ML20049J548

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Forwards Supplemental Matl for Review of Model T-2 Shipping Container
ML20049J548
Person / Time
Site: 07105607
Issue date: 02/16/1982
From: Moser R
ENERGY, DEPT. OF
To: Macdonald C
NRC OFFICE OF NUCLEAR MATERIAL SAFETY & SAFEGUARDS (NMSS)
References
20320, NUDOCS 8203180338
Download: ML20049J548 (40)
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9-y FEB 161982 2 A P h y' s 12 ~ p /, f[ 95 r Mr. Charles E. MacDonald, Chief q Transportation Certification Branch Division of Fael Cycle and Material Safety, NMSS Cu A m U. S. Nucleat Regulatory Commission S Washington, D.C. 20555 g, O.)rM 6 f

Dear Mr. MacDonald:

74C .ff SUPPLEMENTAL MATERIAL FOR TIIE REVIEW OF Tile MODEL T-2 Sill F No 3t$jeg5g [5

SUBJECT:

y gp_.,g ' CONTAINER PACKAGE

Reference:

Letter, Moser to MacDonald, dated February 11, 1982 6 cc We recently provided you with the information in response to the comments which resulted from the Nuclear Regulatory Commission (NRC) review of the Model T-2 Shipping Container package. This was submitted with the referenced letter. As we indicated, additional information to supplement several of the responses was to be provided later. This information is availabic and is enclosed. This should address the remaining comments, and hopefully, will permit you to complete the review of the Model T-2 Shipping Container. If there are any questions, contact R. I. Elder, of my staff, on FTS 972-2269. a Sincerely, R. M. Moser, Director Operational and Environmental Safety Division

Enclosure:

Supplemental Information for Responses to NRC Comments for the Model T-2 Shipping Container Package 20320 EESS*oWQjg, PQ =

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4 Supplemental Informat' ion for Responses to NRC Consnents for the Model T-2 Shipping i

Container Package Enclosed is information to respond further to Structural Consnents No. 1, 3, 4, 5, 6, and for the Shielding Consnent. There is also additional infonnation on the thermal stresses 1. the lead and stainless steel liner 9 which quantifies the discussion for Structural Consnent No. 3. Ij 3 i i I b l 1 I I i 1 l

RESPONSE TO NRC COMMENTS Structural Item 1 Comment: "The bending stress of the horizontal lifting lug will exceed its yield strength if the lifting force is applied at the mid-span of the lug rather than being applied uniformly as assumed in the analyses. Justify the assumption that the lifting force will be uniformly distributed." Response: Inspection.of the horizontal lifting lugs for the T-2 casks by Argonne National Laboratory-West (ANL-W) in Idaho falls revealed that a reinforcing member was missing. After consultation with the Chicago Operations Office of DOE, ANL-W has elected to reinforce the lifting lugs. A description of this reinforcement will be the proper response'to this comment. Item 3 Comment: " Thermal stresses induced by the differential thermal expansion of the lead and stainless steel of the cask should be evaluated." Response: From Section 3.4.5.3 of the T-2 SARP, page 3-37: "While the lead has a significantly higher coefficient of expansion than either the shell or liner, no failure is anticipated. The lead was poured at temperatures greater than 612*F and then allowed to cool. Since normal transport temperatures for the lead will not exceed 300*F, stresses should not exceed those already experienced by the shell and liner." Item 4: Comment: " Consideration of brittle fracture for the shipping case is inadequate. Show that the shipping case provides [ impact.and thermal protection over the range of initial thermal conditions, including: -20"F ambient, no solar heating, and no internal heat." Response: An accurate brittle fracture analysis of the T-2 shipping case would be a highly complex undertaking. It is doubtful if a conclusive analysis is possible. Therefore, a representatiye drop test is the only conclusive solution available at this time. Unfortunately, the drop tests with the T-2 model were completed in 1975, about two years before NRC Regulatory l t e

1 Guide 7.,8 was published "for comment". However, even if the model had been dropped to simulate the -20*F conditions indicated in the guide, tha results would not have been conclusive. This judgement is made because the wall thickness of the shipping case model was less than the actual case wall thickness, and the nil ductility transition temperature (NDTT) of metal decreases with thickness. Therefore, the only completely satisfactory drop test would be a destructive test of the actual shipping case (or a close proximity thereof). This would be an expensive undertaking that., in our view, is unjustified unless reasonable doubt exists that the case is safe from massive brittle fracture at -20*F. Dupont selected the shipping case shell metal with its NDTT in mind. The NDTT of A516 Grade 70 Steel is -40*F according to reference 1 (see copy attached). In the more recent reference 2, (also attached), the NDTT of A516-70 steel was found even lower, from -125'F to -300*F, for a one-inch specimen. Presumably a 3/8" specimen comparable to the T-2 shipping case would have a NDTT still lower. In short, the NDTT of the shipping case is well below -20*F. In our view, this property, combined with the successful demonstration by model drop tests of the cushioning concept of the shipping case ~ design, constitutes a priori evidence of the excellent protection afforded the T-2 cask under -20*F accident test conditions. Item 5 Comment: "The cask is shown in Figure 1.4 (SAR) to be made of a carbon steel body welded to a stainless steel cap. Discuss the weld strength as well as the procedures for making welded joints between carbon steel and stainless steel." Response: As stated on page 9-11 of the T-2 SARP, "The head material is 304 SST to' eliminate the need for heat treating the welds mad'e after lead pour." From the. records of Ionics, Incorporated, copies of the analysis reports of the 16" SS pipe cap and the 309 filler metal are attached. A copy of the welding procedure l (refer'ence 3) used by Ionics, Inc., for welding carbon steel to stainlesa steel is also attached. Note that l the strength of the filler (88.5 ksi tensile) is greater l 1 i I

than the s'trength of the SS cap (86.8 ksi tensile). The weld was radiographed, and contact prints of the ~ radiographic film have been eent to R. I. Elder of the Chicago Operations Office of DOE. Item 6 Comment: "Show that scaling, laws have been satisfied with regard to material properties and geometry for the scale model teats. The demonstration should include dimensional analysis to establish criteria for dimensions and material properules of scale models; compare the criteria established with the scale models used to show adequacy." Response: The dimensional analysis used by DuPont to determine if a scale model drep test would be adequate to satisfy accident test conditios for the T-2 cask, is given in reference 4 (see attached). From page A12 in the reference, the requirements for successful model testing are geometric similarity, the same materials, and the same velocity, provided the stress-strain. relation of the materials are independent of strain rate. As given on page A15, the model strains will approximate those of the prototype if a length scale factor of 10 or less is used. As shown on DuPont Drwings W 700473 and W 700506 ~ together with Details 149018, 149054, 149056 and 149017 (see T-2 SARP), the materials used in fabricating the model were either identical, equivalent, or less strong than the T-2 cask and container materials. The model was 0.278 scale. Therefore, the drop tests as conducted were a valid representation of the accident conditions for the full size T-2 cask and container package. Shielding Comment: "A check on the source of fission products (total photons /sec used in ANISN) indicates a 30,000 curie content for the shielding analysis. The application requests $7,000 curies of mixed fission products be approved. Please, resolve this discrepancy." Response: As stated on page 5-1 of the T-2 SARP,.the shielding calculations were based on 57,000 c:rdes of mixed fission products after cooling for 150 days. The comment indicates that total activity (in curies) p t

corresponds directly to total photon source /sec. This is incorrect. Total activity is the number of decays per unit of time ofallprimargdecaysofmotherisotopes. These decays emitof, B, B and isomeric transition Y's. The residual daughter isotopes are created in excited states that stabilize by / emission. Man B, and B+ decays do not emit any / rays;y primary 4, others emit several / rays. 57,000 curies is the total primary activity of materials permissible in the T-2 cask. This does not imply that 57,000 curies of photon source will be present. To illustrate, the attached table shows the total activity and the total secondary gammas (as a function of time sfter shutdown) for-a typical PWR fuel pin irradiated for 20,000 hours at 100 watts /cc fission power. The cooling time of 150 days in the T-2 cask analysis corresponds to 3600 hours in the table. Note that the total gamma source at 3000 hours is about 39% of the total activity. Since 30,000 curies of photons is 53% of the 57,000 curies of total activity in the T-2 cask analysis, this comparison gives no reason to question the analysis. In our view, the shielding evaluation give'n in Chapter 5.0.of the T-2 cask SARP is correct as presented. ~ /prc l I

References 1. Lee A. James, " Technical Note - Fracture Toughness of A516 Grade 60 Steel," Welding Journal, volume 51, October 1972, page 506-S. 2. " Report Summaries and Conclusions - A515, A-516 Steel", Structual Alloys Handbook by Battelle's Columbus Laboratory, 1981 Edition, Volume 1.

GIC-3959, Rev.

3, "GMAW, GTAW, SMAW of 3. Welding Specification Carbon Steel to Stainless Steel," Ionics, Inc., Bridgeville Plant, August 6, 1973. 4. H. G. Clarke, Jr., and M. M. Reddi, " Structural Integrity of Shipping Containers for Radioactive Materials. Part I. Study of Transport Operations and' Container Construction," (NYO-9859), Appendix A, " Feasibility of Applying Model Theory to Simulate Impact Damage of Shipping Containers," The Franklin Institute Laboratories for Research and Development, July 1962, Contract AT(30-1)-2539, (I-A2412-1). s

n I,. ~ L Teclnical Note-J -racture Toug1 ness of A516 Grade 60 S eel

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5 s I ll BY LEE A. JAMES 3 pi II 4.!, ~! Introduction conditions. Because of a particular tained under semi dynamic corg. l(', t structural application, the applied ditions at several temperatures ASTM A516 grade 60 steel is fre-strain rates in this study were ap. The tensile specimens (0.175 i quently utilized for pressure vessels proximately three orders of mag-diam.,1.00 in. gage length) were and other structures intended for nitude higher than those convention-tested in a standard testing ma- [ ] moderate or lower temperature serv-ally utilized. The results may, how-chine. The crosshead speed et ice. In spite of this relatively com-ever, be applied to other loading con. 2 in./ min resulted in a strain rate = mon usage, fracture toughness ditions through the use of a tempera. 3.33 x 10-2 sec-'. g ((

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.d values have not appeared in the lit-ture strain rete parameter. The Nil-Ductility-Transition (NDT) I j! erature for this material. This note temperature was determined per I describes such a characterization ob-Experimental P.ocedure ASTM specification E208. Type p3 -l tained under semi-dynamic loading specimens were employed. All specimens used in this study Fracture toughness tests were con. } were obtained from a 1 m. thick ducted using 1.in. Compact Tension L A. JAMES is Senior Research Engi. plate of A516 grade 60 steel. In Specimens per ASTM E399. With neer Han/ord Engineering Development order to evaluate the validity of the I laboratory. Westinghouse Hanford Co., fracture toughness tests, the yield the exception of the applied loading I l Richland Washinpron. behavior of the material was ob. rate, all specimen preparatio.i. test-h} - l 1 itMPtR ATutt. 'C -tso --na) -50 o i i i i j ILMP(R Af uRE, 'l 7 -ED -2CD -100 0 g-s- g-y- i NOTI. TEMPER ATURE SC At15 [f.'CI APPtY ENLY 10 - 80 IHL SPIClllC SIR AIN Ratt !.3.33:10-iset-I N = k 3 100 f? i 2 i l '. y 80 t; [ g f a i G a 9 80 ~ - so a b E $ 40 - O A51M A516 ca AD160 Sitit i : 333:10-2 g,c-13 ~ k B 4 set l A A51M A316 cR ADE 70 5Till i.5:10 o d M O Ae5< STIIt (VARIOuS 51 RAIN Raft 5) I ,( e 1 0 430 enc 32D

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Fig 1 "~ld strength behavior of A516 grade 60 steel l cornpaved with that of two sirnitar steels 0 l 506 sl OCTOBER 1972 h-----_________

a 1 ing cnd cnsfysis conf:rmed to this cv:r o wide teng] cf IImperaturcs AcAnowledgement i specificction. Specimens were .and strain rates. test:d on a testmg machine pro.' The NDT temperature was found to This technical note is based on work per. 8tamm:d for stroke control' Stroke be -40 F. Shoemaker and Rolfe8 '0'med under united states Atomic Energy rat.;s were selected to give approx-have shown that for steels of this Commission contract AT(45-1)-2170 with "ntdy the desired semi-dynamic class, the NDT temperature appears the Westinghouse Hanford Company, a str in r:te, and consequently, de-to be the highest temperature at subsidiary of Westinghouse Electric Cor. i. pending upor the temperature, the which a valid fracture toughness can crok] tctis ranged between 24 and be obtained in 1 in. plate under dy-l 4 namic conditions (i

  • 20 sec-').

240 in./ min for the series of tests. The fracture toughness results ob-A'/"'88 } The defsnition of strain rate used is lained are given in Fig. 2. Values for j j one for o point on the elastic plastic A516 grade 702 and ABS-C8 steels 1 t in ra r R$t sen t a erea s bound:ry cs st,ggested by Irwin s are included, and again, com-2 've. parisons should be made using the Journal of Eng/ncering for I 2wer, Tran'. s ASME. Series A. Vol 86,No.4,pp.444 parameter T In(A/i). Except where 450. 1964. i tE indicated otherwise, all values re- ' 2. Succop, L. N., Pense. A. W., and ported in Fig. 2 for all three steels Stout, D. R., "The Effect of. Warm Over-j vvh:rs: e vi. = yield strength for that are " valid" per ASTM E399. The two stressing on Pressure Vessel Steel Prop-i i t;mpetiture and strain rate tests on ASIG grade 60 at -100 F '"'es? Welding Journal. Research Suppt, 1: time of loadmg failed to meet the criterion B 2 2.5 V l. 49. No. 8, pp. 354s-364s. 1970. i E = modulus of elasticity (K a /a,. )2, where B = hoema specimen ..T S S,, D n m c Low-em era thickness. The specimen fracture R;sults cnd Discussion ture Crack Toughness Performance of faces were flat" and devo,d of any i Thz yi3ld strength behavior is

    • necking" or shear lips. In addition, Seven Structurat S tects," Engineering rf, cry,e Mechanics, Vol. 2. No. 4, pp.

given in Fig.1. The results for two the load displacement test records 319 339,1971. similar steels, A516 grade 702 and were approximately as linear as 4 Dennet. P. E., and Shiciair, G. M., ABS C', tre included for com. those for **valed" tests conducted at "T-arameter Representation of low-Tem-parison. Since the strain rates are lower temperatures. Therefore, al. perature Yield Dehavior of Body.Contered Mf;t ent, comparison should be though they are technically not vahd, Cubiy. Transition M e t a ls.*' Journat of mfde on the basis of the parameter the' author feels that the values 888'# I"9 "'#'#"9 I'8"8-ASMf Si'S I T In(A/i), where T = absolute tem. shown are nevertheless useful for D, o 89 No Derature, and A = 108 sec '. This structural analysis purposes. An adde. ,, HT and oernaker. A. K. aartmeter has been shown to cor-tional test, conducted at -50 F at a = .Tracture Toughness of Structural Steels elate the low temperature yield

  • and 3.4 x 10-2 sec-' was clearly not A/j" Journal of - Basic Engineering.

as a Function of the Rate Parameter T in r:cture toughnessS behavior of body-valid, and no values are reported for Trans ASME. Series D, Vol. 89. No.1 ent: red cubic transition materials this test. pp.8G-92,1967. PARAMDl4 In , 'K e

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i i i i mo em 6e no 10.to0 PARAMfMR t ln, '4 fig 2-fracture roughness results for the same steels as in fig 1 I WELDING R E S E A RCH SUPPL E M E NT l 507-s I

AND CONCLUSIONS 4 516 STEEL WELDING MISCELLANEOUS o The fracture characteristics cf Delta specimens of The effects of explosive forming (to a dome shape) on A-517-70 material were determined at Lafayette College. the tensus and impact properties of 1/2 inch thick ASTM These specimens were produced lip welding three seg-A-515 steel were determined at the University of Don-. ments into a triangular shaped specimen which was then ver. Control specimens of similar mat

  • rial were cold
  • e supported at thua paints and loaded in the center. It rolled in two directionn to obtain the same strain levels was abows that the E-7018 electrode produced satisfac-as from the explosive operation. It was shown that tory welds in the 1 inch thick material since all fauvres material explosive formed (both free-formed and die occurred in the plate with none in the weld metal or in formed) to a strain level of 0.35 perent exhibited a the heat affected aone. It was also shown that weld-yield strength increase 10% greater than that of cold ment composites of A-515, A-537 and A-517 steels were rolled material at the same strain level. It was also incapable of performance better than that of the welded shown that explosive formed material subjected to a A-515 steel alone (7),

stress relief treatment gave tenaue strength values that exceeded the ASTM specifications whereas stress re-lieved cold rolled material did not (1). An experirnental continuous strand-cast process has en eve et rporaum and be been Fusion welded specimens of 1/2, 3/4 and 1 inch thick used for the production of A-516 steel. Material was ASTM A-201 Grade A steel plate were tested at Con- ~!

  • I valr. R was shown that weld efficiencies of 100% were Per mMe aM subepedy rM a

obtained for all thicknesses of plate. It was also shown a CUM ran a up to 15 to 1. R was skwn M that all weld joints, both free and guided bend, were em ca c mPosine was ednmdy unUorm M capable of being bent thru 180 degrees without faDure along the entire 100 feet strand and also within the cross II )* section. Impact and tensile properties snet the speci-fication requirements with the exception of elongation values for material rolled at a reduction ratio of 2 to 1 (2). Longitudinally welded plates of 1 inch thick ASTM Fracture toughness tests were conducted on 1 inch thick A-212B steel were tested at the University of Illiaois A-516 Grades 60 and 70 steel at Westinghouse llanford to determine the brittle fracture characteristics of this Cornpany. Specimens used were of the 1 inch compact material. Specimens with a transverse notch thru the tension type. Valid plane strain results were obtained weld failed atless than 10 kal for temperatures of from at test temperatures of from -300F to -125F whereas -40F to 40F. Unnotched specirnens at -40F failed at the NDT was previously found to be -40F (6). j from 10 to 22 kai. Most cracks were arrested within a few inches, however, some traversed the entire test section. These latter specimens were seen to corres-pond to the catastrophic failures observed in some wel-The effects of high pressuce hydrogen on the notch dcd structures of A-212B steel. It was also shown that strength of hot rolled A-515 Grade 70 steel were re-for unwelded plate, a cycle of hot-prestrain (400 to ported by Battelle Memorial Institute. It was shown 600F) rendered snaterial at the root of the notch suscep-that the hydrogen reduced the notch strength by about tible to cracking for loads as low as 87% of the yield 22 and 30% for holding stress amounts of 0 and 67 kai strength for test temperatures of from -80 to 80F (19). respectively (9). e 1973. Selfour hies, lae. ,--..n

A 516 STEEL 1 Otto, H.E., et al, "A CImparison of the Effecta of

  • 12 Hamij:r, G., "De:Ign Data f r High-Yl:Id-Strength Emplostw Forming and Static Deformation on the Alloy Steel", Journal of the Structural Div!aa.

Mschanical Properties of Pressure Vessel Steels", Proceedings of the American Society of Civil En-M-tallurgical Transactions, Vol. 4, (Mar 1973). gineers, Vol. 92, No. ST4 (Aug 1966). 2 M:lville, A.G., et al, " Quality Strand-Cast Slabe 13 Vandenberg, S.R., 'l Fatigue Crack Growth in Nu-for Plate Applications", Metals Engineering Quar-clear Reactor Piping Steels", General Electric Re-terly, Vol.11, No. 4 (Nov 1971). port GEAP-5607 (Mar 1968). 3 But quoc, Thang, "CycIle Stress, Strain and Energy 14 Glutoll, A., " Fusion Welded ASTM A-201 Steel Variations Under Cumulative Damage Tests in Low-

  • Plate" Convalt Report No, MP-58-440 Addendum Cycle Fatigue", Journal of Testing and Evaluation, 1 (Mar 1960), AD 838225.

JTEVA, Vol.1, No.1 (Jan 1973). 15 Crooker, T.W., Lange, E. A., "Im Cycle Fatigue 4 MsHenry, H.I., Irwin, G.R., "A Plastic-Strip Crack Propagation Resistance of Materials for Specimen for Fatigue Crack Propagation Studies in Large Welded Structures" U.S. Naval Research Low Yield Strength Alloys", Journal of Materials, Laboratory, ASTM Preprint (July 1966). JMLSA, Vol. 7. No. 4 (Dec 1972). 16 Cooley, L. A., Lange, E. A., " Fracture Develop-5 Kramer, I.R., et al, " Final Report, Center for ment and Material Properties in PVRC - Penn Illgh Energy Forming". Army Materials and Mech ' State Pressure Vessel", Naval Research Labora-anics Research Center Report AMMRC CR 66-05/ tory, NRL Memorandum Report 1827 (Oct 1967), 31 (F) (June 1972), AD 748416. AD 663203. 6 J mes, L. A., " Fracture Toughness of A-516 Grade 17 Klier, E.P., et al, "The Tensile Properties N ' 60 Steel", Welding Research Supplement (Oct 1972). Selected Steels for Use in Nuclear Reactor Pres-sure Vessels"r Naval Research Laboratory, NRL 7 McGeady, L.J., " Response of the Delta Test to Report 6649 (Dec 1967). Specimen Variables", Ship Structures Committee Report SSL-221 (Sept 1971), AD 733086. 18 Serpan, C.Z., Steele, L.E., " Damaging Neutron Exposure Criteria for Evaluating the Embrittle-8 Albritton, O.W., " Avoiding Brittle Fractures in ment of Reactor P'ressure Vessel Steels in Differ-t Cald-Formed ASTM 515 Steel" Metal Progress, ent Spectra", Naval Research Laboratory, NRL V:1. 93, No. 3 (Sept 1970). Report 6415 (July 1966). 9 Campbell, J.E., " Effects of flydrogen Gas on 19 Kiefner, J.F., Munse, W.!!., " Influence of Ther-Mitals at Ambient Temperature", Battelle Memor-anal and Strain Cycling on Fracture Susceptibility it! Institute, DMIC Report S-31, (no foreign distri-of Mild Steel", University of Dlinois, Ship Struc-bution without approval of AFML) (April 1970). tures Committee (Feb 1967), AD 647906. 10 St:tr. H., " Mechanical Testa of Welded Joints in 20 Schwartz I. A., et al, " Notch Toughness Proper-USS-T-1 and A-201 Steels", Convair Report MP-ties of Pressure Vessel Steels". U.S. Army Chief $8-440 (Oct 1959), AD 834061. of Engineers, Report TR 67-021 (distribution out-side' Department of Defense must have prior app- '11 Simmons, W.F., Cross, H.C., " Elevated Tem-royal of OCE) (Feb 1967), AD 811253. perature Properties of Carbon Steels", ASTM 1pe-cid Technical Publication No.180 (Sept 1955). 21 llawthorne, J.R., Steele, L.E., " Preliminary Observations on the Effectiveness of IIcat Treat-ment for the Recovery of Properties of Irradiated Steels", U.S. Naval Research Laboratory, NRL Report 5582 (Feb 1961), AD 252970. 3 00 - / 22 e sm, artt.ur m len. n=. o

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  • n o. o aweciu e..m Ccrtificcia cf Analysis Ionics Corporation Customer Order No.

0501 REPL 1 MF 5449-6 Bridgev1110, PA 15017 Order No. 617_87 Shipped 7/19/72 --This material conforms to Specificot;on __ ASME SEC. III SFA 5.4 Test No. 911 E 309-15 Type Tr:de Name: Arcaloy 309-15 Concentricity 4% Diam:ter 6ize: 5/32" Type Steel A-285 60 lb. L t Numben 1F220H5C Test No. Full Split Volts Amps He:t Numbers X53501 3 2 5 25 125 Carbon ,06 "1" 8 " ' ' ' 1*79 Test Results: AS Welded Stress Chromium 23.40 Relieved Nidel 12.82 45 Min.O 1100 F. silicon .85 Cslumbium Tensile 88,500 Tantotum Elongation 36%. Milybdenum Impacts 33 45 Test. Tungsten Impacts 43 46 Temp. Copper Impacts 45 -400 r Titanium j Ph:sphorus .016 Sulphur .009 Y:nodium ( fron l Ferrite 8% l Stato cf Penna. ) $5 Csunty of York j The undersigned cert;f;es that this report is correct and that no significant change has been made in any of the elements described 5:bscribed and sworn to before me in the quorircation opproval. this 21st doY of July 1972 CHEMETRON CORPORATION Mi, If/ [ " " ' " " ' " " " * ' ' ' ' ' ~ .g Hetery tehti< ~ My ccmmission empires: 5/8/76 pufosT Atr-2.4775/* BY p w /r. IM O TI' R. T. Lefever

t IONICS, INC., BRIDGEVILLE PIANT Q' WELDING SPECIFICATION: GIC-3959, Rev. 3 August 6, 1973 GMAW, GTAW, SMAW OF CARBON STEEL TO STAINLESS STEEL i CIASS P-1 & P-3 TO P-8 ----- SECTION IX, ASME BPVC ASME Boller & Pressure Vessel Code, Section III & IX with Addenda thru Winter '71 MIL-STD-278, Rev. D All equipment, including accessories, shall be kept in good repair and properly maintained for safe usage. 1.) Both procedure and operator qualifications shall be in accordance with ASME Boller & Pressure Vessel Code, Sections III and IX, NavShips 250-1500-1 or MIL-STD-00248B. 2.) Materials: Plate, Bar, Pipe or Shapes '3.) Filler Metal: AWS AS.4-69, Type 309 & AWS AS.9-69, Type 309 Mil-E-19933D, Amend. 2 & Mil-E-0022200/2B, Amend. 2 4.) Ioint Design, Preparation and Assembly 4.1) Design as shown on contractual drawing.

4. 2)

All joints will be prepared mechanically. 4.3) Limitations for assem'.aly per appendices. S.) Cleaning: All parts at assembly shall be degreased using new acetone. Grinding by alumina-oxide impregnated cloth or rubber wheels, carbide burrs or new stainless steel hand brushes. All slag, scale, oxide, etc. to be removed from each bead prior to continuation of welding. 6.) Inspection: 6.1) Visual at fit-up during welding and final for compliance to contractual dra' ing or appendices. Acceptance per ASME Boiler & Pressure Vessel w Code, Section III, Para. NB-4424 or NavShips 0900-003-8000. 6.2) PT per Ionics Procedure PT-102, Rev. 6 when applicable per drawing. Acceptance per ASME Boiler & Pressure Vessel Code, Section III, NB-5352 or NavShips 0900-003-8000.

6. 3)

RT when applicable per drawing. Acceptance levels to ASME Boiler & Pressure Vessel Code, Section III, Paras. NB-5321 and -5322, or NavShips 0900-003-9000.

6. 4)

Personnel, procedure and equipment approved and qualified to SNT-TC-1A, MIL-STD-271D or NavShips 250-1500-1. Page 1 e =a

  • 9m-* * * > * * * *

= e.

m Welding Specifiention: G TC-39 59, R'v. 3 August 6, 1973 1 7.) Weldino Techrilque: 7.1) Position: Plat or horizontal

7. 2)

GMAW: DC Straight Polarity Shielding Gas: Argon 98%-2% 02 at 35 CFhl Cup Size: 1/2-7/8" Ext. : 1/4-3/8" Travel: 7-14 IPM i Wire Feed: 150-240 IPM Wire Size:.045,.062,.092 7.3) GTAW: DC Straight Polarity Shielding Gas: Argon 98%-2% 02 at 10-15 CTH Cup Size: No. 7 Height: 1/2" Ext.: 3/8" j Electrode: 1/8" dia. 2% thoriated tungsten ground to a taper equal to approximately 3 times the electrode diameter and blunted at the l tip to.02/.03 dia flat with arc initiation b'y high frequency. 7.4) SMAW: DC Reverse Polarity ~ Deposition: In stringer beads with width limited to 2-1/2 times wire diameter. i

7. 5)

Weld back-up tape may be used in lieu of purge when applicable. 7.6) Prehea t: 60*F Min. 7.7) Interpass Temperature: 350*F Max.

7. 8)

Post Heat: When applicable per drawing. 7.9) All temperatures measured using a Pandax surface thermometer or lead-free temperature indicating crayons. 7.10) Covered electrodes are stored in a temperature controlled room. When conditions warrant, small holding ovens are utilized at the work site. 8.) Weldor Identification: Weldor's number to show on flow sheet, listing items wcIded, wire heat and essential variable, j i NOTE: Welds made from two sides shall be back-ground prior to welding second side. SMAW not permitted for root when exposed to environment of pressure containing welds. I, Page 2 i .I i

Walding 'Sp cif tention: 3959, R;v. 3-Figure Process Pass Layer Wire Size Amps Volts GMAW l 1 1/16 dia 220-260 24-28 /\\ As reqd. As reqd. 1/l6 dia 220-260 24-28 GMAW l 1 .035 160-200 22-27 h' ( 'As reqd'. As reqd. .035 160-200 22-27 ,,. g*U Lo" f GTAW l 1 3/32 dia. 80-100 7-13 i t - l6 m w. . As reqd. As reqd.. 3/32 'dia. 80-100 7-13 B2V.1 ~ GTAW 1 l' 3/32 dia. 80-100 7-13 As reqd. As reqd. 3/32 dia. 80-100 7-13 M f f j' { (K/ SMAW l 1 1/8 dia. 90-120 25-29 } i As reqd. As reqd. 5/32 dia. 120-140 25'-29 h ,,i 3 i 86 7 y T2V.1 l/ GTAW I 1 3/32 dia. 80-100 7-13 ~ As reqd. As reqd. 3/32 dia. 80-100 7-13 I 0*IS-k SMAW l 1 1/8dia. 90-120 25-29 5 h i i 'j \\ h t As reqd. As reqd. 5/32 dia. 120-140 25-29 l 3'2.- I6- - C2.v2 GTAW l 1 3/32 dia. 80-100 7.-13 l As reqd. As reqd. 3/32 dia. 80-100 7-13 SMAW l 1 1/8 dia. 90-120 25-29 -a l i \\ As reqd. As reqd. 5/32 dia. 120-140 25-29 GMAW 1 1 .035 160-200 22-27 L2S.1 As reqd. As reqd. .035 160-200 __22-27 Page 3

Walding Sp:cificction: 3953, R:v. 3 Figure Process Pass. Layer Wire' Size Amps Volts 45*h/d GTAW l 1 3/32 dia. 80-100 7-13 y l TYP f /\\ J. gs ~6,4.Hid f As reqd. As reqd. 3/32 dia. 80-100 7-13 SMAW l 1 1/8 dia. 90-120 25-29 } As reqd. As reqd. 5/32 dia. 120-140 25-29 '~ ~~ O fo {. -O lo lb +- s j GMAW l 1 .035~ 160-200 22-27 B2V.3 As reqd. As reqd. .035 160-200 22-27 GTAW 1 1 3/32 dia. 80-100 7-13 As reqd. As reqd. 3/32 dia. 80-100 7-13 / / SMAW 1 1 1/8 dia. 90-120 25-29 g' f ) As reqd. As reqd. 5/32 dia. 120-140 25-29 [0 bo g,. w,+. 7 0 d63-GMAN 1 1 .035 160-200 22-27 fg ClV.2 As reqd. As reqd. .035 160-200 22-27 I Page 4

. s {- '[ THE FRANKLIN IN.STIT.UTE. Laboratories for Research and Development ' {;. =; I-A2412-1 J{ j '- f, i.. v '. e, 3 p&.' p. 3 ): ,g q 1 p .i h.* ,h. i

h..

q i s APPENDIX A FEASIBILITY OF APPLYING MCDEL THEORY TO SIMULATE IMP.'.CT DAMAGE OF SHIPPING COiTAINERS 4 t I l ? I' ; L.* "l .._ ~ t, y e e.' , ~ h* e" -:..:--. p. ,, ?.d.c..r - f.I 's r,i + e F. : e e: f 6, Iu s'

  • t A

l;,r ,13 ,= :, A to. o m t 8 l - - -,.. ~ - - - - - - - - - - -~ - ~ - - - - - - ~ ~ - ~ ~ ' -~ ~ ~ .8,

j THE FRANKLIN INSTITUTE o Laboramries for Research and Development t I-A2412-1 APPENDIX A FEASIBILITY OF APPLYING MODEL THEORY 'IO SDCLATE IMPACT DAMAGE OF SHIPPING CONTAINERS Shipping containers involved in an accidental collision of cven moderate severity can be expected to deform elasto-plastically from ths ('ynamic loads arising in the accident. Under such conditions, analytical methods are presently inadequate for predicting the damage. l Even establishing the dynamic loads on the container structure proves t ^ to be a formidable task. Therefore, one may profitably study the fea- 'l i sibility of using experimental techniques on container models to provide qui.litative and perhaps quantitative answers for collision da= age. The theory of models has its basis in dimensional analysis and in the following, a brief outline of the method will be indicated. Dimensional Analysis i Dimensional theory is ' dependent on two axioms, the principios I of which are inherent in our methods of measursment and evaluation of quantities (Ref. E 399). l l Axiom 1: Absolute numerical. equality of quantities may exist only when the quantities are similar qualitatively. I Axiom 2: The ratio of the magnitudesof two like quantities is indepen-dent of the units used in their =casurement, provided that the same units are used for evaluating cach. i These axioms serve to establish an important theorem, viz., }, "that every derived magnitude must be expressible ac the products of

t some constant and arbitrary powers of the fundamental magnitudes."*

I-The meaning of this becomes clear when.one considers the following:

i..

Let a derived quantity S be measurable in terms of some funda-mental magnitudes A,B,C etc. Then, there exists a function F such that I (.

  • Focken, C.M., " Dimensional Methods and their Applications", Edward

. Arnold & Co.,1933, p. 33. p A1 I e l

l

_ji

THE FR ANKI.IN INSTITUTE o Laboratories for Research and Development k ,'l, LA2412-1 ll S = F (A, B, C.....) (1) ,1 As a result of the above theore:n, the following equality is obtained. } S = K A" B C".....) (2) Whrra X and the exponents a,b,e... are constants. A powerful extension of the above theorem is provided by ii Buckingham as follows:* If an equation is dimensionally homogeneous, it can be reduced to o relationship among a complete set of dimensionless products known . -l$ eg Pi-groups. Furthermore, the number of dimensionless and $.ndependent f.' quantities required to express a relationship among the variables is equa.1 to at least the number of quantities involved minus the number of 5l dimensions in which these quantities may be measured i.e., 4=m-n (3) l Where, 4 is the *1 cast number of Pi-groups, 1 s J m is the number of fundamental quantities, and n is the number of dimensions of the fundamental quantities. /.i As a consequence of the above two theorems the general equation I ,for any particular phenomenon may be stated as follows: e i t F (n n......... n =0 n (O The Pi-terms are dimensionless and independent. V 9 h J Theory of Models I- ~ Equation (4) can be rewritten *as follows: I!.1 Ji = c ("2> "3 "n) (5) - b n1 ,Buckingham, E., "On Physically Similar Systems; illustrative of the ..l, -hl 4 '! 'jj use of Dimensional Equations", Phys. Rev., 4,1914 i 2,j. ;l .n Brid6 man, P.W., " Dimensional Analysis", Yale University Press,1943, .[

p. 40.

A2 ) i l Of U 11) (.-.-.-.

i T'HE FRANKLIN INSTITUTE o Laboratories for Research and Dctelopment i, I-A2412-1 i i' 'l Since this equation, representative of say, system A, is completely g:nerr.1, it is applicable to another system B which is similar to system ) A. If one has a prototype and a model, then, "u " ("an "3 A * * * * * "n A) (6) 1 1 = G (n23, n3B*****"nB) (7) n,tg whare, subscripts A and B represent prototype and model, respectively. If the model is designed such that t n =n for i = 2,3,...... n - (a) j,0 g gg Th:n, $1 > n 5. "lA ~ "lB (9) 1 l I Tho (n -1) equations resulting from equation (8) are commonly known as the design conditions and equation (9) is known as the prediction equation. [ These n equations form the basis of model simulation. I l Types of Models (Ref. E 399) l 't a. True Models. (These are useful in predicting all the l g characteristics of the prototype that have been considered in the model l design.) ' i I., b. Adequate Models. (These are useful in predicting only some e' ': but not all of the characteristics of the prototype.) }; j l,., l c. Distorted Models. (These are models in which a design con-

j L dition is violated sufficiently to require correction of the prediction

] dt equation.)

i. 6(

d. Dissimilar Models. (These are models which bear no apparent f *Ijl similarity to the prototype.) .(, j g + With these preliminaries out of the way, one may profitably ,e. , le f;,. L I A3 l \\ I :t q ..A '

7,. ,W. p j-- m THE FR ANKLIN INSTITUTE. Laboratories for Research and Development 9 I-A2412-1 d:fino the present problem and study the characteristics of the phenos y4 non entering into it. e-i 5 Preblem Definition dk Assuming that a given shipping container collides with a rigid I stctionary object of infinite mass (may be extended later to the case of d j an clastic or clasto-plastic object) at a specified velocity h , can the .q. thcory of models be used to simulate the collision and to predict th i daraga sustained by the container? h,i. e In order to obtain a satisfactory answer to the above question d -I cna may begin by broadly classifying the pertinent physical quantities into three groups. j 'h,! l 'i Structural Simulation a. b. Dynamic Simulation i 5 ] l, Material Simulation c. h s With respect to structural simulation, a major difficulty l t l Srises in the present problem due to the large deflections j ; obtainable in collision. When materials are loaded beyond the yield point, permanent i t train remains after removal of the load. In general, when structural (o unique stress-strain relation can be shown to exist.< e l, c r ,However, when l.' .ha strains increase monotonically and slowly, the stresses can be expressed

.)

s e function of the strains.

9 The Hencky-Von Mises theory of plasticity tr,.tes that the stress-strain relationship under monotonically incre q,.

i I. i asing oads is determined by the true tensile stress-strain curve and Poisson's ,.ifli. l ptio, provided that the rate of loading is small enough. ] Therefore, j, [I 511owing Langhaar's* suggestion, if one plo'ts the tensile stress-strain i l i Irva E (c) in a dimensionless form,.the ordinate being , 1 (c is

nsile stress and c is strain) and the abscissa the strain, then two f;

.terials can be said to have identical stress-strain relationships, !l,5 l ;j' ,l cnghaar, H.L., " Dimensional Analysis and Theory of Models," John Wiley Sons, 1951, p. 81. ..l s i. IiI.

u ;. .THE FRANKLIN INSTITUTE. Laboratories for Research and Dweloprnent '. 6 '.i h3 i j ; 'l I-A2412-1 t-.i e !! i 'f, ,h. e ll I ti I : ', et i. i, I _m.- g ' j.r' i, t de . 1 :'; l;.- l l-1 i-t it t ' I f).. L !s., f l a 3. k [si 8 ....y. . \\ t l = t I l E (c) j ; .l 0 0 6 i ,1 t s. l; .s e E f&\\ e l s' 6 e i,. !, -[1,. 2 .6 1 . s,, 9 4 ' d 1

h.1 4
.' 4.. v.

p s . s e. e*s ' 4 g.' ti! ?-.?- .i e e 1 I' sl6 A5 J'"i

) fY ' W J THE FRANKLIN INSTITUTE. Laboratories for Research and Development ji )U b i A* I-A2412-l* ' 35- -lP if th ir dimensionless stress-strain curves are alike (Fig. A-1) i Th:r: fore, if a model is constructed with a material having the same dimen p sionicss stress-strain curve as that of the prototype and $f all the other }g [ dssign conditions are satisfied, then, under very small rates of loading t tha model will behave like the prototype even though the strains extend j~ into the plastic region. The premise forming the basis of this reasoning (though stated before, bears repetition) is that the load be monotonically -.c N increscing. i 1 In simulating a collision of two objects, to what extent can the cbova requirements be satisfied? A very cursory examinstion reveals that [ 3.. in a collision, the rate of loading is certainly not small 3, Furthermore, no dsfinite evidence can be cited as to whether or not the loads.on the b{ } structural members are monotonically increasing. In ' multi-degree of . i freedom' systems,, such as tractor-trailer combinations , under impact load.ing conditions, intuitively it'is apparent that the loading on some of the .; l <i .cmbers need not be monotonically increasing. On the other hand, a q ; ' single-degree of freedom' system may have monotonically increasing l i j oading { Suring the initial phases of the collision. (In fact, this is the pertinent 2 rt of the cycle for the' present problem inasmuch as m l {, ost of the structural iamage may be expected to happen during this phase.) 1 If the container

tructure, for large deflections, can be considered to behave like a single-

.jj _egree of freedom system (some experimental work in this area may be 'ruitful),then g.' O. models may give reasonable indication of prototype damacc. One further factor remains to be considered, namely, the effect 1.l ' t

v. :

M i, !y @ tha rate of loading. It was stated ehrlier that for loads exceeding the g). iold po' int, the stress-strain relationship is defined by the true tensilo provided that the rate of loading . y j irsss-strain curve and Poisson's ratio The restriction of rate effect can be evaluated if one ]f,j [(- a small enough. .s,

nsiders presently available test data,(E410) where it is found that a

[ .ique stress-strain relationship exists for steel, for example, at any

)! ' T, to of loading resultin6 in monotonically increasing strains (h'hether e sama holds true for lead is not known to the author at the present tirc)-

l A6 ,l I + a-

Mlja THE FP.ANKLIN INSTITUTE. o Laboratories for Research and Development l} 1 Thrr: fore, if it can be established that the strain rates are the same I-A2412-1 ~ in both the model and the prototype, then the theory of models can b I expected to yield significant results in the present problem'. e i 1 The question of dynamic simulation can be studied best by mean2 of dimensional analysis. As an initial step, consider a structure 9 in whjch the true stress-strain curvo of the materials are independ cf tha strain rate. ent Then, the true stress-strain curves can be represented by Ey (c ), E2 ( 2), et. Assume that the structure, moving with a l' y a valocity V, collides with a rigid object of infinito mass. Let pg and p ba the dens 3 tics, L ) and L, the characteristic lengths *, g and u '

1 ;

y 2 tha Poisson's 1 -ios of the respective materials of the structure. 2 L2t Y be a charact,cristic deflection produced in the structure a (!f result of the collision. sa I The product function can then be expressed as follows: o

f!

ga a a a a 1 2 3 5 6 a a [ ! CY L t p p y E (e ) 7 E (e ) 0 = 1 y y (10) where C and the exponents a g are constants. Since the Poisson's ratios aro already dimensionless, they can be substituted later into the l Buckingham function. Then, from equation (10), the following relations j; can be obtained: l! L: a y+a2 + "3 ~ 4"4 ~ 4*5 + '6 - 2a7 - 2ag=0 I l S'. F: a 4+a5+#7+8=0

s

',] j T: 2a 4 + 2ay-a6~ !ij c.' r.,' 's i For this analysis, one characteristic lehgth is sufficient -! i 1 li } svaluation of distortion factors if necessary.'or introducing the second The reason j,,} 1,

i., t hl i,

.[ 1 1 A7 1 d M i g l ,. i

I! THE FR ANKLIN INSTITUTE. Laboratories for Research and Development 1 y' I-A2412-1 !I..I Thrra are eight physical quantities defining the phenomenon whereas cnly three dimensions determine the quantities. Pi-theorem, there are at least five Pi-groups. Therefore, by Buckingham's 1 i To determine these, set tho exponents of any of the five variables, arbitrarily chosen , equal to The choice is valid if the determinant of the remaining quanti zsrs. ties in the equations (11) is non-zero." Let g = a ~ "4 ~ "7 Tha determinant of the renaining quantitica in the equations (11) i~ "8 ~ 2 s i 1 -4 1 O 1 0 = -l < it kl. 0 O 2 -l '[., ' Since the determinant is non-zero, the choice is valid The Pi-groups can now be determined as follows: i i. Sat t i l g = 1 and a =a =a =a ~ 7 8

Then,

,J i ji II.' 1+a3 - 4a3+a6~0 i. 5=0 .s 'a .e ,'l t '. t 2a5 ~ "6 ~ 0 , j 7: ~ . lution of the three simultaneous equations gives ,f, ' ', I,'l, 3=-l I ' t a c c j . 1 a5=ag=0 t herefore, one Pi-group is t'g ' i.3 y 1"$ U 2

i !

6. Similarly, set ! b* !!!$ 2 a = 1 and a il:'. 2 1=a4=a7 8=0 iJ =a i N r *,' i 1 i p :c s c r-s A8 t r e I l.' d Il1 j

'I g*: e THE FRANKLIN INSTITUTE o Laboratories for Research and Developrnent . i'. i.o I-A2412-1 i 3t i.*j l - i 1'

Thrn, 1+a I

3 - 4a5 + a6 = 0 ' J : a =0 ~H3.' 5 t;. > + -

0. :.

2a5 - a6 = 0 5 Ths solution la ? .s a = -1 ~ !; 3 i [h 5 6=0 b:'i a =a \\;. Therefore, . *1 l '!! !,j ". "2 " b !b i!'. 1 2 /

q:,

iii. Let a = 1 and a =a ~8 =a =0 4 y 2 7 g q l 1-Then '!i 3 + a6 - 4 ~ 4"5 a 0 l - i .sg,- 1+a =0 5 q j '< 2 + 2a5 - a6 = 0 O :. '. i -3, The solution is ,'l l i ~' ,I I . 45. li: "3" ~1 l

  • ^

, :1, 3 = a6 = 0 a

f <.

l "3 " 8 /P

l. i 1 2 iv. Set
e. 't 2'

"4 8 -j f f, 7 = 1 and g = a a ~8 =0 il .s-.: d;l l T,' l, A9

p.

? t ? i i I i .i.

o 1,. THE FR ANKLIN INSTITUTE. Laboratories for Research and Developmenc {:ji l 4 I-A2412-1 Jl

I {.'
Then, 3 + a6 - 4"5 -2 = 0 z

a 5+1=0 i a i 2a - a6 = 0 3

t igh Tha solution is

=0 3 = -1; a6 = -2; ay a E1 (e ) E1 (e ) ~ X:. y i y j. / (see rootnote) n = g 2 i "4 "3 ~ "4 2 pV ~E V i 1 ; 2 l } v. Let a = 1 and a =a =a =a =0 8 1 2 4 7 c

Then, l

a - 4a5 + "6 - 2 = 0 , j. 3 ,i 0+1=O a i i 2a3 - a6 " O ~ i i i Tha solution is t 1 =0 -l! ^5 " ~1 i ^6 " -2 ; a3 \\ ' E2 (*2) I (see Footnote) ns"py-T t 2 2 ,i -[ ..*rl t l; i. j 6 In the clastic range, these quantities rcpresent the square of the sound .' :s.; velocity in the respective material divided by the square of the collision j i velocity. et j ] i,il s A10 .!-e, }'

f..:

l.l 4. 2 il1 \\

h h'

,J.4 { V e THE FR ANKLIN INSTITUTE o' Laboratories for Reseamh and Developrnent E.., 'i l.p: h I-A2412-1 4i 1 $'

1f Th2 cquation representing container deformation in a collision can now b2 cxpressed as follows:

. h + Y .i L P El (*]) E,, (e ) l' ,t I"E 0 2 E "13 "2 (12) 2 s s ,~ 3 g Tha dssign conditions for a true codel are as follows, where subscripts h.!I M cnd P represent the r.odel and prototype, respectively: ~9' i;' ( I h) Ihh dl4 Erf ( p) M p/P (13,) - = I F 2 i 2 l'. g-4 ~ 'i l f P 1, (P) jl 1 1 \\ = y ',L iE2/ M L 2/ P O ..I e [E1 (c fE1 (e h 1 y (15) i 2 2 (P v ja (p y jp 1 1 l k I 2 (*2 2 (*2 (16) b p'2V /M i V2 jp n 1M "lP (17) v = v- -it 2M 2P (18) l;* j u The prediction equation is 3 i + i if YI I Y1 k 2 )lP (19)- l =l U .} i i 'i 2 / M ( j 1 Therefore, if the design conditions (13) through (18) can be satisfied, I squation (19) shows that strains in the model and prototype will be alike. l?, ji q q All a O d ; w

1 '., ( I

L i

THE FR ANKLIN INSTITUTE. Laboratories for Research and Development f : i J I-A2412-1 l @ f' a Equation (13) shows that geometric similarity is required. j : } Equntions (14) through (18) can be satisfied most easily by using the i-sama materials in the model as in the prototype. Equations (15) and (16) q thtn reveal that the model should have the same velocity as the proto-1j typa in order to obtain the s'ame strains in both. Thereforeu oll hion. c damago of a structure c,an. be simulated.in.a.model.provided. that-the stress-strain relations of the materials,are ind.ep_ende n_of., strain.Jate,,,

i. I' To understand the effects of strain rate, one may evaluate the

[ l' 1 strain rates in the model and prototype of the previous example. The [ a e significant variables are a characteristic deflection.Y, a characteristic p length L, density p, velocity V, stress-strain relation E (e) and the M.. strain rate c. The product function can then be expressed as follows. d. l a a a a a a i 1 2 3y 4 E (e) 5 6 6=1 (20) n CY L p

I Tha following relations are in. mediately obtained:

' d L: ay+a2 ~ 4*3 + "4 - 2a5 ] =0 3+a5 \\ F: a ~U 3-a4 - a6 = 0 (21) l ' 1 l T: 2a There are six physical quantities defining the phenonemon whereas only g three dimensions determine the quantities. Therefore, by Buckingham's i I l theorem,thereareatleastthreePi-groups. These can be determined ] by the same method as outlined before. Let a =a = 0. The p 2 " "4 l determinant of equation (21) is then as follows: l t i l -4, -2 0 l 1 O- =2 I 2 0 -1 y {," 'l f* I'I!' !u ll n2 ,i 9 0 f' .1, n

't I t,! ) THE FR ANKLIN INSTITUTE. Laboratories for Research and Development 3, i t I-A2412-1 0 -i Since the determinant is non-zero, the selection is valid. The Pi-groups cre obtained as follows: I 1. Set a = 1 and a =0 1 2 ~ "4 Th:n, 1 - 4a3 - 2a5 t =.O I 3+a5 =0 a I - q 2a3-a6=0 ,3 ~, J 7 .]. Th3 solution is .o I hl - 3=};a =-};a6~ a 3 i g i i 1 g

11. Set i

i i a 1 and a =0 2 y=a4 i r

Then, 1 - 4a3 - 2a5 O O;

=0 g

l t

3+ag V, ;; =0 a p j 2a 3 - a6 = 0 j [ A h-n L0 2 b(e) i E f j' iii. Set [- l:j a a l and a =a =0 4 2 1 n' J

Then, 1 - 4a3 - 2a5 ~"

J I' 'i 3+a5 j! =0 a L n

it 2a3-1-ag=0

- U. 4, A13 l

f. ;.

[ t g i, i

t j 'il .l Li THE FR ANKLIN INSTITUTE. Laboratories for Research and Development 3, s I-A2412-1 t Since the determinant is non-zero, the selection is valid. The Pi-groups cro obtained as follows: 1. Set a = 1 and a =0 y 2 "4 l Th:n, 1 - ha3 - 2a5 i =0 ) Y 3+ag =0 a

(

,

.t e-THE FRANKLIN INST 1.TUTE. Laboratories for Research and Developmene p j: .n d" I-A2412-1 introduced by strain rate seem to be a fertile field for further study. .]. ~ In so far as material simulation is concerned, it has already l;h,( b;en chown that use of the same materials in the model as in the proto- 'i typ] should be satisfactory. If' one can find other materials which have 'g tho same dimensionless stress.-strain curves is the prototype materials, 1 then they can also be used effectively in the model. However,'a search i - - for such materials is certain to be time consu=ing and perhaps futile. t. , o The use of dimensional analysis leads to an unknown functional relation .[ 's [y[ bstw:sn the fundamental quantities arranged in the form of dimensionless groups known as Pi-terms. If the magnitude of the Pi-tems are kept l[.. cqual in a prototype and its model, then the model can be used to predict 4 the behavior of the prototype. However, when one or more of the _ I l requircments for a true model cannot be satisfied, which is_1.he case i } in the present study, a knowledge of the fun..c_t...io_n_a_l_ relatio..n_..between the Pi-terms il essential for evaluating the resultant distortion effects. Dimensional analysis fails here and,rceourse__Rud_he_had.to._sxperincntal-methods supplemented by analy, sis., The experimental method is based on a comparison of the results obtained frca tests on models of different j *} geometrically scaled versions of various prototypes. Hence, a series of model experiments (as outlined in Section 4) is a logical approach to the problem of container impact damage. i 1 I, e n"^ i j r g i i i I !. I l l' I / 1 ( h l A16 'f l / f AC'9VZTY EDIT OF SHIELD.PWRBURH.MNTEXP .COMPOSIT.PWRC00L' i IN UNITS OF CI/CC .t TIME-> 500.0 HRS 1000.0 HRS 2000.0 HRS 3000.0 HRS 4000.0 HRS 5000.0 HRS O_lSgyg{,ES ALPHA 3.36426E-03 3.36391E-03 3.36315E-03 3.36239E-03 3.36163E-03 3.36C35E-03 EETA (-) 4.01473E+01 2.95063E+01 2.02516E+Cl 1.53497E+01 1.21:36E+01 1.00413E+01 i EETA (+) 9.11351E-05 8.83213E-05 c.32634E-05 7.87351E-05 7.46655E-05 7.10095E-05 j SP0H FZSS 4.96287E-12 4.96220E-12 4.96083E-12 4.95946E-12 4.95809E-12 4.95672E-12 SS WITH ALPHAS 2.84905E-04 2.34801E-04 2.8458tE-04 2.84375E-04 2.34163E-04 2.33951E-04 j BS MfTH BETAC-3 2.134 27 E+ 01 1.37336E+01 S.24235E+00 5.43230E+00 3.75337E+00 2.63789E+00 t 3MEREC GAMMAS 2.97576E+00 2.14646E+00 1.20216E+00 7.45412E-01 5.21396E-01 4.09931E-01 i nS WITH SP FISS 9.38951E-20 9.38950E-20 9.33949E-20 9.33943E-2J 9.33946E-20 9.33945E-20 f_0TPRIMARY 4.01513E+01 2.95103E+01 2.02850E+01 1.53532E+01 1.219 2 0 E+ 01 1.00447E+01 {OTAL GAMMAS 2.43188E+01 1.58804E+01 9.44529E+00 6.22799E+00 4.23005E+00 3.04816E+00 j (0T ACTIVITY 4.31270E+01 3.16567E+01 2.14572E+01 1.60986E+01 1.27134E+01 1.04547E+01 e, 1 s

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