M FT2 ' COMP, 4 j 2 3 A = 34 FT V = 295800 FT (e) 1 4 A - sa n2 { g u. g
, N .
A = M FT2 (COMP. 5
" 3 i
1 [OMP. 8 4 t8 0 V> V = 32m00 FT i / = 15100 FT3 i ) A = 390 FT 2 I 4 A = M FT 27 COMP. 6
)
-l v = mr00 n 3 ; 'l: i ' i i i ! I e
$ FIGURE 4-10 Illustration of a Structure Depressurization Model l3 i i i .
4 i f i 4
'y
.- .--. . . . - - -- . . . . . - ~ . . - . - - - . _ - _ - . . - - . - . - - . . . _ - - . . - . . - - . . -
Dssign Bisis for Tornado-Gensrated Missil:s ! } Jos ph M. Fariey Nuclztr Pirnt -
- j
, Enclosure- Attachment S l Page 43 of 65 1 j t } 1
< ! t I
- ! l 1 l 3
! 1#" j sE1 WEEN 0000 PAR 1tIENT3 AN0 0intIDE
' ATheosPHERE 100 - t I " """"". SETWEEN CoasPAAftNBtTE 1 AND 3 '
- k MOTE 189U7 TIME HISTOMY PGA FIG,3-1 I j 8- ussu s a mentv ,- e oc !
Asso 4P. 4an,d
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l
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-100 ~
-120 - .
NOTE: THis EXAbrLE IS FONLLUSTRATION PURPOSES ONLY. ATuosmeRic PRessuma cHamog TIME NisTORY POR D551GN 18 TO SE
,OSTAINED FROM EAR.
FIGURE 4-11. Of FFERENTIAL PRESSURE TIME HISTORY FOR COMPARTMENTS 1 AND 3
}
I l Drsign Basis for Tomido-Grnsr ted Missil s Jos:ph M. Fartsy Nuclair PIInt RevisiorlErklosure Attachment 5 i
, Page 44 of 6.5 '
{ t 4 i e r h t . APPRNDIX A . i ! ,' ' CaOSS Q Listine i w ENM 4 l 4 1 ** *-4 w . .. 1 1 1 i 4 i e
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1 l l {,
. . - . - . . - . . . _ . - _ . . - . . . . . - . - . - . - . - . . - . _ . . . _ . _ . ~ . . - . ~ . . . . - .. . . -
i D: sign Basis for Tornado-Gzn:rited Missiles gagggMfarity puclear Plant ThcIDsure - Attachment 5 Pige 45 of 65 ! I
+
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APPENDIX A CROSS REFERENCE LISTING TO AEC PORMAY AEC Format _ Description t BC-TOP-3 i ' Wind _ Loadings 3.3.1.1 Design Wind Velocity 2.0 3.3.1.2 Basis for Wind Velocity 2.0 Selection . 3.3.1.3 vertical velocity 2.0 I Distribution and Gust 2.0 - Factor 3.3.1.4 Determination of 2.O Applied Forces l. Tornado Loadings 3.3.2.1 Applicable Design- 3.0 Parameters 3.3.2.2 Determination of Forces 3.0 j on Structures ' 3.3.2.3 Ability of Category I 3.0 Structures to Perform Despite Failure of l Structures not Designed for Tornado Loads I A-1 I
Dssign Bisis for Tomado-Gsntrtted Missiles , Josrph M. Fart:y Nuclear Plant f Revision JEnclosure- Attachment 5 I , Page 46 of 65 l I t
. i i
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F i I' , r APPENDIX ___8 ' i e I l r NOTATICII c . i , i i . I e ( 5 f f e ) 1 s 1 i O e ,j 1 1 i I i t i . i 1 l r ,
---,c-- ,-- ,-, - - - . - ,, -- , . - - ------n- -
i Design Basis for Tornado-Gznerat:d Missil s Jowph M. Fctby Nuctsar Plant J havisim hnclosure - Attachment 5 , Page 47 of 65. APPENDkXB NOTATION j .; a = small dimension normal to wind. j A , 1 -
= Area upon which pressure is acting. ,
j At = between Area (oncompartments the side of congartment 1) of the wall i 1 and 2. l A2 = Area connecting compartments 1 and 2. ! A3 = Projected area of bare steel. t Ao = Area of openings ,- cc = compressibility coefficient. Cg = Discharge coefficient. I
~
Cy = Velocity coefficient . c t
= Supanation of pressure coefficients for obtaining {
velocity pressure loading on the structure or~ structural element. , l i , 4 cp i
= Drag coefficient
'cr = Net pressure coefficient.
1 CL = Lift coefficient i t i C, = Effective external pressure, coefficient ' Cpi = Internal pressure coefficient c py,ggLocal external pressure coefficient. c, = velocity pressure factor. c, = Ratio of average to maximum velocity pressure of tornado wind on structure or resisting element. - F = Total force on strip of unit height. i g = Gravitational acceleration. B-1 h>
i l Design Basis for Tomtdo-Gencrated Missiles
- Jos:ph M. Farlsy Nuclear Plant i Enclosure - Attachment 5 kevision 3 Page 48 of 65
- G =
Mai$t flow rate of air through an orifice, k Gy = Gust factor response - extreme for calculating wind. overall structural j Gy = i Gust factor for parts and portions - extreme wind.
. h- = Height dimension.
4 k = 4 Specific heat of air at constant pressure divided volume. by the specific heat of air at constant ' 5 , R l ! R = Ratio of vector sum of all velocity com $ to tangential velocity - tornado wlada.ponents ;
= 1 R2 j Ratio of loaded plan length of structure or I j structural element perpendicular to the direction l of tornado wind to radius of maximum winds. ;
R2 l = Ratio of radius r1 to radius of mar 4=n= wind, R,. ! i j Rg , j = Height factor describing variations of extreme ' wind velocity with height. ' ! t i t = Long dimension normal to wind. , ! L j = Length of structure or structural element over i which tornado velocity pressure is distributed. l. ;
- n '
j = majority natio of openof openings. area to solid area of wall having 4 N
= Number identifying compartment or opening.
j P1 = Pressure in compartment 1. { P2 = Pressure in compartment 2 (P 2 "I } l j Pg = Pressure in compartment N. P, = Atmospheric pressure change. ) AP, = Maximum pressure change. } P,, = Atmospherie pressure change as a function of radius.l3 P,g = Atmospheric pressure change as a function of time. i 1 i R B-2 i i 1
D: sign Btsis for Torntdo-Gzn:ratrd Missiles Joseph M. Farity Nuclair Plint Enclosure- Attachment 5 Revision 3 Pag e 49 of 65 , d i Pav, = Average tornado velocity pressure on structure
- or structural element.
t. Per ' = Combined tornado atmospheric pressure change plus velocity pressure loading as a function of radius. I Pasz = wind. Tornado velocity pressure at the radius of maximum Pg * = Tornado velocity pressure. ' Pgr = Tornado velocity pressure as a function of radius. q = Effective velocity pressure, gy = Effective velocity pressure for calculating external pressure loading on main resisting elements and structural systems. qq = Effective velocity pressure for calculating internal pressure loading. q, = Effective velocity pressure for calculating external pressure loading on parts and portions. j r a Radius from axis of tornado.
=
It Radius from axis of tornado'to closest end of structure or structural element (rtik.) . j r2 = Radius from axis of tornado to the far and of the structure or structural element (r2LRm)+ l3 R. = Radius frcan center of tornado at which maximum wind velocity occurs, j t = Time. V = Wind velocity. v3o a Basic wind velocity at 30 feet above grade. ' V, = Tangential velocity component at R .s Vr = Radial wind velocity component. B-3
Design Basis for Tornedo-Gzn rated Missits Jos:ph M, Fortsy Nucbtr Plint Enclosure- Attachment 5 Revision 3 Page 50 of 65 Ve = Tangential wind velogity component. V er
- =
Translational velocity of tornado. w = Least width of building. W = Extreme wind loading. i
=~ Weight of air in coughartment W3 N.' .
- )
' e <
We j = Tornado loading. i Weg = Tornado velocity pressura effects J f. 1 W,e = Tornado atmospheric pressure change effects. . 4 W,e
=
Kissile impact effects. l' i
=
E Height in feet above grade. ! = l yt Weight density of air in compartment 1. } y, = Weight density of air in compartment N. l3 p i = Mass density of air. ! $ = i Slope 6f roof in degrees from horizontal. l' 4 . 1 9 9 9 B-4
._u
DIsign BIsis for Tomado-Grn: rated Missilsa Joseph M. Fart:y Nuct:ar Plint hvisigclofure- Attachment 5 Page 51 of 65 i
\ '
i i 1 APPENDIX C ( j i SUPPORTING DERIVATIONS l 4 POR TORNADO DESIGN CRITERIA
.e 4
d l f i 1 i
Design Basis for Tomado-Gsnzrated Missiles Jossph M. Far13y Nuctsar Plant ? Revision ylosure E Attachment 5 Page 52 of 65 ! 1.0 TOBEEhDO LOAD COMBINATIONS '
'4 >
\
The mazianna combined effect of velocity pressure (Weq) and atmospheric pressure change (Wep) is determined from a combined set of equ'ations for each effect ex-
- pressed in terms of a common radial distance from the center of the tornado. Missile effects (Wee) are com-i bined with Weq and Wep considering the missile trajectory j and the zone within the wind field in which maximus mir.sile velocities are attained.
j 1.1 Velocity Pressure Loading 3
- Velocity pressure loading JWeg) on any structural ele-ment and combined can be empressed pressure coef
- !icient, in terms of C. velocity pressure, q, I
l Wtg = ECqAA * (Bq. Cl-1) i C = summation of pressure coefficients { for obtaining the velocity pressure 4 loading on ithe structure or a parti-i cular element. q = velocity pressure. ) AA = area of portion of structure or element. l { q=fpV2 (Bq. Cl-2) l _. j, p = mass density Of air. j' V = wind velocity. I, 2 ) The wind velocity, V, can be expressed in terms of r by considering V to be linearly proportional to the tangential velocity component, Ve, and assuming that Vc varies directly with radius, r, from the center of the tornado to the radius of maximum velocity, Re , and inversely with r at radii greater than Ra (combined Rankine Vortex). Vg = V, 0<r<R, (Eq. Cl-3a) Ve = V. Rm ".r<= (Eq. Cl-3b) V, = maximum tangential wind velocity.
.~..'
' .: ; 1
'J . . .
C-1
. I 3
; D: sign B: sis for Tomido-Gsnsrated Missil:s I Jostph M. Fcrisy Nucistr Pl nt
- j Enclosure - Attachment 5 Revision 3
,i Page 53 of 65 t.; i V=RV - g (Eq. Cl-4) c , s K = proportionality constant.
; , s i
i Combining Equations Cl-1 through Cl-4, the not velo-city pressure as a function of radius, Pgr, 18: { pK C
.,y . 2 5 Pqr a '
j 0<r<R (Eq. Cl-Sa) s 2 .
.R, , -a d
i pK IC P a qr " T r Ryr <= (Eq. Cl-5b) I The =a wi === velocity pressure l. Pg, occurs at r=R .
! A dimensionless Figure 3-2. plot of Pqr/Pg vs. r/An is shown in l3 j 1.2 Atmospheric Pressure Change The atmospheric pressure gradie'nt at radius r is do-fined by the .cyclostrophic wind equations i
] dP** p V*2
= j dr r (Eq. Cl-6) i 4
With V e defined by Equations Cl-3a and Cl-3b, inte-gration of Equation Cl-6 from infinity to r defines the pressure drop at radius r. Par " *
- l3
. 0<r<R, (Eq. Cl-7a) pV 2 4
7 Par " g Rgr<= (Eq. Cl-7b) A dimensionless plot of Par /Pa vs. r/R. is shown in Figure Cl-1 where Pa is the maximum pressure drop (at r=0). l l Building depressurisiation and repressurization calcu-lations require determination of pressure change with respect to time. ' This is accomplished by substituting
' - )V er t into Ec;ttations Cl-7a mA 01.- . .i . .
1 C-2.
"l
/a
D: sign Basis for Tomido-Genarated Missiles l Jos ph M. Farity Nuclear Pl:nt f Enclosure - Attachment 5 ' ' Revision 3 Page 54 of 65 i e a pV 2 y2 t*'
. P at
=
j :2 Gy,,r<R, (aq. Cl-7c) l3 I Pat = pV( ' R2 i 1
.,y- 2 R,gr<= (Eq. Cl-7d) i v er= translational velocity. ;
t = time l (reference to center of tornado). An illustration'of pressure drop variatice with time , , is obtained by adding a time amie to Figure CA-1. In lieu of i vative ideal tiens Cl-7c and C1-74, a nose conser- - linear pressure-time carwe'cas'be' i used, assuming full pressure drop occurs in j ecconds (see example superimposed plot - Fig.RCl-11. /Ver I
- 1. 3 - 3 ,
1 Wind Load Plus Pressure Droo ! The combined effect of velocity pressure and atmos- i pheric P pressure change is the sununation of Pgr EBd ar- i Pcr* Pqr + P., (Eq. Cl-8) Substituting the values for Pqr and Par (as dotarained by Equations C1-Sa, C1-5h and Cl-7a and Cl-7b) into Equation terms of r. Cl-8 yields the following formulae for Per in i Per = 2+ 4 2 - g (Kt C - 1) 0 <r <R (Eq. Cl-9a) pv 2 g a
- P
; er
- 7 p (1 + K C) R <r < =
(Eq. Cl-9b) Equation Cl-Sa shows that Per will be a maximum at r=0 or at r=Re depending on the value of Kac. For K2 l C<1, Per is a maximum at r=0 and is equal to the full (see value Equation of maximum Cl-7a). atmospheric pressure change ' For K 2C>1, Per is a maximum 1 at r=Re and is equal to maximum velocity pressure 1 effects plus one-half of maximum atmospheric pressure change. i' l C-3 1 i
1 Design Brsis for Torntdo-Gan: rated Missiles Joseph M. Fart 2y Nucl3:r Plant l
. Revision 3 Enclosure Page- 55 Attachm of 65 t
- i 4
j Equation Cl-Sb shows that Per will be a maximum only
- at r=Re (rogardless of the value of X C) 8 and again
! will be equal to maximum ~ velocity pressure effects l plus one-half of maximum atmospheric pressure change. l For structures with openings loading due to atmos-pheric pressure change may ap,proach zero (as for ccm-pletely open structures). Therefore, the load case j i of velocity pressures acting alor:e urust be considered.
- These considerations result in the following design load equations
4 I 7 ; velocity pressure acting alone: i We=Weg (aq. Cl-10) ' { Atmospheric pressure change acting.alone Wg =W, g (Eq. Cl-11) j Velocity pressure cencurrent with atmospheric pressure change: We=Weg + 0.5 Wep (Eq. Cl-12) l These equations are identical to Equations 3-1, 3-2 1 4 and 3-4 in Section 3. ' ( 1.4 Missile Load Combinat_ons i Missiles within a tornado wind field tend to be ejected from the tornado. The maximum missile velocity is obtained when the missile is near but outside of the radius of maximum wind (a.) . For design purposes, missiles are therefore assumed to strike a structure at or near the radius of max & mum wind at which time the structure is subjected to full velocity pressure effects plus one-half atmospheric pressure change. Since the missile may also be ejected from the tornsdo before striking the structure, missile effects are considered acting independently or in combination with velocity pressure and atmospheric pressure change. This results in the following design load equations: he C-4
- s. .. _ _
_ ._ .I
__ _ -___ ._ . _ _ . .. _ _ _ _._ ..._. . __ . . . _ _ _ . . . _ . . . ~ _ . . _ . _ _ . _ . _ _ _ _ - _ _ _ _ _ _ . D: sign BIsis for Tornado-Gsn:rtted Missiles
- Joseph M. Farlsy Nucisar Plint 3
Enclosure - Attachment 5 1 Revision 3 Page 56 of 65 1 4 Missile acting alone -5 i Wg=w, r (Eq. ci-13) i Missile impact concurrent witt wind loads: / i We=Weg+#a t . (Eq. C1-24) p.
- )
Missile impact concurrent with wind load und atmospheric pressure change: 4 We = W g , + 0.5 Wep+W, e (Eq. ci-15) ! These equations are identical to Equations 3-3, 3-5 j and 3-6 in Section 3. i 2.O STRUCTURE SIRE EFFECT 05 VEI4 CITY PRES 8URE IDADING t
- The tornado wind velocity varies with distance from the centernot vatively) of the tornado to vary with(r) but is assumed (conser-height.
- The total load on j a structure (or structural element) is therefore a direct function of its plan dimension, L, perpendi- ;
cular to the direction of wind. j The total load will be a maximum when the radius of j maximum wind speed falls within the length, L. Referring to Figure 3-3: 1 l3 i rg<R,<r2 L = r2 - f1 (Eq. C2-1) An integration of the velocity pressure profile (de- l3 fined by Equatiqns Cl-5a and Cl-5b) on a horizontal ; strip between limits of r1 and r2 results in thir following expression for total force on a unit width strip of length, L.
~ pCK'V* "
rf d' 2 b ~ 3Rj ~ 5 Ofrg jR, (Eq. C2-2) R jr 2 ** i i s C-5
-- - - . . . . - - - - .- - . _ . - . - - - . - . - - . - _ ~ - . , . .-
. s
^
D: sign Bisis for Tornado-G:nk$ted M Joseph M. Fart:y Nucl:.ir Plant l 1 . Revision fnclosure- Attachment 5 l Page 57 of 65 j s From===4== examination of Equathon C2-2, it is found that F ! is a when the structure is positioned such j that rt=R 2 /r2-1 4 Making the following subs: ,itutions into Equation C2-2;
- -Ki dK! l I4 .
K2* 2
, , (Eq. C2-3) 1, '
La K11 i r1 = K R2a \ l ..' 5 P,,,={ . ! 2 4 - P = pCK9"2y - max 2 e 1 i i The ratio of average presiure to ===i=um pressure is: I i i 3 I i ave 4 2 1 P B (Nq. C2-4) 3K (K1+E 2J K max 1 {K1 1 i ( A plot of Equation C2-4 (Pave /Paax V8' I)I is shown in Figure 3-3.
. b l3 Knowing ratio of structure the maximum length veloc$ty 3to radiuspressura of maa (Pand the
,la)us n wi d velocity (L/m,directly from Figure = Kg) can be deteEstined 3-3. , the Th$ average pressure (P ,Oa)lu of Re is specified in the plant SAR. 3 t
4 1 m
. :: o E
5 C-g
Time * (sec) i
.*r n-
,e ..
1 2 3 4 5 6 7 :2.- 0.0 : : " 8 9
; l !
0.1 , , 3 sec.
= _
0.2 , _ Tamm11aed . Osme , , . .
- 0. 3 , .
Curve based on squations C1-7a through Cl-?d ' O.4 ,_ 0.5 . . _ .. k :
- Time scale based on a value of --
o." 0.6 . R" V
= 3.0 sec.
u , . D.7 --
'Ihis value was aniacted for illustrative purposes m1y. (Design values of Ih and vtr to be
., g ,, obtained fr a plare m .)
t 0,? . .
~ . . . -
e. i S 1.0 / ; m m 0.5 l ] 5-1 1.5 2 2.5 3 r_, g& t g jg i PJGURE Cl-1 ms3 ' Atmospheric Pressure Change variations With Radius And Time :s
$ gay i w
Emo BS$
,.<a .
m>ZB
$$bk !
N"a a am:m s [ Soa8 , h .. ~
J Drsign B: sis for Tomado-G:nsrated Missiles Joseph M. Farily Nuct:Ir PI:nt g,y{,gggesgre - Attachment 5 Page 59 of 65 4 4 e ) l APPENDIX D i l CMP RER PROGRAM 4 FOR BUILDING DEPRE880RIEATIon j RBCHTEL CORPORATION PROGRAM CE 899 4 I i l a l d e
N D: sign Basis for Tornido-G:n:r.-ted Missiles
- Joseph M. Ferlsy Nuciser PI
- nt y,yg,glopre- Attachment 5 i ' Pago 60 0f 65 j .
~
. I i-
[ APPENDIX D f* r 2 COMPUTER PROGRAM FOR , { . i. BUILDING DEPRESSURIIATION g j 1 BECHTEL CORPORATION PROGRAM CE 899 j 1.0 PROGRAN CAPABILITY . i 3 i *
- Bechtel Corporatica program CE 899 is used to calculate i difforential pressures between compartments within buildings and across interior and exterior surfaces of a building subjected to torn l3 atmospheric pressure change.,edo-induced time-dependent 1.1 Theory and Eqtuations Laws for quasi-steady, one-dimensional motion of an l3 ideal compressible gas are used to calculate the flow 3
- of air in the structure and the differential pressure - history with the three-dimensional effects taken into ' account by a factor of safety. 3 The weight flow rate of air and the relationship between pressure and air weight-density are based on an adia-batic process. l 1.1.1 Weight Flow Rate The weight flow rate, G, of air passing through an orifice is defined as follows (from Ref. 20): G = C,C Ae 2 I29Y1(P1-P2)) (Eq. D-1) 4 C,= Cd ll-IA2 /A)2) 1 %. >2) fP2 'A2,2 UC " fP,i2/k f k I l~ k 1~ N ~ 4 { Q 1 f p2' 1-
'A 2 2 iP2'2/kI, g L P13 ) ,A1 ; (P1j l (Eq. D ~i)
, t D -1
-. _ _ _ _ . _ _ _ _ . . _ . . _. i
_ _ _ _ . _ _ . . . . . . _ _ _ _ _ _ _ _ _ _ _ _ , _ . _ _ _ _ _ _ ~ . _ . _ _ . _ . _ _ _ _ _ . _ _ _ i
- 1; Y:
i Dssign Bisis for Tornido-Grnsrtted Missiles # l j Jos:ph M. Farisy Nuciser Plant I Revision Onclosure- Attachment 5 Page 61 of 65 j - . 3{ - j l j A1 = Area (on' the side of compartment 1) of ' 3
, the' wall between compartments 1 and 2.
A2 = Ar.ea connecting compartments 1 and 2. ! cc = Compressibility coefficient. Cd = Discharge coefficient (which is a func- { tion of asynolds number - Ref. 20, p. 125). C, = velocity coefficient. ! g = Gravita,tional acceleration. 1 x .. Specific heat of air at constant pressure a j ,J Specific heat of air at constant volume
- 1*4 if i
' P1 = Pressure in coagprtment 1.
} P2 = Pressure in oopt 2 (P <Pt) ! 2 i v1 = Weight density of air in compartment 1,. - i j* ' Bquation D-1 is valid if the flow through the orifice is suberitical. The flow is suberitical when the ] 4 conditions of Equation D-4 are satisfied (Ra]. 21) . P2 j- l>,go.528 (Eq. D-4) I i j 1.1.2 Pressure Weight-Density Relationship l 2 The following relationship between pressure and weight-lI density is assumed to be constant: 8 4 l3 e
-k PYNN = a constant (Eq. D-5) e PN = Preneure in compartment N.
yg = Weight-density of air in compartment N. i l Within each time increment, At , the flow is assumed to l be steady and subcritical. The weight of air in com-partment N, W N , at time tg4g is therefore j l Wg(t i+g) = Wy (tg)+(G y (ig)(ti )-Gm (out) (t t) ] At (Eq. D-6) The weight flow rate, Gy, is defined by Equation D-1. Since the volume of each compartment remains constant, the ratio of weight densities is equal to the ratio of weights: Yg(tg ,g)/yy(tg ) =Wy(tg,g)/W,(t g) (Eq. D-7) D-2
Design Basis for Tornado-Gen: rated Missil:s i Joseph M. Ferisy Nuctsar Plant Revisiecl3sure - Attachment 5 Page 62 of 65 1 - 1.3 Input Data f The input data required for the program are as follows: I
- 1. Total transient time and time integration i terval.
- 2. Table of weight density of air vs. pressure
! 3. Table of atmospheric pressure vs. time. i 4. Number of compartments, number of ports, nuqber of in-tercompartment connections, initial pressurg for all compartments and ports, velocity coeffici , C, and compressibility coefficient, Ce. If not ified, the values of C, = 0.6 and cc = 0.98 will' W in the program.- -
- 5. Compartment and connectivity list, inal the com-partment volume and whether it is ao a port.
3 6. Port and port area table ,giving initial area, blowout panel area and blowout pressure.
- 7. Intercompartment area table giving initial ponnecting
- area, blowout panel area and blowout pressure.
I Most of the data required for the program can be esta-blished from the geometry of the structure and the inter-I connection of compartments. Values of Cv and Ce can be ! assigned using data for standard orifices such as those [3 ! contained in References 22 and 23 as a guids. i 1.4 Example i An example of a structure depressurization mokel defining compartment volumes, connectivity, ports and interior vents is described in Section 4-6 and Figure 4-10. A typical differential pressure-time history resulting . from an atmospheric pressure-time function (Figure 3-1) l3 applied to this model is shown in Figure 4-11. l
. l s
D-4
_ . .. - . . . . -- . - -- - _...-.- _~. - - - - - - . _ . _ . . - - . . . . . . . _ - - . . . . - - , - . - . ~ . . _ - 1! t . DIsign Basis for Tornado-Ginerated Missiles gse h VI. Farity Nuctsir Plint V M99suk - Attachment 5 i 4 Page 63 of 65 i i ( f
- 1
+ l l 4 i APPENDIX E t I i-4 i 4 s i REFERENCES . I i 4 4 t e s s, 1 ; e
- 1 l
I I f f I i. l
. )
9
,, v., ,
_ _._.__ _ _ ___._ - . _._ . _ _ .___..... _ .. _ .. _ ..-.__.._ _ __ _ .. _ .__._. _ .~ . M 1 Dssign Basis for Tornado-Gen: rated Missiles Joseph M. Fartsy Nuctaar PI:nt' j Enclosure - Attachment 5 RevisAon 3 Page 64 of 65 i i $ ! l APPENDIX E; , 1 , 4 i t i REFERENCES' i 1.- "American National.Stan d sui % ding code Reggirements for Minimum Design Lo in Buildings and othey Struc-tures", American Mation 1 Stand rds Institute
,.+ 3. A58. g-19 72.
I ASCE cossaittee Report, " Wind Forces on Structures" , 4-Transactions of the ASCF, Paper No. ! ! 3259, 196g i i i 3. ! i W forl. Missile { sechtel Pcwor Corocration, " Design of Structures . Impact", Topical lteport SC-TOP-9, Rev.1, Jul 1973. i l 4. \
" seismic Design Classificat' ion", Regulatory G de 1.'29,
~
Directorate ofRevision Consitission, Regulatory 1, AugustStandards, 1973. U. S. Atomic Energy '3 5.- Irish, K., ACI Journal,and R. Cochrane, September,19 72." Wind vibration of Chimneys", 6. Kessler, E. , (of National Severe Storas Laboratory), letter to E. Denton, on the Subject of windspeed and regional characteristics of tornadoes, April 25, 1973.
- 7. Bechtel Corporation, " Design Criteria for Nuclear Power Plants 12, 1970 Against Tornadoes", Topical Report B-TOP-3, March
- 8. Shanahan, J. A., " Engineering Report on the L 4 bock Tornadoes of May 11, 1970", Bechtel Corporation, Power and 1972.Industrial Division, San Francisco, Calif. , October,.
- 9. Plora, S. D.,
" Tornadoes of the United States", University of Oklahoma Press, Ncrman, Oklahoma, 1953.
- 10. Reynolds, G. W., " Venting and other Building Practices as l Practical Means of Reducing Damage from Tornado Low Pres-sures", Bulletin, American Meteorological Society, Janu-ary, 1958.
E-1
_. _____.___.__.__.._______________.-__.m _. - _ _ _, Design Basis for Tornado-Gensrated Missil s [ Jos:ph M. Farity Nuctsar Plant L Revisiolkictpsure - Attachment 5 Page 65 of 63 l I f
- I l I
- 11. Fujita, T. T., " Estimate of Maximum Windspeeds of Tor-nadocs in Southernmost Rockies", SNRP Research Paper No.
105, The University of Chicago, June, 1972. 2
' 12 . Fujita, T. T., " Estimate of Maximum Windspeeds of Tor-
, nadoen in Three Northwestern States", SMRP Research ] $ Paper No. 92, The University of Chicago,1970.
- 13. Fujita, T. T., "A Detailed Analysis of the Fargo Torna-does", U. S. Department of Commerce, Weather Bureau, .
Research Paper No. 42, December, 1960. : l l 14. Fujita, T. T., D. L.. Bradbury, and P. G. Black, "Esti-nation of Tornado Wind Speeds from Characteristic Ground Marks", SNRP Research Paper No. - 69, The University of Chicago, 1967. - ]
- 15. Fujita, T. T. , D. L. Bradbury, and C. F. Van Thullerar,
" Palm Sunday Tornadoes of April 11, 1965", Monthly -
Weather Review, 9 8, No. 1, 1970, pp. 29-69.
- 16. Hoecker, W. H., " Wind Speed and Air Flow Patterns in the Dallas Tornado of April 2,1957", Monthly Weather Review, May, 1960, pp. 167-180.
- 17. Lewis, W., and P. T. Perkins, " Recorded Pressure Distri-bution in the Outer Portions of a Tornado Vortex", Monthly Weather Review, December,195 3.
- 18. Mcdonald, J. R., " Structural Response of a Twenty Story Building to the Lubbock Tornado", Texas Technical Univer-sity, TTU-SSR-01, October, 1970.
- 19. Mehta, K. C. , et al. , " Response of Structural Systems to the Lubbock Stors", Texas Technical University, TTU-SSR- )
0 3, October, 19 71.
- 20. Binder, R. C., Fluid Mechanics, Second Edition, Prentice- i Hall, Inc., New York, New York, 1949.
- 21. Eshbach, O. W., Handbook of Engineering Fundamentals, Second Edition, John Wiley & Sons, Inc., 1952.
- 22. " Flow of Fluids Through Valves, Fittings , and Pipe",
Technical Paper No. 410, Crane Co., 300 Park Avenue, New York, New York, 10022, 1969. [3
- 23. Perry, J. A. , " Critical Flow Through Sharp-Edged Orifices",
Trans . , ASHE, October, 19 49, pp. 757-764. E-2
1 Design Bisis f r Tornrdo-G:n: rated Missiles Jos:ph M. Farley Nuclear Plant ! Enclosure l l l l ATTACHMENT 6 1 I l 4 l
a Dssion Basis for Tornado-Generated Missil:s ; t
- Jossph M. Fariey Nuclsar Pl:nt ,
I Enclosure- Attachment 6 ! dgI1Lun AND y0Wst Cgvsg3105 SYSTEN BRANCE Page 1 of 2 i QUESTION AFC-1 (Transmitted by letter March 6,1974) 3.5 Missile Protection ! 1. Based on the destga tornado, provide the following information, ! is addition to that provided in the FSAR. for the missiles listed j in *aragraph 'e' belaws - i i s. The nazimum velasity and height attained. Assuma in tha ! analyses that each of the missiles originate at ground level i mad at inereestag elevatione is increments of 30 ft up to the j highest strastusal slavation as the site. ! b. In developing the above Laforest1ms, asses the missiles de not i tumbia and are at all tians orieted smak as to have ths anzimme vnha of (C,A/W) while is flight, share C is the drag i coefficiant A is can area and W is the weidt. erite the ! calcalational method used and list any references'used.in j this evaluatima. I j c. Supply the taformation requested above for the following tornado missiles l (1) 4-in. a 12-in. plank z 12 fs less with' density of 50 lbs/ft 3; l (2) Utility pgle 13.5-in. dia x 35 ft long with density of 43 lbs/ft I (3) 1-in.seligsteelred3ftlosswschadensityof 490 lbs/ft a i
- (4) 3-ia. s y 40 pipe, 15 ft less with a density of
- 400 lbs/ft 1
l (5) 6-in. sehegule 40 pipe, is it 1ses with a demnity of
- 490 1he/ft
1 j (4) 12-in., sopa 40 pipe,15 ft lens with a damsity of 490 lbs/f t . l j l
- 2. With the aid of site plot plans and layout drarings cf Units 1 and 2, identify and locata all essential syetans and - e *= that are required in order to attata a safa abatdema in the event of a tornado.
. 36 Amend. 39 9/16/74 Amend. 36 6/3/74 APC-1-1
- - - . - - . - . . . - _ . - - . - - - - - - . . - - . - - - .~...- - . -.-.- -
t i Design Basis for Tornado-Generated Missil:s 5
' Joseph M. Farley Nuclear Plant Enclosure Attachment 6
! Page 2 of 2 i RESPONSEt /
)
., Part 1 l - i ._ - The tornado-senerated missiles considered La design of the safety-related j structures of Farley units 1 and 2 are given in F5AR Section 3.3.2.1(c) and ' are the sans as those previously included in PSAR Section 5.1.2.5, " Tornado Isads." The PSAR Section 5.1.2.5 was revised specifically in response to the AEC's PSAR questions 5.2 and 5.36 and filed as Ammadasat No. 6 on l October 14, 1970. Upon completion of the ABC revier sad the ACES favorable I action, this FSAE section became the basis for Farley's tornado missile protection criteria for all safety-related structures, systems, and components. 36 Each of the six postulated tornado missiles listed by the ABC in Question APC-1 is differsat in one respect or another, from those for which Farley's j l safety-related structures, systems, sad cosposeats are designed. Consequently, none of the postulated missiles in question was eensidered in the design ( criteria for the saisting Farley Units 1 and 2. j The reinforced concrete wells and roofs of safety-related structures have a ! mini = = thickness of 2 ft, and a =4=4== ( 4000 pai. compressive strength (f'e), of 39 i j Part 2 j Table 3.2-1 lists the mechanical systems components. The tabla shows that all equipasat required for safe shutdown in the event of a tornado, with I the exception of the condensate Storage Tsak, are protected in the event of 39 a tornado by virtue of being located in a structura designed for a tornado j wind. The Coedensate Storage Tsak is self protected to 150,000 gallons. The electrical equipasat required for safe shutdown is also protected agatast tornado effects, since they are located in structuras designed for tornado i winds. i i i ) 1 l 1 i
. .a cu I4 II 4%
Ansad. 39 9/16, m d. 36 6/3/7s APC-1-2
)
Design B sis f:r Tcrnnd;-Gen: rat d Alissil:s Jrseph 31. Farley Nuclear Plant Enclosure l l I ATTACHMENT 7 l 1
l D:isign BIsis for Tomado-G:nerated Missiles , Joseph M. Farlsy Nuclear PI:nt l
- Enclosure - Attachment 7 Page 1 of 7 i NUREG-75/034 i 1
I May 2. 1975 I i SAFETY EVALUATION REPORT BY THE OFFICE OF NUCLEAR REACTOR REGULATIOR U.S. 4) CLEAR REGULATORY CapetIS$10N ! j IN THE MATTER OF j ALABAMA POWER COMPANY 3 F JOSEPH M. FARLEY NUCLEAR PUUIT UAITS 1 AND 2 DOCKET NOS. 50-348 AND 50-364 i i 1 1 AvaBalde hem National Tednesal lafonuseine $srvase Sprhgemid, Vlegenes 22161 hw Priend copy s&25; Muronske $2.25 i i i w*i
) W M \ i^ l9q.
u
_ _ _ _ _ ~ _ _ _ _ _ _ _ _ . . . _ _ _ _ _ _ _ _ _ __ _.__ Design Basis for Tornado-G:n: rated Missil s Jos ph M. Fartsy Nuclear PI:nt Enclosure- Attachment 7 Page 2 of 7 TABLE OF CONTENTS PAGE i
1.0 INTRODUCTION
AND GENERAL DESCRIPTION OF PLANT...................... 1-1 1 1.1 Introduction............................... 1-1 1.2 General Plant Description.................. .................. ............. .... 1-2
- ' 1.3 Comparison with Similar Facility Designs................. ....
1.4 Identi fication of Agents and Contractors. . . . . . . . . . . . . . . . . 15 1.5 1-5 Sunnsry of Principal Review Matters. . . . . . . . . . . . . . . . . . . . . . ..... ... 1-5 1.6 Facility Modifications as Result of Regulatory Staff Review 1.7 1-6 Sumary of outstanding Review Itas and Issues . . . . . . . . . . . . . .... 1-7 2.0 $1TE CHARACTERISTICS................................................ 2-1 2.1 Geography and 0 mography...................................... 2.2 Nearby Transportation 2-1 2.3 Meteorology.......... Industrial and Military Facilities..... 2-2 . 2.4 .............................. 2-4 Hydrol ogy and Hydrologic Engi neeri ng. . . . . . . . . . . . . . . . . ......... ........ 2-6
! 2.5 Geology. Seismology and Foundation Engineering................ 2-13 3.0 DESIGN CRITERIA FOR STRUCTURES. COWONENTSc EQUIPDENT 31 AND SYSTEMS..
3.1 Conformance wi th General Des ip Cri teria . . . . . . . . . . . . . . . . . : . . . . 3.2 3-1 Classification of Structures r=- 3.3 Wi nd and Tornade Loadi ngs . . . . . . . .n = ts . and Sys tems . . . . . . . 3-1 .. l 3.4 ............................. 3-3 l 3.5 WaterLevel(Flood) Protection...... 3-4 Missile Protection............................................ 3.6 .......................... 3-5 Protection Against Dynamic Effects Associated With Postulated Rupture of Pi 3.7 Seismic Des 1 p ............ ping.....................the ........... 3-6 3.8 .................................... 3-6 3.g Desip of Sei smic Category I S tructures . . . . . . . . . . . . . . . . . . 3-7 !' Mechan ical Sys tems and Components . . . . . . . . . . . . . . . . . . . . . . . . .... .... 3-10 3.10 Seismic Qualification of Category I Instruentation and ; Electrical Equipment........................................ 3-13 4.0 REACT 0R............................................................. 4-1 4.1 4.2 Genere1....................................................... Fuel Mechanical Design. . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 4.3 Therieel and Hydraulic 0esign.................................. 4-1 4.4 4-4 Nuc l ea r Des 1 gn . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . ............
............ 4-7 5.0 PEACTOR COOLANT SYSTEM............ ................................. 5-1 5.1 5.2 Genera 1.......................................................
Integrity of the Reactor Coolant Pressure boundar 51 5.3 Integri ty of' the Reac ter Vos se1. . . . . . . . . . . . . . . . . .y.............. ........... 51 5-3 5.4 teacter Cool ant System Overpres surt Protecti on . . . . . . . . . . . . . . . . 5-4 5.5 Pep Flywheel Integri ty. . . . . . . . . . . . . . . . . . . . . . . . . . 5-6 5.6 Lestege Detection............................................. ............ 5-6 5.7 Inservice Inspection............................. ............ 5-7 5.8 Loose Pa rts Moni tor. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-7 6.0 ENGINEERE0 SAFETY FEATURES.......................................... 6-1 6.1 6.2 Genera 1....................................................... Conta i runent Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-1 6-1 6.2.1 Conta inment Func tional Des ign. . . . . . . . . . . . . . . . . . . . . . . . . 6-1 6.2.2 Con tai nment Hea t Removal Sys tem. . . . . . . . . . . . . . . . . . . . . . . 6-4 6.2.3 Containment Isolation System.......................... 6-5 6.2.4 Combustible Gas Control System.............. ......... 6-5
**'^ainment Leakage Testing Program................... 6-6 ra t ion Room Fil tra t ion Sys tem. . . . . . . . . . . . . . . . . . . . 6+7 i
4 i Design Basis for Tornado-Grnsrated Missil s ; i Joseph M. Fartsy Nuctur Plant ; Enclosure- Attachment 7 1 Page 3 of 7 , 2 r TABLE OF CONTENT 5 (Cont'd) l 4 4 PAGE I a f 6-8 l
- 6.3 Emergency Core Cooling 5ystem................................ 1 Design Bases......................................... 6-8. l i 6.3.1 6-8 6.3.2 System Design........................................
l 6-11 6.3.3 Tests and inspections................................ 6-12 6.3.4 Conclusions.......................................... a i 6-12 ) 6.4 Emergency shutdoun Cooling Capab111ty........................ 6-15 6.5 Residual Hea t Removal 5ystem. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Habitability 5ystem.......................................... 6-16 i
- 6.6
.t . 7-1 7.0 I NSTRLSENTATION AND CONTROL 5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-1 7.1 Gomore1...................................................... 7-1 7.2 Reactor Trip System.......................................... 7-1 7.3 Engineered safety Features Actuation and Contro1............. 7-2 1 7.4 Systems hoguired for Safe Shutdeun........................... 7-2 7.5 Safety Related Displ ay Instrissenta tion. . . . . . . . . . . . . . . . . . . . .. . Control Systems het Required for 5afety......:............... 7-2 '- 7.6 7-2 - 7.7 Environmental and Seismic Qualifications..................... 7-3 . 7.8 Cable Separation and Identification Cri teria . . . . . . . . . . . . . . . . . 8-1 i 8.0 ELECTRIC P0WER..................................................... s a 8-1 8.1 Genere1...................................................... 8-1 ' 8.2 Offsite Peuer System......................................... 8-2
- j. 8.3 Onsite Pouer System...........,..............................
9-1 9.0 AUXILIARY 5YSTEMS.................................................. 9-2 9.1 Chemical and Volume Control System...............c........... 9-2 9.2 Fuel Storage and Hand 1tng.................................... 9-2 , 9.2.1 New Fuel Steroge..................................... 9-3 i' 9.2.2 Spent Fuel 5torage................................... 9-3 9.2.3 spent Fuel Pool Cooling and Cleanup System........... 94 ) 9.2.4 Fuel Handling 5ystas................................. 9-4 9.3 Cooling Water Systems........................................ 9-4 9.3.1 Auxiliary Foodneter Systas........................... 9-6 9.3.2 Caspement Cooling Water 5ysten. . . . . . . . . . . . . . . . . . . . . . . 9-7 9.3.3 Service Meter 5ysten................................. 9-8 9.3.4 Ul tiests Meet $1ak. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9-10 9.4 Air Canditieming Notting, Cer, ling' and Ventilation Systems... 9-10 9.4.1 Centre) Room Air Conditioning and F11tretion System., 9-11 9.4.2 Ammil lary Buil ding Ventil ation Systes. . . . . . . . . . . . . . . . 9.4.3 Service Water intake Structure Heating and Ventils- 9-11 tion 5ystem........................................ 9.4.4 River Water Intake Structure. Heating and Ventila- 9-12 tion System........................................ 9.4.5 Diesel Generator Building Heating and Ventilation 9-12 5ysten............................................. 9-12 9.5 Fire Protection System....................................... 9-14 9.6 Diesel Generator Auxiliary 5ystems...........................
D; sign Bisis for Tomado-G:n rated Missiles + Jos ph M. Farity Nucbir Plant Enclosure - Attachment 7 Page 4 of 7 TABLE OF CONTENTS (Cont'd) 7 _PAGE 10.0 STEAM AND POWER CONVERSION SYSTEM.................................. 10-1 10.1 Summa ry Descri ption . . . . . . . . . . . . . . . . . . . . . . . . . . 10.2 Turbine 10-1 Generator............................................ 10.3 Main ; team Supply ............... 10-1 System..................... ... ........... 10-1 10.4 Circulating Water System.........................
........... 10-2 11.0 RADICACTI VE WASTE MMAGEMENT. . . . . . . . . . . . . . . . . . . . .11-1 ..................
11.1 Source Teras............................. 11.2 Liquid Weste 11 2 Treatment....................................... .................... 11-2 11.3 Gaseous Weste Treatment...................... 11-4 4 11.4 Sol id We s te Trea tmen t. . . . . . . . . . . . . . . . . . . . . ................
. . . . . . . . . . . . . . . 11-8 11.5 Process and E f fluent Radiological Moni toring. . . . . . . . . . . . . . . . . 11-10 12.0 RADIATION Ph0TECT!0N............................................... 12-1 12.1 Radiation Protection Design Fea tures. . . . . . . . . . . . . . . . . . . . . . . . . 12-1 12.1.1 Shielding.......................
1 .................... 12-1 12.1.2 Vent 11stion..................... .................... 12-2 12.2 Health Phytics Program.................................... 12.3 .. 12-2 Conclusions.................................................. 12-3 13.0 CONDUCT OF OPERATIONS.............................................. 13-1 13.1 Plant Organization, Staff Qualifications 13.2 Emergency Planning. . . . . . . . . . . . . . . . . . . . . . . and Traini ng. . . 13-1 ..... < .......... 13-3 13.3 Sa fe ty Re vi ew and Aud 1 t. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13-3 13.4 Plant Procedures............................................. 1 13.5 Industrial Security................................. ........ 13-3
........ 13-4 14.0 INI T! AL TESTS AND OPERAT!0N. . . . . . . . . . . . . . . . . . . . . . . . . . . . 14-1 ............
- 15.0 ACCIDENT
- AN4.YSIS.................................................. 15-1 16.1 Genere1...................................... 15-1 15.2 Thernet and Hydraulic Analyses............... ............... ............... 15-2 15.2.1 Anticipated Operational Occurrences. 15-2 15.2.2 Accidents............................................
................. 15-3
- 15. 3 Offs ite Dese Ana lyses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15-6 i 16.0 TECHNICAL SPECIFICATIONS........................................... 16-1 17.0 QUALITY A$31 HANCE.................................................. 17-1 17.1 Genere1........................... 17-1 17.2 Organization.................................................
............. 17 1 17.3 Quality Assurance Program....................................
17.4 Conclusions.................................................. 17-2
.............. 17-3 18.0 REVIEW BY THE ADVISORY C0petITTEE ON REACTOR SAFEGUARDS (ACRS)...... 18-1 19.0 C0peq0N DEFENSE AfG SECURITY........................................ 19-1 4 20.0 FINANCIAL QUALIFICATIONS........................................... 20-1 i
4
D sign Basis for Tornado-GIntrated Missiles Joseph M. Farity Nuclicr Plint Enclosure- Attachment 7 TABLE OF CONTENTS (Cont'd) Page 5 of 7 i PAGE l 21.0 F INANCIAL PROTECTION AND INDDt't!TV RE@ IRDtENTS. . . . . . . . . . . . . . . . . . . 21-1 21.1 Genere1..................................................... 21-1 21.2 Preoperational Storage of Nuclear Fuel..... ................ 21-1 21.3 Operating License........................................... 21-1 22.0 CONCLUS10NS....................................................... 22-1 4 A*PDCICES , i , APPDCIX A Chronology of Radiological Rev1ew........................ A-1 APPD G1X B Bib 11ography............................................. B-1 1 4 f I ll .
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l i b i t B G 40N. . . -c 6, , , IV J-
D: sign BIsis for Torn!do-Gsnzrtted Missiles ' Jos:ph M. Farisy Nucinr Plint ' ) of these criteria is an acceptable basis for satisfying the requirements of GeneralEnclosure- Attachme , Design Criterion No. 2 of 10 CFR Part 50. Page 6 of 7 +
- 3 i i The method of combining buoyancy and hydrostatic loads with other design basis loads is evaluated in Section 3.8 of this report.
} 3.5 Missile Protection. . ) The seismic Category I structures and components are either designed for or l shteided from postulated missiles including tornado-induced missiles and missiles generated by failure of components in the reactor coolant pressure boundary within i containment such as a loss-of-coolant accident. Seismic Category I structures have concrete wells and roofs that are at least 2 feet thick. 4 Appiteent's calculations result in a menise penetration in concrete of to inches. Cooling ster pipes (including river water and service water systems) are borted over most of their length. The seismic Category I equipment that is outside of Category I structures (refueling unter storage tank, condensate storage 1 tank and reactor makeup mter storage tank) a=e protected by a thick steel tank well or by cercrete retaining alls to safeguard the quantity of unter in the tanks needed for safe shutdown. ! ' The applicant has concluded, and we concur that the 2-foot-1 i minium thickness of concrete roofs and usils provides adequate protection against ; tornado-induced missiles. . The applicant has provided adequate information in FSAR 5ection 3.5 regarding ' I the structures, shields and berriers that are designed to resist the effect of missiles generated within contalmeents, including the chorectoristics of missiles selected to demonstrate their adequacy. The analysis of structures. shields and barriers to determine tie effects of missile tapact is accomplished in tuo steps. In the first step, the potential damage that could be done by the missile in the
- immediate vicinity of impact is investigated. This is accomplished by estimating the depth of penettetton of the missile into the impacted structures.
Furthermore. I secondary missiles are prevented by fixing the target thickness mall above that determined for penetration. In the second step analysis, the ovem11 structural i response of the target when ispected by a missile is determined using estabitshed methods of analysis. We have reviamed the appitcant's criteria fler protectlen from postulated missiles l caused by tornadoes er failure of components inside contateneet. We have concluded that use of these design criteria provides ressenable asserence that the structural ) integrity and safety function of seismic Category I structures and components will not be tapetred by potential missiles and that the use of these criteria is an ; { acceptable bests for satisfying General Design Criteria Nos. 2 and 4 of 10 CFR Fart 50, 3.6 Protection Aestnst Dynamic Effects Associated with the Postuisted Reture of Pisine The applicant has incorporated provisions in the design of the piping systaus both inside and outside of containment for protection against the dyramic effects ! associated with pipe ruptures and the resulting discharging fluid. We have reviewed these provisions as described in the FSAR Sections 3.6 and Appendia 3K and have concluded that in the event of the occurrence of the combined loadings imposed by en earthquake of the magnitude specified for the safe shutdown earthquake and a con-current single pipe break of the largest pipe at one of the design basis break
; locations, the followir; ;Witions and safety functions wC :~ r;n emodated and assured:
h 5 I ,_ _ _
Drsign Bisis for Tornido-Gsntrated Missiles Joseph M. Fart 2y Nucl:ar Plint
- Enclosure- Attachment 7 Page 7 of 7 !
APPENDIX B BIBLIOGRAPHY h
' i Farley Nuclear Plant Units I and 2)(Documents referenced in or used to prepare the Safet *
- General Farley Nuclear Plant Units 1 and 2"" Preliminary Safety Analysis Report (PSAR) with Amend .
j USAEC by Alabama Power Company. (Docket Mos. 50-348 and 50-364), submitted to 4 1 Safety Evaluation of the Farley PSAR by the Division of Reactor Licensing. USAEC l 1 (Docket Nos. 50-348 and 50-364). Deceshier 2.1971. United States Atomic Energy Commission (USAEC). Rules and Regulations, 10 CFR: Part 1 Statement of Organization and General Infomation ' Part 2. Rules of Practice j Part 9. Public Record Part 20 Standards for Protection Against Radiation 1 Part 50 Licensing of Production and Utilization Facilities ; Part 100 Reactor Site Criteria United States Atomic Energy Commission Regulatory Guides: 1
- Division22, August 1. 1974 Power Reactors. Guide Nos. 1.1 through 1.88 as revised through i Division 8. Occupational Health Guides. No. 8.8 Issued July,1973 '
i i United States Atop >ic Energy Commission. Regulatory Standard Review Plan (Sections issued through November, 1974).
- " Standard Fomat and Content of Safety Analysis Reports for Nuclear Fower Plants (Revision 1)" United States Atomic Energy Commission. October 19?2.
l
- Geography and Oesseraphy l j
Regulatory Standard Review Plan. Section 2.1.3, Population distribution. USAEC, October 1974 _ Nearby Transoortation. Industrial and Military Facilities i Regulatory Standard nevleu Plan. Sections 2.2.1 and 2.2.2. Locations and routes. descr1Ptions. USAEC Octater 1974. l Meteoro10er Cry, G. W.,1965: Tropical Cyclones of the North Atlantic Ocean. Technical Paper No. 55 U.S. Department of Casrrrce, Weather Bureau, Washington. D.C. Holzworth, G. C., 1972: Mining Heights Wind Speeds, and Potential for Urban Air Pollution Throughout the Contiguous United States. AP-101 Environmental Protection Agency. Office of Air Programs, Research Triangle Park, North Carolina. Huschke P g E.,1959: Glossary of Meteorology. American Meteorological Society, Boston, Massachusetts. Korshower, J.,1971: Climatology of Stagnating Anticyclones East of the Rocky Mountains, 1936-1970. NOAA Technical Memorandum ERL ARL-34. Silver Spring, Maryland. Sagendorf, J.,1974: A Program for Evaluating Atmospheric Dispersion from a Nuclear Power Station. NOAA Technical Memorandum ERL ARL-42, Idaho Falls. Idaho.
.s l
D: sign Bisis f:r Tcrnid:-Gen: rated Missiles Jos:ph M. Ftrl:y Nuclear Plant Enclosure ATTACHMENT 8 4
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i l
4 I j Design Batis for Tornado-Gzn rated Missiles i Jos:phn((MWWWuctsar Plant 1 l y [.e%\ U.S. NUCLEAR REGULATORY COMMISSION Enclosure- Attachment 8 Page 1 of 4 ; I i
%ee....
) STANDARD REVIEW PLAN OFFICE OF NUCLEAR REACTOR RESULATION i
I' SECTION 3.5.1.4 MIS $1Lt3 CCKtAATED BV NATURAL PHENCBENA l AEVIfw etss0NSIBILIT!ts ! Primary - Accident Analysts Branch (AAS) ! Secondary - Strwetural Engineering Branch ($tt) j Availiary and power Conversion Systems Branch (APC54) I
!. AREA $ 0F REVIEW The appitcant's assement of possible hazards due to missiles generated by the design j basis tornado, fleed are any other natural phenomene identified in section 2.2.3 of the safety analysis report (SAR) is reviewed. The purpees of the review is to. assure that hasards l due to these missiles are acceptably small se that they need not be included in the plant j design basis, er that appropriate design bests missiles have been chosen and properly j characterized. Currently, only missiles from the design bests tornado (Ref.1) are considered l In plant design bases.
l The APC50, under Standard Review Plan ($AP) 3.5.2 identifies these structures, systems and j components that should be protected against missile impact and the $tt. under SAP 3.5.3, l l , assures that adequate protection is pmvided by structures and missile barriers. I l I !!. ACCEPTANCE CRITERIA
- 1. The identificatten of appropriate design basis missiles generated by natural phenomena f, 13 considered acceptable if the methodology is consistent with the acceptance criteria defined for the evaluation of potential accidents from external sources in SRP 2.2.3
'i (Ref.2).
- 2. The staff's positten regarding the systems to be protected against tornade missiles is covered in Branch Technical positten AAB 3-2 (Ref. 3). A representative spectrise of tornado missiles is described in idASM-1341 (Auf. 4) and currently acceptable tapact ;
valecities are Ifsted in item 4 under Review Phres (Section !!!, below). ; i
!!!. REYllNPROCEDuats The revle.er selects and emphasises aspects of the area covered by this review plan as may be appropriate for a particular case. The judgment on areas to be given attention and emphalls in the review is to be based on an inspectfen of the material presented to see whether it is sistler to that recently reviewed on other plants and whether items of special safety significance are involved.
UefeRC STANDAnO nEView PLAN llllll:'."lllll'"::.""'". .":Y'* **'":."."'.'".".L"::'" tllll".*::'ll"4"." '.""".t'."ll*."L"." :'.'." ".2
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- 1. The reviewer obtains fres 5AR Section 2.2.3 the idantific itn o t h'
< natural phenomena which could possibly generate missiles. Enclosure- Attachment 8 ~ , 4 Page 2 of 4 i
- 2. The total probability per year of missiles generated by a specific design basis phenoment striking a Critical area Cf the plant is estimated. This total probability i per year (PT) may be estimated by using the following espression:
Pg=Py aPy xP gg xN , 4
- where l P,, = frequency of octurrence (per year) of the design basis phenomenon ( as calculated in SM 5ection 2.2.3),
4 P, = proba0111ty of the generated missiles reaching the plant, 1 P SC = probabiltty of missiles that reach the plant striking a critical area of the
- plant and N = number of missiles generated by the design basis natural paenomenon.
I P g and P SC are assumed to be egal to I unless analysm htrete louer values.
- 3. If P is greater than about 10*I per year the reviewer should verify that the proper j T design basis events have been chosen and the missiles properly characterized.
l 4. All plants are required to be designed against tornado. enerated missiles (f.e., the l probability of a tornado strike is between 10*3 snd 10' per yur and therefore PT is assumed greater than 10*I per year). The following missiles (described in Ref. 4) and associated impact velocities are presently accepted as an adequate design basis until , more definitive guidelines, based on the review of several topical reports and fndepend-ent analytical work under way by the staff, are developed. l 1 1 5 Fraction of total l I tp,r,nado velocity Note plank, 4 iP.112 in, i 12 f t, tieight 200 lb. 0.8 A. l Steel pipe, 3 in. diameter, schedule 40,10 ft long,
- 8.
0.4 weight 75 lb. Steel red,1 in. diameter a 3 ft long, weight 8 lb. 0.6 C. D. Steel pipe, 4 in. diameter, schedule 40,15 ft long, weight 285 lb.- 0.4 E. Steel pipe,12 in. diameter, schedule 40,15 f t long, 0.4 weight 743 lb. F. Utility pele,131/2 in. Jiameter, 35 f t long, 0.4 weight 1490 lb. 2 Automobile, frontal area 20 f t , weight 4000 lb. 0.2 G. These missiles are considered to be capable of striking in all directions. Missiles A, 8. C. O, and E tre to be considered at all elevations and missiles F and G at elevations up to 30 feet above all grade levels within 1/2 mile of the factitty structures. 3.5.1.4-2 11/24/75
l i ! The staff has, as 42 inter 13 positten, accepted the "no-Q$$${dfrhfoI(Wp4dbGeesrated Missiles vslocitics presented in the Topical Report TVA-TR74-1 (Refs. 5 and 4)J M. {}gleg Nuclear Plant
, 4000-16 automobile at 70 mph and elevations.up to 30 feet above grade levei Ya%.Ma '
pa These velocities are: I l Horizontal Velocity , ft/sec l A. Wood plank, 4 in. x 12 in. x 12 ft, weight 200 lb. 364 , i 8. Steel pipe, 3 in, diameter, schedule 40,15 f t long, l weight 115 lb. 264 ! C. Steel rod,1 in. diameter x 3 ft long, weight 8 lb. 25g , D. Steel pipe, 4 in. diameter, schedule 40, il ft long, } weight 285 lb. 230
- E. Steel pipe, 12 in. diameter, schedule 40, 30 ft long
, weight 1600 lb. 205 F. Utility pele,14 in. diameter, 35 ft long, weight 1500 lb. 241 . G. Autamo6fle, frontal area 20 ftt, weight 4000 lb. 100 I Ussets! win 1 to 80s of the TVA horisontal velocities are aise acceptable j on an interim basis. ' 1 At the operating license stage, applicants who were not required at the construction permit stage to design'te one of the above missile spectra and the corresponding velocity set, should show the capability of the existing structures and components to withstand at least missiles "C" and "F.' The adequacy of entsting protection and any requirements i for improvements will be determined on a case-by-case basis in conjunction with APC58. , The AA8 Branch Chief should be consulted in making such detersinations. , l
)
- 5. The capability of structures to withstand the postulated missile impacts is reviewed by the SE8 and vital target areas are defined by the APC58.
IV. EVAL.UATION FIN 0!!IGS The reviewer verifies that sufficient information has been provided and the review and calculattens support conclusions of the following type, to be included in the staff's safety evaluation report:
"These analyses result in a probability of missiles generated by having conseguances worse than the design basis accident of less than 10*7 per year.
We, therefore, conclude that the probability of missile impacts due to causing radiological consequences greater than the design basis events analysed is so small that it does not present an undue risk to the health and safety of the public.
"These analyses verify that design basis missiles have been properly chosen and i characterized." )
i 3.5.1.4-3
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y* D: sign Basis for Tomido-G:n: rated Misshes REFERENCE 5 JosepNM. F:rtry Nucisir PI:nt
- 1. Regulat ry Guide 1.76, " Design Basis T4rnado fEr Nuclear Power Pla.tsEnclosure- Attachment 8 Page 4 of 4
- 2. Standard Review Plan 2.2.3. " Evaluation of Potential Accidents."
- 3. Branch Technical Position AAD 3 2, " Tornado Design Classification," attached to this plan.
4 "$afety Related Site Parameters for Nuclear Power Plants." WASH-1361 U. 5. Atomic Energy Cosuitssion (1975).
- 5. "The Generation of Missiles by Tornadoes." TVA-TR74-1. Tennessee Valley Authority (1974).
(Topleal report under review by the staff.)
- 6. Regulatory Staff, " Preliminary Evaluation of Topical Report TVA-TR74-1." U. 5. Nuclear Regulatory Commission. February 1975.
3.5.1.4-4 r.n 11/24/75 1
Desiga B: sis f:r Tcrn:d:-G=:rcted Missiles J::eph M. Farley Nuclear Plant
. Enclosure ATTACHMENT 9 i
i f l I l l
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D: sign BIsis for Tornido-G:ntrat d Missiles t CONFERENCE NOTES No. 187 Joseph M. Fart:y Nucle r PIInt j Enclosure- Attachrnent 9 ) EDWIN I. HATCM NUCLEAR F0WER FIANT SOUTHERN SERVICCS, INC./CE0tCIA F0WER Co. 1 DECHTEL JOB 6511
= l
] A ac:ing was Bir-ingham, Alabama held inontheMarch of fices 5,1970. of Southern Services, Inc., Those present were: ' Southern Service,s, Bechtel P. Fischer T. Dowdle M. A. liustes J. Thoruten G. Norton L A. Danaec I H. Williamson R. Conry T. Nienzak J. Windhorst The major portion of the day was devoted to M. A. Suares's emplanation of cornado missile analysi,s. ' In answer to a question on Bechtal procedures for purchasing missile proof doors R. A. Deneau advisad he had not had the opportunity to ! review the details of other Bechtel lobs. The roastor building has i
~j only one exterior door (railroad entrance) and pre 11sinary computation using the Suares method indicate a steel door perhaps 2" thick will !
satisfy the tornado criteria. Preliminary discussies with project ) architect Ted Bennett indicates that it asy be better te perform the ,{ assails design in house rather than burdenieg the deer asenfacturer '
- with the impostive dynamic analysis problem. Seashern Services has !'
eeveral doors whir.h will eme under the tornado ersteria sad will request further infonimation or ask nachtel to perform this merk. \ Regarding missile resistant roof constructios k. A. Dessau believes that the tornado criteria imply hesisontalvelocities and that roofs l may be designed for lesser velocities such as the eseputed free fall ' terminal veleetty of the wooden plank. It is postulated that the auto missile can be lif ted to 15' above ground and for reefs lower than this the effect of a free fall from 25' above ground to the roof shovid be ! i considered. ' ) The only missiles considered by techtel thus far se the gatch project j are the auto and plank (tornado) and the fuel cask drop. At present
- we have no knowledge that the AEC will require the analysia of additional missiles (such as the missile spectrums typical of P.W.R. plaats),
a . Southers Serviae will write requesting fits infesasties as missiles to l be applied to reefs of the diesel gaaerster building and eestrol room. i 4 ff
. R. A. Deneau
- ^: ^
March 16, 1970 e
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4 D:s'gn Bcsis for Tornido-Genstated Missil s
- Joseph M. Ferisy Nt,cisar Pl:nt 5 '
Enclosure. Attachment 9 SOUTHERN SE AVICES, INC. por optics son asm 1 llRMINCHAM. ALABAMA 35202 i M,.I,YJf7U l Edwin I. Hatch Nuclear Flaat - Unit No. 1 Miselle Desian Criteria for Doors and Roofs / j a I. Mr. F. H. Hanson ! Bechtel Corporation i F. O. Box 607
; Gaithersburg, Maryland 20760 i
Dear Mr. Hansomt f i ke would like to have Rechtel's recommended procedure for time apucificath i and purchase of doors located is ireas designed for the effects of tornadoes. Thie would faciude a pair of doors for a.19' .x 10' ant 9 tier eseniaa to ths ) traiskt alavator on the west side of the Control Building and a maraammal j anama daar located nearby. 4 i These doors must withstand tornado wind plus crushing / bursting plus missiles. The architectural appearance of the doors into the Control Building is a j significant consideration. j j j' It is our understanding, from a review of the depressurisation study, that ' interior doors are asemed to blow open at 50 poi pressure differential. We would like your suggested specification and/or design provisies to accomplish
- ibis. -
l The pouring sch3dule requires that we have inforestion on the Control Building j esterior doors withis h . l Additionally, we regaaet a ressmasadaties as to what, if say, adas11e desima i criteria should be applied to the reefs of the anstgency Diesel caserotor j 5 sliding and the Centrol Room. Missile shielding of the air canditismias
- equipeast, whish serves the Control Room and is located on the Control Roon
! roof, should be considered. It is our understanding that the roofe eftehaw j C,gagggl,,,}gg&glas and Turbine Butidiar; to not require design for missiles. ~
a l If yea need further clarification of these requests, please call us. ! Very truly yours. l-Q
./ ,
F. Fischer s
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_ .. __ _ ~. _ _ _ . . , _ _ . . . _ _ _ _ . _ _ . _ . _ _ . _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ . _ _ Dssign Basis for Tomido-G:nsrated Mi<siles Jos ph M. Farley Nuciser Piant
. Enclosure- Attachment 9 Page 3 of S l
April 27.1970 Mr. Paul Fischer Southem Services. Inc. P. O. Box 2641 81mingham. Alabama E202
Subject:
Edvin !. Hatch Nuclear Plant Bechtel Job 6511 ' l Missile Design Crf teria For Doors and, Aseft File: A.29.2/0315 )=33 10'47 Dear Mr. Fischer With regard to your letter of March 17,1970, concoming the above subject, we have the following commnts and mcassendations: 1. Enclosed f6r your infomation aN internal use is a copy of a specification for special doors and frames for peach settom. The supplier of these doors was the overly Manufsetselag Coupsstr. Greensburg Pennsylvania 15602. supply any,further infermation that you usy require.I em certain that they 2 Our specialist, M. Suarez, has studied the need for a missile proof door 6s mentioned in your letter and concludes thet the door should be designed for crushing / bursting but is not required to De missile proof (attsched $neet #1).
- 3. The interior doors are assumed to blev open at 50 paf pensense differential. The following items should be considered in the desip of these doors.
a) All doors should open out. b) Latches of the doors should be designed to fail at 50 psf (see attached Shoot #2). c) An attachsent should be provided to hold door open when the latch fa11s and the door blows open. 4 No particular missile design critaria need be soplied to the roofs of the Emergency Diesel Generator Buildino and the control Asen (attecned Sheet #3). We are in accordance with your understanding that the roof of the control and turbine buildings are not required to be missile proof. l
,, , . . . ~
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e , tr. " ' - D sign Basis forTornado-G:n rated Missiles
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Joseph M. Fart:y Nuclear, Plant cat lCULAYfON Y ~
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D: sign Bas;s for Tornado-G ntrated Missiles Joseph M. Faty Nuclear P, tnt Enclosure- Attachment 9 ,
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When becaus 0/ il.1; frai/slaGuaf nfru.'f -N.o kirado $asca over ce roof a sxhon ix c<catza y go wina eu a ,cas eu, i.w<iaaos a.< 4ino a.r l
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Design B: sis f:r Torn:do-Gen:rcted Missiles Joseph M. Farley Nuclear Plant Enclosure i i i I l ATTACHMENT 10 l 1 J
Design Besis for Tomedo-Gen rtted Missiles i Joseph M. Farisy Nucisar Plant Enclosure- Attachment 10 l "***' BC-TOP-SA , J Revision 2 . SEPTEMBER 1974 1 e
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i i l TOPICAL REPORT l DESIGN OF STRUCTURES l FOR MISSILE IMPACT , i s
. l i
Bechtel Power Corporation San Francisco, Califomia <
!- Design Basis for Tomado-Gen: rated Missiles l Joseph M. Fert::y Nucl:Ir Plint Enclosure - Attachment 10 Page 2 of 82 l TOP 6 CAL REPORT
~
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BC. TOP 9-A Revision 2 DESIGN OF STRUCTURES FOR MISSILE IMPACT PREPARED BY: , R. B. Underman J. V. Rou G. C. K. Yeh APPROVED BY: W. A. Brendes A . d*4MJ K W. Wahl CECHTEL POWER CORPORATIONS lesw Osamt Sorsember 1874 i 3,. .,,
1 i,
.' BC-TOF-9-A Design Basis for Tomado-Gan: rated Missiles Joseph M. Farisy Nucisar Pl:nt Rev. 2 Enclosure - Attachment 10 Page 3 of 82 i
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i CAVIAT: TEIS RDORT RAS DEEN PREPARD M Am FOR TME USE OF RECNTEL POWER CONCEAT10ll AND ITS RELATED ENTIIIRS. ITS USE R OTE RS IS PDMITTE ONLY 011 TEE UllDRSTANDING TMAT TNDE ARE NO REPRESENTATIVES a WARRANTIES. EEPRESS DE IMPLIO AS TO THE VALDITY OF TEE INFORMATION OR CJIICLU810NS CONTAIND RER115. s 6 4 6 e 4 0 e S t-
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I Design Btsis for Tomtdo-Gzn: rated Missiles ' Jos:ph M. Fartry Nucitar Plint ;
,. Enclosure- Attachment 10 ;
Page 4 of 82 { UNITED STATts ,. h. ATOMIC ENERGY COMMISSION l, . u . . ... t l Mr. John V. Morowski l Vice President-Engineering Bechtel Power Corporation Fifty Reale screet sen Francisco, California M119
. Dear Mr. Morowski The Regulatory staff has completed its review of Rechtel power ' '
Corporation's Topical Raport, RC-TOP-9 Revisten 2, dated September ! ! 1974 and entitled " Design of Struct* ares for Missile Impact". We I conclude that the design eriteria and procedures described hp this report are acceptable to the Ragulatory staff and that BC-10P-9 . i Revision 2, is acceptable by reference in applications for sonstruction ; permits and operating licenses. A summary of our evaluation is ; anclosed. . i 30-70P-9 does not provide all of the pertinent information required by the Reguistory staff in its review of specific applications. Therefore, the appropriate supplementary informaties identified in the Regulatory Position of the enclosed Topical Report Svaluaties will have to be prqvided la individual Safety Analysis Reports. The staff does not intend to repeat its review of BC-Tor-9, Revision 2, when it appears as a reference in a particular license application. Should Regulatory criteria er regulattens ebenge, such that sur conclusions concerning RC-T0p-9 Revision 2, are invalidated, you will be notified sad given the opportunity to revise and renubmit your topical report for review, should you so desire. l i
._ . - - . _ . - . ~ _ _ - _ . . - .
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. Drsign Basis for Tomado-Gtntrated Missiles Joszph M. Farlsy Nuctsir Plant
* , Enclosure- Attachment 10 I 1
Page 5 of 82 i Mr. John T. Norowski b#
- b II4
-2 1
J Us request that you reissus BC-TOP-9, Revision 2. dated September 1974 in accordance with the provisions of the " Elements of the Regulatory Staff Topical Esport Review Program" which was forwarded to you on August 26, 1974. If you have any guestions in chie i, regard, please let us know. ; i Sincerely, y ho
. V. Klackar, Technica'. Soordinator
. ' for Light Water Reactors Group 1 Lirectorate of Lic==. sing I Enclosure Topical Report I aluation .
]
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, D: sign Basis for Tomado-Gensrated Missiles Jos:ph M. Farlsy Nucisar Plant i
Enclosure- Attachment 10 i Topical Report Evaluation Page 6 of '82 Report: BC-TOP-g Rev.2 Report
Title:
Design of structures for Missile Impact Report Date: September 1974 . , Originating Organization: Sachtel Power Corporation
- Reviewed by
- $tructural Engineering Branch, November 1974 l ._
l i Summary of Report _ 1 g This report contains the current general procedures and criteria i used by Bechtel Power Corporation for design of nuclear power ! plant structures and components against the effects of ispect; of i missiles. The report covers the evaluation of local effacts due to i j missiles impacting on both concrete and steel' structural elements. ! It also covers the procedures used to evaluate the overall structural ! re'sponse to missile impact loads. Design guidelines related to use ! ) of dynamic capacity increase factors, allowable ductility ratjo and , allowable range of steel ratios used i' nconcrete structural elements - l are also discussed in the report. Brief discussionsof special problems related to (a) force-time history for automobile crash and *
- (b) penetration of a missile through a liquid are included as a l part of the report.
! The formulae which can be used to predict the penetration resulting from missile impact are included in the report. The penetration and i
- perforation formulae assume that the missile strikes the target normal to the surface, and the axis of the missile is assumed parallel to
} the line of flight. These assumptions result in a conservative i estimate of local damage to the target. The formula used to predict . the penetration is tho' Modified Petry equation, while that for per-I
.foration and spalling is the Ballistic Research Laboratory formula mod-
) ified to allow its use for concrete strength other than 3000 psi by replacing the constant coefficient 7.8 by 42Uh The wall j thicknesses to prevent perforation and spalling are that calculated i using.the Ballistic Research Laboratory formula multiplied by factors . of 1.25 and 2.5. respectively. The Ballistic Research Laboratory l { fornula for steel is used to predict design thickness requirement 4 i
_ _ m.. _ , _ - _ _ _ _ . _ _ _ _ . . _ _ __ _ .... ~ _ _ .. _ . _ . .. _ _ _.__. __ _ - . ----- - _ _ _ i Design Basis for Tornado-Gsnerated Missil s ' 3, Jos:ph M. Farlsy N1clur Plant
- , . Enclosure- Att
- Achment 10 Page 7 of 82
.r-i for steal targets. .The thicknesses of steel targets to prevent perforation are obtained by multiplying 1.25 by the thicknesses j for threshold perforation as determined by the BRL formula.
4 The report discusses both elastic and plastic modes of overall structural response of target subjected to a missile impact. Expressions for (a) velocities of missile and target after impact. l (b) strain energy of a target required to stop a missile after j ' j impact. (c) target effective mass definition and (d) resistance ' functions for' various target configurations are presented .in the ! report. The overall structural response of a target is detamined
, , by equating the availab1p target strain energy to the required strain energy to stop a missile. The resistance function for a structural i element is datemined using yield-line theory for concentrated loads impacting steel and reinforced concrete beam and slab. The allowable
' {
ductility ratios to be used for design are based on the available data i from the literature accepted in the engineering practice. However the governing requirement for an overall structural response design co*- n sideration is that the maximum deflection of the target shall be limited so as not to impair the function of other safety related
; aquTpment. Due to the complexity of the impact phenomena, the target j effective mass is conservatively derived based on the tests performed on concrete slabs and beams.
j The report covers two types of special problems i.e., determination of an empirical formula for force-time history gf automobile crash
; and an evaluation of a missile velocity as it passes through a liquid.
In deriving the force-time history of an automobile crash under frontal impact, the automobile is considered as a deformable missile and the structure a rigid target. The partine'n t equations are based on theoretical considerations backed by experimental data. e e 4 1
Design Basis for Tornado-Generated MissilIs Joseph M. Fariey Nuclear Pknt
- - Enclosure - Attachment! 10 t
Page 8 of- 82 I The derivation of the velocity of a missile after it has penetrated . l , through a liquid takes into consideration the buoyant force, which is ! vari,able during the process of immersion of the missil,e and constant ; after the entire missile is imersed in the liquid, and drag force i which may be considered as constant for any particular set of con- l ditions. The non-linear second crder, non honogeneous differential l , equation is transformed into a linear differential equation which I is solved by applying pertinent boundary conditions. . t ! For the postulated missiles and their properties'as well as for - structures, shields 'and barriers that are mquired to be desioned I i against effects of missile impact, the report refers to the plant SAR. Appendix A provides the cross reference between sections of the AEC's' - Standard SAR format and the sections of BC-T0p-g. Glossary of the report is given in Appendix B. A review of existing design formulas is given in Appendix c whereas Appendix D discusses theoretical der- ! 1vai,1on for- force-time history associated with automobile crash and velocity of a missile penetrating through a liquid. Sample applicai: ions of the procedures presented in the report are shown in Appendix E with references and bibliography listed in Appendix F. Sumsey of_ the Reoulatory Evaluation . The Structural Ehgtneering Branch of the Directorate of Licensing has reviewed the subject report and its appendices. -The procedures
- overed by this report with the qualifications stated in the follow-inig Regulatory position-and augmentation of, pertinent information that is referred to and to be providdd in the plant SAR are ,iudged to-
! represent the'present " state of the art" in .the field of design of structures and components against missile impacts. If properly i utilized in nuclear power plant structural design work, the pro-cedures and criteria contained in the report should provide 1 l t - i- ._ . _
Dasign Basis for Tomtdo-Gantrated MissilIs Joseph M. Ferisy Nuclair PI:nt ) ,
, Enclosure- Attachment 10 Page 9 of B2 Y
4 conservative and acceptable bases for design of structural . lee.ents against nissile impact effects. l Reaulatory e Position i j The design criteria and procedures are acceptable to the Regulatory ! staff. The report may be referenced in future case applications [ provided that the following specific information reviewed and l accepted by the Regulatory staff is included la individual SAR: l a) Parameters that define the postulated missiles such as striking I velocity, weight, missile configurations and ispecting area. etc. l
. b) structures, shields and barriers that are required to be designed
- for missiles with their pertinent characteristics.
4 c) If use of a dactility ratio greater than 10 (i.e.. p 10) is , ! required to demonstrate design adequacy of structural elements j against missile impact, such a usage should be identified in the j plant SAR. Information justifying the use of this relatively high i ductility value may become necessary for inclusion in the plant
' SAR. In such a case, the Regulatory staff will request the
,, applicant to provide the inforsetton on a case by case basis.
d) The evaluation of punching shear effect due to impact of uncon-ventional missiles, is not included as a part of the overall structural response consideration in the report. The subject should be adequately addressed in individual plant SAR. 4 9 , 9
+
--d
Design Basis for Tornado-Generated Missiles BC-TCP.4xWtph M. Farley Nuclea.r Plant e Rev. 2 Enclosure - Attachrnent 10 Page 10 of 82 AssTRACT This report coetains methods and procedures for evaluating the effects of missile impact on structures. A meanp to evaluate the change of velocity cf a missile passing through a liquid is also included. Missile impact > offects on structures are evaluated in terms of local damage (penetration. ! perforation, and spalling) and structural response. Empirical formulae l cre used to evaluate local effects. f tructural dynamic principles are used t to evaluate structural response. ACDICVLEDC)G3tT
'6 1
i This docusent is the result of a joint effort es the part of several contributors. Th's fc11owing is a chronological account of. major participanta contrib-I uting to the development of this document: * , Revision 0 (issued October,1972) was prepared by M. Fakhari, ;
- 5. Linderman, J. Bots and M. Suares and approved by A. J. Bingaman (Caithersburg Of fice Chief Civil Engineer) and D. W. Halligan (Power and industrial Division Chief Civil Engineer). .
s Revision 1 (issued July,1973) was prepared by R. 3. Linderman, M. Fakhari, J. V. Rotz. E. Thomas, G. A. Tuveson, and C. C. K. Yah; and approved by W. A. Brandes (Los Angeles Power Division. Ottaf i Civil Engineer) and L. C. Binkelman (Thermal Power Organisation, Chief Civil Engineer); Technical Consultant, N. N. Newmark. Revision 2 (issued September,1974) was prepared by R. 5. Linderman, J. V. Rotz and G. C. K. Teh; and approved by V. A. Brandes (Los ! Angeles Power Division. Chief Civil Engineer) .and R. W. Wahl (Thermal ' Fower Organisation, Chief Civil Engineer); Technical Consultant, N. M. Newmark. em 4 i i - 2 I i
- - ~ ~ ~ " ~ ~
. SC-TOP-V-A 0: sign Basis for Torntdo-Gan: rated Missiles
'Rev. 2 ,
Joseph M. Fari y Nucl2)r Plint Enclosure- Attachrijent 10 g Page 11 of 82 ) . CONTENTO
- (
! 5ecti n Title g
- 1. INTRODUCTION 1-1 1.1 -General 1.2 Approach l 1-1 '
l 11 t 1.3 Missile Characteristics
- l 1.4 Target Characteristics 1-2 -
12 1 2. LOCAL EFFECTS 21 , 2.1 Retaforced Concrete Targets j 2.1.1 Penetration 2-1 2.1.2 g 2-1 Perforatima 2-2 l 2.1.3 spalling 2.2
- Steel Targets 3-3 '
l 2.3 Multiple Element Barriers 2-3 ! 2.3.1 j 2-4 l Reinforced Concrete Berrier , 2-5 2.3.2 Steel Barrier l 2-3 '
;4 '
- 3. STRUCTURAL RESPONSE TO M18SILE INPACT 10AD
- 3-1 1 General i 3-1 2- Velocity After Impact '
3-1 3.3 Required Target Strain Energy Capacity 3-2 3.3.1 Elastic Impact 3-2 3.3.2 Plastic Impact q 3-3 3.3.3 Force Time Fdnecion Emown 3-3 3.4 Target Effective Mass t-3-5 3.5 Structural Response by Energy palance Method 3-7 j 3.5.1 General Procedures 3-7 ! 3.5.2 Elastic Target Response 3-7 3.5.3 l Elasto-Flastic Target Response 3-8 3.5.4 Woo-Lineer Target Responsee l 3-9 ' 4 DESICX GUIDELINES 4*1 4.1 A11ewable stresses and taadings 4-1 l 4.2 Design Paramete7s 4-1 4.3 Allowable Ductility Ratio N 4-3 3
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6
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D: sign Basis for Tomido-Gzn: rated Missil;s . Joseph M. Farisy Nucl:ar PI:nt i Enc 5 fed 9314tukhment 10 Rev. 2 Page 12 of 82 COETDifs (Cent) i Section Title
~
M
. 5. sFr.CTAL PR08LDis 5-1 i
5.1 Force-Time history for Automobile Crash 5.2 5-1 ' Penetrattom of a Missile Through a Liquid 5-1 5.2.1 Lsgsid Depth is Less Then or Equal to Missile ' 14ngth 5.2.2 5-2 Liquid Deptb~is creater Than Missile Length (M > L) 5-2 , 5.2.3 Definitions of Motations 5-3 f I i l O
- e ,
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- t e
t , 9 e sii
~~ *** ' *
- Drsign Basis for Tomado-Gensrtted Missiles 4 I* V' I Joseph M. Farlay Nuct:ar Plant {
Enclosure - Attachment 10 l
'. LIST OF APPENDICES Page 13 of 82 l
{ 1 Appendia Ticle g i A*FENDIE A Cross Reference Listing to AEC Standard SAR Format A-1 l s APPENDIX E Cloocary 31 APPENDIX C Review of Existing Formulas C-1 APPENDIX D Derivations ! b-1 APPENDIX E SasPle APP l ications 31 , i l 4 AFFENDIX F E4ferences and Bibliography F-1 j 1 f ! f i . i 1 ] i 4 e 1 a111 l I _= . . . . . _ . . . . . . - - . . - - -- - - . . 1
D: sign Basis for Tomido-G:n: rated Missiles
* ~ ' ~
Joseph M. Fartsy Nucl3tr Plant Enclosure Attachment 10' i
, LIST OF TARI n Page 14 of 82 g Title g j 4-1 Dynamic Increase Factor (DIF) 4-4 4-2 ,
Resistance-Yield Displacement Values for
! Beans 45 4
4-3 Resistance-Yield Displacement Values for Slabs 4-6 ! 4-4 Ductility Ratios (From Reference 24) 4-7 Dres coefficient for Variously shaped Bodies 5-1
- in incompressible Flow 5-4 , i l
C-1 Concrete Penetraties, Forferstion, and Spalling Formulas - C-5
~
C-2 Perforation in Steel Formulas C-8 O O O 9 6 9 l an EV M 99O -
- l i
Dssign Basis for Tomtdo-Generated Missil:s BC-top.9-A Joseph M. Farlsy Nucisar PIInt l 4 p,2 ~ Enclosure- Attachment 10 l Page 15 of 82 LIST OF ILLUSTRAT10Its Flaure Title Page 2-1 values of Penetration coefficient (KP ) for
. Reinforced Concrete 2-6 '
2-2 Penetration of Reinforced Concrete for Various ! Missiles (Modified Petry) 2-7 i l 2-3 Perforation of Reinforced Concrete for Various Missiles (Sallistics Research Laboratory) 2-8 e i 1 . ! 2-4 Penetration. Perforation, and Spalling of '
- 2 Reinforced Concrete Target by Featulated 2-9 i
Tornadogasiles 1 , 3-1~ Resistance-Displacement Functions With ! Associated Structural Response With and Without The Effects of Other Leeds 3-12 ' 3-2 Energy-Displacement Functions - Impact Loads Only 3-13 l-1 3-3 Energy-Displacement Functions - Impset Combined j With other 14 eda . 3-14 .
. \
! ' 4-1 Coefficients for Moment of Inertis of Cracked -
! sections 4-8 I
) 5-1 Penetration of a Missile in a Liquid 5-5 , 1 - 5 C-1 Typical Crater Profiles C-9 , C-2 Deleted 3 thru ', C-22 ! I o 4 avii
.. _ - . - - . . .- -- . - . - . . . - - ~ - - .. . . - . - - . - -. ' Design Basis for Tomado-G:nsrated Missiles SC-TCP-9.gseph M. Fcrisy Nucletr Plent '
l . nav. 2 Enclosure- Attachment 10 Page 16 of j82 . Secties'1 ' l INTRog10H j i ' 1.1 H!!!Beir, h3 design of nuclear power facilities includes the effects of missile i impact on structures. systems, and equipment. Esternal building surfaces, interior walls and floors, and special barriers (constructed of concrete cad /or steel) that will resist or deflect missiles may be used to protect systens and equipment where necessary. His ;eport contains methods and preferred proceduras to evaluate missile tapact en structures and barriers. Missile effects are evaluated is terms cf local damage (penetration, perforaties, and spellias) and structural racponse. I Mi:siles may be generated by an avsat that is not related to plant operation, l cr by the failure of plant equipment. The prihery asurces of utssiles not ! rolsted to plant operatimas are debris transported by tornada winde, and
- falling objects generated by activities near the plant site (such As com- l mercial, industrial, or military activities). Missiles that may result -
free the failure of equipment generally result from the uncontrolled release af energy and forces from a pressurised system or rotating machinery. Missiles that may raeult from the failure of equipment are fittings. valve . parts, various nuts and belts, and parts of rotating machinery, etc.
,1.2 APPtoACH Determining the affact of missile impact is outlined in the following !
32neral steps. Novaver. *there are many interactive effecta la each step th:t should be considered in the complete analysis. I e Determine missile characteristics. e Define target, considering impact la combinaties with other leads and requirements (preliminary properties). e Determine local effects of missile on target. o potermine target characteristics for structural response and stability. o Determine equivalent target mass during impact. o Determine structural response. 1 o Evaluate structural integrity. o Verify that the maximum deflection does not ingair the function of other safety related systaas. 2 l 1-1 i
Dasign Basis for Tornrdo-Gensrated Missilis
* ' DC-TOP-9-A say. 2 ' Jos:ph M. Farley Nucitar Plant f Enclosure. Attachment 10 Page 17 of 82 1.3 MIS 8It.g cuARACTER!sT!cs Missile patsasters required for missile impact analysis include trajectory.
, mass, velocity, seemetry,' and deformation ebaracteristica. The geometry
} should taclude contact area, projoetd frontal eres and veristion of
, area with respoet to length. . Beforestica characteristics include if the missile will deform or la rigid and if it is ductile or brittle. Missile geometry and deforastion characteristics haea a significant effect on pene-tration or perforation of a target. A pointed missile will penetrate deeper inte a target than a blunt missile; it will also perforate a thicker target.
Deformation of a missile during impact consumes energy. which results in diminished local damage. Postulated missiles and their properties may vary with each plant and are defined to the 'gafety Analysis geport (34R) for nuclear power plants. l 1.4 TARGET CMARACTERigTICg l , l- : . Structures or barriers (targets), providing missile protection, oct as i ' energy absorbers. The target absorbs the amargy by local damage at the location of impact (i.e. penetrattom of the alas 11e into the barrier) and by the structural response of the target. , , l 14 cal damage depends en miseite characteristics, target asterial properties, l and structural respaase. Empirical asthods are used to estimate local l : damage because of the complex phenomena associated with missile tapact. The ability of a target to absorb energy by structural response depends on l . 2 the dynamic properties of the target, support conditions and other imposed i loads at the time of impact. Structural dynamic principles are used to estimate the structural response and determine if the target will remain t stable during and after missile impact. 1 ! Structures, shtalds and barriers that are required to be designed for a missile are given in the Safety Analysis Reports. I r I t i i i l 1-2 t _ .. .. .
___ _ _ _ _ . ~ . . _ _ _ _ _ . _ _ _ . _ _ _ _ _ _ . _ . _ Dssign BIsis for Tom do-Gsnsrated Missiles l ( Rev. 2 Jos ph M. Farlsy Nuclear Plant ' l . Enclosure- Attachment 10 Page 18 of 22 Section 2 , LOCAL EFFICTS l Fredicting local damage la the tapact area includes estimating depth of l penetration, minimum thickness retutred to prevent perforetion. and minimum j thickness required to preclude apelling. The penetration and perforation ! farsulae in this section assee that the missile strikes the target sermal ' to the surface, and the exis of the missile is assumed parallel to the line cf flight. These assusprions result in a conservative estimate of local d: mage to the target. Appendix C has information on the more comon local ; i effect formula and a discussion of the affects on the penetration for a missile striking a target at oblique angle. t ' t ! 2.1 REINFORC D CONCRETE TARGETS l 2.1 1 PEWETRATION , The' depth to which a rigid missile will penetrate a reinforced concrete torget of infinite thickness is estimated by the folleving formuis
/ v2 i x = 12 E, A, leg 10 1
- 21$. (2-1)
)
where X = Depth of missile penetration into concrete element of safinite , thickmass (inches) Note: Usually this e'quation empresses the depth of peme-tration in feet; bouever, for this document it has been modified to empress it in inches. E, = Fenetration coefficient for reinforced concreta (see Figure 2-1). g ,1,_ Missile weiaht (pof) p A Projected frontal area of missile l2 V, a Striking velocity of missile (ft/sec). (Limit V, 1 1000 ft/sec) This formula is known as the Modified Petry formula. When the element has a flatte thickness the depth of penetration is: r 4(1. x 2[ x, (t , n> (2-2) \2
- q. 1.e I
i l 2-1 l l ,
- - - * * * * - * * ~ * * ~ ~ ~ ~
- i w __ __ . , . ---- -
. _ . - - - -u - + -
i
. Design Basis for Tornado-Gtner*ted Missiles l Jossph M. Farlay Nucitar Pfar( l BC-TOP-9-A Enclosure- Attachment 1 '
, Page 19 of 8 Rev. 2 1 I i
' 4 whers X e Depth of penetration of missile into a concrete element of finite , I thickness (laches). t
- e = Sase of Napierian lagarithms i t = Thickness of concrete element (inches) .
penetrations or vart us illustrative examples of missiles are shown in 2 figures 2-2 and 2-4. -l
- 1 2.1.2 PERFOEAT10R
!l ' The thickases of a osacrete element that will just be perfor'ated by a
- missile is given byI ! !
[ 1.33 47 y Te gg11000f (2-3)
- I'
. i where l 7 e Thickness of concrets alement to be just perforated (inches)
W = Weight of missiles (1b) l
, D e Dienster of missiles (inches)
'%te s For irregularly shaped missiles, an equivalent *
' diameter is used. The equiealent diameter is taken as the diameter of a circle with an area equal to the cir-etaseribed contact, or projected frontal area, of the men-cylindrical missile.
V, = Striking velocity of missile (ft/sec) l', = Compressive strength of concrete (psi) Thiu !;4: mala is known as the ,Bellistic Research Laboratory, BRL formula. The thickness, ty, of a concrete element required to prevent perforsties must be greater than T. It is recosmonded required to increase T by 25 percent, but to prevent perforation not more than 10 inches, to obtain the t, I (2-4) t, = 1625T 5 T + 10 (in inches) l
. 2-2
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Design Basis for Tornado-Gensrated Missites
,gsjpAM Farlay Nuclear Plant
*I EiRiosure- Attachment 10 Page 20 of B2
~ The missiles threshold of perforation.
is shows in figures 2-3 T.sad for various2-4. illustrative sameples of I
~
[2 1 2.1.3 SPALLluc i spallihg of concrete from the side opposite the sentact surface of the ele-ment any occur even if the missile will act perforate the element. For an estimate of the: thickness that will just start apalling, it is recommended that the following equation be used: 4 T, = 2T (2-5) 1 where . T, a Concrete element thickness that will just stars spellfag (Saches) ! t
. T = Concrete thickness to be just' perforated (inches).
See Equation (2-3) i l The thickness, te, of a concrete element required to provost spalling must be greater than Ts. It is receanended to incrasse 7, by 25 percent but . ! not more than 10 inches, to prevent spelling. t t,
- 1.25 T, 5 T, + 10 (in taches) (2-6) 2.2 STEEL TARGETS ,!
greel targets, eseh ag pipes and anchanical equipment vessels, may be per- l forated by a missile. Sometimes, protruding elements of a missile any ' puncture a steel target when the entire missile does not perforate er pass through the target. The minimum contact area of a missile protrusion is used to calculate puncture thickness and the projected area of the entire missile is used to calculate perforation thickness. l The BEL Formula is abown below, modified by setting a material seastant K = 1 and solving directly for steel plate thickness T dich will just be perforated by the missile. r 2) 2/3 i
\ ,n,I I I
To (2-7) j 672D r i
.e
, '. , i, ,,
I l l i 23 . i
- , Design Basis for Tornado-Generated Missiles t Joszph M. Farlay Nuclair Plant SC-TOP-9-A Enclosure Attachment 10
< 2 Page 21 of 82 , i Where T = Steel plate' thicknese to just perforate (inches). M = Mass of the Missile (1b sec2fgg) t l v=urightoftpMinip(th) { V,'o Striking Velocity of the Missile Normal to Target Surface (ft/sec) i l D = Diameter of the Missile (in.) Notes For irregularly shaped missiles the equivalaat i diameter is used. The equivalent diameter is takes as the ' diameter of a strale with en area equal to the circun- l ocribed contact, or projected frestal area of'the , non-cylindrical miss11a. i i
- The thickness. t,, of a steel barrier required to prevent perforation should exceed the thickhess for threshold of perforations. It is recommended to
- increase the thickness, T. by 25 percent to prevent perforatten.
t,= 1.15T (2-4) i :
- 2,3 WULTIPLE ELIMurr BARRIERS
} l It may be desirable to construct a missile barrier of several thinner ele- ! ments, instead of one thick element. Analysis of missile barriers composed j of several elements involves determining the reeldmal velocity (v r) af ter perforatips of one element and using this value for the striking velocity (V,) on the next element. The following formula is used to determine the i residual veloetty, Vr (see Appendia C) ' i 1 2 1/2 V, = -V p ,,, g,p , ,s) i ! (2-9) . T, = 0 For (V, a V,) )
~
l 4 where I l - l j V, = residual velocity of missile af ter perforation of an element of ' j ,
- 2l thickness t. (fpe) .
- i
{' ; V, = etriking velocity of the missile normal to target surface (fys) j ! v = velocity required to just perfo' rate an element (fps) p 4 l . J .
. 't ,
f t i d i 2-4 e i g
.. . . - . - - . . .-.-._ . . . - . - . - - ~ ~ _ = -. . - , . - - .
I
- D sign Basis for Tomado-Grnsrated Missiles
~
- BC ggg1M. Farity Nucisar Plant i 4
. . Rev. 2 enclosure- Attachment 10 l
- Page 22 of 82 l 1
2.3.1 REINFORCID CONCRETE BARRIER , l i ! ' \ i Combining equations (2-3) and (2-9), the residual velocity of a missile i perforattag a concrete target is ' 1
- " )
=
.1 - V = V, f y a .sY ,1/2 l l r s 427v 10 (2-10) ( ) i where t a thickness of eencrate sleemat (Laches) l. I
- 2.3.2 STEEL BARRIIa 1
i Combining equations (2-7) and (2-9), the reefdual velocity of a missile j pqrforating a steel target is . 1/2 i Y
- 92 *~ 1.12 m 100 (Dt)I*3
- l 1 r a v (2-11) '-
} - . - {
4 where t = thickness of steel element (inches) ' f
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.a m .
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i ' 1 Dssign Basis for Tornado-Gsnsrat:d Missiles J 1 Jos ph M. Farisy Nuclear Plant ' BC-TOP-9-A j , gay, 2 Enclosure- Attachment 10 , Page 23 of 82 1 l 0.00$0 - 4 l I ! ! 0.0040 l r , i - 2 0.0030 0.0027 4
- < 0.00m g
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l: I E N ! l 1 i l 0.0010 i i 1 1 e i i l 0 ' 2,000 3,000 4,000 5,000 6,000 7,000 ! as - DAY COWRE55tVE $TRENGTH OF CONCRETE l l 1
- 1 .
4 ll l ! I i Figure 2-1 1 j gtygg gy ygggTRATION Cor.FFICIBIT Ots) FOR REINFORCED CONCRETE j , p.rerens. 141 4 i !
. i.3 a . :, , .
h; - r .*. ;,:
. PLW12::7 ' ! t*
1 i ~.$ i , - a4 i ; - . t.
24 w y = 12 22 X J COMPRESSIVE. STRENGTH OF m z come.ET. . y 7-u [ : 20 ' ' k E x+ 10 novs: s. w me=== A = 10 N / 3.Ah4MhmI 2 i 5 a, em u == g E N"
- 1. ,
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*- vW//X a J l,o ,
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wy b4 K ., 2 C'2 A 7
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f2 f- l w M
~ w fn 0 50 4 100 .200
- ==-C - -
300
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4o0 gj soo g anSSILE VELOctTV (FT/5ECl SFE Figure 2-2
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PSEmtATION OF M INFORCED CONCRE M FOR m ** R i VARIOUS MISSILES Omotrisp FETnt) {of g MRE a a 3 G. ' gg '
Design Besis for Tomado-Gensmted Missiles ! SC-TOP-9-A i ,' Rev. 1 cos e Attac m nt 10 l SNsN\\\ l ltli'"" l MAN\X \ \ \n J l MsSSN.NN X \ u1f l. inh "
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I l Design Basis for Tomatdq-Gantrated Missiles i 8~ h;G M. Farlay Nucisar $ lint
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D: sign BIsis for Tornado Generated Missiles ' l- - ; BC-TOF-9-dostph M. Ftrisy Nuclair Plant
~ say. 2 Enclosure. Attachment 10 Page 27 of 82 Secties 3 ;
l gTgDC111 GAL RgspomSg TO N1551LE INFACT IAAD ' l I i 3.1 SDIERAL f . l Whea a missile strikes a target, large forces develop at the missile - I l j j t:rgat If the interface interface,forcing whichfuncties decelerate is known. the missile and attelerate (esperimentally the target. k daterataed), ths target structure can be modeled mathematically and eenventional numeri'-
- a est techniques can be used to predict structural response. For nest cases
{ thsforcingfunctionisnotknown,andarattomalmethodfavolvingenergyf l j b:Isace techniques is used to estimate structural reopease. This lavelves-l using the strais emergy of the' target at maximum respense to balance the ( ! residual kinetic emergy of the target (or target-missile combinaties) l resulting frea missile tapact. i I Fcr lavestigation purposes, it is ceavenient to model the event as a missile j af assa. M ,. sad striking velocity, V , impacting a spring-backed target ; mass, M . The spring may be 11aser, hilinear, or non-limaar. depending em 1- the carsst structure resistance-displaceamat functies. giace the actual i coupled ases varies during tapact, an estimated average effective target
- mass. He is used to evalusta inertia effects during ig act.
! 1he impact any be either elastic or plastic. depending on whether er met i i sigtificant energy losses are sustained during tapact. These leases are
- 2 l .ociated with inalastic deforestions, local damage in the impact sene.
ces. l l Flestic impact is sharacterised by the missile remaining in centset with ; , ths target, subsequent to. impact. In an elastic impact, the missile and ' target reasia in contact for a very short period of tima, and than disen-j sags due to alastic interface restoring forces. , 4 i Aa clastic missile tapaat asse is rarely encountered in awelaar plant I l design. For emaaple, based on informatism available, a plastie e>111 sten ) i can be considered for all p atulated tornado-generated missilse, i ' i j 3.2 YELOCITY AFT B IE ACT . since the duraties of impoet is very short. (asually less than a few millt- - l sectads)5 the target'anos denlacement and the eerraspeeding spring forse I cro slee very small. Reg 15a ins the sprias force affect during impact, ! (s Slight ceaservatise), the velocities of the missile and target after ! tapcet are calculated from the following relatieashipss .
'a % ~ **aE j u M, + N, .
i l'
- V,((14e) ' ;
(3-1) l; yT . -- g + N, ) - 3-1
~ . - - . . -- . - - - . - . - - - . - . . - . . - - - . - . - - . . - . . . - - - - - - . . -
1 l D: sign Basis for Tomtdo-Gantrated Missiles l Jossph M. Fartsy Nucisar Plint ; 3C-10p-9-A - Enclosure- Attachment 10 ) gev. 2 Page 28 of 82 i
, Vn = Missile velocity after impact l VT = Target velocity after tapact i
, V e = Missile striking velocity 1 Ma = Moos of missile l i l i I j M, e affective mass of target during impact e = Coefficient of restituties l l i ! ! 3.3 RgQUIRD TARGET STRAIN ENDCT CAPAC11T ! l 2 l
- 3.3.1 EMSTIC INFACT i .
3 Equations (3-1) and (3-2)(12)* show that the velocity of the missile after { impact is opposite to that of the target if M is less than eM,. For this - case, the strain energy. Es. of the respondin,g target spring required to diminish the target mass velocity to aero (maximum target response) is
- numerically equal to the kinetic energy of the target mass at the end of
- the impact duration.
1 l y' ,'2 ! ; E, = 2 (3~3) j If the impset is determined to be elastic and the coefficient of restitution i j g is not known, a conservative value of e equal to unity can be assumed. !
- Making this substitution in equation (3-2), and substituting this value for j VT inte equation 3-3 the required strata energy of the responding target j
h; - 4
=+ a-o e-(,*.v*e),
m } )
- Referring again to equations (3-1) sad (3-2), the velocity of the missile af te: ,
j impact la in the some direetten as that of the target if M is greater then j eM.. In this case, the target spring decelerates the target asse, allowing j , the missile to overtake the target, which results la multiple impact. I j If the tapact is purely elastic (e a 1), the target will eventually stop the g, , missile through a series of impacts and sheerb all the initisi kinetic
- t .
eReferences are in appendix F. l l 3-2 l
_ = . . _ _ _._ , _ _ _ _ _ _ . - _ . . _ _ _ _ _ . . . . _ _ _ _ _ _ _ _ . _ _ . _ _ _ _ _ . . _ _ . _ _ l Dgipn,B[ sis fgr Tornado-Gsnsrated Missiles ! , say, 3 Jossph M. Fartsy Nuclear Plint l Enclosure- Attachment 10 {* Page 29 of 82 I i castgy of the missile. N required strata energy of the responding target . is than equal to the initial klaatic energy of the missile. M l 3e .n (3-5) 2 , l l ! 3.3.2 MASTIC IMPACT l2 l i '
- Far o plastic collistes, the coefficient of restitution reduces to aero
- (o o 0) and the miestle and target assses attain the same velocity at the
! c:d cf lapact duration. If the impact is of short durattee, the target displacement and corresponding spring force effect during lapact are small, j and can be conservatively neglected. The streia energy required to step i the target-missile cashinattes is them the sua of the kleetic energy of the ' j .a10:11e and the target masses.at the and rd the duraties of impact. i
. N j E, a 2
- 2 (3-6) ;
i
- l From equatsoas 3-1 and 3-2 -
N*V* Y, o V, a y (3-7) a e
- b stituttag the value fo' rV sad V free y equaties (3-7) inte equation (34).
l the required target strain e,nergy is
@ (3-8)
E, a 2' 08, + M,) , 3.3.3 Poact TIME Function Emplet to some toelated cases. (eash as for frontal impact of an automobile, see ccetion 5.1) aufficient asperimental data are available to enable deftai-tion of a force-time functies, F(t), at the interface between the missile and target. This enables direct solution of the equation of mottom , F(t) - R(a) = M,tf (3-9) F(t) = Force-time fumaties R(x) = Basisting spring force as a function of displacement, a it=Asealeratiesoftargetmass D' N, a Effective target asse . 3-3 l p __ _
l . Dtsign B: sis for Tornado-Gen: rated Missiles j . Jostph M. Fartsy Nuctsar Plint Enclosure - Attachment 10 i BC-TOP-hA Page 30 of 82
! Rev. 2 i
Numerical methods are usus}1y used for solution of equation 3-9 which is solved for the maximum value of displacement a.. The target strain emergy
} is then; i
j 2 ( ! ! f** ] , E, = R(a)da i i ! An abbreviated conservatip solution for required target strain energy can i he obtained if 1(a) during impact is eas11 compared to F(t) and plastic or ] . penneneet deforesties is (satamat at the missile-target interface I i l - The velocity of the targst' mass at tias, t. is;
- i 1 .
I ~ ggg) ,, .,gg , M (t) RM de . i , I j The kinetic energy of the ' target mass at time t is thea . .a ! l
, N,[i (t)]2
- E(t) ,= 2 G
l i
- <3 (3-10)
R(t) ., (F(t) - R(s)] de l . Rguation (F 10) sheve that deletion of the R(a) term will result in.s conservative overestimate of E(t). If R(a)" F(t) during impset, t, the inaccuracy is usually sogligible. For this soodition, the kinetic energy 1 of the target mass at ties tg is cesservatively estiasted as:
, -2 1 . 1 i .
F(t) dt i i R = - - (3-11) i i t 8 1 "a l , the app 114 impulse. I. is by definition, the area under the force-time j { curve.
! : ti
- ; 1 F(c) de i or
.g m.ast, 3
! i
- i . .
! M
Design Basis for Tornado-Gsnerated Missil:s BC-TOP-Weseph M. Fartsy Nuclear Pl:nt f ,' Rev. 2 Enclosure. Attachmen' 10 j Page 31 o' 82 ] Making this substitution into equation (Fil); , 4 2
~
1 2 Ig = y * (1/2)M,V9 (3-12) : i e - ! If the elastic restoring forces at the missile-target interface are small. l l the velocity of the missile approaches that of the target at the end of ' i time, t i. equal to the duration of impact. The strain energy of the target !
- r
- guired to stop the missile-target combination la then; 1
! 2 M ,V 2 la i I, = 7, + 2M II~13) i ' For a plastic asilision,
- 2 l . 's - 'T .
From equatico (3-12): t 2 - 7" i l and. 4 2 . ! v.L 2
, 4 !
l Making this substitution into equation (b13): i (M ,+ M,) I g . i (3-14) . tu2 3.4 TARCtT EFFECTIVE MASS
- The effective target mesa during impact varies from a low value at initial contact and generally increases to an upper limit during er at the end of tha tapact duration. Due to the comples phenomenelegy associated with Ci:sile impact, no general analytical solution is available to evaluate the effective coupled mass on a continuous time basis. The average effective as:s can, however, be estimated, utilising the results of impact tests en rainforced concrete beams (7) wherein the measured maximum structural .
rasponse was used to back-calculate the average mass during impact. c~ 4t ug u. . 3-5
l Design Basis for Tornado-Gsnerated Missil;s Jos ph M. Farley Nuclsar Plant i !- 3C-TOF-9-A Enclosure - Attachment 10 j Rev. 2 Page 32 of 82 Based on these data, the fe). lowing formulas provide a louer limit estimate
- of impact M. )(which
. results in an upper limit satinate of kinetic energy afte.r For concrete beams:
e - W *T M,s.(D, + 2T) , if 3 5 (Dy +27)) 2
- yT (3-15)
M, = (D, + 27)(p, + 2T) f 6 [if8!(Dy +27)] )4 For eencrete slabe .
. Y N,l3= @a+T) 9,+f) ],
M i
- r. . .el b..a : '
l l N, = (D, + 24) Ma (3"17) j For steel plates y j Ma =es n, ;a o-1.) j N,= Average effective mass of target dutieg impact i M ,= Mass per unit length of steel beam i ? i . D* = Maximum missile contact dimenstem in the a direction (longitudinal l suis for beses or slahs) - . D = Maniams missile contact diawasion la the y direction (transverse to 7 fongitudinal axis for bases or slahs) } T = 1hickassa or depth of concrete elemmat
, t = Thickness of steel plate 1
4 4 l d = Bapth of steel haam i j B = width of concrete beam (not to suc*ed Dy + 27) y, a Weight per unit volume of concreta j y , = Veight per unit volume of steel i
- s t- ., leration of gravity -
d 1
j_ Dssign Basis for Torntdo-Genzrated Missiles '.- SC 70F-gph M. Farlsy Nucl3 r Plant
- l. Rev. 2 Enclosure- Attachment 10 l 1 Page 33 of 82 I 3.5 STRUCTURAL Resp 0NSE M DERGY BA14NCE METHOD i .5.1 GD ERAL PROCEDURE 8 i
! The strain energy. E , required to stop the target (or missile-target soebination), is determined free the relationships is sections 3.2 and 3.3. ! The resistance-displacanest functies. R(s). for a soscentrated lead at the i crea of impact is determined free the target structure physical cesfigurs- l . tion and asterial properties. .. . i ? . The estimated maximus tarSet response is determined by equating the avail- l , chio target strain energy to the requirp strain emergy and solving for the l l assimum displacement a ,. (See Figare 3-1.) ! i I 3.5.2 E1ASTIC TARGET RESPONSE 1 , 4 l i Far elastic response. R(m') = km i
- k = Elastic spring constant ,
l If no other loads are acting concurrently with the missile tapact loading, j the maximum response is l 2 5 *1/2 l 3 . -- A (3-19) ! a k' j- If scher loads are present on the target structure which will act concurrently } with missile impact loads. ths =aut - e combined displacesset is detessised ! as follows: W .
.e = a o . .. ,
Since
.g g <112 n' = J k -
Let m' = Displacement due to missile impact (See Figure 3-1) z , = Displacement due to other' loads .
" eesat z ,= Maximum combimC
. 3-7 i
i - Design Basis for Tomado-Gensrated Missil s j - ' Jos!ph M. Fartsy Nuclear Pitnt
- j. ,
gg_gy.g.A . Enclosure- Attachment 10
- Page 34 of B2
- gew. 2 I i
l 2l it follows that . . gf 3 $ m m o =e + (3-20) 3 h
~
i i 3.3.3 EIASTO-FIASTIC TARGET RESPONSE For elasto plastic target response with no other concurrent loads acting: , 4 } R(s) = km, (0<xsay i 1 l , aca) - nm, - g , (a ,< s s g3 , where l z, = Yield displacement - i l l 1, a Plastic resistance. ) l Then f s1 l ! .' 5. - =. (=. r,/ l
.b+b \ I (3 21) l
! The required ductility ratio, yr, is obtained from equation (3-21) by dividing i both sides.,of the equation by x,. a )
.' i *e I
e 1 i l u, g +y (3-11) i, ! i i ,, If other leads are present on the target strwetura dich will act concurrent with missile impact leads, themstmum combined displacement is determined l 8 as followsa
?
! I let i i j m' = m, = s, (see figure 3-1) 1 i
- I m,a displacement due to other loads 4 e 4 *"%-=
i ' i 1 l ! l i )3 ' i
. - . - - . - - - . . . . . - . . - . . - . _ ~ . . . - - . . - . . - - - - . - --.-. -..- --..- . _ ... - -. -
r
. D: sign Basis for Torntdo-Gen: rat d Missiles
~
'. . "* *** ~Ks%ph M. Ftrisy Nuclair Plint Rev. 2
. Enclosure. Attachment 10
. Page 35 of 82 m
e
=jielddisplsessant i
.n, = maximum meabined displacement
. R = plastic resisting force , a . 1 . j k
- elastic spring constaat 1 q 4 Thas ,
s up'.,..(. . e
<.e. ,1..r. ,1) l cr 8 :
e. l s " E' 'T
- 8e ;
! Substituting m' = s, - s, in the abov equati,en gives . i E n *e + *e
- C3 23)
N,=1@e=5)+ o 2 l-i . i l The required ductility raties Wr, is obtained by dividing both sides of ! l cquation (3-23) by z,. l f I
- E, 1 + s,/s,
- W (3-24) r = R , (a, = s,) + 1
\ . , j, Tho values of pr should be less than the allevable ductility ratios w giwa ! is section 4. , 8
- J
- 1 3.5.4 NOW-LINE(JL TARGET RESPONSES -
I If the resistance-displacement functies is sealiacar (figure F1) the . j*, datermination of structural response is facilitated by first defining the j ctrain energy-displacement fumation (see figure F2). (2-25) E, =[ a(s) 4: , $I j E, = strain energy at displacement a 1 j' E* = strata emergy at displacement x
\
j j! . ii ' j , F9 i'
j
- Design Basis for Tornado-Gensrated Missiles Jossph M. Farley Nucistr Plant
- Enclosure - Attachment 10 gg. Top-9.A Page 36 of 82 s
new. 2 1 i men me other concurrent leads are settag, the naminum displacement occurs l st the value of a where E. is equal to Es. The correct value of an is there-t fore the value of m, which will satisfy the following relationships E, =
- R(a) da (3-26) 3 j
j 4 A typical graphical solution la shown in figure 3-2. ! W en other loads are acting concurrent with missile impact loading, the ! correct value of % will satisfy the following relationship: l
/"a
! l j E, . (3-27) ; R(m)da - 1,(m, - x,) j e '
- \
! E = equivalent static resistsace required for other loads (see figure 3-1) i ! I i x,= displacement associated with R ,.
- 1
. A typical graphical solution for a ,is shown schematics 11y in figure 3-3.
l To provide an adequate margia of safety the values of E, should satisfy the
- condition
, E, 1 F,Ig (3-23) t' .,
ll 8 Eg = impact strata energy capacity ! F = safety factor ! I e I
! F, = 0.5 if 1(a) in well defined from tests i
! F' = 0.25 if R(m) is appresimately detemined (such as by failure i . analysis) !< i l l . For impact only i' . Il ' l Eg
. E g= R(s) da (3-29)
- . o
,, = di., lace.e.t at fsilur.
l
~u r, , s.,e 9 m.m.-
k J - h d b
Design Basis for Tomado-Gznerated Missiles
- Joseph M. Farley Nuclear Plant
- Enclosure - Attachment 10 i -
SC 70F-9-A Page 37 of 82 Rev. 2 I l' } . s ] : } l _ , ,a - f l ,._b, i EN-i:i 1r # ,
=
5 o
=
x ** 5 l
' - ., I I !
. n S :
i s l i,
. 1 \ .
W . . f:a*, lh[ r ! eE E l l . f* i . a [ n l l In I = g $E l* ' l 1 i -
,.v..
y , i l i ! l i 1 M2
M
, Dasign Basis for Tornado-Gensrated Missil:s j ,
BC-TOP-9-Aseph M. Fartsy Nucisar Plant Rev. 2 Enclosure. Attachrrient 10 i. t Page 38 of 82 ' j . E,=l,.nMe ; g
; i
- i l I <
l i o . = Is :
- l. ,
4 ! 8r j 1 I i - 1 o am er
. 368PLACEtatatY E i
, ,I t . I I
- 1 i :
I l 4 a 1 I i Figure 3-2 i
! t
- ENERCT-DISPEACDIENT MDICTI0018- .
l DIPACT 14 ADS' OIILY e 1 4 2 i .
>u i
i "* .
1 l Design Basis for Torngdo-Gzn: rated Missiles , g,g g Joseph M. Ftrisy Nuclear Plant 1 . nav. 2 . Enclosure- Attachmer.t 10 i Page 39 of 821 1
.i
) . i
'l 4 l
- l
- I l*e %In h:
P %w. 1 > l ? 8 I
- a P 1 .
I or \ , l'
. t .
1 .l .
- o I
j t
- ; =
, < n .
i r, N t . r, . a, s . ,,a 3 i~
. s, . .
1
\ r,. n, . ..s l ,
i i 1 f ,, ** ** se l I i l siaPLacassant x i $ l i ' i Figure 3-3 1 aracr-orsraemmer rectran -
' newr cootm via eran ums i 1 J s 1 l . i 2
- 0
! i i,
5 i 3-14 i o
-m .
i
- - Desi Rev.gn2 Basis for Tcmado-Gsn
- rated Missiles j - Jossph M. Fartsy Nucisar Plint 1* e Enclosure- Attachment 10
.' Section 4 Page 40 of 82 l .
l i DESICM GUIDE 1.INES 1 ) t
. 4.1 ALLoWAntz sitzssrs AND toAnincs Tha combinaties of loadings, allowable strees and strata limits, and , cyp 11 cable codes used with the missile impact leading are given in the
- Sofety Analysis Report. The resistance of a structural component must be l based on its minimum strength, i.e., the minimum of' its flexural or shaar-
- ing ecpacity. The dynamic capacity of the structural elseents must be i b
- s:d on asterial dynamic strength properties which are obtained by applying j o dynamic increase f actor (DIF) to the static strength value: 2 i
I dyn = (DIO f,t,t (4-1) , f wh:re i , f g = allowable dynante strength value _ j 2 } f g ,,g = specified static strength value .
- r
) DIF = dynamic increase factor {, , The dynamic increase factor for various materials are given la table 4-1. . 4.2 DESIGi PARAMETERS The resistance of typical structural elements, whose flemural strength d3 fines the miniana capacity, and their yield displacement approstantions cro presented ta tables 4-2 and 4-3. Similar equations can be developed far the lead at other location on the structural element. It is prefer-abic that the limiting capacity of an alament be in the fissural mode not la shaar. In evaluating the yield displacement with the usual clastia analysis, the moment of inertia must account for erecking of eencrete cactions. The aspirical relation for this type of loading is as averste moment of inertia I. calculated as follows is:
+ W 2)
I, = f (1, + 1,) = f wh ro J = noment of inertis of gross concrete cross section of thickness t 8 about its centroid (neglecting steel arass) Ic = noment of inertis of the cracked concreta sectica 1 G se e e e e sees e 68 - * *
- emme e musuman e
Design Basis for Tornado-Gen: rat:d Missil:s
.: Joseph M. Farity Nuct:ar PI int Enclosure- Attachment 10 BC-TOP-9-A Page 41 of 52 Rev. 2 ,
b = width of concrete secties F = coefficient for aposat of inertia of cracked section with tension reinforcing only. (See figure 4-1.)
~ ,! :
; t = concrete thicknese a d = distance from entreme compression fiber te centroid of tension
- reinforcing The moment of inertia I , as calculated by equation (6-23, must be used in ;
the displacement equati8n in tables 4-2 and 4-3 for all reinforced concrete ; l members. The mitiants annant capacity of a eencrete seetten shall be een- ; i sidered as the moment strength ,' !
, M,= 0.9 A, fb I# ~ "#*) I'"33 whee i ;
., = .res .f te. size reinforcing steet , l
!j 1
f,, = allweble dyn =,1c yield stress for reintweing steel
'1 I d = distance from extreme compression fiber to centroid cf tension reinforcing
{' a = depth of equivalent rectangular stress block , g ;.
! If the element has compression steel, it should be considered and the appropriate equaties used.
The amount of rainforcing st el in a concrete asabers must satisfy the following criteria: Formemberswit5itensionsteelonly 0.25 f; (4 4) 1.4 /( (t)2 bd
, g_ f
. F r 2
For members with tension and compression steal: l I*' A t, .a f F (d)2- 34 c.- s>
', 2 0.25fl
, -A,.Alj f,
01 . l. j 4-2 1
1 Dzsign Basis for Tomido-Gsnerated Missiles Rev. 2 Jos:ph M. Farlsy Nucle:r Plant
, Enclosure Attachment 10 Page 42 of 82 where -
f' = compression strength of concrete c Aj = area of compressive reinforcement of concreta 1
- 4. 3" ALL0FASLE DUCTILITY RATIO The maximum allowable ductility ration for concrete and steel members are 2 pra:ented in Tabis 4-4. However, the maximum deflection aball be limited os cs not to impair the function of other safety related equipment.
4 1 O O e i 4 e e I i W e 0 l 4-3 em
- D: sign Basis for Tomado-Gsntrated Missiles '
Joseph M. Ferlsy Nucirr PI:nt ' DC-207-9-A Enclosure- Attachment 10 Page 43 of 82 1 Rev. 2 Table 4 1 $ DYNAMIC BCREASE FActon (DIF) (From Ref. 19) { I. Rainforced or Prestressed Cenerate
- ponerate
, DIr . Compreesten 1.25 Diagemal Tenstes & Direct Shear (Fuch Out) 1.0 I Bond i 6 1.0
, Rainforcism Steel -
Tensies & Compression For 40ksi yield strength steel 1.2 i 2 4 60ksi yield strangth steel 1.0
- l Diagonel, Tensino & Direct Shear (Stirrups) 1.0 i
- 11. Structural Steel l Flexure. Tension, & Compression for 40ksi yield strength steel 1.2 l 2 '
- 60ksi yield strength steel 1.0 1
g Sheer 1.0 i e e
't
. H e e
i
, Design Basis for Tornado-Generated Missiles i,
" g,gy,gsph M. Farlsy Nuclear Plant hv. 2 - Enclosure- Attachment 10 Page 44 of 82 1
I Tabla 4-2 i RESISTABICE-Y121,D DISMENDff TAGES FOR BEANS vieLD Des >Laceaettet Dfb8 M 88 M i til CANTitavan a i , -F . . m!
. p 3/
p- - as esseLYsuppenTse 3 N
** 2
.n.h 7
A - . . al . ta pausasupponts 8 a p 1 , 4 , y., .g I - s
" ,LR LR ' l l
a ;
= wui.*aa A . '
. . , , e, . _ *.<. l i
L
$U NN N hk Mnars Ip, . ULTst4 ATE POSIYlvE 88084ENT CAPACsTV
& sg &(' & l
*
- g- ULTIMATE ht4AYlvt MOMENT CAPAc3TY '
- - MouanTosmannase ,
POR REINFOaCSD CONCRE78 8. la, ' ! SEE SOWATION 64, c ., <- ! j 4
&5 9 *
-_ . . - - . ~ . ..__ . . _ . - . - - - . . . . - . - . . - - - - . - - .~ ..-. ... _ . . - . ~ . .
i D: sign Basis for Tornido-Gsnerated Missil Josrph M. Far13y Nucl:ar Pla . Enclosure- Attachment 1 j . . BC TOP-9-A , Page 45 of 81 , . 2
, Table 4-3 ;
RESISTA18CE TIELD DISPMCDCENT i VALUES FOR SMS$ , AND PIATES . o i i . 4 k e
- 1 i .
2 4 e t a Vista . i 8 Steca n en SE!E.42EJES.M.81.at IREld$$Ml3T,tal a' i (11 OIIsrby supFORTBS ON ALL f qi I e asetssuiTH LEAD AT '
- CENTER ,
., ..=,, x , o g it. a l ,g .
,4 i N _
- 4 DAs 1A 1.1 12 1A 1A 1A 2A SA 154 .t944 .1881 .sest JE ,
a 1300 1618 .16M 1181 j *, PtESO SWPPORTS ON ALL F e P90AB00r$ RATIO l tal { 4 OIDis WITH LOAD AT , , gggg g I E = te00ULUS OP ELAST4CITV tabAa l
,
- 8
' l e RACR$8NT OP 600ERTl4 PER U001T Wel81N in 6 POS R8tNPORCEO CefeCRETE SECTICIf i* b 'l
- SEE 80UATIOelM j ,
e ULTitaAft P0&Iflys ta004ENT CAP AC17Yle te,* i 2 eg = ULTihAAYE 8854ATIVE A40 MENT CAP l i k 1
- . .A .. .,,t .,, . -g , a t jf~ 1A 1B 1A S.0
- a- - m 12 1A i '
i 2 r a a .ns,1 .ene ,asso Aess .come asas __' j i i !
- i k' -
I i em - . 8
)
l 4-6 1
i Dssgn,ggis for, Tornado-Genzratrd Missilis
- . Bay. 2 'J'oseph M. Fertsy Nucisqr Pl
- nt
- Enclosure- Attachntent 10
- Page 46 of 82
{ Table 4-4 i DUCTILITT RATIOS (Free Reference 24) ! Max. Allowsble Talue of v 3 , i, . l M i-forced Concrete i ]
, I
? Flamure f i ! 0.10
- d. Beans n , s 10 t
%- 1 30 F ,
Siebs s Compraesten -
'1.3 ,
Walls & Columns i . i where A y is the ratio of tensile reinforcenset i
=
f A' p' is the ratio of ecopressive reinforcement a f . S __t el Elements - Maebers proportioned to precluds lateral and local buckling
' 20 Flexura, compressies and abaar 2
Steel Telumni
- 1.3 Froportioned to preclude elastic buckling Members stressed in tension only 0.5[.F ,
I
- e ,= ultimate strain e = yield strain 7
I 1,,u e < .
]
4-1 ^ <>e. c.. c l
. = ~ -- a e
.e
. . . msnm . a. . .*e. ese .
.. .... a awes-. __
- Design Basis for Tomado-Gensrated Missil9s
, . Joseph M. Parisy Nuclzar Platit i Enclosure- Attachment 10 ) j sc 707-9-A Page 47 of 82 , l Rev. 2 } 1.0 1 i
- i i
- I g
j I, = F tuf3 j
'1.0 I 1
A - ($). A l iE@ @V l i l s l to , E' _f M
--s i i
I
, i -
2 pr 1 i # _ I Y I I J [ \
. f .
! 10'2 1.0 ) 10 2 10 1 RATIO ps i
..e. . -e. it K3 I2 \
2 +\ a1, / (pn) P',(K -h2 i F =y- + pn (1 K1 21 m 1.3, 8 0.10, K = -m + (m2 + 24)% 4 i -
- m. n .1 f i. - - o .0.i. 0 t
l Ft cotriscIzwTs voE E-. T 8M1A I or cancxs0 sacu m S*I
Desgn
" Basis
' for Tomido-Gsnsr:ted Missiles i Joszph M. Farlsy Nuctsar Plant
{ - Enclosure- AttachrMent 10 SECT 10m 5 Page 48 of 82 { a ! SPECIAL PROBLEME i i e i l Das cPecial problems are the detersimation}of an empirical formula for j fcree-ties history of automobile crash, sa( the evaluaties of a missile's lvelocityasitpassesthroughaliquid. (" g
, I l .
i 5.1 NORCE-TIME HISTORY FOR AUTOMOSILE CRA'iH l C l l laimpact, deriving the force-tKas the automobile history is considered asof an automobile a dpferamble missilecrash and theunder frontal , i ctructure as a rigid target. According to M endia D Paragraph D.1, ! which is based on a theoretical eensideratipo and considerable espari- , l maatal data, the force-time history under such a seedition is approat- ' l mately as follows: 4 1
- r(t) - 0.625 Y' v" sin 20t. (o 5et 0.0785 see)
. (5-1) l
- r(s) = 0 (t > 0.0785 see) i l wh
- re -
) t = time from the tastant of initial contact (sec)
- I !
3 ! v(t) . time-dependent forse on target (Lb) . l l V, - striking velocity of the automob:.le (ft/sec) l W, = weight of automob,ile (16) Esforences sa derivattens of more elaborato force-time histories for auto-sobile crashes are given in reference 11. 5.2 PUETRATIM OF & MISSILE TEROUS A LIQUID I T3 cvaluate the effect of a missile en a tpraet that is submerged la a liquid, deteratae the striking velocity of the missila, Y, af ter it has pe20trated through a depth, 5. of ligeid covering the target (figure 5-1). 9 13 involves evaluattag the velocity than'ge due to missile we15 t, the h buoyant fores, and the drag force. . l R e penetratten of a missile as it enters a liquid depends se the genastrie chaps of the missile. For the vertical saltry of a missile with mifers hsrisontal cross-sectional area An* and length L, the depth of penettsties ' and the velocity at a depth, s, are ta terms of two fumettees of E. (The factions are evaluated at a e a er L.) ( i 1 te'
- om e O em __
l Dasign BIsis for Tornado-Gzntrated Joseph M. Farlay Nuclair PIInt , [ ' DC-TOP-9-A Enclosure - Attachment 10
- Rev. 2 Page 49 of 82 l .
Eg (s) = g/a + ba g(1-2as)/Ra +e=2ang ,0 ~8/** " 0 a . (0 y a s L) (b1) i 3 (a) = T2 +e bA e (1-2aL)-1 /2a2,90
- EI" L 4 - .
0 TI'm"I)/* *
, (s ! L) (5-2)
I Estatione used above are defined at the end of this section. Missile pene-l tratien in a 11guid saa be estagorised by the fellowing cases: 1 l i 5.2.1 Liqu1D DEPTE 15 LES$ THAE OE EQUAL TO MISSILE LINGTH (M< L) l l 5.2.1.1 If E g(s) is Eegative er Zero et Depth a e 5 (E g(E) 5 0) i . 1 ! h missile will ast strike the target. It will penetrate a depth Eg g I l such that Eg(Eg ) = 0, and then float to the liquid surf ass. ' j 5.2.1.2 If 3 (a) is Positive at Septh a = R g(E W > 0) 1 i j The striking velocity at depth I is Y= E g (5W I l i 5.2.2 L10UID DEPTW 18 GERATER MAN MISSILE LENGTE (E > L) j 5.2.2.1,, If 3 C*) 2 18 "'8**I'* ** 3*** ** 8'P"" 8
- L (32 (') 8 0) b missile will not strike the target. It will penetrate a depth Eg<L l such that Eg (E g ) = 0, and then float to the liquid surface.
5.2.2.2 If 1,(s) le Positive at Depth a = L'(12(L) > 0) The missile will penetrate'the liquid deeper than L. There are two possibilities: A. If 1 (a) 2 is Eegativa er Earo at Depth a = 5 (E2(E) s 0) m missile will not strike the testet. It will penetrate a depth 5 5 s 5) such that E g(EE ) = 0, and then float to the liquidIur(Leface.2 E. If 2 2(8) 18 F**itive at D*Pth *
- E (1 2(R)
- 0) h strikist valecity at depth I is V= E2 (E)
(5-4) 5-2
, - - . . . . . - - - - - - - - - - - - - - ^ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ' ~ ~ ~ ~
l Dzsign BIsis for Tomedo-Gsn:reted Missiles 1 { . Rev. 2 Joseph M. Farby NuclItr Plint
- . Enclosure Attachment 10
!' la case the udssi),e shape dess set have a uniform cross-sectional area, Page 50 of 82 sofer to equativne (D-23) and (>36) in Appendia D.2 for more general oc*<stions. j 5,2,3 gEFINITI W S OF IIOTA715 2 4 0=Y AO 'D (>5) ! b = TR/W (5-6) ! g = gravitational acceleration : l (t = 32.17 f t/sec2 at see level) , I U 4 weight of missils l Y = weight density gf liquid q 4 j (Y = 62.4 lb/ft3 for water at M*F) , j l Ya =. weight density of the missile. fN ; 1 ! a = depth of missile e.g. below the in:;tial e.g. as shawa la figure 5-1. , e q .i i A , 0 = Imagth horissatal L) cross-sectional arse of. the missile (constaat ever l Cy = drag coefficient (given in zahle 5-1 er other referesses on fluid l anchanics) which'is a functies of L/d. R and shape of the missile. L = vertical length of the missile f l d = chor teri. tic 4imen.i.a of th. .tssite as .h a in cahl. 5-1. l 1 = asyneide number - (5-7) l l ! v = kineastic viscopicy2of the liquid , i ( = 0.95 a 10-5 ft /see for water at 80'F) I l 7 = initial velocity of the ases11e at x = 0 (see figure 5-1) 0 l 3 V = atriking velocity of the missile at u = I! (see figure 5-1) l 1/2 gpg3 l v2* E*rminal '*18ititF " 5(1 'a Y/Y,)/a i l 4 . i i 4 j . .. _
. _ _ _ _ . _ _ _ _ - _ _ _ . - . - - - - - - -- - - - - - - - - - - - ~ ^ - " ~ ~ " ~ '
4 i 1;
- Dtsign B
- sis for Tomido-Gsnerated Missiles. I Joseph M. Fartsy Nucl2ir Planti !
i .
,g
, , Enclosure- Attachment 10' i
- new. 2 Page 51 of 82 J
} ,
" Table 5-1 j
l naAC COEFFICIENT POR VARIOUSLY SEAPED BODIES U 2 00MPRE55IBLE FLOW (25) ! l ! - Form of Body L/d R C D Circular disk ,103 1.12 I l Tanden diska o 0 >10 1.12 L = opacing 1 0.93 l d = disaster 2 1.04 j 3 1.54 l . *' 3 ) Rectangular plate. 1 310 1.16 L
- 1ength 5 1.20 4 = width to 1.50
< ~ 1.95 s 3 ' l Circular cylinder (amia 5 to flow) 0 >10 1.12 j L = length 1 0.91 i d = disantar 2 0.85 - 4 0.87 l 7 0.99 5 2 Circular cylinder (amis 1 to flow) 1 10 0.63 ! L = length 5 0.74 d a disaster Q 0.90 j 1.20 ( 4 5
- 5 >$ u 10 0.35
- 0.33 4
streamlined feil (1 3 3 airpisas strut) e 84 a 10 0.07 { 2 L= spa l 1 d = chord . ! 3 Hemisphere No11ev upstream >10 1.33 i 0. 34 Belise devastreas _ l 5 5 10 0.5 l sphers i Il 33 s 105 0.20 2, asjer smis 5 to flow) >2 s 10 0.07 2l E111peoid (1 5 i ^
>2 s 10 0.05 Airship hvil (sedel) 3l I !
i i I .
. _ . _ - _ _ _ _ _ _ . . _ . . _ _ . _ _ _ _ _ _ . _ _ _ _ - ..__.m_.__. _ _ _ _ _ _ _ _ _ _ . _ _ . . _ _ _ _ _ . _ . .
j i: Design Basis for Tomado-GentrIted Missil:s - SC-TOP-ppgeph M. Farley Nuc!str Pl:nt 3' W.2 Enclosure- Attachment 10 4 - Page 52 0f 82 4 1 l i i t . 2 - essant { o Lausosunuct
\' t ** Ve *** **e y
- i6 <
- t - . , - - - _
y
- o t r e v, m*L s = ry
- i i
i l j s t i m:3859 [h* *
~
l < , n *
- y. - -
7 . . e-1 '
' Fy
- W9h,
{ i I j ' F,* mt /4 - ) - i 4 p-- --- - l i <, 1 **v s=N I u .
~
es0TE: 388 APPENDIX 9.PARAGRAPM e.3 Pen ass AssALyses er Yuas SAGE. Figure 5-1 PENETRAT100t OF A MISSILE IN A 1.1 QUID e i , _ , , , , . . . . . . - - . . . . . . . . . . . . . *** * - - ** *
.4 . . . . . . . . _ . .
l 1 D: sign Basis for Tomido-Gsn:rsted Missiles )
" Joseph M. Ftrisy Nuct:ar Pl:nt i "hv
' ". 2 Enclosure- Attachment 10 Page 53 of b2 Artamts A CROSS REFERDICE LISTINC TO AEC STANDARD SAR FORET Thi3 CPPecdix shows the cross reference between sections of ARC's Standard EAR format and the sections of this topical report.
AEC SAR Format _ BC-10P-9 3.5.4 2.0, 3.0, 4.0 i I I O i
- l i
I i e e e O sr 4 9 A-1
i j D
,Jsign, Basis for Tomtdo-Ganzrated Missil:s j
Jos2ph M. Farisy Nuclear Plant j *
. ApF3NB11 5 Enclosure. Attachment 10
, . Page 54 of 82 { SASSARY , l 4 s 1 I 3.1 PENETRATION ! , t ! l ramtrcties to the displacesset of the missile ints, the target. It is a
- meccuro of the depth of the crater formed at the some of. tapact.
i I J 3.2 PERFORATION 1 i Farferction is " full Penetration" or where the missile passes through the j terset with or without exit velocity (o%sissile). i ' l 3.3 stautus or conca Ts i' iSpa111a5 is the peeltag off of the back face of the target opposite to the ' lfac3ofimpact. .
' t
+ - 4
< B.4 DUCTILITT RATIO I ,'i - l Tho ductility rette is the rette of the monimum deflectica to the ldsficctionatthe"effectiveyieldpoint." grFECTIVE YIELD p0 INT lS. 1 l That point sa an idealised bilinear resistence funetton separattag the i cicotic and perfecti; plastic portion of the function. The effective yield l l poizt is based on the strength of the structure by ultimats (or plastie) s
- dseigs methods. ;
I i i 3.6 elastic DEPACT An olastic collision As characterised by alastic deformations at the ainsile-target interface. l ! 2 ,
- 3.7 FLA$ tic DtPACT l
A picatic esilisies is characterised by inalaatte deformation For aand purely local , l l 4 asse of the sineile and/or target in the layect none. plastic cellision, elastic i j fcca and associated elastic rebound emergy release converse to sero. i t i j 3-1 1
- l
- - - . . - - - . . , ___ \
i i' j i . Design E> . sis for Tornado-Generated Missiles i Rev. 2 Joszph M. Farley Nuciarr Plant ; Enclosure- Attachment 10
.- AFygNDIX C r Page 55 of 82 ;
) REVIEW 0F EElly1NC 70RMULAS i l C.1 PENETRATION AND PERPORATION j the meet segmen formulas need La determining the local effects of a missile
- en a target, such as penetraties, perforation, and spalling for missiles j striking either a concrete er steel target, are gives in tables C-1 and C-2. l j These tables include equations C-1 through C-11. These are the current
- secte-of-the-art formulas en tapact analysis, which consists primarily of !
l espirical mathese based on esperiments senducted for specific and limited i i cyplications. Generally, the emperiments were conducted for the Goveressat veins mineilee, such as bombe and bullets, and having velocities above I 1000 ft/sec. Current tapact analysia aesumas that the missile tapinges the target merest to the surface. The effecta of the oblique eagle of ctriking at various velocities are 111uetreted la figure C-1. It saa be
- seem that assuming normal striking of the target is senservative, since a
! ses11 deviaties from a asemal impact decreases the depth of penetration censiderably. . l Tb3 Army Corps of Engineers and Natiemal Defense gaseanh Coenittee. j cgu:tions (table C-1) for penetraties, perforaties, and spalling have a , i stra, which depende saly on the diameter of the missile. However, this I tenu providea overly conservative results when a low velocity and large - i Per exemples as V, + 0 the penetration ldiametermissileisseasidered. approaches 0.5D; perforaties approaches (1.3)Ds and spelling approaches
- ( 9)D. which is met realistic.
l dev. lop, with the emphasis sa the effect of impact sa the target.Emperimental e sees data with ve ! esperiments have been esapJeted with missila velocitias in the range of i interest. Mongver, the tests were met necessarily senducted for target i int:rmation.(21) therefore, available partiment data are limited. The modified Patry formula has had the vidaat applicatias for determining : the pcaetration of a misgile into concrete targate and is adoptad'for use ct the present time. It was developed by the Poncelet theory, provides eatinate of penetraties, and has functiemed best in the velocity range of intercat. Also, conservatisa is built into this approach because of the following A. The eagle of striking the target has a large effest if the angle is greater than 20'. A mesmal angle of strike is assumed. l
- j i
)
0-1
j 1: Dssign Basis for Tomado-Grnerated Missiles Jossph M. Fariey Nuclear Piirit !. SC-TOP-9-A ' Enclosure- Attachment 10
- Rev. 2 Page 56 of 82 i
1 3. The probability of a missile being oriented la a manner that would > l produce the greatest penetraties is remote. In addities, any
- matiemal effe.t toads to a.mos tie area of ta,-t.
{ C. Commervative estimates for weight, velocity, area of tapset, and l target strength provide senservaties. ! Even though t8e modified Petry forauis was developed in 1910, the material i coefficient reported by for penetraties, Amirikian(14) andK,hown s ta figure 2-1.has been revised by esperime 6 i The BRL formula for perforaties of concrete targets to used. It is 4 aslected instead of the modified Petry forunnla of T
- 21 because the BRL l formula was developed for perforaties and est as en appresimaties free a
- penetratism. 3' j
- y .
i The BEL equaties, given la equation (2-3), has been modified to secount for ! l
- eescreta stres th other than 3000 ygg by replacing the coastant eseffietant j 7.8 by 427/ is equation (C4).uJ
! I e l 1 0 steel perforaties formulas are available, the Ballistic Reeserch and the(g ferd Research Institute i Laboratories formula, kneum (BEL) formula as the (2)(3) Stanford Equatism. l Tha Stenford Equar.ies is j based en asperiaantal data, using missile velocities with3 d.e range of l interest. Bewever, its limits of applicability are we'ty restrictive
- because test stasiles encountered fall outside the rangs of the Stanford i Equatism.
l
- The Balliotta Basesrek formula, tabla C-2, to used with en assigned value of
} 'E equal to amity. Raarranging teres and selving directly for T 1eads to the j formula for salculattag the threshold of perforation. , f y,232/3 f l , yJ2A )1 (C-12) suo i . l The Staufers Equation (table C-2) has the fellowing defined limits of l appliambility: t l-0.1 < T/D < 0.8 ! 0.'002 < T/L < 0.05 l loc VD< M. 5 < W/D < 8
- a < v/r < 100, 3
i
.)
. C-2
4 Design Basis for Tornado-Gensrgted Missil s
- Rev. 2 Jos:ph M. Parisy Nuclear Plznt
,
- Enclosure. Attachment 10 '
a Page 57 of 82 j 70 < V, < 400, L e length of sylindrical missile I
- y a striking missile velocity normal to the target surface for the ..
l thresheid of perforatten (ft/sec) 9) 1
; Solving egustion (C-11) directly for plate thickness gives.
". 2 l
l T= 0.045 , + 0.0022lfv 7 L as l ,2 - 0.047 ,,e (C.13) ! a i M l
- who .
\
I ! vV 8 . i l# -E = y , 3 { . I W = weight of missiles (pounds) l i e c -
)
i A p:rametric study comparing the BRL formula and the Stanford Equation, ' j withis the limits of applicability of the Stanford Equation, showed the s BKL cod SRI formula are generally in good agreement for the shorter spass. l But, for longer spans the SRI formula is less conservative. Considering 2 j
- this cod the narrow band of limits for the SRI equation the BRL equation j i med for design.
1 l' C.2 MULTIFLE ELINDtf BARRIER EQUATION . i j Egestion (1-9) assumed the' residual kinette energy of the missile after ' 1 perf3raties (Er) is the differases between the kinetic energy of the missile befsre impact (Eg) and the energy required to perforate the steel (Ep ) l l E,
- Eg - E, = j = j - (C-14) !
chus . f \ ab u- .e of the missile 2)j i i C-3
.. - . . -. . - . . - . . . - - . . = _ . _ - . .. . - . - . . . . . - - - . . - . . _ . .-. . . . ... _.
j Dzsign Basis for Tornado-Gcntrated Missiles Joseph M. Fartsy Nuctsar Plint'
, Enclosure - Attachment 10j BC-70F.9-A Page 58 of 82' -
3 f Rev. 2 4 { solving for Y, j i
/v3 -y 331/2 1
~
y' = i b \' ')l Thf.s aquation neglecta the asse ef the ping which any be punche4 evt ei ! the target, wktch would be very small for a steel target; for a conerate j target. the concrete would fracture and not act in conjunction with the miseils nase.
- V, saa be obtai sd from equations (2-3) and (2=7) by selving for v., which
- v111 be the velocity to ,just perforsta. V ,. when a given thickness of
! target, t is used. i i' i 3 4 I l e i A
- l l
l I l i , i i a I I i h 1 1 i ._ i
;!c. -
4 j .. w
- !{! 'l; !$ ;: l. ' !! I,! t{il .j,jl.i;1 !1. !: ! ;i;; : i : .l; !l
$ 5 ,, *
[ ,. g u j ow 2 E
} 5_
11=2W I -l2 . i l. -
. 2I3:3 l #.; 3 &.
g .
- ,e ~
2eiS e3e e i
. wN a ". r. v . 0.I ~
gh l~$2 a~$ a p. .=
.e .. 4 > ,. IM.u Sb C
[. ai .1ew. Y ,
= e
. sS$.s "2TB
" ' *M .
5 ~ I 2 a.. l h2s, A.5I
, ,e . w _I ,?- "w W .9 ~
Y. w ,~ at55 ]".t _
!*$ x :. c ~
* *-[ M
~E = _. e
-]$ ~< = A 5Le ,a .~alA I ~- _
d . i-l 82 2e1n .
--- - R
- d .I e eD l*$1 3g a*$ *x x. 2^
.N Ip4
*, 3 vi
.g 2B n
s a s i s Jf o o s r
- Ep o eT nhr n
- c l
o s .M da uF- o r
. e aG r e .
en l P Ay e t at Nr g a ut a e hl c cd e
.:*. - e 5m aM
! '. i ! . il i.:.'. , t - l .
9 er i onPsis f t lal 81 n 20t s e 1
t Design Basis for Tornado-Generated Missiles i Jossph M. Farley Nucisar Plant 3C-TOP-9-A
, Rav, 2 Enclosure - Attachment 10 Page 60 of 82 3.
i j8 3 3 3 3 3 l
- " 1
! ^ E j e !
- n ..
l .! . t . . !' ] I y 7E j$ 15 I j I ]E
- *w W w w 1 I I M .E C us ug I
M . b e E l 1 a a 4 : 2 1 i s . g W si v g i 3 = M I t
,g . B . . # 2 9 i ,
a . _ a ! s4 5 s I. a a a 5 8 B
- i B B B
" s i > > > B.
3 ' i d 1 i . E 1 I i. 1- 1 A m e y i= A
= .: =
j 4 i Id #d gl}g Ed 3; 1d ! 3 1u -a au.- g p. - a s
, e h ?
4 a
.q
' & N N
a !
'abla C-1 ,
ll ' CONCRETE FENETRATIiW PERFOIIATIN, AltS SPALI.ING FOIORRAS (Sheet 3 cf 3) l
.l .
W = Wei $t of Missile (ib.) ., j StrikinS Velocity of Moe11e (ft/see.) l! , V, = D = Dienstet of Missile (ie.) Nieelle Mothe A Prejastes Frontal Area of Missile IP'II p " X = Depth of Fametsstian tote Sieb of Inflatte nick Caecrete (ie.) ,
= Bapth of heatration Sete e Fleite hicksees St b of Concrete (in.) j Xg i i.
i J h ienness of the Sieb (ie.)
> t =
i r
~
f' = Ceepresolve Strength of Cenerete (Foi) ;
- i X = Emporimmet.11y Steined Noterial Coefficient for Femetretion (See Figure 2-1) - l P i l '
I N = Wees Feeter = 0.72 + 0.25 (a - 0.25)1/2 , i ' I resies er e meette. ! l* diameter of miselle j
; T = Dichnese To Be Jeet Perforated (ie.) o. ;
Ig2 E.o l T = hiekness To Be Just Spelled (Ga.) 3 e ' I l g l I NOTE: Some of the equetiene have been rewritten to reflect eenstatset emits see tersimelegy. I l N
. L" O
.\: O SH ! ( -_
?%y i RFa-sme
*Ef
..O i I . T AM S i
. _. . .. . . . . . _ . . . . - _ . . . . . . . . . _ _ _ . . . a g ,. g ;
~R'?E. I 085N
i t i e Table C-2 I E. :
<g, l runronaTron is sren, name.as c
1 .
. S.
' Egentime Smeerho No. l i
Focus 1s l' Identificettes t 0.5 M,2 C-10 I T = l Be111ette Sesserch Lab 2 (mete. 2, 3, 13) 17 ,400 K ,34 i Steford Research y T See Limite page C-3 C-11 16,000 Y + 1, iKnotitute
.. 20) f= lL e) .
?
i T = steel thichmoos to be just perforated (ie.) ! i 2
- M = ease of the missile (1b-see /ft),
striking volecity of the missile morant to target eerface (ft/soe), t T = ! e [ l cemeteet depending en the grade of the steel, (K le eseetly
= 1.) g i E =
D = dienster of the missile (ie.) N g l, E = eritteet kamette energy regelred for perferetism (ft-1b), Er ( gj y S = elet==te tessile strength of the target edene the tessile strese le the steel (pei) R=B r {FE cn9 l W = lassth of e egeere side between rigid ogperte (ie.),
= length of a standard width (4 to.). (See Ref. 20) fhf m k* a W,
; b c l i~ $2@i Rav !
Ei$ b
l 1 } , , Dssign gis* f Torntdo-Gsnsrated Missilis ! . seph M. Farisy Nuclser Plint t Enclosure- Attachment 10 i i Page 63 of 82 4 i . 4 2 ! Effect of OWigue strike t - j $pelling l 1 L L / wp.rt.,.ii i ' c - d WOAerfeestien 1 l e. e' wa ae' se* saa i , ;i:.
- . . , :..- ' ?.,>r.
; -d ..:.,'^ .: .
..> ..s 1
. . . .. .. : ..;;o .;. :.: . . . ,
.s ' .
- .q m. .
m .:"q 4 . , . , j v.. lasse b 4. 4 4 f l , l~l%. . a..h@:2.,
.; , ,.. p~..- ts..
'1,
< .s. ;9 , V &, .; td.
y.u. M .<.f, , . . . , . .,. i i .v.. . . . m,. p:;. r. -
.,4 .s. . .< . ..y;. . .,y .. a .
. g, . .. s . .
l , , : .. . 1 1 v . 1 t W : ! v.. h 6 he (e l 3 , 5 *
. 3. *5 ;3 h'., :~ '
, [::.p.f:.k
. I,. ,' ,:. ,;-..s:: a . . . 7'f'.::a,
. I
.; :-.y..Q99,. .~.:
I
>. n... :I.*.If g ,.! .
} ,
- i. v,- w w, we w a -
;.1 , ... . u ', ; W J '
.i .. . . . 'l
' l-s'i.s..t;% ..
t > yW',. . .. /..g l\
.y: *1 I >is' .:ll' :. Cu).
i .,j;;i:'y
.zt;, .:y I
- .i:j!:'.I;i:,i$-
1.*
;r-...; ?'y'. i -
. . W ' s. . 1 1
2 .hQ's}}:.~."i i l$q.A.[ :.4&.eny.1N j W.l . [ .H; ; 4-Q .?l,l .%W
- v. W. - 6 6 6 'm 4 . 'm i
l . . . m. ,.s...aj. w:.q..%..s.::
.e ...m, . .. .{ . .; *u . .
- 3 r ;,., - .: i:... ...
i (EJ...:.d!Qp
. I l .M; .v.W.y '
.w.: I i .:L: b f:1%s v.;y l
' ,?g h?r.$$%gg.b
.1 p, f$hyi
. JM. m'm:7l@,$.4 khf*4tsh '
u .y 4w.W. 3 l(46.!.%.. .1 2 t s _.a. c . t v.= 'm %s %= h k. *"h a , , V,= b Isas - hTe as. be%as. 37 MM. M80 Projoettle : Concrete TWeknese e 33". Compresolve strength a $700 ' Abs /ts.g Strthtag velocity (Vs) and angle of ebilguity ( f ) shown. # Steek projectiles and path of rieschet projectiles ebewr Figure C-1 TYPICt.1,CRA W R PROFn.E8 C-9 4
. . . , . . , , . ... ... == = - *
- _- .- . - - _..- ~.. - - . - . . . . - . ~ . . . - - - . . . - - . - . - - - . - . - . . - . . - - . - . - - - .
4 : I Degn V' Bayis for Tornado Generated Missil:s Josiph M. Farley Nuclear PIInt Enclosure - Attachment 10 t , AFFDIDIE D Page 64 of 82 ISRIVATI(NI5
- p.1 DERIVAT10810F PGacE-Tilt M1$10RY POR AUToleSILE CRASH, gQUAT10 lit (5-1) ,
4 f i As cypromin(ste relationship has basa observed in esperiosats se auteeshile grzhss.(22J The deceleration per unit deformation associated with the
- crushing force was observed to be approsiastely the same for a wide variety of ctandard-sise U.S. automobile askes and models.. The decelera- -
j tira during a frontal tapact is as follouss 4
- M = 12.5g n (0-1) l
. l l where .
I f =E = decelersties (ft/sec ) s e distance automobile crushes into target (f t) { l , i ! 2 *
- l
! 3 = gravitational secaleration (ft/sec ) l
- peutea's law of action and equation (P-1) give the relation ,
i j y l
" (o-2)
= 11.5 W ax l r=-3 -
..-g .
0 l are 1 } W e weight of automobile (1b)
- a Equation (D-1) is the noclan for an undeeped limaar oscillator with a unit ,
mass and a spring coastsat equal to 12.53 Its solutten with initial sere . ! defsrasties is a = c sin (12.53)1#8 t (3 33 1 4 a f To determine the constant. C. cassidet the balance of the input klastic sa:rgy, Ea, by the striking satoasbile with work done by the tapact force - plus energy test. Ep by other phenomena such as target roepense UV 8 (n-4) 1, a .. a .12 a.a.3 2 mas asa T whsre T = striking velocity of the automobile (ft/ses). e i I>-1
. . . . . . . 1
.-.- - _ - . . - - . - - - . . . - - . . - . _ . . - . - . . _ . - _ . - . - - . . . . - . - - . . . . _ ~ . -
} i, Dssign Basis for Tornado-Gensrated Missilss
, Joseph M. Fartsy Nuctsar Pltht
- l. Enclosure- Attachrnent 10 Page 65 of 82 I 3C-T07-9-A -
{ 3aw. 2
! la the senservative same of Eg,= 0 the cometant C can be determined by i substituting equattens (>2) and (>3) inte equaties (D-4) ,
C=(1253 's (D-5) l Finally substituting equations (D-3) and (D-5) into equation (0-2) gives i, the force-time history 1 - u.i W. (uh,f' ., .ta u,.,g)m t l 4 i i J
= 0.625 T,W , pia 20 t (8-83 This is a eine wave of freteeney y
- 20 rad /see and period T = 1s/w
. = 0.314 ses. The maalaus force.maeurs at t = T/4 o 0.0785 sac when the i velocity of the striking automobile is saro relative to the rigid surface
'2l and then rapidly reducing to sere. Thus under the condition of plastic col-l lision (i.e.. missile and target acquire same velocity after impact) the *
,! duraties of the impact force is frem t =.O to t T/4 = 0.0785 sec. At i 2l t = 0.0785 see., the force diminishes from a maximum value to aero. i j As an example of using the resulting expreseiens, seasider the superiaantal 1 data La reference 23. Test No. 505-IW for a 1963 Flymouth automobile ! striking a rigid well yielded the folloulas data. , Wa = 3270 lb 9,
- 53 3,aph = 78.17 ft/see s ,= 3.82 ft t
j gF,,,N, = 2% (everage ever distance) b' From equations (p-3) and (D-5) and the above data the stopping distance is r g
" ass"k12.$g)1/2 (78 17)
- 3.91 ft
! 2l According to the foretag function equation (D-6) the average deceleration t (aversga over distance, not over time) for Test No. 305-IV is l . { 3F,,,/M, = 3F,/2W, = (0.625)(78.17)s/2 = 24.423 J J which agrees with the test result (25g) quite elessly. 1 4 i f b
>2 4 ~- =. ._. -- _.
. . _ _ . _ _ . . . _ . . _ . _ . . - _ . . _ . _ . . _ _ . . . ~ ~ . _ . _ _ . - _ _ _ . . . . . _ _ _ _ _ _ _ _
i
. gsi,gn, Basis for Tomado-Generated Missiles Joseph M. Farley Nuclear Plint l
Enclosure - Attachment 10 . Page 66 of 82 l l D.2 3ERIVATICII 0F TME TE14 CITY OF A MISSILE AFTER IT MAS PENETRATED I , Titaouel A LIQUID i } Coueid:r the metten of a missile, length L. entering a liquid medium and ' otriking a target at depth E from the liquid surface. es shown in fig-i ero 5-1. When the missile first hits the liquid a sempressive shock wave i may ba generated ta the 11guid with a resulting less of missile velocity. l This to sailed the " compression phase" of liquid entry la reference 24 l (page 18). As the missile displaces the liquid it esperiences a hydrody- ! camic force with variable impact dras coefficient C,. This " liquid- l ! disp 4coment phase" further reduces the velocity. M ter the asutaue missile l 1 cross-sectional area is immersed, the " cavity drag phase" to initiated in j which the drag coefficient CD may be seasidered constant. In this appendix -
- she velocity of the missile during liquid entry is analysed on the assump- ,
j tiens that the velocity less in the "sempressies phase" is negligible and j that the impact drag coefficient Cp sa the " liquid-displacement phase" ta
- ct ' to the drag coefficient Cp is the "sevity drag phase." giace CD is -
alw s eas11er them Cp (see referessa 24 pass 30 and fieste 2-7) these ,
- assptions give more esaservative (high) results for tbs missile valecity.
j caly tbs.caos of vertical satry (aernal to the horisontal liquid surface) l
- sa consider.d. . .
- Wadsr these assumptions the equaties of missile settaa is ; .
E=W-Fh - F, M . ! i j wh 3 l i l W = Weight of missile b j 's = gravitatismal acceleraties , i ! u a depth of sissile c.g.' belev the initial c.g. as sheva ta figure 5-1 t = time after initial acatact of missile wich liquid l ' P = buoyant forca l b
,,= drag f.re.
and o det denotes differentistles with respect to t. Betweem a = 0 sad a = L the beeyent force varies with a (n-s) , y, = y ,8f* a(ag ) da g = vi(a). (o s a s L) i. 4 D-3. e 3
_ . . _ _ . _ . . _ _ _ _ . - . _ _ . ._____._ _ _.___.__.._._..____....__......____._m . - _ _ _ _ . Design Basis for Tomado-Gsnzrated Missil:s j Josaph M. Fartsy Nucl31r Plint) g ,gy.g g Enclosure - Attachment 10 Page 67 of 82, Rev. 2 f where ! y = weisht density of the liquid
^ A(my = distencehorisontal cross-sectiemal area of the missile at vertical a 'from the tip
{ g Uban a > L the buoyant feras is a coastest i Fb
- D /Ta ' $8 # L) (D-9) l' i where I
Y ,a weiskt density of missila l The drag force is given by the espression 74*Y Qv/2s (D-10) l l where j g = ===i=um horisontal areco-esctiemal area of stes11e v . t = velocity of missile at depth a If the liquid la assumed to be Sacompressible, the drag coefficient, CD* 1R f equation (D-10) is a function of the missile shape and the Reynolds ausbar R, defiged as Tdo (D-11) 1=7 where d = ebaracteristic di===atea er missile as shown in table 5-1
= initial velocity (at t=0 sad =0) of sissile v = klaeastis wiseesity of liquid Table 5-1 free reference 25 liste sees typicalReference D for varisuely values of24C(page
. 35) presense shaped bodies sa taoeapressible fluid flow. Other references en fluid sees CD values for a family of aese shapes.
mechanico can slee be coseuited. . 0
s i a DgV*ign Basis for Tornado-Gansrated Missil s { , Joseph M. Fartsy Nuciatr Pl:nt f Enclosure - Attachment 10 I Page 68 of 82 l
- S:bs.tituting
. fo11o.a.equations t f.t of(>S),o.(D-9) ue. of and.aea (D-10) inte equaties (D-7) results and .1.ue.., i A. For 0 S u $ L ,
E + est + bf(a) - g = 0 , (0 $ s i L) (D-12) wheire l s = YA,CD/2w (D~13) b = yg/W (p.14) . and f(a) is given la equaties (D-S}. N ! This sa a analinear, seesad order, asehemessessus, ordinary diffor- - ential equation for x(t). i . .- l .Aceerding to reference 26 (page 551) it,can be solved as follows: . 1 . j Let ' 2 (.-15) ! r(a) - *2 -v - . j i Them if a prias denotes differentiaties with respect to a, ' ( . j 'y'(s) a ti(ty = 21 E/a = 2 i (D-16) , l . Equaties (D-12) becenas : i y'(a) + 2ay(a) = 23 - 2bf(x) (D-17) l
- f which is a 11asar,' first order, asahemogeneous, ordinary differen-l tial equaties for y(s), and has the solutica J y(s) = 3 p(s) [34f(a)) da + a fp(a) (D-18) j i
where c le the integraties cometent and J
- I2.da (..t,3
- p(a) = e; = a3 ,,
e g .e s) I
. I e
t
- - - - _ . . . - ,._ - . . - . . _ . - . . . . ~ . - . - ._ .. -
, t i
- D
- sign Basis for Tornado-Generated Missil:s i .
Jos2ph M. Farlsy Nucisar Pirnt Enclosure - Attachment 10
. . EC-TOP-9-A Page 69 of 82 nav. 2
! substituting equation (D-19) inte equation (>28) gives y(m) = v2,,-Saa 23 g, ,gg F,2az gg,) g, , , f2am (D-20)
-2as f = g/a - 2be C(u) + e s' "" . (01 m i L) j whera taz G(s) = e " f(x) ds = [e xy dag as (>21)
'I in which equaties (D-8) has beam used. l ! At the initial posities (see figure 5-1) x = 0. T = Y O' '"# equation (D-20) gives 8*Y 02 - 5 /a + 2bC(0) (B-22) , l i i Thea equation (D-20) becomes 3 y(s) = v2 , ,f, , ,-1as 9 ~
- 0 (D-23) f + 2h (G(0) - G(s)h (0 i a 1 L) e j At x = L equation (D-21) gives 1
C(L) = I A (D-24 fa"" A(a}da g g 1 1 - and equattom (D-23) gives i i 2 -tat 2 i y(L) = vt =Y 2 2 + sY/Y * + * 'O - 8/* i (n-25) 1 ,
+ 2h (c(0) - c(L)]
. >6
_ . . . . _ . _ _ _ _ _ _ _ _ _ _ _ _ _ _ . . . _ . . _ _ _. .. .- .._m.________ _ _ _ _ _ _ _ ___.___ ___ ___ _ . 1 a Dg, Basis for Torntdo-Gtn: rated Missiles
- Joseph M. Farlay Nucinr Plint Enclosure- Attachment 10 whera V g is the miss11e velocity at a = L (see figure 5-1) and Page 70 of 82 i
- V " 1
- T/Y (D-26) 2 2
( a/ - j Consider the special case of a missile with uniform horisontal sto2e-sectional area A0-*'
- I"1I*A. Equation (D-21) gives D
G(s)=,[a"" Ad D I d'
- A0 f ** #" 2 l (D-27)
! *AeD (2am-1)/4a , (0 3,a 1 L)
. (
) from which , s(o) = -ag /4 * (p-2s) l M ' l c(L) = age*"' (2aL-1)/4a* (p-2s) l , I
- j Equaties (D-23) bessees j v* = s/a + BAD (1 - 2as)/2a2, -taa (, 2 , ,f, .
bAg /1a2 , (0 g a 3 L) 7;roulas for other missile shapes aan be derived similarly. l i For a 1 L l 1 s + aA* + sv/T, - s - 8 5 (* A L) (0-21) nis is a special case of ogsstima (D-12) with 3 (m 1 L) (D-32) ; I(a) = sv/7.b , which, when substituted inta eguatima (D-20), gives
,2 g,y g3 (3 33) :
,,2 ,g,-2as ,
D-7 N O' M " g3m e33 6 S e
,, a ppp
_ _ _ _ . - . . ~ . - - - ~ - - - - - ~~~^ ~~^~^^~~ ~' ~ ~ ~ i
, Design Basis for Tomido-Gsnsratsd Missiles I
Jos:ph M. Farisy Nuclear Pitnt i BC-10P-9-A Enclosure- Attachment 10 saw. 2
- Page 71 of 82 i
The integraties seastant k sea be detemised by the sendition that at a
- L. *
- V gobtained la equaties (Ib-25)
! g. y 1 2 ] 1 2)1,2aL (D-34) 3 . . Nence the missila velocity at a 1 L is given by ] v= V 2 * (Il ~ '2 *
* *1N (D*33) i Substitutias Fg from equatism (D-15) inte equaties (D-35) saves
.. . ,,= . . - Ano) . .(in . V g>
i i > i 1/2 (*">')
+t,e Y/Ya-1 /a ,
. (E E L)
In the special casa of a missile with unifers horisontal crose-
. sectional area A0 equations (D-18) and (D-29) are substituted inte equaties (D-36) to give 2
v=' V 2
+a (e (1-taL)-1)/2a L
# ' (D-37) 1/2
+VO+8 TITa "I #*] ' I" A ' i At a
- 5. dem the miss11a strikaa the target (See figure 5-1) the velocity V is given by equaties (D-36) er equation (D-37) with a replaced hy R.
- i S
D-8
4
, Design Basis for Tornado-Genzrated Missil:s Rev. 2 Joseph M. Farley Nuciser Plant
~ .
Enclosure - Attachment 10 p gggg g Page 72 of 82 , SAM LE APPLICATION 5 ; k E.1 CDNCRETE (PENETRATION, PEUORATION AND SPALLINC) A 4-tach a 12-inch wooden plank, weighing 108 poses, strikes at 300 mph 4 (440 fpe) fa a normal head-on collision with a reinforced concrete (ff = 3000 psi) wall. The plank has a 48 square toch cross-sections! , i crd with the equivalent diamatar of 7.8 inchas. i l s.1.1 PENETRATION remetraties is siven by equaties (21): I [ y2 } .; E = 12 E,A, h alo *2 j Far 3000 poi sencreta E = 0.00348 (figure 2-1) P , l, cad . A p *4 g = 324 Pef' i .i sa 1 1 i I* uot) '
- 3*II A"*
1 = 12 x 0.00348 m 324 x 14 10 'N ! them t.he thickness of a wall is less then 3 x 3.77 = 11.3 is. the depth of j penetraties is given by equaties (2-1): 1 i s ! -4(i-) x
- s= 1.a
( - i i-War ausmals, for a well with thickness t = 8 in., we gets i
~
j 1+e - Q* . 2 ? f Eg= L J z 3.77 = 6.08 in.
; . l
, l j m 2
i l f
,,M 4.
i i
. . . =
j _.
4 1
- Dasign Basis for Tornedo-Gansr ted Missiles 1
** Joszph M. Farley Nuclear PIInti j ,
- Enclosure - Attachment 10' sc-T0p-9.A l; Page 73 of 82 l- 6 i nov. 2 1
4 , 3.1.2 PERPORATION ' m thiekasse af a well to be just perforsted is given by formula 2-3s
. 47 y 1 ~
l c D fwe$)1'33 -i 1
- For l' = 3000 poi,
. c ! 427 e f 4601 l'33 , T= ~ gl = 7.01 is. 4
- p 1.
Thersfere, the sencrete skicknese regoired to prevent perferettee accordia,s to equatten 2-41er t y
= 1.'25 x 7.01 = 8.76 is.
E.1.3 $ PALL
- v h thiskasse of a well to be just spelled is given by equettes (2-3).
l Ta = 2 T = 2 s 7.01 = 14.02 in. d 4 Therefore, the concrete thicknese required to prevent spelling according to
- equation J2-6) ist t,= 1.25 a 14.02 = 17.53 in.
l l l E.2 STEEL TARGET 1. ) Givent ,A tea pound missile one inch in dinaster impacto e target at
- 200 ft/sec.
- Questies: Find the thichases of steel plate. T, to just perforste and the j thickases t, required to prevent perforettaa.
Solutten Use ogwattaa (2-7) and (2-8) l i Then l - 10 2' f 2 s 32.2 i T= 0.5 inches 672 W chec. f' t'-
, and t, = 1.25 a 0.5 l
i E-2 1
Design Basis for Tornzdo-Gsnsrated Missil:s i . hav. 2 [, Jos:ph M. Farlsy Nucistr Pirnt Enclosure- Attachment 10 [ . Page 74 of 82 ! R.3 i - ITRUCTURAL REEMEtSE !. sider a 10 lb solid natal missile of 1-inch diameter striking with 200 f t/sec velocity at the mid-span of p simply-supported steel 1-been of i ' 10 ft spam and AISC designaties W6m12(8J with static ytand strength fy = 50.000 pai. It is required to evaluate the structural roepense of the j besa accordin8 to Section 3 under the condittom of plastic impact. i i Acestding to equation (3-17) the effective asse of the stest beams may be } eene:rvatively the d:pth of beam'd estimated = 4" as andthe D,mass of amineile
= 1", the 13-inchdisaster)length ofwhich the beam is for (since V6x12 beam (B),
i
- ye, (12)(13) ,, g37, l 123 l
l Acacrding to equaties (3-8) for plastic impact, the required target strata . { energy to abeerb the tapest amargy is t . N 2,2 ! M (200 x 11)2 - ! Is"2 + Mg" 32 440 in -1b ' 2{Q*I+Nh *s ) t s ( l Tha resistance-displacement function of a simply-supported beam under i c:strcl leading can be idealised as a bilisest function (figure 3-1 and i t to 4-2) with 81t I I
'"o d i n " T*
- Y " s(21.7)(50.000)di.2) (10 s 12)(6;, = 14.467 lb i , 1
' and 3 Ik , (14.467) (10_s 12)3 = 0.00 is. j , , nn ' 48 (30 a 10')(21.7) , whers the value of the moment of inertia. I for the been crops-secties is
- taken from reference 8. and med sles of alasticity E = 30 s 10' and dymanic
! la:r:ses fgeter DIF = 1.1 (table 4-1) have been used. Aescrding to iigure 3-1 the seminun strain anergy for purely elastia ctructural respease is 3o =1aa 2 a e
= 1 (14,467)2 (0.00) = 3,787 in.-1b 5-3 i
. I i
. i
. .. -.. . . . . . . . .- - . . . . l
i 4 o j , Dssign Basis for Tomado-Generated Missilts j , Josrph M. Farlay Nuctsar Plant i
- Enclosure Attachment 10
- 3C-10F-9-A Page 75 of 82 j Sev. 2 ,
which to lese than E.
- 32.440 in.1b.ee the structural response is
! alaste-plastic. Then according to equaties (3-22) the required ductility i ratie is d E l e 9,4 r ...:M:*een + 0. = >.- J l gimes, escordias to table 4-4 the allewahla duett 11ty rette for a steel
- 2 been under lateral leads is 20. this been een withetend the postulated l
missile impact if me other lease are acting staultanoosely. In case other
- Roads are present as missile impacts and reasia in effect throughout the j structural reopease the required ductility ratie should be evaluated by 2 oggaties (3-24) inetoad of aquattom (3-22).
! I l t i l e ' ! s.4 Miss1Ls PENETRAT1 5 1RER93l WA1 R ! 4 Consider the postulated eccident eseditima of a fuel shippias eask (the ! missile) falling from en everhead erase end possibly damaging the opent feel l pool floor elah (the target) underneath. The aeok le a sylinder with length j L = 17 it, diameter d = 7 ft. and wei,kt U = 2 s 103 lb. (The spent fuel . j peel contains water of depth 5 = 37 ft. If the cask is to drop h = 11 ft j to just hit the water surface the initial valecity is l l ,,=a,e/>t1(,173(11)p>.....ti..c. The Bayaside number is, according to aquetten (5-7), l i
. . .n* 3,. ,1 7 l " . o5.5) o)-3
. 95 a 10 1
Since L/d = 17/7 e 2.43 the drag coefficient is, according to table 5-1 for
; the anos of circular cylinder with amis parallel to flew and with R >.10 1
CD * ***IO i j . The horissatal eross-sectiemal area se \ l Ag = ss*/r = v(7)2f4 , 3,,3 ,,2 , l j them equation. (5-5) givne l , , NA0 , (62.4)(0.gH)Ds.5) 3
= 0.0051 ft-1 .
2 (2 x 10 )
! s-4 l..
1 i j p
,pysi ppgsis for Torntdo-Gensrated Missiles
- Rev. 2 Jos:ph M. Fartsy Nucitar Plint
- j. Enclosure- Attachment 10 1 I Page 76 of 82 '
and equat$on (5-s) 31was i f b . p - D II
- I = 0.010 ft~1 sec
~I
- 2 s 10 I
i The weight density of the cask is s 5 i t U 2 m to 3 j Y, * # L (38.5)(17) = M5.6 lb/f t . . D - 1 . 3 I j Acerrding to equation (5-8) the terminal velocity is ! 4 l { - 1/2 1 { V2* , 8(1~T/I)f* m , l c i j - 1/2 1 i . e (32.17) (1 - 62.4/305.s)/0.0051 = 70.9 ft/ses, i 8 3 j stato N > L, and according to equation ($-2) ,
. 1 i s2 (') * '22 + *-tal. '
h 'esaL (1 - 1st.) -1 l 2a 2 ' < ' 2 I j +V " o
- A (* *l' Y/Ya~1) i j (yo,,3 , f (0.0051)(1t) (0,01)(se s) [,o.17m g , ,,g,y) 2 2
! , 2(0.0030 , l < l l - i + (2s.s>8 + M (.' ""st.4/w5.s - 1) .- l
- 02; 1,02 ,O.
, on . (0..so.) [- l 1 i b i I E-5 i
i
- Dssign Basis for Torn do-Generated Missil::s
! Joseph M. Fartsy Nuclzar Pitnt l gqy ,9,g Enclosure- Attachment 10 2 - Page 77 of 82 4 , the value of 123) should be calculated: i
- 32 0'I
- Y 2 +a bA 0
e (1 - 2at) - 1 /2aI + T,2 4, , 2 = (70.9)2 , ,-2(0.M51)(37) g,41,3) , l +3(ab/y,-11/a ) 5027 + (0.6356)(-4193) = 2152 > 0 71as11y the striktas valecity of the saok en tho' opent fuel peel fleer slab
. is, according to equation (5-4). ,
- -1/2
. V= ,2 1 8) . = (2152)1/2 ,44,4 ,,f,,,
It is interesting to mete that if the opent fuel peal is dry the striking - velocity would be 1/2 .- 1/2 Y= 23(h+5) = 2 (52.17)(11 + 37) = 55.6 ft/sec For missiles of lighter weights, the reduction of striking velocity due to the presence of a liquid would be more pronounced.
' 4 o
h e e' t . o
7.-- i'
- Design Basis for Tornido-Gtnzrtted Missues ;
- Rev. 2 Joseph M. Farisy Nuclair Plant Enclosure- Attachment 10 l- . .
Page 78 of 82 ! APPENDIX F i l REFERDICES AND BIBLIOGRAFET i i F.1 MSi, . i 1. Ests. J. V. , Yeh. C. C. E. , Bertwell. W. , Tornede end Extreas Wind Desian Criteria for Nuclear Power Plante. Topical Report. DC-TOF-3 I l i tavision 3. Sechtel Power Corporaties. August 1974. 2 Russell. C. L. 3esetor Safeguards, MecM111aa. New York.1962. ! 3. F-4-atale of Protective Desian. TM 5-435-1. Needquarters. D.C., Jaly 1MS. l Department of the Army. Washington I ! 4. Norris. C. R., et al.. Stsveteral Desian for Draanic LeaderMcCraw1111 i asek company. Ime., New York New Nk.1959. i *h l 5.* Goldsmith. W., tiIveet, Edward Arme14. Ltd. leaden.1960. . j ! 6. John M. Sigge. Introducties to structural Dreamies. McGraw41111M4 4 pp. 202-244. , }
- 7. Newmark. N. E, and Richart, F. E., Issect Teste of Reinfereed 1
_Cencrete Beamge NDRC Esport No. A-125. A-213 and A-304, 1941-1946. S. A.I.S.C. Steel Cemetructies Manus _1. 7th Edities. American Institute of
. tea 1 .ea.t.u. a. .. T.. .. x., 19,0. !
l2
- 9. Buildian Code Reeutremente for Rainfereed Concrete, ACI Standard 318-71 Emerises Cenerete Eastitute. Detroit. Michigan. 1971. *
- 10. 5. E. Duras. C. P. Sfees, Plastic Eisatan in Beinfereed Ceneret_e_.
ASCE Pres.192 (J. Struct. Div.) a ET 3 Cat.1966. s-
- 11. Tail. C. F., "Bynamic tiedeling of automobile Structures from , Test l Data." j ModelsSveten from Test identificaties Data. The of TibratinaSociety Amerieen Structures - hathematical og N-ical Eastaaers,
- a. T. (1972),pp. 149-177.
- 12. Berris C. 31. and Crede. C. E., Shock and Vibraties Eendbook.
Mestaw-5111 Desk Company 5. Y., IM1.
- 13. Gwaltasy L C., **8*=11e esmeretion and Proteegen in tisht-Wates.
Ceeled Power Reseter Flante 03ML 351C-23, Oak Eidge Watsenal Leberatory. Oak Ridge. Tennasses, for the O s. Ateete asersy Commisoles september 1M S. A. Amirikian. Desian of Protective Structures; Report Ilp-3726 l2 14 Sureau of Tarde and Docks. Departamat of the . Navy August 1950.
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., Dssign Basis for Tornado-Gensrated Missiles
, Joseph M. Farlsy Nuclair Pl:nt
, g4g Enclosure- Attachment 10 g Page 79 of 82 l ,
i 15. Samuely. F. J., and Ramaan. C.-W., Civil Protect'tes. The Architectural i Frees. Landen.1939. t i .
- 16. Fnedamentals ef Protocttwe Deeiga. Repert AT1207811 Army CsTPs af j
Engineers. Offica of the Chief of Engineers,1946. i ) 17. National Defense Research Committee. Effects of Iasset and tupleston, Sammary Technical Raport of Divisiem 2. Telume 1. Washington. D.C. I 18. Industrial Enaineerina study to Establish Safety Desisa criteria for ! Use in Basiasering of Emplosive Facilittu and Operations Wall ! Reesense, a asport submitted to Freceos Engineerlag Braath, A.P.M.E.8. Picatiany Arsenal. Dover. 5. J., April 1963. l
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- 20. White. E. W., and Botafords N. 5. Costatament of Fransents free a
! Runavey Reacter. Empert ERIA-113. Staatsre Basearch Institute, i septasener 15, 1963. ! 21. Hardrock Site Debris lapset Prearan. Phaos 1 Testina. Test Report,
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Physite International Co./Bechtel Cory.. (unpublished). ) ! 21. Emort. L I. Analytical Aspssach to Automob11e Collisions. Paper us. 400016 Automocive Easiseering Coastees. Detroit, Michigan (1968).
- 23. Evey D. L., Ruth. E., and Eirsch, T. J., Feasibility of Liahtweinht cellular Ceeerete for Vehiele crash Cushions. Paper presented at tha
- Amasal Meeting of the Eighway aseserch teard. Washiestem. D.C. (1970).
- 24. Earnhauser. M., streeterst Effects of lasect. Spartas, Baltimore, Maryland. 1960.
2 25. Rouse. B., and Eeus. J. W., Basic Mechanics of Fluide. John Wiley and ! Sea Inc., New York (1953), i 26. ! Kassa.'.E., Sol. 1 91ffereattalsteichunnen Wounasmethoden und L5emm l Worlagsgesellahaft. Becker & Etter Esm.-4es. Leipsig. { ,
- 27. Boeht. E. F., and Ipeen. T. W.. Ballistic Forforaties Dynamies.
J. of Appl. Nachm ics, ASW, Sept. 1983.
- 28. Woumark, W. M., and Waitivsager. J. B., Air Force Desian Manual.
l l AFSWC-TDE-62-134, prepared by the University of 1111aets for l Air Forca Special Weapone Center. Eirtland Air Perce Basa.,N. M., j 1962. i j . .19 10:. . l f ! F-3 F-2
t' l . D: sign Bisis for Tornado-Gtnsrated Missiles } Bev. 1
- Joseph M. Farisy Nucisar Plint i,, Enclosure- Attachment 10 '
age o of 82
- 29. Johansen. K. W.. Yield-Line Formulae For Slabs. Cement & Coacrete j Association, Lentaa (Translation by Paulin M. Ratherg).
I A. Fergumen. P. M. Rainforced Concrete Fundamentals, 3rd Edities, j John Witey 1973.
- 3 1. Bognestad E., Yield-Line Theory For the Ultimate Flexural Stremath cf Retaforced Concrete Slabs ACF Journal 24 No. 7 March 1953.
l
' 32. Wood, R. M. Flestic and Elastic Desian of Siebs and Plates, Ronald Press Co., 1961.
l 33. Timeshenko, S. and Weinewsky-Kriegers, . S., Ti-La-;
. of Plates and Shells, l Mc-Oraw-1111, 1959.
! 34. Cowell, W. L. Dynaste Teste of Concrete Reinforcina Steels. Technical j tapert 1394. U.S. Eses! Civil Engineertag Laboratory,1965. I 35. Watstein. D., Effect of Strainian Rate en the Compressive Streenth and l Elastic Properties of Concrete'. Journal of the American Concrete
- i tastitute, Vol. 24, so. 8. 1953. -
I ! 36. McNeary, D. , Shideler, J. J., Review of Data en Effect 'of Soe'ed in . , Mechanical Testina of Comerate. Sulletia D9, Port 1 sad Coment Associ. stica Research and Dewetopment laboratories. (also reprint, Special 2 Technical Publication No.185. by ASTM,1956). i L ' l 3* Rao, W. R. W., tahrmann, M., Tall L., Effect of Strata Rate on The i Yield Stress Of Structural Steels, Frits laboratory Reprint No. 293, i Lehigh University lastitute of Research, (alse Journal of Materials, j Ve1. 1. No. 1. American Society for Testing and Materials. i March 1966). !30. .astee, J. m. , Sie.s, c. v. , s.d neuma* m. m., in rm .tsa. tion of
- the Load-Deformation Characteristics of Beinforced Concrete Seems_
l Up to the Point of Fathere. Daiversity of Illinois, December 1952, . Reprint July 1959. l
- 39. Desten, D. R., & Dwaanie Ultimate Stranath Sesdy of Simply Supported Tue-Way teinfor d Centrata Slabs, TR 1-789,t.S. Army Engineers Waterways Espartnset Station, Corps of Engineers. Vicksburg, Mississippi July 1947.
l 40. Albrittaa, s. 36, = :: : of Does seinforced and Unreinfereed Coa-j creta Siebs to Statie and Dynaste Leadins, ASCE Nattemal Meeting on
- Structural Engineertag. September 30 - October 04, 1968.
\ j 41. Untreuer, R. E., Behavior and Desian of Deep Structural Members, P art 4. Dynamic Tests of Reinforced Concrete Deep Beans, University j; of Illinois. May 1960. 1 j 42. Corley, W. C., RotatGaani Capacity of R/C Seams. ASCE Proceedings, l . Journal of Structuraa D& *'rd.% October 1966. . . L .. i .
- , - - , n .-. , , --- , .,.,
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i D: sign Basic for Tornado-Gzntrated Missiles > - Joseph M. Fartsy Nuclezr Plant Enclosure. Attachment 10 BC-TOP-94 Page 81 of 82 tov. 1 4 43. Feldman. A., Sissa. C. F.,' tavastinaties of Destatance and Behavior I l ef Reinformed Conerate teams $nbiected to Dyneese Leadina University et 1111aois. September 1956. , 2
- 44. Chelepati. Eennedy E. Wall Probabilistic Assessment of Aircraf_t
. Haserd for Nucisar Power Plants. First International Conference on structural Mechanics in teactor Techselogy nerlin 20-24 september i 1971.
l l 4 l i , e j - 1 1 1
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- Ossyi ma .n 'BasisJossph for Tomido-Gsnzrated Missiles j ,
M. Fsfisy Nucle:r Plint Enclosure Attachment 10 y.2 BIBLIOG W Page 82 of 82 i j
- A.I.S.C. Plastic Desian in Steel. American tastitute of Steel 1,
Construction. N.Y., N.Y., 1959. i . j 2. Seedle Lyna 5.. Flestic Deeian of Steel Frames John Wiley & Some, j Inc., 1958. i
- 3. couns'ntary of Flestic Design in Steel. A.S. E. Manual of Engineering Practice. No. 41, 1961.
i 4. Desian for Pipe Break Effects. DN-707-2. Sechtel Corp., August 1972. I i 5. Desian of structures to Resist the Effects of Atomic Wessons. The. ! EM 1110-345-414 to 421. Massachusetts Isetitute of feeheelegy for the l Office of chief of Engineers. U.S. Army. Usshington, D.C.,1957. . i i 6. Eerser. D. J.. Metals Basineerina Desian. Americes Society of unchen- . ) teal Engineers Bandbook, McGraw-Eill Wow York 1953. t 8 } 7. fohansen, R. W. , "Fladeformler Formelsealing". Polytekaiah Forenias.
- 8 j Copenhagen. 2nd Edition. 1954. ,
- 8. Johansen. E. W. , "Pladefotaler". Polyteknish Ferening Cepeahagen, , .
2nd Edition. 1949. ' Lorenz Rans. Gilbert Associates. Zac., Aircraft tapact Desian, j
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Power Engineering. Nov.1970. . i i
- 10. Nevaark. N. M., et al. Notes os Blast Resistant Desise. Bechtel 5 Associates Symposium. New York.1MB (vapublinham).
- 11. Rinder. R., Saffisar L. W. , Uschte11. S. , Cohen. E. , Debbs. N. .
Manual for Desian of Protective Structuree Used in Exposive Proe-4 j . l essina and Storene Facilities TR3505. Pisatiamy Arsenal. Dover. I New Jersey /Asman and whatney. New York New Yest. November 1968.
$3 l ,e Flow. BCRL-7322
! 12 Wilkins, M. L., Calculottom of Elsette-Piset - lawrence Radiation Laboratory Livermore. Cahiferais. Jesuary 24 1 ' . j 1949. Rev 1. l i .
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