ML18117A371
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.....----......:... REACT ION P(t}lai!J Nuclear 1MI Unit-1 Update-1 7/82 p.5A.FIG-l Total Reaction vs Time Curve Fig.5A-l 1_WINGS&ENGINES J\-ATTACHED h\\VWINGS&ENGINES ,JI"" DETACHED j\I\\*.....'" V-J V11 16 1.1 12)(.=101&1 U I¥2 I t-U C A.6!*2 o o.01.12.21.2..21.32.36...0 TIME-SlCONDS B:imNuclea, 1MI Unit-1 Update-1 7/82 p.5A.FIG-2 Load Time Curve for 720 Aircraft at 200 Knots Fig.5A-2
- ']J II ,*T'IIr 1 1\11 IIWM++, I:l I 11 l n-....-100 1.6 1.2*o1.0&&.a c ouz0.1 a)(c 2 0.6so 30 20 FREQUENCY (CP$)10 532 0.2 0.01 0.02 0.030.05 0.1 PERIOD (SECONDS)0.2 0.30.5 1.0 ra:im Nuclear 1MI Unit-'Update-, 7/82 p.5A.FIG-3 Maximum Dynamic Load Factor vs Period or Frequency of a One-Degree-Freedom System under the Impact of Boeing 720 Fig.5A-3 cr Z...j ,II ,...a:: C II'it[a:iEl Nuclear TMI Unit-1 Spherical Cap under a Ring Load u-c"0*0-"-'"IIII II a::...*Update-1 7/82 p.5A.FIG-4 Fig.5A-4 I I I...I u.DC U DCZ w Q C)DC...;:)-I CD ex DC c-0 Q.--...u.c V)5...Q.U WDC A.;:)!w u..DC 0 Q.-I wGIl: 2DC 0...Z0-ta::il!I Nuclear TMI Unit-l Update-1 7/82 p.5A.FIG-5 Spacial and Time Distribution of Load on Shell Fig.5A-5
_N-N"" ..r 1MI Unit-l**;1ft*62**o Update-1 7/82 p.5A.FIG-6 Grid for Dynamic Finite Element Analysis of Aircraft Impingement on Dome Fig.SA-& )0.1 SECONDS 0.2 0.3 I I I" NOTE: eKSI CORRESPONf)5 , TO A LO D OF 5800 KIPS20)(E.1611T Of TII£AIR-VERTICAL OFT"EIAPEX (BASED.lKS')..0.16 SEC'., CASE@TIt.1E Of LOAD APPLICATI$N 0.4 TIME INNIN6 OF IMP.I t.*0 tJ.: 0.16 SEC 0.2'*0.16 SEC 0.8 I , 1.0 I\!V-4 , , t.=0 z I , ta.IIC'" 0 I t.*00.6 TIC SOLUTION , 1--,'---, C"C Q......," C'D CO I N....U1:J>I......Vl>."a I-J""C:)-1m:::a m3::::ao-=;: c:::a::;':::1 Z....n_.en"...C....m I..-1:.......nn-....:1-I:-a*II om..:::a:I en m....:::a m.... c:::a mC n 0!!.:I=m m 0....-0'.":::a cP' I/)£FL.C_..()<:)...SIRE S5- (-) I2iE Nuclear TMI Unit-1 Update-1 7/82 p.5A.FIG-8 Deflections and Stresses for Aircraft Impingement for Time=0.16 Seconds"Constant Deceleration Fig.5A-8 350.....----......----.....----.....----....0.4 0.3\0.2 TIME-SECONDS 0.1 C-JJ9C---...... .......----......---------........o 250 \\100 300 a a"200.....------+---;.---+----""'--+------1 V)..........w W LL.Ito-g 150 ........--+-----......-----I\\Iai!J Nuclear 1MI Unit-l Update-1 7/82 p.5A.FIG-9 Velocity Diagram for 720 Aircraft at 200 Knots Impact Speed with Wings and Engfnes Detached Fig.5A-9 350.... ....---.......... ---.....300 0.4 G.!........... _-0.2 TIME-SECONDS 0.1 0.....----....----......----.....---........o 250 C-1l9C----.....a", z 0 u 200 w\w , W&L I\>-U 150 0-oJ\w>\\100\\\50[[il!]Nuclear TMI Unit-1 Update-1 7/82 p.5A.FIG-IO Velocity Diagram for 720 Aircraft at 200 Knots Impact Speed with Wings and Engines Attached Fig.5A-l 0 IfJO 110 10 60 AIRCRAFT WEIGHT BREAKDOWN FUSELAGE 51,000 La EMPENNAGE 5,680 NOSE GEAR 700 , MAIN GEAR 5,380 INB.ENG.10,800 OUTB.ENG.10,300 WING STR.29,700 S 113,560 LB 0 PASS.&BAGS 13,000 8 CARGO 10,000--FUEL 63,440...---G.W**200,000 LB4 w c:L. DI5l£70 co-J LOSS f OU R POll.ION I OFW 1J(j z 0i=:::>co a:...U)is...2 is wI DISTANCE-FEET o 200 4{)()60D 800 F.5.IfJOO IZOI'"10 B:iEl Nuclea, TMI Unit-1 Update-1 7/82 p.5A.FIG-I1 720 Aircraft Mass 0 istribution Fig.5A-11 -7//-V-7---------,",,-IIIIP a ,..." CRUSHING LOAD IN POUNDS)(10'[aj[I Nuclear TMI Unit-1 Update-1 7/82 p.5A.FIG-12 Boeing 720 Fuselage Buckling (Crushing) Load Fig.5A-12 r=0.0" MAXIMUM DISPLACEMENT OCCURS AT CENTER OF DOME AT TIME t=.2 SEC.41)w J: U!IZ WW U-'Q.Q-'UOl: W>-2.0--r..---&...L.---J o 0.1 0.2 TIME-SECONDS 0.3lm1!I Nuclear 1MI Unit-1 Update-1 7/82 p.5A.FIG-13 Time Variation of Shell Vertical Displacements with Wings and Engines Detached Fig.5A-13 ,...-----------------------------. MAXIMUM DISPLACEMENT OCCURS AT CENTER OF DOME AT TIME t=.2 SEC.,=0.0"-1.2 ....-4-1.6 I/)w];: U ZI...z ww u-0.8-oJ a..I/)Q-oJU...al: W>-2.0 o 0.1 0.2 TIME-SECONDS 0.3[[iI!]Nuclear TMI Unit-1 Update-1 7/82 Time Variation of Shell Vertical 0 isplacements with Wings and Engines Attached p.5A.FIG-14 Fig.5A-14 MAXIMUM AND MINIMUM WINGS&ENGINES ASSUMED PRINCIPAL STRESSES TO BE DETACHED FROM A T THE TOP AND BOTTOM FUSELAGE SURFACES OF THE DOME 2;;;W I'"'" 0 W I¥...'" W I¥A.i-2...UA.CJ...w'"-6 w'"'" W I¥...'" Q-I w z CD MAXIMUM COMPRESSIVE STRESS 2 0 IS 9372 PSt u-10 0 0.1 0.2 0.3TIME-SECONDS 1MI Unit-1 Update-1 7/82 p.5A.FIG-I5 Time Variation of Shell Surface Stresses Aircraft with Wings and Engines Detached Fig.5A-15 2 0." 0.3 BOTTOM SURFACE MAXIMUM COMPRESSIVE STRESS IS 9352 PSI,=o*0.2 TIM!-SECONDS 0.1 MAXIMUM AND MINIMUM PRINCIPAL STRESSES AT THE TOP AND BOTTOM SURFACES OF THE DOME-10.....------..&.------- .....------.....--------'o v;I O..... V)V)w a:V)w-2..UQ.!-..ow::::)o-6 w a:V)o w-8 co 2 o U OBi!)Nuclea, TMI Unit-1 Update-1 7/82 p.5A.FIG-16 Time Variation of Shells Surface Stresses Aircraft with Wings and Engines Attached Fig.5A-l& FOURlEi SERIES=.Q7955*,1575 COS,+.1558 COS 2'*.1"6 COS 3'+*\33 COS'"*.1208 COS 58+1058 COS 6'*.08CU COS 71+.0722 COS 8'*.0551 COS 98&o* ..r 1MI Unit-1 Update-1 7/82 p.5A.FIG-I7 Pressure Distribution for Aircraft Impact Fig.5A-17 020"1 r Update-1 7/82 lail!J Nuclea, TMI Unit-1.75" 1129 FT*K/FT.\1'+150-<<9 140-0.-A 130-120-<0110-100-t-W 90-w u.*80to-70>W.-oJ 60 w SO-40 30 20 10 0 MERIDIONAL MOMENTS.SHEARS DEFLECTIONS Aircraft Impact at Girder to Dome Transition p.SA.FIG-IS Fig.5A-18 Update-1 7/82 TMI Unit-1.....-1.04" 326 K/FT 150_--+-...... 998 FT-K/FT 17.5 x 10 6 LB (TOT AL LOAD)140-so-130-30-40-10-20-100-110-120-1616 FT-K/FT...ww u.*z o I->60-LIJ 0-MERIDIONAL MOMENTS SHEARS DEFLECTIONS Aircraft Impact at Spring Line p.5A.FIG-19 Fig.5A-19 Update-1 7/82 1.14" p.5A.FIG-20" , ,\\\, , I///,/-'"" ELEV.149'-1" TMI Unit-1 Radial Deflection Impact at Spring Line Fig.5A-20 .127"l r I t Update-1 7/82[ffi[1 Nuclear TMI Unit-1......-1.00"-177 K/FT 184 K/FT-226 K/FT 14--1297 FT-K/FT 1658 FT-K/FT 150-140-130-120-110-100-t-90-w w u.*80-z 0 t-70-<>w 60-...J W 50-40-17.5 x 106 LB 30-(TOT AL LOAD)20-10-0-MERIDIONAL MOMENTS SHEARS DEFLECTIONS Aircraft Impact at Grade p.5A.FIG-21 Fig.5A-21 z y/__(a)GEOMETRY (b)51 X FORCE COMPON ENTS AT NODAL POINT tai!I Nuclear 1MI Unit-1 Update-1 7/82 p.5A.FIG-22 Rectangular Finite Element Fig.5A-22 Update-1 7/82 Heat Exchanger Vault Moment Diagram For the Roof Slab[ffil!l Nuclear 1MI Unit-1 thickness: 6-:'0 N--MOMENT ENVELOPE impact positio/IS p n along secflon A-A F,,'cr,.';/c o/ Q.5 oircrorf'2"*.......-.--- 60'*6..-"--....-t b.5 momenTS Secn'tn?AAfo*o..,HOn?I?,.,f 2,800 2,'00 2,40D 2.,200 2,000/,800'S"'ao/'400""/,].00-/, roo\J" 800 ,"00.\'::: " 400t:: 200200400 i)ftJoo ctJ 800 1,000 1,200/,'100/'fD OO/,800 2,000 p.5A.FIG-23 Fig.5A-23 TMI UFSAR
Figures 5A-24 through 5A-25 Deleted v p.5A.FIG-26 BimNuclear TMI Unit-1 Critical Aircraft Impact-Direction 1 Update-1 7/82 Fig.5A-26 IMPACT DIRECTION<D c==::C>r-----A--.............. _SEE TEXT PG.SA-18-,f--I-*I*I'*. ,--,-....'.la:im Nuclear TMI Unit-1 Update-1 7/82 p.5A.FIG-27 Concrete Cover to Protect Against Aircraft Impact Fig.5A-27
,.--.-.-"------t'o...t-l.--..-.--.----...---II fIIIIIIII I I I I I If I TYR I I I III I I I III I 8iI!l Nuclear 1MI Unit-1 Update-1 7/82-p.5A.FIG-28 Detail of Anchor Block Fig.5A-28 IMPACT OlQECTION A A (a.)lb)IASSUMEC N.A..0]!]Nuclear TMI Unit-1 Update-1 7/82 p.5A.FIG-29 Prestress Stresses after Nine Tendons Fail Fig.5A-29 8 z ou uJ ex 6u<Q...'t'{)ta:im Nuclear 1MI Unit-1 Update-1 7/82 p.5A.FIG-30 Critical Aircraft Impact-Directions 2 and 3 Fig.5A-30 p.5A.FIG-31 ta:iZ!l Nuclear TMI Unit-1 Equal Spacing of Roof Tendons Update-1 7/82 Fig.5A-31 UPdate-J 7/82 Do,.,.r endons-------
BUTTRESS ir IMPACTDIRECTION 0---------------------------------- ---.....------......----.....-------------------------------.....---------------------_..----- ..r TMI Unit-'Update-, 7/82 Minimum Spacing of Hoop Tendons p.5A.FIG-33 Fig.5A-33 ELEVATION DUE TO A.IRCRAF"T) IMPACT DU&TO L.OSS OF HOOP PRESTRESS DuE To VEsctlCAl PfiEST2ESS ..DUE TO HOOP PRESTRESS DUE TO PRESTRESS*E:LEVATION DUE TO HOOP \DUE.TO ArRCRAFT TO A.L.OF'H P F>QE&TRESS Iai!l Nuclear 1MI Unit-1 Update-1 7/82 Comparison of Prestress Loading p.5A.FIG-34 Fig.5A-34 I I I I I 1 ir, I I Ie!'ww01 Ii..1<1(10 w/ 1 0 1 051UI V Ie Ij 1&1)1 0 C).......{Ie!f)"" ISV tt'"\0.4 0.3 0.2 TIME*SECONDS 0.1 cs/r r ,'\S'(j....,-, I r;f-, I::;.I!:: , I 1\./U':/0.,:;, , ,.u,!\..L"'"" 4 , I*,\, J I:\-.I/..I\, I ,\I\, , f\,/, ,"---" I , , , o o CALCULATED REMOTE"G" LEVEL 90 80 70 C)60..J w U w 0 w 50 C)<I(...J W&I)40::::>u.w030 w20 10 0.4 0.3 0.2 TIME*SECONDS 0.1 RIGID STRUCTUREo o 20 15'0 2)(co.J e!'0 100..J Z 2UW 01: 5 SEE TABLE 5A-6, REACTION LOAD CALCULATIONS WITH WINGS&ENGINES DETACHED la:im Nuclea, TMI Unit-1 Update-1 7/82 Reaction Load and Fuselage Decel.(Calculated for 720)p.5A.FIG-35 Fig.5A-35 f/\I\\\ V , 1\0.-0.3 0.2 TIME.SECONDS 0.1.......I V l\/I.1/I'C.119C (TEST)!I.I r I , , j I ,./\I.I**" lII,I*1;(', I l'.1\,I/\\.f I A20 (IALCULj TED)*'......",I'"., o o 80 90 CALCULATED REMOTE"G" LEVEL 70 d I 60.J w u w Q SO w C).J W.,...0::J&L W t-O 30W 0: 20 10 0." 0.3 0.2 TIME.SECONDS 0.1 RIGID STRUCTURE ,---.---.R---+-..-.o o 20-0 15 0-)(a>>.J g Q10 0.J Z 0 t=uW 0: 5 SEE TABLE SA.7, REACTION LOAD CALCULATIONS WITH WINGS AND ENGINES ATTACHED ..r TMI Unit-1 Update-1 7/82 Reaction Load and Fuselage Decel.(Calculated for 720)Fig.5A-36 p.5A.FIG-36 2---TOP SURFACE STRESS----BOTTOM SURFACE STRESS MAXIMUM COMPRESSIVE STRESS:;5268 PSI r HOOP STRESS/",,---,_}I (BOTTOM)/"'....... .......---MERIDIONAL STRESS..... TOP BOTTOM-8-2-6 a UJ z eno u In Q..I 0w a::...In W a:: Q....,...uQ..o...wa In In W a::...In-10 o 0.1 0.2 TIME-SECONDS 0.3 0.4 ..r 1MI Unit-l Update-1 7/82 p.5A.FIG-37 Hoop and Meridional Stresses at 36 Inches from the Edge of the Load Area Fig.5A-37 r=115.2"1\tL'\\\\1 MAXIMUM AVERAGE SHEAR STRESS ACROSS SECTION=482 PSI SHEAR ATr=145.2-=354 PSI UL T1MATE SHEAR STRESS FROM CHAPTER 26 OF ACI 318=\I=+0.3 fpc v=3.5x 10.1+0.3.1600=128 PSI)354 PSI OK la]!]Nuclear TMI Unit-1 Update-1 7/82 p.5A.FIG-38 Average Shear Stress in the Dome at the Time t=0.20 Seconds, Wing and Engines Remain Atuched to FUHIaga Fig.5A-38 r=115.2"I'" t:;L'\\a::\\/II MAXIMUM AVERAGE SHEAR STRESS ACROSS Sf CTION=4&2SHEAR AT ,=U5.2"=354 PSI ULTIMATE SHEAR STRESS FROM CHAPTER 26 OF ACI 31S=v=3.5K +0.3 fpc v=3.5*70.7+0.3.1600=728 PSI)354 PSI OK 0i!jNuclear TMI Unit-l Update-1 7/82 p.5A.FIG-39 Average Shear Stress in the Dome at the Time t=0.20 Seconds, Wing and Engines Detached from Fuselage Fig.5A-39 .J uI Q o L Iai!J Nuclear TMI Unit-1 Update-1 7/82 p.5A.FIG-40 FEM Model-Radial Stresses Due to Prestress and Aircraft Fig.5A-40 /','"l'V 0\)Ci 0 o Update-1 7/82 rai!l Nuclear 1MI Unit-l o'" Q o 00 I 0'0 (),0 0 L -_..---.--rta* r---------------------DOME SECT'ON p.5A.FIG-41 Radial Stresses Due to Prestress and Aircraft Impact Fig.5A-41 RADIAL TENSION ZONES HOOP AND MERIDIONAL COMPRESSION ZONE-_ -- --&TENDON G..T EN DON ci<'0-'-lmmNuclear 1MI Unit-1 Update-1 7/82 p.5A.FIG-42 Zones in Compression or Tension Due to Prestress of Aircraft Impact Fig.5A-42}}