, AO-A092 071 NEW MEXICO INST OF MINING AND TECHNOLOGY SOCORRO TER-ETC F/G 19/1HIBAL PROGRAM PRELIMINARY WARNEADDOESIGN. VOLUME I.dWMEP Go N0002-79-C.5333

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NAVAL SEA SYSTEMS COMMAND

CODE: 62R54

WASHINGTON, D. C. 20632, .... .. ,ccess ion For

CONTRAI.II N00024-79-C-5333 INTIS GA IDD C TABUnannounced dA

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NEW MEXICO INSTITUTE OF MINING & TECHNOLOGY, TERA GROUP

RESEARCH AND DEVELOPMENT DIVISION

SOCORRO, NEW MEXICO 87801

15 SEPTEMBER 1980

9"IS "-DIV'Il i FITI ON STAT A

App roved for pubic rrleaOZDsfrrlhution Unlimited

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WHITE OAK LABORATORYN DEARMETOFTFNV SILVER SPRING., M. 20910

VDEPARTMENT OF THE NAVY394-(iD>'#,-I° \ NAVAL SURFACE WEAPONS CENTER

DAHLGREN LABORATORYDAHLGREN, VIRGINIA 22448 VADAHLGREN, V 22448

.* ~, 1703) 663- 8715

IN REPLY REFf R TO

G34:ARH:dmc

8800

OCT 0 3 1980

From: Commander, Naval Surface Weapons Center

To: Distribution

Subj: HIBAL Program, Preliminary Warhead Design

Encl: (1) NMT/TERA Report No. T-80-1356-U HIBAL Program Preliminary WarheadDesign Volume I

(2) NMT/TERA Report No. T-80-1356-U HIBAL Program Preliminary WarheadDesign Volume II (appendices)

1. The HIBAL Program was initiated in FY79 as part of the Army/Navy AreaSAM Advanced Prototyping Program in NAVSEA 62R5 to develop and demonstratenew fragmentation warhead technology for defeat of bomber aircraft. Theprogram is being conducted by the New Mexico Institute of Mining & Technologywith technical support from NSWC and NWC/CL. The primary emphasis has beenon obtaining fuel ingestion kills by penetrating through the large bomberfuel tanks with a relatively large fragment having good hydrodynamic penetra-tion capability. This same fragment design has also been shown to yieldimproved capability against aircraft engines and on-board ordnance. The

enhancement in end-game effectiveness has been found to produce not onlyhigher probability-of-kill (Pk) but also a redundancy of killed componentswhich should yield reduced susceptibility of Pk to future changes in targetdescriptions and vulnerability models. Development of this technology isnearing completion with the final Prototype Demonstrations scheduled forearly FY81.

2. In the course of this program, a considerable amount of warhead technologyhas been developed in the areas of liquid penetration, fuel dump capability andfragmentation control. A series of four reports is planned to document thistechnology to ensure maximum utilization of this data. These reports willinclude:

a. Fragment Drag through Liquidsb. Vulnerability Modeling Procedures for Fuel Cellsc. Preliminary Warhead Designd. End Game Analyses

in addition, a separate report will be published documenting the Prototype

Demonstration firings against running engines as well as a final reportsummarizing all work under this program.

L

'.! ... . ... : . . .. ...... . ,: - .. . ...

G34 :ARI41:dmc8800

3. Enclosures (1) and (2), Preliminary Warhead Design, are the first published

in this series of reports. This report documents the application of the HIBAL

fragment designs to four warhead configurations from 80 to 200 lb using both

controlled fragmentation, with an opposed grooving technique, and preformed

hexagonal fragments. Full scale warhead test results verify the ability to

predict warhead performance and establish guidelines to successfully obtain

good fireformed HIBAL fragments. These tests have also formed the basis forI defining warhead characterizations for each of the HIBAL configurations.

An additional 135 lb warhead and 200 lb annular warhead are currently beingtested to verify the new fragmentation control guidelines. These tests will

be reported separately.

4. The four HIBAL configurations were selected to be compatible with current

and projected missile systems. These designs represent Advanced Development

Concepts. Application of the HIBAL technology to a specific missile systemwarhead design will require more extensive design tradeoffs in a number of

areas including threat spectrum weighting, encounter conditions, warhead size,

warhead shape, length-to-diameter ratio, and structural design.

< .WILLI S, IIIBY DIICTION

1

I

NMT/TERA NO. T-80-1356-U

TABLE OF CONTENTS

TITLE PAGE

1.0 INTRODUCTION ..... ....................... . ... I.

1.1 Background. ..................... .. 11.2 General Design-Guidelines................ ..1.3 Objectives ......... ..................... 31.4 Approach .... ... .. ...................... 3

1.4.1 Warhead Designs ... ............... 31.4,1.1 Preformed Fragment Warheads. .... 31.4,1.2 Fireformed Fragment Warheads . . . 4114.2 Testing ................ 4

2,0 RESULTS

2,1 Detailed Warhead Test Results. ............2.1,1 Summary of Warhead Test Conditions, Explana-

tion of Page Numbering System, and Definitionsof Terms Used in Results ..... ........... 4

TEST QN0225AO - 8-inch, 80-lb, FIREFORMED-FRAGMENT WARHEAD

2.1.2 Test 1, QN0225AO .................. .... 225-12,1,2.1 Design Summary and Rationale .... 225-12,1,2,2 Description of Test Objectives and

Test Arena ............... .. 225-22.1,2,3 Description of Test Results ..... ... 225-3

TEST QNO311AO - 11.5-inch, 135-lb FIREFORMED-FRAGMENT WARHEAD

2.1.3 Test 2, QNO311AO .................. .... 311-12.1,3,1 Design Summary and Rationale . . . 311-22.1.3,2 Description of Test Objectives and

Test Arena ............. . 311-32,1,3,3 Description of Test Results..... 311-3

TEST QNO319AO - 8-inch, 80-lb PREFORMED-FRAGMENT WARHEAD

2,1,4 Test 3, QNO319AO, . ........... 319-12,1.4,1 Design Summary and Rationale , . . 319-12.1,4.2 Description of Test Objectives and

Test Arena . ............ 319-12.1.4.3 Description of Test Results ..... 319-1

TEST QN0328AO - 11.5-inch, 200-lb FIREFORMED-FRAGMENT WARHEAD

2,1,5 Test 4, QN0328AO. ................... .... 328-12.1,5,1 Design Summary and Rationale . . . . 328-12,1.5.2 Description of Test Objectives and

Test Arena ........... 328-2a2.1.5.3 Description of Test Results ..... .... 328-2a

NMT/TERA NO. T-80-1356-U3 TABLE OF CONTENTS (con't)

ITITLE PAGEITEST QNO409AO - 19-inch ANNULAR, 200-lb FIREFORMED-FRAGMENT/

PREFORMED-FRAGMENT COMBINATION-WARHEAD

2.1.6 Test 5, QN0409AO. . . ........ . 409-12.1.6.1 Design Summary and Rationale .... 409-12.1.6.2 Description of Test Objectives and

Test Arena ... ............. .... 409-32.1.6.3 Description of Test Results ..... ... 409-3

TEST QN0429AO - 11.5-inch, 200-lb, PREFORMED-FRAGMENT/FIREFORMED-FRAGMENT COMBINATION-WARHEAD

2.1.7 Test 6, QN0429AO ..... ............... 429-12.1.7.1 Design Summary and Rationale . .. 429-12.1.7.2 Description of Test Objectives and

Test Arena ..... ............. 429-22.1.7.3 Description of Test Results ..... ... 429-3

TEST QNO514AO - 11.5-inch, 135-lb PREFORMED-FRAGMENT/FIREFORMED-FRAGMENT COMBINATION-WARHEAD

2.1.8 Test 7, QNO514AO .................. .... 514-12.1.8.1 Design Summary and Rationale . . . . 514-12.1.8.2 Description of Test Objectives and

Test Arena ..... ............. 514-22.1,8.3 Description of Test Results ..... ... 514-2a

2.2 Summary of Warhead Test Results ..... ........... 92.2.1 Summary, PREFORMED-FRAGMENT WARHEADS ........ 9

2.2.1.1 Velocity . ... ............. 92.2.1.2 Polar Angle: ....................... 9

2,2.1.3 Fragment Quality ..... .......... 92.2.2 Summary, FIREFORMED-FRAGMENT WARHEADS . . .. 10

2.2.2.1 Velocity ....... .............. 102.2.2.2 Polar Angle ................ ..... 102.2.2.3 Summary ....... ............... 102.2.2.4 Summary of the Design Evolution for

the Fireformed-Fragment, OpposedGroove, Warheads ..... .......... 12

3.0 CONCLUSIONS

3.1 Concerning Fragment Ejection Characteristics . . .. 203.1.1 Fragment Velocity (Fireformed vs Preformed) 203.1.2 Polar Angle .... ................. 20

3.2 Concerning the Opposed Groove Fireforming Technique'For Generating Hibal Fragments ............. ..... 20

3.3 Warhead Models Formulated For Use in End GameL Analyses ...... ...................... .... 20

i

INMT/TERA NO. T-80-1356-U3 TABLE OF CONTENTS (con't)

IITITLE PAGE

3.4 Caidelines For the Design of Future Warheads. 213.4.1 Warhead Characterization ............ .... 213.4.2 Opposed-Groove Design ............... ..... 213.4.3 Structural Strength ...... ............. 21

4.0 EVALUATION OF UNCERTAINTIES

1 4.1 For Both Preformed and Firefonned Fragment Warheads 224.1.1 End Configuration ................. ..... 224.1.2 Shroud Details ..................... .... 221 4.2 Preformed Fragment Warheads ...... ............ 224.2.1 Skin Thickness ... ............... ..... 22

4.3 Fireformed Fragment Warheads ............... ..... 224.3.1 Fragment Case Alloy ...... ............. 22

t WARHEAD CHARACTERIZATIONS ...... ................... ... 23-30

PREDICTED FRAGMENT EJECTION CHARACTERISTICS ........... .... 31-38

DESIGN FOR WARHEADS USING PREFORMED HEX-HIBAL FRAGMENTS . . 39

DESIGN FOR WARHEADS USING FIREFORMED HIBAL FRAGMENTS ..... ... 40

DISTRIBUTION LIST ...... ...................... ..... 41-43

THE FOLLOWING APPENDICES MAY BE FOUND IN VOLUME II:

APPENDIX I SUMMARY OF FRAGMENT MAT TEST CONDUCTED IN SUPPORTOF THE FIREFORMED FRAGMENT WARHEAD DESIGNS

APPENDIX II RESIDUAL WEIGHT OF 560-gr FRAGMENTS AFTER1OO00-ft/sec IMPACTS WITH THIN STAINLESSSTEEL TARGETS

APPENDIX III METHODOLOGY FOR PREDICTING WARHEAD FRAGMENTVELOCITY AND POLAR EJECTION ANGLE CHARACTERIZATIONS

I APPENDIX IV 19-inch-DIAMETER WARHEAD-SECTOR CALIBRATION-TESTS

I

I- ..

1.n INTROLICTION

1 BACKGROUND

his report presents the results of tests done under the Preli-minary-Wa. head-Design Task of the HIBAL Program. In this preliminarytesting stage, basic engineering data were collected on the perfomanceof various HIRAL-fragments, and various HIBAL-warheads. The resultsobtained fron these tests will be used to provide warhead models for the2nd phase of the HIBAL end-game-analysis effort. The wiarheads showingthe greatest lethality (highest Pk) in the analysis will be selected forthe design and fabrication of a set of prototype warheads for use indemonstration firings scheduled for the fall of 1980.

TL

1.2 GENERAL DESIGN-GIIELINES

A he first year's effort in HIBAL consisted of a survey of aero-space contractors to identify potential HIBAL applications, creation ofa HIBAL-fragment vulnerability-data-base, and a preliminary end-gameanalysis comparing numerous HIBAL "paper" designs.-his effort resultedin a set of guidelines for the preliminary warheadI esigns that arediscussed below.

Warhead Sizes: The aerospace-contractor survey defined four base-

line HIBAL-warhead sizes; 1) 8-inch O.D., 80-lb, 2) 11-1/2- inchO.D., 135-lb, 3) 11-1/2-inch O.D., 200-lb, and 4) 19-inch O.D.,10-1/2-inch I.D., 200-1b. Designs 1, 2, and 3 are solidcylinders, while design 4 is an annulus with a 10-1/2-inch I.D.The various shrouds associated with the missiles were alsoidentified in the survey. (NOTE: Shrouds can effect both fragmentvelocity and quality and thus need to be included in warheadcharacterization tests.)

Fragment Sizes: The HIBAL vulnerability/lethality testing wasdone with 700-, 1200- and 2000-grain HIBAL-fragments, and the"paper" designs for the first phase HIBAL end-game analysis in-cluded these three fragment sizes. The end-game analysis resultedin the 700-grain fragment being selected as the best choice of theabove three sizes. At the January, 1980 HIBAL program reviewmeeting it was decided to acquire data for 500- and 900-grainfragments, as well as for 700-grain frag::ients, to enable thesecond phase analysis to detenine the sensitivity ot P to achoice of fragments over the range of 500- to 900-grain.

Fragment Ejection Velocities: Because the first-phase end-gameanalysis had determined that 5000- to 6000-ft/sec (static) ejectionvelocity was sufficient for the encounter conditions that wercstudied, 5000-ft/sec to 5500-ft/sec was set as the guideline for thepreliminary warhead designs. It should be noted thaL the targets

PAGE I

__7

were heavily weighted towards manned aircraft, not cruise missiles.If the cruise missiles were heavily weighted, the ejection-velocityi requirements would go up.

Fraqment Shapes: The design choice was to use the maximumwarhead-case-thicknesses consistent with the above ejection-

velocity guidelines, because thick cases can generate "chunky"frigments that are shaped best to survive target impacts and topenetrate fuel.

I Fragment Alloys: It was determined in the vulnerability testingthat mild-steel fragments deform at anticipated warhead shroud andtarget impact conditions, and that properly heat-treated, alloy-steel fragments would better survive these impacts as demonstratedin the tests reported in Appendix 2. The preliminary warhead designsall utilized alloy steels, as discussed in the "results" section.

Warhead Style: Two separate warhead-styles were included in thepreliminary designs. The first style used pre-formed, hexagonal,HIBAL fragments laid inside an outer skin. The second style useda solid case, scored inside and out with "opposed-grooves' to pro-duce "fireformed fragments" of a controlled shape and size. Thepreformed fragments have adequate fuel cell penetration capability,as demonstrated in liquid drag tests. The solid-case designassociated with the fireformed fragments has some potential advan-tages. For example, the elimination of a need for inner and outerskins associated with preformed fragment cases permits firefonmedfragments to be thicker, therefore to have smaller surface dimensionsto give the same weight fragment, thus providing a more compactfragment and a better fuel penetrator. Opposed grooves were usedbecause existing Pearson-type grooving technology or liner technologydoes not produce fragments that have good drag characteristics dueto the fragments shape and roughness. Opposed grooves showed feasi-bility for achieving fireformed fragments having acceptable dragcharacteristics. At this point in HIBAL, both styles are consideredto be design candidates.

Preliminary Designs: The design guidelines recommended after theJanuary 1980 HIBAL Program Review resulted in four warhead configur-ations being defined for full-scale characterization and engineer-ing tests:

A. Solid 80-lb with 500-grain (fireformed) and 700-grain(pre- and fireformed) fragments.

B. Solid 135-lb with 700-grain (pre- and firefomed) and900-grain (fireformed) fragments.

C. Solid 200-lb with 700-grain (pre- and firefonned) and900-grain (fireformed) fragments.

0. Annular 200-lb with 700-grain (pre- and fireformed) and900-grain (fireformed) fragments.

LPAGE 2I

I iL .. .... - - - . .. . . '. . . . .. . ,

I

The devices actually designed and tested differed somewhat from theabove recommendations in that all three fragment sizes (500-, 700- and900-grain) were included in all four warhead sizes. This was possiblebecause of the large amount of data surface available in all the warheadsizes, and was deemed desirable because it would provide models of allthree fragment sizes for each of the four warheads in the second-phase

end-game analysis.

1.3 OBJECTIVES

The basic objectives of the test program included:

1. Generation of data on fragment polar ejection-angles,velocities, shapes, and weights for each of the preliminarywarhead designs.

2. Utilization of the generated data to:

A. Recommend any warhead design alterations which may be re-quired (for example, if a particular shroud configurationshattered the fragments, a design alteration would berequired).

B. Formulate warhead characterization models to be usedin the second phase end game analysis.

1.4 APPROACH

1.4.1 WARHEAD DESIGNS

1.4.1.1 PREFORMED FRAGMENT WARHEADS

Warhead case thickness and length dimensions for the various warheaddiameter choices were guided by the weight limitations and by the velocityconstraints imposed, using the prediction methodology presented in Appendix3. Only an outside skin was used, with hoops provided at each end to pro-vide rigidity. The inside skin that would be required in a final warheaddesign was not considered necessary at this level of the testing effort,because the structural strength was not needed, and the effect of the thinskin (0.010-inch thick) on performance was deemed negligible. The fragment,were arranged on the inside of the skin and potted in laminac. Hand-packedC-4 explosive was used in all the tests.

PAGE 3

I ,!

1.4.1.2 FIREFORMED FRAGMENT WARHEADS

Warhead case thickness and length dimensions for the various warheaddiameter choices were guided by the weight limitations and by the velocityconstraints imposed, using the prediction methodology presented in AppendixIII. The approach used to design the opposed-grooves was to use theshallowest grooves which would fireforn fragments of the desired shape andweight. Shallow grooves would leave the warhead case strongest, wouldremove the least metal and would permit faster and easier fabrication of

I the warhead case. Hand-packed C-4 explosive was used in all the tests.See section 2.1.1 for definitions of the terms used in discussing fire-formed warheads, and also see Figure 1.

~j I1.4.2 TESTING

IWitness sheets were used to record fragment hit locations for themeasurement of polar ejection angles and to measure fragment velocitiesusing high-speed cameras. Celotex was used to recover fragments so as toj measure fragment weights and to provide a record of the fragment shapesattained.

Prior to testing the first fireformed warhead a series of mat testswere made to generate some design data for the opposed groove technique.The mat tests were much cheaper and faster than tests of full scalewarheads would have been. The design of the first warhead was based onthe results of these mat tests.

2.0 RESULTS

2.1 DETAILED WARHEAD TEST RESULTSI

2.1.1 SUMMARY OF WARHEAD TEST CONDITIONS, EXPLANATION OF PAGE NUMBERING1SYSTEM, AND DEFINITIONS OF TERMS USED IN RESULTS

Table 2.1.1, presents a summary of the physical characteristics ofthe warheads in each of the tests. The tests are presented in chronolo-gical order, which is the sequence shown in Table 2.1.1. The page numbersand figure numbers used in this section are tied to the NMT test number.For example, the first test conducted in the series was NMT test numberQN0225AO. Therefore the page numbers and figure numbers associated withthis test are prefaced by 225- (i.e., 225-1, 225-2, etc.). The follow-ing pages and figures are numbered similarly.

PAGE 4!

I:

Definitions of certain terms used in the discussion of the designsof fireformed warheads are presented below. Refer to Figure 1.

1. Longitudinal Grooves

Grooves parallel to the warhead axis.

I 2. Circumferential Grooves

I Grooves perpendicular to the warhead axis.

3. Inside Grooves

Grooves on the inside of the warhead case.

4. Outside Grooves

I Grooves on the outside of the warhead case.

5. Groove Angle

Interior (apex) angle of the groove.

6. Longitudinal-Groove Spacing

Circumferential distance between the longitudinal grooves.

1 7. Circumferential-Groove Spacing

Longitudinal distance between the circumferential grooves.

8. Metal Remaining Between Grooves

The thickness of metal remaining between the apexes of theinside and outside, opposed grooves.

In all tests, the warhead case was of heat treated alloy, andTable 2.1.2 summarizes the heat-treatment procedures.

Appendix III presents the methodology used to predict fragmentejection velocities and polar angles.

1

I

IPAGE 5

. ...... ... .. . . .,

TABLE 2.1.2

SUMMARY OF HEAT TREATMENT PROCEDURESUSED IN EACH OF THE WARHEAD TESTS

TEST WARHEAD HEAT TREATMENT PROCEDURE MEASUREDNO. CASE RC

MATERIAL HARDNESS

QN0225AO 4130 Quenched from 1575 degrees in 43water, tempered at 800 degrees

QNO311AO 4140 Quenched from 1550 degrees in 40-42 !oil, tempered at 800 degrees

QNO319AO 4130 Quenched from 1575 degrees in 42water, tempered at 800 degrees 4I

QN0328AO 4140 Quenched from 1550 degrees in 37-42oil, tempered at 800 degrees

QNO409AO 4130 Quenched from 1575 degrees in 42oil, tempered at 800 degrees

QN0429AO 4140 Quenched from 1550 degrees in 37-42(Fireformed) oil, tempered at 800 degrees

4130 Quenched from 1575 degrees in 44-47(Preformed) oil, tempered at 800 degrees

QNO514AO SSS-100 Quenched from 1650 degrees in 42(Fireformed) oil, tempered at 800 degrees

HY-BO Quenched from 1640 degrees in 40-43(Fireformed) oil, tempered at 800 degrees

4130 Quenched from 1575 degrees in 40-42(Preformed) oil, tempered at 800 degrees

NOTE: All temperatures refer to the Fahrenheit scale.

PAGE 6

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I\ GROOVE\ ANGLE T = WARHEAD

- CASE

THICKNESS

M= MMETALTHICKNESSBETWEENINSIDE AND r CIRCUMFERENTIAL

OUTSIDE GROOVE LOCATIONGROOVES PACE BETWEEN = DISTANCE FROM

ONGITUDINAL GROOVES : BOOSTER-END OF

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PAGE 8 FIGUR[ I i ,

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IIIITEST QN0225A0

8-INCH, 80-LB, FIREFORMED-FRAGMENT WARHEAD

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I2.1.2 TEST 1, ON0225AO

2.1.2.1 DESIGN SUMMARY AND RATIONALE

*The basic design characteristics of the warhead (Figure 225-1) firedin Test 1 were:

OUTSIDE DIAMETER: 8-inchINSIDE DIAMETER: 2-inchLENGTH: 15-inchCASE THICKNESS: 0.438-inchCASE MATERIAL: SAE 4130 (RC-42)FRAGMENT TYPE: FIREFORMEDWARHEAD WEIGHT: 80-lbSHROUD: 0.050-inch titanium, with 1-inch

urethane foam insulation

The 2-inch inside diameter was used because it is a typical cavity-size (for safe-and-arm requirements) in warheads of this size-range.The case thickness and length combination was designed to provide frag-ment velocities between 5000 and 5500-ft/sec (after passing through themissile shroud) and, also, to maintain the 80-lb weight limitation. SAE4130 alloy was used for the fragment case based on the design guidelinesgenerated by the results of the mat tests (presented in Appendix-I).The shroud design, Figure 225-2, was based on information provided bymissile manufacturers.

The fragment case was grooved circumferentially to provide for 15rows of equal-length fragments, each 0.933 -inch long (i.e. 0.933-inchspacing between grooves). The spacing between longitudinal grooves wasvaried to determine if the spacing significantly affected fragment qual-ity. The spacings tested were 0.75-, 0.875-, 1.0- and 1.25-inch. (NOTE:The weight of the fragments, if ejected with no loss of weight during the

fireforming process, would be 550-, 640-, 740- and 840-grains, for therespective spacings. These weights were designed to be on the heavy sidewith the expectation that fireforming losses would bring the fragmentsdown to their appropriate nominal weights.

The interior angle of all the grooves in this warhead (and all thefollowing warheads) was 37°. This angle was used because the attempt tomachine smaller angles resulted in excessive shaper-tool breakage (andin significantly increased fabrication time).

From the mat firings (Appendix 1) for this warhead case-thickness,the depth of the longitudinal grooves should be about 0.095-inch deep(inside and outside, or a total depth of 0.19-inch) and, near the booster-end, the depths of the circumferential grooves should be 0.095-inch(inside and outside, or a total depth of 0.19-inch) and, near the non-booster-end 0.130-inch (inside and outside, or a total depth of 0.26-inch).Variations around the above groove depths were made in this test device,to increase the likelihood of encompassing groove depths that would pro-duce good results.

PAGE 225-1i4.a-"'--,.

I

The longitudinal groove depths were:

1 METAL REMAININGINSIDE GROOVE OUTSIDE GROOVE BETWEEN GROOVESDEPTH (inch) DEPTH (inch) (inch)

0 .090 0.060 0. 285

0.090 0.090 0.258

0.100 0.080 0.2580.110 0.080 0.2480.100 0.100 0.2380.110 0.110 0.2180.120 0.120 0.198

The circumferential grooves were of variable depth around the cir-cumference of the warhead but, at a given circumferential location, theinside-groove depth equalled the outside-groove depth.

MAXIMUM MINIMUMMETAL METAL

REMAINING REMAININGMINIMUM BETWEEN MAXIMUM BETWEEN

GROOVE GROOVE DEPTH GROOVES GROOVE DEPTH GROOVESNUMBER (inch) (inch) (inch) (inch)

1, 2, 3, 4, 0.080 0.278 0.125 0.188(booster end)5, 6, 7, 8 0.090 0.258 0.135 0.1689, 10, 11, 12 0.100 0.238 0.145 0.14813, 14, 15, 16 0.110 0.218 0.155 0.128

Note (in Figure 225-1) that the location of deepest longitudinal groovescorresponded (approximately) to the location of the deepest circumferen-tial grooves, and the location of the shallowest longitudinal groovescorresponded to the location of the shallowest circumferential grooves.

2.1.2.2 DESCRIPTION OF TEST OBJECTIVES AND TEST ARENA

The objectives of this test included recovering a sample of fragmentsfrom each opposed-groove design-choice, and characterizingthe warhead fragment-pattern in terms of fragment polar-ejection angleand of fragment velocity. Celotex was used to recover the fragments, andsteel witness sheets were used to record fragment pattern and as flashscreens for velocity measurements. A plan view of the test arena is shownin Figure 225-7, and photographs of the arena are shown in Figures 225-12and 225-13.

LP 2-

PAGE 225-2U *. -

2.1.2.3 DESCRIPTION OF TEST RESULTS

A. Fragment Ouality

Judgement of the success or failure of each opposed-groove designis based on two factors, the shape of the fragment and the weiqht of thefragment. The shape of the fragment is important because, if not correct,fragment individual weights vary and fragment survivability during im1, actwith the target is decreased.

1. Longitudinal Grooves

The quality of the fragment breakout along the longitudinal groovesis given in relative terms, in the table below. The tern "borrowed" meansthat the fragments did not breakout properly, some fragments having so:meof the steel attached to then that should have remained with neighboringfragments.

INSIDE OUTSIDE METAL REMAININGDEPTH DEPTH BETWEEN GROOVES* BREAKOUT QUALITYinch (inch) _ inch)

0.090 0.060 0.288 Poor - all fragments "borrowed"0.090 0.090 0.258 Poor - almost all fragmients "borrowed"0.100 0.080 0.258 Poor - almost all fragments "borrowed"0.110 0.080 0.248 Fair - 50% of fragments "borrowed"0.100 0.100 0.238 Good - 20% of fragments "borrowed"0.110 0.110 0.218 Very Good - 10% of fragments "borrowed"0.120 0.120 0.198 Excellent - no fragment borrowing

Fragments of the desired quality are illustrated in Figure 225-4, and thepoorest-quality fragments are illustrated in Figure 225-5.

* The metal remaining between groove apexes was not shown to be a

significant parameter until much of the test program was canpleted.Results are presented in terms of this parameter, to explain why certaingroove designs work, and others do not.

PAGE 225-3

I Y

I

2. Circumferential Grooves

The fragment breakout along the circumferential gronves was xcel !nt,except for two minor faults. These were, (1) occasional fragment doubles orlengthwise pairings occurred (Figure 225-5) and, (2) when the internalcircumferential grooves exceeded 0.120-inch depth (Figure 225-6), tile non-booster-e d inside corners of tile fragment broke off.

I CIRCUMSTANCES WHERE FRAGMENT DOUBLES OCCURRED

METAL RLIAi I GFRAGMENT FRAGMENT INSIDE GROOVE OUTSIDE GROOVE BETWEEN GRO)V[S*

ROW DOUBLES DEPTH (inch) DEPTH (inch) (inch)

1, 2 NONE

3, 4 YES 0.118 0.118 0.2025, 6, 7, 8 YES 0.113 0.113 0.2129, 10, 11, 12 YES 0.100 0.110 0.23813, 14, 15, 16 NONE

Fragment weights are presented in two tables for each longitudinal groovespacing, one which lists the fragments which could be identified by roworigin, and one which lists all recovered fragments. The tables arelocated on pages 225-20 through 225-25.

B. Fragment Pattern and Velocity

Fragment patterns from the witness sheets are plotted in Figuresj 225-8 and 225-9. Photos of the witness sheets appear in Figures 225-14and 225-15. Coordinates of the fragment hit-locations are presented inFigure 225-10. The fragment velocity and polar-ejection-angle charac-terization are summarized in Figure 225-11.

C. Conclusions

There is no need for further 8-inch diameter, 80-lb, firefoniedwarhead tests. The recovered fragment shapes and weights were satisfactory,and the pattern and velocity data were adequate to fonulate warhead char-acterization models for the second phase end-game analysis.

l11

I PAGE 225-4

1.?5* SPACING IOVTSIDE)

BETWEENETEE GROVS ROVEDETH

8SI1,EGRO.c lrPTkHS EPHIsl OUTSTI DE-..0E0

3/4 SPACING (OUTSIDE) BETWDETHBE~EEN GROOVESGROEDPH

GROOVECOV DETHPOTTm-.SOUTSIOO.IOO INID OE0"

iSIDE-' INSIDE SECIONA-

-Il SPACIN SPACITSIDE)BETWEE GRRVE

OUT.D __.___1___1

GROOVE~ROY\ HSISAGOOEDPH$(CRsOVE E ourIDE UT E . 0 8

TESTID 0 .0INSID

WR ED CAE '0.5L .1. .

0.TAL .438

CIRCUMFERENTIELRE.5-ALFAND

(INSDE UTSIEJ INIDE AtNGL E )1.

TSTON2B-B

NOTE1.AD ~ CASE 05LP-

ED WLATE R-QUENCHED;-1.

2.. ALL GROSVES, BOOOVHFILLNGTUDNA =I PANT7

oo .0.

TEST 1.22A FRGETCS

AND WWARHEADEDESIGNDRW PAG 225-5 FIGUR 225-1"

1 .050" TITANIUM (10-1/2" O.D.)

1" URETHANE FOAM(-10.4" 0.0.)

16"

SHROUD FOR 8" O.D., 80-LB WARHEAD

TEST ON0225AO

PAGE 225-6 FIGURE 225-2

I - - .- - -

I TEST: 0N0225A0

IIII

*I

I[.

II r

1WARHEAD COMPONENTS PRIOR TO ASSEMBLY AND LOADING

I

1IIIII

PAGE 225-7 FIGURE 225-3

I_____________ ____________ 4_____________________ -. -. .~-. - - - -----.-- ~-----.- - ------------- -- -- ----- - ----------

-- - 14 ~

II

0 2

I HII

.1

QN0225AOI

RESULTING4-FRAGMENT

SHAPE

FRACTURE LINE

LONGITUDINAL GROOVE

H.E. SIDE

FRAGMENT SHAPE RESULTING WHEN THE METAL REMAINING BETWEEN

LONGITUDINAL INSIDE AND OUTSIDE GROOVES IS BETWEEN 0.200" AND 0.240'

EXAMPLE FRAGMENTS FROM TEST QN0225A0

PAGE 225-8 FIGURE 225-4

i 1,'

-METAL REMAINING*K BETWEEN CIRCUMFERENTIAL

3OUTSIDE VIEW OF FRAGMENTS............. GROOVES WAS TOO THICKAS ILLUSTRATED BY

I FRAGMENT LENGTHWISE

PAIRINII

INCHES

QN0225A0

RESULT INGFRAGMENTSHAPE

15

FRAC URE .E. SIDE

LONGITUDINAL GROOVE

REDUCED-WEIGHT FRAGMENTS RESULTING WHEN METAL REMAINING

BETWEEN INSIDE AND OUTSID)E LONGITUDINAL GROOVES WAS 0.2,90" OR MORE

EXAMPLE FRAGMENTS FROM TEST QN0225AOPAGE 225-9 FIGURlE 225-5

INCHES

QN0225AOi I

Ii

EXPLOSIVEL SWEEP

i 0 1 2RCUELN

DIRECTIONFRACTURE LINE

INSIDE CASE

ILLUSTRATION SHOWING THE FRACTURE WHICH OCCURRED WHEN THEINSIDE CIRCUMFERENTIAL GROOVES EXCEEDED 0,120" DEPTH

EXAIPLE FRAGMENTS FROM TEST ON0225AO

PAGE 225-10 FIGURE 225-6

FASTAXFASTAX CAMERACAMERA

.105" STEEL "BA" 05"' STEELWITNESS SHEET WiTNSS SHEET

15' 15'

81 8'

WARHEAD

8'

8' j8'

INOTE: DEEPESTCIRCUMFERENTIALGROOVES AIMEDAT "A".

4' x 4'1 x 8'CELOTEX PACKS(7 EACH)

TEST ON0225AO

8" O,D., 80-LB, FIRE-FORMED HIBAL FRAGMENT WARHEAD

PAGE 225-11 FIGURE 225-7

mm i_

III

NUMBERS INDICATE WHICH ROW THE

40 FRAGMENT ORIGINATED FROM

DENOTED FRAGMENTS PAIRED TOGETHER

LU

20*

22

TOP OF WARHEAD

20 40 60 INCHES0 3 2e3- 4

40 45

o 60 5

-20- 78. 9o .7

10910. .910uLJ 0 8el1 15 13

14• 12 0120 13 104

-40 15

FRAGMENT PATTERN ON WITNESS SHEET "A"

AS VIEWED FROM EXIT SIDE

TEST ONO225AO

PAGE 225-12 FIGURE 225-8

Ii _

NUMBERS INDICATE WHICH ROW THEFRAGMENT ORIGINATED FROM

3 e~DENOTES FRAGMENTS PAIRED TOGETHER

40

L#)

20 2

TOP OF WARHEAD

20 40 60 INCHES,

I .4

-20 * 6*1

1215 11

115 14 13

-4

FRAGMENT PATTERN ON WITNESS SHEET "C" AS

VIEWED FROM FRAGMENT EXIT SIDE

j TEST QN0225A0

IPAGE 225-13 FIGURE 225-9

TEST QN0225Ao

COORDINATES* OF FRAGMENT HIT LOCATIONS (INCHES) ON THEWITNESS SHEETS AT 15-FT RADIUS

FRAGMENT WITNESS SHEET WITNESS SHEET VROW "A" "C""

NUMBER COLUMN 1 COLUMN 2 COLUMN 1 COLUMN 2HORIZ. VERT. HORIZ. VERT. HORIZ. VERT. HORIZ. VERT.

1 59 +28 - - 43 +22 - -

2 35 +15 63 - 6 46 +21 - -

3 30 - 5 63 - 6 39 - 7** - -

4 26 - 8** 68 - 7 39 - 6** - -

5 26 - 9** 59 -15 35 -16 72 -166 29 -13 55 -21 32 -19 67 -237 25 -21 54 -23 30 -22 60 -248 20 -22 55 -28 28 -25 63 -269 20 -26 48 -24 26 -27 60 -2810 17 -27 49 -26 22 -28 58 -3011 13 -29 48 -31 21 -30 54 -3112 12 -33 49 -33 16 -31 52 -3313 10 -33 42 -31 15 -33 50 -3214 9 -33 41 -35 10 -32 49 -3115 6 -37 34 -31 6 -31 43 -28

* Vertical measurements are measured from the top of the warhead

aimline; horizontal measurements are measured from the left handside of the witness sheet as viewed from the fragment exit side.

** Fragments paired together.

PAGE 225-14 FIGURE 225-10

AVERAGE POLARVELOCITY EJECTION(0-15 FT) ANGLEFT/SEC (DEGREES)

-~4500 +8.50

4300 +4.10

530

__________ 48500 -1.00

5300 -1.90

5300 -4.20

5300 -5.60

01

550 -6.3

ITEST: Q02A

VIEW OF WARHEAD IN PLACE IN TESTARENA WITH SHROUD REMOVED

Ar~r-WARHEAD IN TEST ARENA WITH0. SHROUD INSTALLED

IPAGE 225-16 FIGURE 225-12

I TEST: ON0225A0

VIEWS OF THE TEST ARENA BEFORE DETONATION

QNO225AO

*fil

liPAGE 225-17 FIGURE 225-13

TEST: QN0225A0

~ ..hWITNESS SHEET "C" BEFORE TEST;

x. A~

WITES WITNESSATE TSTSEXIT SIDE; 15' RADIUS

PAGE 225-18 FIGURE 225-14

F-=TEST: QN0225A0

rwo

PAG 22 9FGUE251

Q OI IDI I I I I I

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PAGE225-0 FIURE 25-1uj C-$11

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i t ! ) I M) IV D I I Ha II I ( ) C1 3 Z ; 01) N

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NIOT

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LPAGE 225-22 FIGUREP :)n-i8

I -~~~H 1H[i 3.iJOJ1

1 JIM OJl1]AOJ3l1 T Ir

f 13 V~IlflIO3H1I m II-)cLn ~~~ Co: (.20 6-, Co 1H13 011O

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IP

II'

I

ITEST ONO311AO

I 11,5", 135-LB FIREFORMED-FRAGMENT WARHEAD !

1IIII

IIIIII -

I ,*fri

I,2.1.3 TEST 2, QNO311AO

I2.1.3.1 DESIGN SUMMARY AND RATIONALE

The 13sic design characteristics of the warhead (Figure 311-I) inthis test were:

OUTSIDE DIAMETER: 11.5-inchINSIDE DIAMETER: 2.875-inchLENGTH: 14.0-inchCASE THICKNESS: 0.5-inchCASE MATERIAL: SAE 4140, (RC40-42)FRAGMENT TYPE: Fi reformedWEIGHT: 135-lbSHROUD: Double walled steel, 0.020-inch inside,

0.030-inch steel outside, with 1-inchurethane foam between warhead and shroud

The 2.875-inch-inside diameter is a typical cavity size for safe-and-anni devices in warheads of this size. The length and case-thicknesscombination was designed to provide for fragment velocities between 5000-and 5500-ft/sec, after passing through the missile shroud. SAE 4140 case-material was used because the design-choice of SAE 4130 tubing could notbe found in this size. The warhead was designed to generate 15 rows ofequal-length fragments (0.867-inch long). The ends of the warhead weretapered to reduce end effects on fragment pattern and velocity. Three

choices of spacing between the longitudinal grooves were tested (0.75-,0.906-, and 1.188-inch inside-spacing). The theoretical weights of thesefragments (after grooving but with no loss due to fire-forming) are about630-, 780-, and 1010-grains, respectively. The amount of weight inexcess of the nominal values of 500, 700, was expected to be lost duringfiring.

The first test, QM0225AO was a success in that excellent qualityfragments were generated. In this following test, however, the warheadcase was thicker (0.5-inch vs 0.438-inch). There were several designapproaches which were possible for the opposed grooves. Proper fireformingof fragments could be dependent on:

1. The Iepths of the inside and outside grooves (or sumof the depths).

2. The ratio of the depths of the grooves to the casethickness.

3. The thickness of the metal remaining between the apexesof the opposed grooves.

For this test, the decision was made to use approaches 1 and 2.

PAGE 311-1

I ,.

... "_ . : .# d ; , ,, , . , .• .. ... . . .". , _.. _> _

I

A. longitidinal Grooves

Opposed groove designs having depths of 0.100, 0.110, and 0.120-inch(inside and outside) worked well in the previous test, so these designswere repeated. In the event that the case thickness increase froin0.438-inch to 0.5-inch is significant, (roove depths of 0.130-inch (insideand outside) will be tested, which is approxiwately in t- sa:;ie ratio otgroove depth to case thickness as the 0.120-inch grooves in the previ(,ustest. One relatively shallow opposed groove design (0.100-inch deep inf ide,0.080-inch outside) was also tested to provide for the event that shallowiergrooves might he either required or sufficient. The longitudinal groovedesigns are summarized in the table below.

METAL R[IIAI!1INGINSIDE GROOVE OUTSIDE GROOVE BETWEEN GROOVLISDEPTH (inch) DEPTH (inch) (inch)

0.100 0.080 0.3200.100 0.100 0.3000.100 0.110 0.2800.120 0.120 0.2600.130 0.130 0.240

B. Circumferential Grooves

The fragments fron the rows nearest the booster end which were deemed"best" in test 0N0225A0 resulted from opposed groove depths of 0.100 to0.110-inch deep. The average value of these depths was increcised by theratio of 0.5-inch case thickness to 0.438-inch case thickness for this

test (i.e. 0.105" x 0.5 = 0.120"). The depths of the four grooves0.438

nearest the booster end were then varied ±0.020-inch about this value.

The same procedure was followed for the renaining (non-booster end)grooves: The "best" non-booster end fragments from 225 were generated

A_0_5-fran groove depths of 0.123 to 0.133-inch, thus, 0.128 x 0.438 = O.146-inch.

Groove depths were then varied from 0.130 to 0.160-inch. The groove designsare summarized in the table below.

PAGE 311-2

!f -

tTI I

ii

-, The circumferential grooves are numbered sequentially, starting withthe groove nearest the booster end.

SMAXIfMUM -MI NIMUIMETAL METAL

REMAINING REMAI NI NGMI N IMUM BETWEEN MAX IMUH BETWEENGROOVE GROOVE DEPTH GROOVES GROOVE DEPTH GROOV[S

! NUMBER (inch) (inch) (inch) (inch)

1 0.160 0.180 0.160 0.1802 through 5 0.100 0.300 0.140 0.220t6 through 15 0.130 0.240 0.160 0.180

16 0.160 0.180 0.160 0.180

2.1.3.2 DESCRIPTION OF TEST OBJECTIVES AND TEST ARENA

The objective of the test was to recover a sample of each groove-design choice, and to measure fragment ejection angles and fragmentvelocities. The test arena (Figure 311-7) consisted of seven celotexpacks and six steel witness sheets. Photographs of the test arend arepresented in Figures 311-11 and 311-12. Fastax cameras were used tomeasure fragment velocities.

2.1.3.3 DESCRIPTION OF TEST RESULTS

A. Fragment Quality

1. Longitudinal Grooving

The longitudinal-groove breakout-quality was a function of the metjiremaining between the apexes of the opposed (Irooves.* 'When the metalranaining was 0.240-inch, the desired frayment quality was achieved(Figure 311-3). For metal remaining values between 0.240-inch and O.2u0-inch, borrowing occurred (Figure 311-4); for metal thicknesses greaterthan 0.280-inch, partials occurred (Figure 311-5).

2. Circumferential Grooving

I No fragment doubles occurred for fragment rows 1 and 2. Fragmentdoubles were recovered for rows 3, 4, and 5 where the metal reiiailningbetween apexes of the grooves was 0.240-inch or more. Fragment doublesoccurred for all choices of circumferential groove depth for fragmentrows 6 through 15.

* The designers did not recognize this until nuch later in theI proqram.

PAGE 311-3

I

I _B. Fraqment Velocity and Pattern

Recause of the lengthwise pairing of fragments, the fragment polar-ejection-anqles for this test are suspect. The coordinates of all thefragrient hits are presented in Figure 311-8 and 311-9, with an estimateas to which fragments were paired.

I The Fastax films yielded good time-of-arrival data, and fragmentvelocities are presented in Figure 311-10. Photographs of the witnessJ sheets are presented in Figures 311-12 through 311-15.

C. CONCLUSIONS

1. The warhead design will have to be altered to achieve properf case breakout and achieve the desired fragment sizes and shapes. k2. The "best" fragments resulted for the following opposed grooveI designs:

LONGITUDINAL GROOVES: 0.100-inch deep (inside and out) forrows 2 through 7.0.130-inch deep (inside and out) forrows 8 through 15.

CIRCUMFERENTIAL GROOVES: 0.130-inch deep (inside and outside)for rows 2 through 5.0.158-inch deep (inside and outside)for rows 6 through 15.

IiI1I

III

IPAGE 311-4

777___

3/'GROOVE SPACING (INSIDEl 39.10' (HOIzo 01 PiN 293'GROOVE SPACING £OT(INID OT).110- CRUOVE DEPTH(NSD

3/4' GROOVE SPACt 116 *.

!130. GROOVE O(PII . .. 29/32' GROOVE

1 00: GROOVE UIEP1H (INSI)j .:080' GROOVE DIPIH (OUTSIDE)

SECTION B-B -

SA*3/l* GROOVE SPAC ING

12,GROOVE DEPH

1/2' (NIE

29/32: GROOVE SPAC1W, (INSIDE)

.100'00 GROOVE TWPH 2/32(INSIDNSID 9 OOU HJ)

1/8" 52' 1.O GROVOOVEIN>JI (I3SIDE

.100- GROOVE DET 1/2

DEEAIH (360' BOTOM A

MAXIMUM MRO I T I P1C

GROOVE DEPTH GROO VE DIIH

1. ALL GROOVES HAD .13 67' ..

37* INIERIOR ANGLE. (TYP) I

2. WARHEAD OFFSET .015'IN LATHE TO VARY

CIRCUiEiRENT IAL 'GROOVE DEPTH FOR ALLGROOVES EXCEPT THE *. ..

END GROOVES. .. B1'O3. WARHEAD FRAGMENT CASE B140

MATERIAL -SAL 4140OSTEEL, HEAT T~rATED,OIL OUEN(CHI0. ANID MNrDRAWNI AT 800* FOR LIiU * ROEDPTH2 HOIIPS MEASURED AXIMMhARDINESS - FC GROOVE DEPTH ..

130'U-42. - .160' .~

SECTION A-A 1

SCREWS frPR

-11-1/2"1 O.D. 135-LB FIRE-FORMED HIBAL WARHEADTEST QN0311AOIPAGE 311- 5 FIGURE 311-1

18" O.D. x.030" STEE 14" 0.0. x.020" STEEL 1" URETHANE FOAM

15"1

SHROUD FOR 11-1/2"1 O.D., 135-LB WARHEAD

TEST QN0311AO

IiPAGE 311-6 FIGURE 311-2 tj

I

I1II

QN031 1lAO

RESULTINGFRAGMENTSHAPE

FRACTURE LINE

i LONGITUDINAL GROOVE

H.E. SIDE

FRAGMENT SHAPE RESULTING WHEN THE METAL REMAINING BETWEENLONGITUDINAL INSIDE AND OUTSIDE GROOVES IS BETWEEN 0.200" AND 0.240"

EXAMPLE FRAGiENTS FROM TEST QNO311AO

PAGE 311-7 FIGURE 311-3

PAGE,''

BETWEEN.,lf m "I CIRCUMFERENTIAL

GROOVES WAS TOO THICK,, "-- "IAS ILLUSTRATED BY

FRAGMENT LENGTHWISE/PAIRING

INCHES

ON031 1AO

FRAGMENTSHAPE

FRACTURE

LONGITUDINAL GROOVE

REDUCED-WEIGHT FRAGMENTS RESULTING WHEN THE METAL REMAINING BETWEEn!jll I I:,ID[ AID OUTSIDE LOiTUDINfAL CROOVES WAS 0.240" THROUGH 0.260"

[ EXAMiPLE FRAGNENTS FROM TEST QNO311AO

PAGE 311-8 FIGURE 311-4

I

TOTAL METAL REMAINING'." w 'Mr/ BETWEEN ' CIRCUMFERENTIAL

. GROOVES WAS TOO THICK ASILLUSTRATED BY FRAGMENTLENGTHWISE PAIRING

AO 1o I 2

RESULTINGFRAGMENTSHAPE

', / " -

H.E. SIDEFRACTURE

LONGITUDINAL GROOVE

REDUCED-WEIGHT FRAGMENTS RESULTING WHEN METAL REMAINING

BETWEEN INSIDE AND OUTSIDE LONGITUDINAL GROOVES WAS 0.280" OR MORE

EXAMPLE FRAGMENTS FROM TEST QNO311AO

PAGE 311-9 FIGURE 311-5

INCHES

QN031 1 AO

EXPL SIVESWEEP

IDIRECTION/4---FRACTURE

L INE

INSIDE CASE

ILLUJSTRATION~ SHOWING THE FRACTURE WHICH OCCRRDWENTE

INSIDE CIRCUMFERENTIAL GROOVES EXCEEDED

0.120" DPT

EXAMI~E RAG~tIT FI~M TIST 0NCIAOEXAMLE RAGMNTSFROMTES ONFiGURE 311-6

I PAGE 311-10

........ .

II

TARGETS A, B, C, D, E, F, G = 4'x4'x8' CELOTEX PACKSWITH 1/2" STEEL BACKPLATE

TARGETS 1, 3 = 2 EA. .105" STEEL PLATES 8'HIGH SPACED 3" APART

TARGETS 2, 4, 5 = 1 EA. .105" STEEL PLATE4' WIDE, 8' HIGH

TARGET 6 = 4'x'6'xl/2" MILD STEEL

2 EA. FASTAX,I SPLIT FRAME,I'FULL FRAME

1

.6

15' 15'

20' 8.5' 15'

B

215'm

2 15'..WARHEAD

/515'C 20' I

15'/ E

2 EA. FASTAXI SPLIT FRAME1 FULL FRAME

ARENA FORTEST ONO311AO

11-1/2-INCH O.D., 135-LB FIREFORMED WARHEAD

PAGE 311-11 FIGURE 311-7

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PAE31c FGR 1-[C

I'I FRAGMENT FRAGMENT

ROW VELOCITY

1 4800

2 5200

3 5500

4 5500

5 5500

6 5500

5500

8 5500

9 5500

5500

5500

12 5500

5500

5200

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FRAGMENT VELOCITY CHARACTERIZATIONL BASED ON TEST QNO311AO DATA

PAGE 311-14 FIGURE 311-10

' ., ,,-4* ,4 ~.. A, .- oo

TEST: QNO311AO

II

• iI

VIEW OF WARHEAD IN THE TEST! ARENA WITH THE SHROUD REMOVED

" * '

TEST ARENA BEFORE DETONATION SHOWING THEWARHEAD WITH THE SHROUD IN PLACE

, .+ ,... .

IT " PAGE 311-15 FIGURE 311-11 '

TEST: QN0311AO

IWIESS SHEE #1 AFTER TET2-RAIS

ENR SD

PAGE311-6 FIURL 11-1

TEST: QNO31iAO

WITNESS SHEET #2 AFTER TEST;- 15' RADIUS; ENTRY SIDE

WITNESS SHEET #4 AFTER TEST;15' RADIUS; ENTRY SIDE

[PAGE 311-17 FIGURE 311-13

TEST: QNO3I1AO

I

WITNESS SHEET #5 AFTER TEST;1" 15' RADIUS; ENTRY SIDE

1/2" STEEL WITNESS SHEET AFTERTEST; 8'6" RADIUS; ENTRY SIDE

I~

PAGE 311-18 FIGURE 311-14

I . -..r ' " " -,

TEST: QN0311AO

WINS SHE 3ATRTS;2KRDU;ETYSD

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'I viIIIII

VI TEST 0N0319A0

8", 80- 1D PREFORIIED--FRAGMENT W/dThEADIIII

I.

II 3

IIIII

.~- ~-. -, 4

I 2.1.4 TEST 3, QNO319AO

Il2.1.4.1 DESIGN SUMMARY AND RATIONALE

The basic design characteristics o'r the warhead (Figures 319-1 and319-2) were:

OUTSIDE DIAMETER: 8.0-inchINSIDE DIAMETER: 2.0-inchLENGTH: 15.2-inchCASE THICKNESS: 0.445-inchFRAGHENT TYPE: Pre-fonued Hex HIBALFRAGMENT THICKNESS: 0.420-inchSKIN THICKNESS: 0.025-inchFRAGMIENT MATERIAL: SAE 4130, (RC-42)SKIN MATERIAL: Mild SteelWARHEAD WEIGHT: 80-lbSHROUD: 0.050-inch titanium with 1-inch urethane

foam insulation

Three choices of preforned hex-HIIBAL fragments were used; 7/8-inchacross flats by 0.42-inch thick (500-grains), 1-inch across flats by K0.42-inch thick (700-grains) and 1-1/8-inch across flats by 0.42-inchthick (900-grains). The case thickness/length combination was designedto achieve fragment velocities of 5000-, 5500-ft/sec after passing throuhthe shroud. Only an outside skin (0.025-inch steel) was used, and 7/10"'x 1/2" hoops at each end provided for rigidity. The fragments were pottendin laminac. The shroud (Figure 319-3) is the same design as for the 8-inchfirefomed-fragment warhead.

2.1.4.2 DESCRIPTION OF TEST OBJECTIVES AND TEST ARENAS

The objectives of the test were to measure fragment velocities andpolar ejection angles, and to recover the hex-HiBAL fragments, fordetermining the detonation arid/or the shroud effects on the resultingfraqrient quality. The test arena plan is in Figure 319-6 and photographsof the test arena, are in Figures 319-12 and 319-13.

2.1.4.3 nESCRIPTION OF TEST RESULTS

A. Fragment Quality

The recovered fraqr;ents exhibited minor deformation resulting fr(x:the detonation-wave sweep, but showed no loss in weight (Figure 319-1).

IPAGE 319-1

B. Fragment Pattern and Velocity

c The fragment polar-ejection-angle, as a function of the fraymentcenter-of- length distance fron the booster end of tihe warhead, is pre-

sented in Figure 319-7. A summary table of the fragimient polar-ejection-angles and velocities is presented in Figure 319-8. Fragyle nt-hit-

"easureients are presented Figures 319-9 through 319-11.Photographs of the fragment pattern on the witness sheets are presentedin Figures 319-14 and 319-15.

I I-C. Conclusions

There is no need for further 8-inch diameter, 80-lb prefoniied fray-ment warhead tests. The recovered fragments were satisfactory in teros offragment shape and weight, and the pattern and velocity data were adequiteto formulate warhead characterization models for the second phase end qui;;eanalysis.

PACE 19-1

7/8" A( OI S I A IS f. IIII" ACROSS: !I A-/8 IS~: 0.4L.' 1111 KI S

SECTION B-B

I ACROSS riAlS x 0. 4?" I CKt>Ill'X-I} fAt. I RATG :iNl S

700 grain

1/2" THICK ALREM. PLUG

/; "END RING 7A

SJEFL SKIN"". ~

I KI: PINS

NOTE: ALL IFRAG!WENTSB ' .. . WERE SAE 4130,

1fFX FIIPAL HEAT-I RElATEDF RAGNPF:S I S AND WATERPUT1 if U IN . .

LAM INAC (,q E QUENCHED, DRAWNDL [AILA AT 8000 FOR1 HOUR.

S It A IURE . " 5

5."

(.25 '1-07 " .63 )

SHIM . *.

n 2-. . I

80--PRLI O, IFLX-IIIAL WM11EAD[ TEST ON03I9AO riGURr 31'-1 5

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10.5" 0.0. x.050" TITANIUM

1" URETHANE FOAM

1611

SHROUD FOR 8" O.D., 80-LB WARHEAD

TEST QN0319A0

A

PAGE 319-4 FIG~URE 319-3

I

I

ITEST: QN0319A9

VIEWS OF WARHEAD WITHOUT C-4

j PAGE 319-5

FIUE 1-

IiI..

"2 II-

INCHESQN03 19AO

TYPICAL 500 GRAIN HEX HIBAL FRAGMENTS RECOVERED

IN TEST QNO319AO

ILPAGE 319-6 FIGURE 319-5

. . . ..... .. . .."

TEST: QN031A9

I

8' HIGH, 9' LONG.105" STEEL WITNESS

8' HIGH, 9' LONG.105" STEEL WITNESS/

10 ' 10'

8'

81 CELOTEX(4' x 4' x 8' HIGH)

CELOTEX(4' x 4' x 8' HIGH) WARHEAD

8'

CELOTEX(4' x 4' x 8' HIGH) 20'

=--::: 12' HIGH x 18' LONG STEELWITNESS SHEETS, .105" STEELON ENTRY, .25" STEEL ON EXIT,SEPARATED BY 6 INCH AIRSPACE

ARENA FOR

TEST ON0319AO

2 EA GROUND LEVEL I-ASTAX CAMLRA, 1 SPLIT FRAME,

1 FULL FRAM.PAGE 319-7 FIGURE 319-6

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- -TTT T7TTC

TEST QN0319AOi _SUMMARY OF POLAR EJECTION ANGLE AND VELOCITY RESULTS

FRAG. C.G. POLAR ANGLE (DEGREES) POLAR AVERAGEFRAGMENT DIST.* FROM ANGLE VELOCITY

ROW BOOSTER-END 500-GR 700-GR 900-GR SUMMARY (0-20')**

1 1.1 (5) +4.5 4.5 4210I 1 1.2 (7) +4.7 4.71 1.3 (9) +3.2 3.22 1.9 (5) +1.2 1.2 46702 2.1 (7) +1.2 1.22 2.2 (9) +0.4 0.43 2.7 (5) -0.2 -0.2 50003 2.9 (7) -0.7 -0.73 3.2 (9) -1.5 -1.54 3.4 (5) -1.6 -1.6 50804 3.8 (7) -1.8 -1.84 4.2 (9) -2.5 -2.55 4.2 (5) -2.6 -2.6 53805 4.7 (7) -2.7 -2.76 4.9 (5) -3.2 -3.2 54005 5.2 (9) -3.6 -3.66 5.5 (7) -3.2 -3.27 5.7 (5) -3.6 -3.6 54706 6.2 (9) -3.6 -3.67 6.4 (7) -3.6 -3.68 6.4 (5) -4.0 -4.0 54907 7.1 (9) -4.4 -4.49 7.2 (5) -4.3 -4.3 54708 7.3 (7) -3.9 -3.9

10 8.0 (5) -4.7 -4.7 55809 8.1 (7) -4.2 -4.28 8.1 (9) -4.2 -4.2

11 8.7 (5) -4.9 -4.9 566010 9.0 (7) -4.3 -4.39 9.1 (9) -5.0 -5.0

12 9.5 (5) -4.9 -4,9 563011 9.9 (7) -4.7 -4.710 10.1 (9) -4.6 -4.613 10.2 (5) -5.4 -5.4 569012 10.7 (7) -5.4 -5.414 11.0 (5) -5.6 -5.6 558011 11.0 (9) -5.2 -5.213 11.6 (7) -5.2 -5.215 11.7 (5) -5.6 -5.6 566012 12.0 (9) -5.0 -5.016 12.5 (5) -5.6 -5.6 549014 12.5 (71 -5.7 -5.713 13.0 9 -5.7 -5.715 13.3 (7) -5.8 -5.817 13.3 (5) -7.3 -7.3 557014 13.9 (9) -4.8 -4.818 14.0 (5) -6.0 -6.0 549016 14.2 (7) -6.1 -6.1

• DISTANCE INCLUDES END PLATE AND THROW AWAY RINGVELOCITY RESULTS ARE FROM THE 500-gr DATA SECTOR, AND ARETHE AVERAGE OF THREE FRAGMENT HITS FOR EACH FRAGMENT ROW

PAGE 319-9 FIGURE 319-8

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PAGE 319-12 FIGURE 319-]]

1*TEST: QN0319A9

WARHEAD IN PLACE IN TEST ARENAWITH SHROUD REMOVED

m I

.404 WARHEAD IN PLACE IN TEST ARENAWITH SHROUD INSTALLED

PAGE 319-13 FIGURE 319-12

TEST: 0N0319A9

VIEWS OF THE TEST ARENA BEFORE DETONATION

PAGE 319-14 FIGURE 319-13

TEST: QN0319A9

WITNESS SHEET AFTER TEST; 700gr FRAGMENTS;ENTRY SIDE; 10' RADIUS

WITNESS SHEET AFTER TEST; 900gr FRAGMENTS;ENTRY SIDE; 10' RADIUS

PAGE 319-15 FIGURE 319-14 p

I TEST: QNO319A9

I .

!

LL

ITNESS SHEET AFERTSTj00rFRGENSENR SID; 2' RDIU

~;

.t. "

II!

II

ITEST 0NO328AO0

i 1.1.5", 200-LB FIREFORMED FRAGMENT WARHEAD

I

II

Iii

4'

IIl

"

2.1.5 TEST 4, QN0328AO

2.1.5.1 DESIGN SIXINARY AND RATIONALE

The basic design characteristics of the warhead (Figures 328-1 arid328-2) were:

OUTSIDE DIAMETER: 11.5-inchINSIDE DIAMETER: 2.875-inchLENGTH: 18.375-inchCASE THICKNESS: 0.563-inchCASE MiATERIAL: SAE 4140, (RC37-42)FRAGMENT TYPE: Fi reformedWARHEAD WEIGHT: 200-lbSHROUD: Double walled steel, 0.020-inch inside,

0.030" outside, plus 1-inch urethanefoam insulation between warhead and shroud

The fragment case was grooved circumferentially to provide 19 rowsof equal length fragments, each 0.888-inch long. The spacing betteen thelongitudinal grooves was varied to determine if the spacing significantlyaffected fragrnt quality. The (external) spacings tested were 0.675-,0.866- and 1.108-inch. The fragment weights for these spacings would he600-, 770-, and 990-grains respectively (with no loss in the firefonmijng).The shroud (Figure 328-3) tested was identical to that of the previous11-1/2-i nch-di ameter warhead.

The "best" opposed groove designs frui test Q!N031AO indicated thatshallower qroove depths were required for fragments locdted near thebooster end of the warhead, than for fragmcnts located near the noi-boosterend. This was true for both longitudinal and circunfur'.ntial grooves.

A. Longitudinal Grooves

The longitudinal grooves were tapered in depth, frw one end of ti,ewarhead to the other. The tapering of the longitudinal grooves was tedon the depths of the "best" opposed groove design, frmi test O,31lAO,and ratioed to account for the increase in case thicknes!. from 0.5 to0.5625-inch. Calculations are presented below:

For Booster End:

use same ratio as in 0.100-inch deep grooves of QNO311AO.

00 0,5625 x = 0.225 total depth, or 0.113-inch deep

inside and outside]

PAGE 328-1

I

For Non-Booster End:

use same ratio as in 0.130-inch deep grooves of QNO311AO.

0 .260 x[0.?0 - x = 0.293-inch total depth, or 0.146-inchR-5766 0.76625'inside and outside]

The longitudinal grooves were tapered in two styles; one with theinside and outside grooves symmetrical, and one with only the outsidegroove tapered in depth, the inside groove renaining a constant depth.See figure 328-2.

B. Circumferential Grooves

The circumferential grooves were uniformly increased in depth, fraoithe booster end of the warhead. The "best" circumferential groove depthsfron test oti311AO were used as a basis, the depths being increased bythe ratio of the case thicknesses. Calculations are presented below:

For Booster End:

use same ratio as in 0.100-inch deep grooves of QNO311AO,0.260 x

for first 7 rows. [0:500 - 0.5625; x = 0.2925-inch

total depth, or 0.146-inch inside and outside]; for rows

8, 9, 10 ' 0 0.5625' x = 0.3375-inch total depth, or

0.169-inch inside and outsid

For Non-Booster End:

grooves calculate same ratio as in 0.130-inch deep grooves

of 0N0311A0. x = 0.356-inch total depth,or .17-inh 0 .500 0.5625'ue01-ic

or O.178-inch deep inside and outside1 ; use O.190-inchbecause of 18-inch length instead of the 15-inch length inQNO311AO.

C. Booster-End Fragments

The first row of fragments on the booster end of the warhead weretapered, in an attmipt to stop the fragment scabbing problems whichoccurred in the previous test. The fragments were therefore madesomewhat longer to compensate for the weight lost in tapering.

L

I

2.1.5.2 DESCRIPTION OF TEST OBJECTIVES AND TEST ARENA

The test objectives were to recover a sample of fragments fronl eachof the parametric choices in groove design, and to ieasure i ragment p loi -ejection-anqlies and velocities. The test arena details are sho.wn in

Figure 328-8. Photographs of the test arena are shown in Figure 328-11.I2.1.5.3 DESCRIPTION OF TEST RESULTS

A. Fragment Quality

1. Longitudinal Grooves

The longitudinal grooves were of inadequate depth, and the results(of poor-quality fragments) typified by too much metal relliiring betweenthe apexes of the inside and outside grooves occurred in this test, in-cluding a significant amount of scabbing of the fragment. Figure 328-34shows examples of the fragments having the deepest longitudinal grooves(i.e. the thinnest metal remaining between opposed grooves).

2. Circumferential Grooves

Numerous fragment lengthwise pairs were recovered, indicating that thetotal metal remaining between the apexes of the inside and outside cir-cumferential grooves was too thick. Where the inside grooves exceeded0.120-inch depth the non-booster-end inside-corners broke off as illustratedin Figure 328-11.

B. Fragmen9 : t Velocty and Polarc-Angle Characterization o

The ieasurements of the fragment-hit locations are presented on

pages 328-11 and 328-12, but polar-ejection-angles and detailed fragmentvelocities are not presented because the fragment lengthwise pairingsand fragment scabs make identification of the primary fragimentsdifficult. The velocities of the fragments ranged from 5700-ft/sec atthe center-of-length of the warhead to 4900-ft/sec at the ends of thewarhead.

C. Conclusions

1. The warhead design will have to be altered to achieve properfirefoming of fragments.

2. Change the design approach to consider metal reiiaining betweenthe apexes of the opposed-grooves.

PAGE 328-2a

A? A? A2'

SECIO A-A2?-

122

(,I, L T t W IS,,

(UUI~I st I I

AlAlll~

SEC IO A-A B LtJ.

NOTE:A- FRGMN2CS

QUENCHED, ANDRAN.T000 *I

MEJ UE -.003

SECIO B-BU- .10U 0.1483

1~ r i-0

LTETD OI-/2 A .. 20L REFR[HILWAEA

DRASN AT038000

MAGE3A-SFURRE38-

....... ,..., i

TYPE B TYPE AILONGITUDINAL GROOVE LONGITUDINAL GROOVE

-01-BOOSTER i BOosIER1U END END

H.E. H.E.SIDE SIDE

TYPE B1 GROOVE: FILLED Wih 1

LAMINAC

18" 18"

TYPE B2 GROOVE TYPE A, GROOVEPAINTED WITH TY11-LED .;ITIELAM INAG I ILE 871

LAMI NAC

TYPE A, GROOVE= PAINI LI) W III

LAMINAC

.110 .190" 150

263" 9/]6"

..

0PAGE 326-4 FIGURE 3;'[-?-Ik

18" O.D. x.030" STEEL 14" 0.0. x.020" STEEL 1" URETHANE FOAM

SHROUD FOR 11-1/2"1 0.D. 200-LB WARHEAD

TEST ON0328A0

0PACE 328-5 FIGURE 328,-3

TEST: QN0328A0

I0

I [A

I WARHEAD ON LATHE DURING MANUFACTURE

20 .I COMPLETED UNLOADED WARHEAD

1 FIE FOMEDSHOWING EXTERIOR GROOVING

tuBAL WARHEAD,

I -- 3-28-80:

PAGE 328-6 FIGURE 328-4

ITEST: ON0328A0

NMIL

WARHEAD BEFORE BEING LOADED WITH EXPLOSIVESHOWING INTERIOR GROOVING

14~

PAGE 328-7 FIGURE 328-5

TOTAL METAL REMAININGBETWAEENCIRCUMFERENTIAL LGROOVES WAS TOO THICK,AS ILLUSTRATED BY .FRAGMENT LENGTHWISEPAIRING

' -, -

o 1 1INCHES

QN0328AO

RESULTINGFRAGMENTSHAPE

FRACTURE

LONGITUDINAL GROOVE

REDUCED-WEIGHT FRAGMENTS RESULTING WHEN THE METAL REMAINING BETWEENL INSIDE AND OUTSIDE LONGITUDINAL GROOVES WAS 0.240" THROUGH 0.260"

EXAMPLE FRAGMENTS FROM TEST QN0328AOPAGE 328-8 FIGURE 328-6

METAL REMAINING BEWECIRCUMFERENTIAL

GROOVES WAS TOU THICK,AS ILLUSTRATED BYFRAGMENT LENGTHWISE

1 PAIRING

1 2INCHES

0N0328AO

EXPLOSIVE, SWEEP,! DIRECTION/4- FRACTURE LINE

INSIDE CASE

I.ILLUSTRATION SHOWING THE FRACTURE WHICH OCCURRED WHEN THE

11SIDE CIRCUMFERENTIAL GROOVES EXCEEDED 0.120" DEPTH

EXAMPLE FRAGIIENTS FROM TEST ON0328AO

0PAGE 328-9 FIGURE 328-7

I 1 EA SPLIT FRAME FASTAX2 EA FASTAX CAMERAS (GROUND LEVEL)

1 SPLIT FRAME, 1 FULL. FRAME

6' x 12' HIGH.105" STEEL

~ WITNESS PLATE

9' x 13' HIGH* .105" STEEL WITNESS SHEET 6"

IN FRONT OF 1/4" THICK STEEL PLATE 30'

20'

13'13'

13'

12 EA CELOTEX 13' 13'

PACKS

13'1

113'

WARHEAD 13'

13'13'

[

TEST QN0328A0

11-1/2" O.D., 200-LB FIRE FORMED tIBAL PARtlEAD

PAGE 328-10 FIGURE 3?8-8

TEST QN0328A9

COORDINATES* OF FRAGMENT HIT LOCATIONS (INCHES)ON THE WITNESS SHEETS

FRAGMENT 20' RADIUS WITNESS SHEET COORDINATES __

ROW C[MN COLUMN COLUNN ] COLNUMBER 1 2 3 4'-

1 -46-1/2 +35 +42 +442 -50 +34 +41 +25-1/?3 -49 413 +21 +54 -63-1/2 +3.5 +11 -3-1/25 -5.5 +8 -116 -20** -6 -18-1/27 -28** -22** -22-1/28 -32-1/2** -24 -29**9 -32 -29-1/2 -34**

10 -35 -35 -36**11 -38-1/2 -34-I/2"* -41 l

12 -42-1/2** -37 -4313 -36-1/2 -43-1/2 -44-1/214 -41 -42 -4415 -42 -46** -4516 -43 -48 -5217 -45 -48-1/218 -46-1/2 -4519 -48 -4820 -63 -4921 -62-1/2

* VERTICAL MEASUREMENTS ARE MEASURED FROM THE TOP OF THE WARHEAD AIMLINE(BOOSTER WAS ON TOP OF WARHEAD.)

** FRAGMENTS PAIRED TOGETHER

.

UPAGE ,128-11 FIGURE 32,8-9

K I TEST Oo328AO

VERTICAL MEASUREMENTS* OF FRAGMENT HIT LOCATIONS

K I (INCHES) ON THE WITNESS SHEETS

30' RADIUS WITNESS SHEET

FRAGMENT COLUMN COLUMN*** COLUMNNUMBER 1 2 3

1 -.39 +68 +61-1/22 -47 +55 +283 -41-1/2 +31 -4-1/24 -62-1/2 +9-1/2 -45 -64-1/2 +2 -66 -87 -9-1/28 -12-1/29 -17-1/2

10 -22**11 -26-1/212 -2913 -30-1/214 -34-1/215 -3416 -34-/1217 -35-/1218 -34-/1219 -3620 -37-1/221 -4122 -4423 -43-1/224 -41-1/225 -42-/1226 -46-1/227 -68-1/2

VERTICAL MEASUREMENTS ARE MEASURED FROM THE BOTTOM OF THEWARHEAD AIMLINE (BOOSTER WAS ON TOP OF WARHEAD.)

**FRAGMENTS PAIRED TOGETHER

*** THE NUMBER OF FRAGMENT LISTED IN COLUMN 2 EXCEEDS THE NUMBEROF FRAGMENT ROWS IN THE WARHEAD BECAUSE THE FRAGMENTS WERESCABBING

PAGE 328-12 FIGURE 328-10

I

I TEST: QN0328AO

I

TEST ARENA BEFORE DETONATION

WARHEAD IN POSITIONIN TEST ARENA

I.

PAGE 328-13 FIGURE 328-11

i 77 ,

7AD-AGOX I7 NEW MEXICO INST OF MININGe AND TECHNOLOGY SOCORRO TER--ETC F/G 19/1

01 HIBAL PROSIRAM PRELIMINARY WARHEAD-DESIGN. VOLUME I.(U)SEP so N00024-79-C-5333

UNCLASSIFIED NMT/TERA-T - B01356U V0L-NL

I TEST: QNO328AO

I!

.I

WITNESS SHEET AT 20' RADIUS SHOWINGFRAGMENT HIT LOCATIONS

(5/8-inch SPACING BETWEEN LONGITUDINALGROOVES, SYMMETRICALLY TAPERED, H.E.-FILLED)

[ PAGE 328-14 FIGURE 328-12

3 TEST: QN0328AO

II

WITNESS SHEET AT 30' RADIUS SHOWINGFRAGMENT HIT LOCATIONS

(5/8" SPACING BETWEEN LONGITUDINALGROOVES, SYMMETRICALLY TAPERED IN-SIDE AND OUT, LAMINAC-FILLED)

PFPAGE 328-15 FIGURE 328-13

I

I1I

TEST QNOLIO9AO

I 19' ANNULAR, 200-LB FIREFORMED FRAGMENT/PREFORMEDFRAGMEN1 COMBINATION WARHEAD

II

I.

II.IIIIIU

I

2.1.6 TEST 5, QNO4O9AO

2.1.6.1 nESIGN SUMMARY AND RATIONALE

This warhead was partly firefonned fragments and partly prefonmedfragments. The basic design characteristics of the warhead (Figures 409-1thru 409-3) were:

OUTSIDE DIAMETER: 19-inchINSIDE D IAMIETER: 10.5-inch

LENGTH: 12-1/2-inchCASE THICKNESS: 0.5-inchCASE MATERIAL: SAE 4130, (RC-42)WARHEAD WEIGHT: 200-lbSHROUD: 0.080-inch titanium for preformed fragment

side, 0.020-inch titanium for fireformedfragment side, plus 1-inch urethane foaminsulation between warhead and inner shroud

Three sizes of hex-HIBAL fragments were tested, 500-grain (7/8-inchacross flats x 0.47-inch thick), 700-grain (1-inch across flats x 0.47-inchthick) and 900-grain (1-1/8-inch across flats x 0.47-inch thick). Thefragments were layed up inside a 0.030-inch skin (mild steel) and pottedin laminac.

The firefonned fragment case was grooved circumferentially to provide14 rows of equal length fragments, each 0.886-inch long. Three choicesof spacing between the longitudinal grooves were evaluated, 0.633-inch,0.886-inch and 1.139-inch. The theoretical fragment weights for thesespacings (with no loss in firefonning) were 550-, 770-, and 990-grains.

The decision was made to investigate the possibility that the metalremaining between opposed grooves was the critical design factor, asopposed to the groove depth or ratio of groove depth to case thickness.The most successful warhead design of the first three tests was the firsttest (ON0225AO), the design for QNO4O9AO was therefore based onit.

A. Longitudinal Grooves

The best fragment longitudinal breakout in test QN0225AO occurred formetal-thickness-remaining values of 0.193 to 0.238-inch. For test Q(O0409AO,the metal-thickness remaining between longitudinal opposed grooves wasvaried from 0.190 to 0.260-inch.

The depth of all inside longitudinal grooves was also made0.110-inch, so as to equal the depth of the circumferential grooves (Seediscussion below.)

PAGE 409-1

Ii

Ia

I B. Circumferential Grooves

The results of QN0225AO indicated that no doubles occurred for metalthickness values remaining of 0.160-inch or less for the non-booster-endfragments. For 0NJ409AO, the metal reiaining values were varied fran0.140-inch to 0.248-inch.

I The inside circumferential grooves were uniformly 0.110-inch deepto prevent the inside non-booster-end corner from breaking off. Theoutside circumferential-groove depths were each varied fron 0.142-inchdeep to 0.250-inch deep. By using this design, the data should providea guide to the required groove depths (as a function of groove distancefran the booster end) to prevent the fragment doubles.

The circumferential and longitudinal groove designs are summarized

in the table below:

LONGITUDINAL CIRCUMFERENTIALGROOVES GROOVES

INSIDE OU(TSIDE METAL INSIDE OUTSIDE METALDEPTH DEPTH REMAINING DEPTH DEPTH REMAINING(inch) (inch) (inch) (inch) (inch) (inch)

0.110 0.130 0.260 0.110 0.142 0.2480.110 0.140 0.250 0.110 0.155 0.2350.110 0.150 0.240 0.110 0.171 0.2190.110 0.160 0.230 0.110 0.188 0.2020.110 0.170 0.220 0.110 0.207 0.1830.110 0.1P0 0.210 0.110 0.221 0.1690.110 0.190 0.200 0.110 0.242 0.1480.110 0.200 0.190 0.110 0.250 0.140

The preformed fragments were fired through a 0.080-inch titanium shroudand the fireforned fragments were fired through a 0.020-inch titanium shroud.

[PAGE 409-2

2.1.6.2 DESCRIPTION OF TEST OBJECTIVES AND TEST ARENA

The objectives of the test were to measure fragment pattern andvelocity for both the firefonned and preformed fragments, and to recovera large sample of the fireformed fragments. The test arena is presentedin Figure 409-8, with photographs appearing in Figures 409-14 through K409-1 6.

2.1.6.3 DESCRIPTION OF TEST RESULTS

A. Fragment Quality

Since all inside grooves were 0.110-inch deep, the results aresegregated below by outside longitudinal-groove depths.

1. Outside Depth = 0.130-inch (Remaining Metal = 0.260-inch)

No recovery was made of fragments.

2. Outside Depth = 0.140-inch (Remaining Metal = 0.250-inch)

Ten fragments were recovered which were 0.886" wide, all ofwhich were very good quality. The minor fault of the fragmentswas that some "borrowing" was evident on all fragments, bothcirctnferentially and longitudinally.

Twelve fragments were recovered which were 0.633-inch wide.Five of these fragments (fron rows 9 through 13) were joinedtogether in a string. Three of the remaining seven fragments werescabbed. The longi tudi nal -groove breakout was excellent for all butthe scabbed fragments. The circumferential-groove depth for thisfragment string was 0.155-inch outside, thus leaving 0.235-inchremaining metal.

3. Outside Depth = 0.150-inch (Remaining Hetal = 0.240-inch)

Six fragments were recovered, two of which scabbed. Borrowingwas evident to a slight degree on both the longitudinal andcircumferential grooves.

4. Outside Depth = 0.160-inch (Remaining Metal = 0.230-inch)

Nine fragments 0.886-inch wide were recovered, two of whichwere in a doublet. The doublet was in rows 12 and 13; thecircumferential groove depth being 0.188-inch at this point(0.202-inch remaining metal). Borrowing was evident Lo a slightdegree on all the fragments. One fragment was a partial.

Eight fragments 0.633-inch wide were recovered, including twodoublets, rows 10, 11 and rows 12, 13. Slight borrowing wdSevident on the longitudinal grooves of the doublets. All otherfragments scabbed.

.i ~PAGE 409-3

iT.

5. Outside Depth = 0.170-inch (Remaining Metal = 0.220-inch)

Three fragments, 1.139" wide, were recovered. Two were in adouble (rows 3, 4) and scabbed. The appearance of the scabbedfragment was different than scabbed fragments previouslyrecovered in that the scabbed face was very smooth. The thirdfragment, from row 2, had borrowing on all four sides.

Eight fragments were recovered which were 0.886-inch wide.Four of the fragments were scabbed (not the "smooth face" scab).remaining four had excellent-quality breakout UAong the longi-tudinal grooves, but showed evidence of borrowing along thecircumferential grooves.

6. Outside Depth = 0.180-inch (Remaining Metal 0 O.210-inch)

Nearly complete success was achieved, in that the frag-ments averaged 911-grains weight, or about 90,% of theoretical.

Eleven fragments (1.139-inch spacing) were recovered (nodoublets). Slight borrowing was evident on the longitudinalgrooves for all the fragments. There was one partial frag:ent.Borrowing was evident circumferentially on two of the fragments,row 3 and 13. The outside circumferential-groove depth was0.221-inch, or 0.169-inch remaining metal.

7. Outside Depth = 0.190-inch (Remaining Metal 0 O.200-inch)

Nearly complete success was achieved, in that most, frag-ments were excellent quality, averaging 732-grains each, or about

95% of theoretical.

Twenty two fraginnts were recovered (0.886-inch wide), includingone double (rows 4, 5) and one scabbed fragment (row 10).

The 0.020-inch titanium shroud left an imprint on the frayments,which had not occurred in any of the previous tests. No otherdamage than the imprint can be attributed to the shroud.

Recovered fragment weights are presented on page 409-24.

B. Fragment Pattern and Velocity

The fragment polar-angle and velocity characterizations, for boththe preformed and firefonned fragments, are presented in Figures 409-5through 409-7. The data for the firefoned fragments are not as cL:mpleteas the data for the preformed fragments because the column of fragm:entswhich was intended for velocity and polar-anjfe characterization did notproperly breakup, circumferentially (i.e., fragment mnltiples occurred).The data are presented in Figure 409-8 and 409-9.

PAGE 409-4

.. . ... ........

I

C. CONCLUSIONS

1. Firefoned Fragment Warhead

a. Longitudinal opposed grooves which provide for 0.250-inch orless metal remaining between the apexes of grooves will provide for

j proper case breakout along the longitudinal grooves.

b. For fragments near the booster end of the warhead, clrcumferen-tial grooves should provide for about 0.240-inch remaining metal betweenthe apexes of the grooves. For fragments near the non-booster end ol

the warhead, the circumferential grooves should provide for about 0.200-inch relaining metal.

2. Prefoned Fragment Warhead

There is no need for further 19-inch diameter, 200-lb preformed

fragment warhead tests. The fragments were satisfactory in quality, asjudged fran the witness sheet pattern, and the pattern and velocitydate were adequate to fonulate warhead characterization models for thesecond phase end game analysis.

PC4.

I PAcf: 409-

, ... 2" 1P x

C3G EXPOSVE INSIDE

/ /:,, i" "LONGI TLID NAL

I -.- G ROV ES

,.. I .... _ _. B I

_-- -/ j/--461,

0.0HIG Ex PLOSI"VGROVE

OUTSIDE

10 5 . .. . .. .. ..- ST E]- 19"LDIAITUDINALGROOVES

SECTION: A-A BOOSTER V

A iA

STEEL .c{* i

HIBAL9 D U AE

--I NS I D

PAGk CIRCU E - RENTIAL0.03".-. . . GROOVES

STEEL P 4 0 025"' r 4- O UTS I D

~~~~ C STI '- JRCIJIi LRE14T]I

U____ ELLO 5~ jO.~J. GROOVES IAl

L.SECTION: B-BC)L

1 19" 0AD ANNIJIAP WARHEAD--PAGE 409-6 rIGLIRE 409-I

LnI

LLCM

-34

U,<

L~~~~~> PAE=97FGR 0-

uj uj t

II

V~ I i f 00S I VL C I RC;M~f K I N1I fA Ik' E S

in tn w w. -c at (D - '1 - '

L c> C 3 , c c: C3 : c:; c:; c D c :; o C 6 6 CD C :; c

~DEPTH P O ALLI S IDE LON GITUDINAL G OOVE S D.

t DEPTH OF ALL NSIDE CIIHFEETA GROE OU 0.S0 DEP

81__ CI i I El Fl 0 ] H l LI M I I 01 P1 I1 1 I T SI t ,

B? LDEPTH OF ALL INSIDE CIRCUM'FERENTIAL GROOVES = 0.110" DEEP .

VIEW: A-C IRCUMIFERrN TIAL GROOVES /. -\ LONGITUDINAL GROOVES'

7 BOOSTER END ... i

81B ci 01 Ej Fl GI/r HI ..... Kj L , M IN 0I- P1 Q1 P1 .l TI 01,..X1. _

85A 8

B5

66

8712.5"

B8

B9

8 10

Ell

B12

BI4

FRAGMENT )WEIGHT C) Co D C C) C3 (4 C3 C) ro ) "" CD(GRAINS) ' ' U '., .,U C,. I1&1

G-ROOVE Y . .. U) 'n p. , o , ,^ w w ",SPACIN G - o o ) o '- o o o o .-W t ) U) ) - to ? D 1 ILI

(ICH C)Z ) c) C), C)D C 3 c) C)0 -4 C3 CD m) C3 CD C) C) C) <)

O.646 - - 4.177" 4.177" -4.177" j77O

18" -

GROOVE DETAIL FOR FIRE-FORMILD FRA,.[NTS

L. 19 " O.D. ANNULAR WARHEADTEST: QN04O9AO

PAGE 409-8 FIGURE 409-3

I" URETHANE FOAM INSULATION

.080" TITANIUM 1800(for preformed .020" TITANIUM 1800

fragmnts)(for fireformedfragmen ts)

13"11

-d 22"

SHROUD USED IN TEST QN040O9AO

FOR THE 19" Q.D. ANNULAR WARHEAD

LPAGE 409-9 FIGURE 409-4

I TEST: QN04IO9AO

IR A

WARHEAD BEFORE BEING LOADED WITH EXPLOSIVE

ti1

PAGE 409-10 FIGURE-409- 5

I

"II

I I

0 1 2 LINCHES

QNO4O9AO

4- FRAGMENTSHAPE

FRACTURE LINE

LONGITUDINAL GROOVE

H.E. SIDE

FRAGMENT SHAPE RESULTING WHEN THE METAL REMAINING BETWEEN

LONGITUDINAL INSIDE AND OUTSIDE GROOVES IS BETWEEN 0.200" AND 0.240"

EXAMPLE FRAGMENTS FROM TEST QNO409AOPAGE 409-11 FIGURE-409-6K-:_ -TILT LL- ... .' -;LLi'. ,-_ [_. ,. ....-

INHEQN40A

REUTNFRGMNI SHAPE

FFRAGMENT

LONGITUDINAL GROOVE

REDUCED-WEIGNT FRAGMENTS RESULTING WHEN THE METAL RE,"AIN.If, BETW'EENINSIDE AMD OUTSIDE LONGITUDINAL GROOVES WAS 0.240" THROUGHi 0.260"

j EXAMPLE FRAGM-UIITS FROM TEST QN9'409AO

[PAGE 409-12 F IGURE- 409- 7

2 FASTAXCAMERAS

TARGETS: A, B, C, D, E 4'x4'x8'-HIGH CELOTEXjI PACKS WITH 1/21 STEEL BACKPLATES

TARGETS: F, G, H, J * 2 EA. 4'-WIDE, 12--HIGH,0.105"-TIIICK STEEL PLATES. SPACED611 APART.

20 'R

WARHEAD

10'0

15'R

G 15'R

15'R

H

2 FASTAXCAMERAS

ARENA FOR TEST QN0'409AO

LPAGE 409-13 FIGURE-409-i8

TEST QN0'409A0

SUMMARY OF FRAGMENT POLAR EJECTION ANGLE AND VELOCITYRESULTS FOR HEX HIBAL FRAGMENTS THROUGH

.080'; TITANIUM SHROUD

FRAGMENTC.G. DISTANCE FRAGMENT HIT LOCATIONS

FRAGMENT IFROM BOOSTER RELATIVE TO BOOSTER-END POLAR AVERAGEROW' END (INCHES) 500-gr 700-gr 1900-gr jANGLE VELOCITY(O-15')

1__ 5)__0.8__+45.5____14.40__3400

1(7) 0.9 +47.3 +15.00

1(9) 1.0 +20.5 +6.802(5) 1.6 +16.5 +5.70 38002(7) 1.8 +13.5 +4.902(9) 1.9 +1.3 +1.003(5) 2.3 +3.3 +1.80 42003(7) 2.6 0 +0.803(9) 2.9 -4.8 -0.604(5) 3.1 -2.5 +0.20 44004(7) 3.5 -5.8 -0.705(5) 3.8 -8.0 -1.30 46004(9) 3.9 -10.0 -1.905(7) 4.4 -12.7 -2.606(5) 4.6 -12.3 -2.40 46005(9) 4.9 -16.0 -3.506(7) 5.2 -16.3 -3.507(5) 5.4 -16.0 -3.40 48006(9) 5.8 -19.3 -4.307(7) 6.1 -20.7 -4.608(5) 6.1 -18.5 -3.90 48007(9) 6.8 -20 -4.209(5). 6.9 -19.8 -4.10 49008(7) 7.0 -20.3-4210(s) 7.6 -22.3 -4.70 49008(9) 7.8 -24.8 -549(7) 7.8 -25.2 -5.50

11(5) 8.4 -25.0 -5.30 490010(7) 8.7 -25.3 -5.309(9) 8.8 -28.3 -62

12(5) 9.2 -25.0 -5.00 490011(7) 9.6 -28.8 -6.1010(9) 9.7 -28.5 -6013(5) 9.9 -27.5 -5.60 490012(7) 10.4 -29.2 -6.0011(9) 10.7 -29-5814(5) 10.7 -28.8 -5.70 460013(7) 11.3 -35.3 -7.6015(5) 11.4 -30.8 -6.20 450012(9) 11.7 -37.3 -8.1014(7) 12.1 -44.8 -10.3"L16(5) 12.2 -41.3 -9.2() 4500

1NUMBERS IN PARENTHESIS INDICATE FRAGMENT SIZE

I PAGE 409-14 F1C(LRE-409-9

*LLJ =

Li ii

I--LL-

LLj-Cl

(LU -L

V)a U- C)

C) 'C) = C)x

i OLLJ 0

LL10 *iCL)i. : C/ = _T

tO) 00 Cz C

-JJ - C

LI) 0mC

LOi

LAO

~0C) uj

UU

Ii

TEST QN04O9AO

FRAGMENT VELOCITY AND POLAR ANGLES FOR FIREFOR.IEDFRAGMENTS THROUGH 0.020" TITANIUM SHROUD

POLAR FRAGMENTFRAGMENT EJECTION AVERAGEROW* ANGLE VELOCITY (0-20-ft)

1 50 4300

2 2.70 4800

3 -0.60 5260

4 -0.90 5260

5,6 -3.00 5400

7 -4.60 5500

8,9,10 -5.30 5500

11,12 -.550 5500

13

14

*THE FRAGMENT ROWS LISTED IN THE SAME LINE WERE JUDGEDTO BE PAIRED TOGETHER BASED ON THE HOLE SIZES IN THEWITNESS SHEETS.

..

TEST QSHEETS

VERTICAL MEASUREMENIS*OF FRAGMENT HIT LOCATIONS

* 9O0UJGR1N HEX -HIBAL, lYi RbDIUS -

-FRAGMENT CO-L-UMN -- CO-LUMN --- CO L-UAN COLUMNROW 1 2 3 4 AVERAGE

1 -22 -19 +20.52 +0.5 -2 +1.33 -5 -4.5 -4.84I1 . 9. 1 .4 -10.5 -9.55 -10.06 -20 -18.5 -19.3

7-19 -21 -208-25.5 -24 -24.8

9 -28 -28.5 -28.310 -30 -27 -28.511 -29 -29 -2912 -38 -36.5 -37.3

FIRE-FORMED HIBALS -20' RADIUSFRAGMENT COLUMN

ROW 1

1 +20.52 +10.03 -5.04 -7.05 -17O*

6 -ii'oJ FRAGMENT DOUBLE7 -26.58 -309 -30 FRAGMENT TRIPLE

1 0 -30)I11 -33 FRGMN DOUBLE12 -33 )J13 - (HIT BELOW WITNESS SHEET)14

*VERTICAL MEASUREMENTS ARE FROM THE TOP OF THE WARHEAD AIMLINE.

[PAGE 409-17 F[GURE-409-I?

..........

TEST ON040O9AOVERTICAL MEASUREMENT* OF FRAGMENT HIT LOCATIONS

(INCHES) ON THE WITNESS SHEETSI ~500-GRAIN HEX HILBAL ___

FRAGMENT COUMN -COLUMN COLUMN COLUMNROW j 1 2 3 4 AVERAGE

1 +45 +46 +45.52 +18 +15 +16.53 +2.5 +4 +3.34 -2 -3 -2.5I5 -9 -7 -86 -12 -12.5 -12.37 -16.5 -15.5 -16.08 -18.5 -18.5 -18.59 -21 -18.5 -19.8

10 -22.5 -22 -22.311 -25.5 -24.5 -25.012 -25 -25.013 -28 -27 -27.514 -29.5 -28 -28.815 -31.5 -30 -30.816 -43.5 -39 -41.3

___ 700-GRAIN HEX HIBAL ____

FRAGMENT COLUMN COLUMN COLUMN COLUMN COLUMN COLUMNROW 1 2 3 4 5 6- AVERAGE

1 +45.5 +47.5 +49 +47.32 +13 +14 --- +13.53 -0.5 0 +0.5 04 -6 -6.5 -5 -5.85 -12 -13 -13 -12.76 -15.5 -17.5 -16 -16.37 -20.5 -22 -19.5 -20.78 -15.5 -23 -22.5 -20.39 -25 -25.5 -25 -25.2

10 -22.5 -27 -26.5 -25.311 -29 -28 -29.5 -28.812 -26 -30 -31.5 -29.213 -35 -34 -37 -35.314 - -42.5 -47 -44.8

*VERTICAL MEASUREMENTS ARE FROM TOP OF WARHEAD AIMLINE

PAGE 409-18 FIGUR[-409-13

is'low

I TEST: QN040O9AO

WARHEAD AT TEST SITE WITH SHROUD REMOVED

PAGE 409-19 FIGURE-409-14

7i

TEST QN0409AO

NM.

WARHEAD AT TEST SITE WITH SHROUD INSTALLED

IPAGE 409-20 FIGURE-409-15

ell. . kool*v

3 TEST: QN0'409A0

Ch - ;t

TEST ARENA~ BEFORE DETONATION

IPAGE 409-21 FIGURE-409-16

Mao

TEST: QNOLO9,AO

V.1A

500-gr FRAGMENT WITNESS SHEET AFTERA( 11TEST; 15' RADIUS

700-gr FRAGMENT WITNESS SHEETAFTER TEST; 15' RADIUS

PAGE 409-22 FIGURE-409-1.7

900-GRAIN FRAGMENT WITNESSSHEET AFTER TEST; 15' RADIUS

_T;-

FIRE-FORMED HIBAL WITNESSSHEET AFTER TEST; 20' RADIUS

I ; PAGE 409-23 FIGURE-409-1B

::li ... . . ... . , .. . . _ -. . .

I I ~LI I lh: (i :!uI.<I;L C.l btkLLM~i~h I,', ui14; S

I4 11-L CI C; C; I . 3 t.3 C). 0N Cl C> CD C 3 c;

D !JCfJH U OUTSIDL LO II LJ! , UhLAA, S,

* ~ ~ ~ ~ ~ ~ 1 C)L .C ( ., 3. 4

tC --. ,. ..) y _. _ x . . ,,_ _ '_. ,, ..1_ * =- - .- --- ,_- - .- l x *4 _ . . .. _ .. --J

DlITH GF ALL INSIDE tMOGITUDINAL GROUVL S 0.110" V; i P

- DEPTH OF ALL INSIDE ClRCU'lRIEI[TIAL GROUVLS = 0.110" Lt.P

CiRCULI ER[ MAiL GROOVES -- LONGITUDINAL GROOVES

-FOSF - f-N,_ -j

COLU" ,-

2 92 741 790 370 577 383 867 975 '782 387 755 733

3 83 799 556 427 '95 8 745 4,14 932 739 730 TA 4 473 682 1994 730 894 fI 4 q9 709 A

5 85 784 3611 T14S 745 1 332 93? 733

6 86 560 750 716 904 748 721

7 B7 769 244 583 731 909 713 2. 5"

8 B8 742 565 560 636 162 894, 708 719

9 59 1731 t8.09 765 603 932 745

10 B 0 927 715 213

i 111 704 I 846 741

12 812 1525 932 722

13 B13 775 -1 784 965 744

14 11 819 616 622 838 830 779 792 93

FI A (C1) 14 S) r c C. C ) I'D C) CS 1 ) c

( IFIt C C) . I r ;3 6C-1 (4 C S ( C 43 C,(6k IN )1 21cI

6RMOVE ("AI fORN . ;R -r.)1_I - V,%(;: I''

~~F'Ar ~ ~ I IV III u: C) U L -1 c' . ) 4(4 .. 0 ua 4) V '4 C n) S )~71.A II NG.7? -1INCH)0 C 4 C '1 ) C 3 0 f 1 0: C) C D C): C)> c) 4)

GkOOVE. orTAIL.o IN.- fILuiNS

RECOVERED FRAGMENT WEIGHTS (GRAINS)*Assuning 10% weight TEST: QNO409AO

I loss in fireforming.PAGE 409-24

FIGURE 409-19

.maw . . ... 'a' - '... , .

IIIIII

I.

ITEST QNOLI29AO

11.5", 200-LB, PREFORMED-FRAGMENT/F iREFORMED-FRAGMENT COMB INAT ION-WARHEAD

IIIII1II1II

* ~

I

2.1.7 TEST 6, QN0429AO

I 2.1.7.1 DESIGN SUMMARY AND RATIONALE

This warhead was a combined (preformed plus firefonmed) fragment warhead.The basic design characteristics of the warhead (Figure 429-1 and 429 2)were:

OUTSIDE DIAMETER: 11.5-inchINSIDE DIAMETER: 2.875-inchLENGTH: 18.375-inchCASE THICKNESS: 0.563-inchCASE MATERIAL:

Preformed Fragments: SAE 4130, RC44-47Fireformed Fragments: SAE 4140, RC37-42

SKIN THICKNESS:Preformed Fragments: 0.015-inch (mild steel)

WARHEAD WEIGHT: 200-lbSHROUD: Two steel skins, 0.020-inch inside,

0.030-inch outside, plus 1-inch urethanefoam insulation between warhead andinner shroud

The prefomed hex-HIBAL fragments were all 0.548-inch thick, and werethe following sizes: 3/4-inch across flats (500-grian); 7/8-inch acrossflats (700-grain); and 1-inch across flats (900-grain). They were packagedwith a 0.015-inch steel outside skin and potted in laminac.

The fireformed-fragment case was grooved circumferentially to provide19 rows of equal-length fragments, 0.888-inch long. The spacing betweenlongitudinal grooves was 0.75-inch. No variation in spacing betweenlongitudinal grooves was made because it was not judged that the spacingbetween longitudinal grooves would affect the fragment quality. Thetheoretical weight of the fragments (before any weight loss due tofireforming) was 750-grains.

A. Longitudinal Grooves

0.250-inch metal thickness remaining between grooves (or less)resulted in good fragment breakout longitudinally in test QNo4o9AO. Soin test QN0429AO the grooves were varied so as to achieve metal thicknessremaining values from 0.248 to 0.273-inch, to explore how thick metalremaining between grooves can be and still produce good fragments.

The inside longitudinal grooves were all made 0.100-inch deep. Theoutside longitudinal grooves were varied in depth to provide the range ofvalues of metal thickness remaining between inside and outside groovesdesired. The groove depths are summarized below.

PAGE 429-1

K ,

METALREMAI NI NG

IN-SIDE OUTSIDE BETWEENDEPTH DEPTH GROOVES(inch) (inch) (inch)

0.100 0.190 0.273I 0.100 0.195 0.2680.100 0.200 0.2630.100 0.205 0.2580.100 0.210 0.2530.100 0.215 0.248

B. Circumferential Grooves

Metal thickness remaining between opposed grooves should be aboutt'-e same as what worked in previous test. Metal thickness remainingvalues = 0.243-inch near booster end = 0.193-inch near non-booster end.

All inside circumferential grooves were 0.110-inch in depth, to pre-vent the inside non-booster-end corners of the fragments from breakingoff. The outside circumferential grooves were made deep enough to reducethe metal tickness between the apexes of the opposed grooves to the valuefor which no fragment doubles had been recovered in test 6. The depthsare presented below, groove-1 being nearest the booster end.

METALREMAINING

INSIDE OUTSIDE BETWEENGROOVE DEPTH DEPTH GROOVESNIIBER (inch) (inch) (inch)

1 THRU 6 0.110 0.210 0.2431 THRU 19 0.110 0.260 0.193

2.1.7.2 DESCRIPTION OF TEST OBJECTIVES AND TEST ARENA

The test objective included characterizing the polar ejection anglesand the velocities for the preformed fragments, and recovering a sample ofeach preformed-fragment size to determine if damage resulted during thedetonation or fron the fragment perforating the shroud. Fragment recovery,only, was desired, for the fireformed fragments. The test arena isillustrated in Figure 429-6, and photos appear in Figure 429-12.

PAGE 429-2

!I

2.1.7.3 rESCRIPTION OF TEST RESULTS

A. Fragment Ouality

1. Firefonmed Fragments

The longitudinal-groove designs were inadequate in that the metalremaining between the inside and outside opposed grooves was toothick. Example fragments are shown in Figures 429-4 and 429-5. Also acontributor to the poor longitudinal breakout (which is demonstratedin the following test) is the too-shallow depths of the inside groove.

The recovered fragments were of such poor quality that it was

decided there was no useful information to be gained by weighing than.

2. Preformed Fragments

The fragment quality was excellent. The fragments exhibited someminor deformation from the explosive sweep, but lost no weight.

B. Fragment Velocity and Pattern - Preformed Fragments

A summary of the fragment velocity and polar ejection-angles forthe hex-HIBAL fragments is presented in Figure 429-7. The fragmentpolar ejection angles are plotted as a function of the fragment center-of-length distance from the booster-end of the warhead in Figure 429-8.Measurements of the fragment-hit locations are presented in Figures 429-9,10, 11. Photographs of the fragment pattern are presented in Figure 429-13.

COMCLIISIONS

1. Firefonmed Warhead

a. Opposed longitudinal grooves should have maximum of 0.240-inchremaining metal between the apexes of the opposed grooves to achieveproper breakout.

b. The circumferential grooves will have to be deeper, so as toreduce the metal thickness remaining between the apexes of the groovesto less than 0.193-inch.

c. The Celotex recovery may have contributed to fragment breakupin test QNO4O9AO. In the next test more witness sheets should be usedto verify fragment lengthwise breakup prior to impact on the Celotex.

2. Preformed Warhead

There is no need for further 115-inch diameter, 200-lb preformed-fragment warhead tests. The quality of the recovered fragments wasexcellent and the fragment velocity and pattern were within acceptablebounds.

PAGE 429-3

--- --- mom

I HEX tUBAL -FRAGMENTS OLPTH OF OUTSIDE t

900-rainLONGITUDINAL GROOVES

20 ROWSALL INSIDEI.O.NGITUDINALGROOVES: 0.1"

-DEPTH, 3/4" SPACING

700-gra in781ACROSS 14

FLATS I

23 RWS1'0

LI0.10"

27- RORWOLWCS

2.OALTES: D RO.1.FILLED WITH

PREFRMEDHEXHIBAL R1GETCSFRAMEN MTRICKLS MAERA bA

OIL~~~ ~ ~ ~ QUNHD AND DRW 0OVETRAEOI19 D1PTH CE.DA.I

CI~cUMEASUREMENT

TEST QNO37-42

NiAGl49- FIGUED 429-1

loom,

CIA LO CD. *

001

CCcj

A~. C) ) f

C'CD

_jt1~ 2~-

W~ V LL-CD~. 000, V

L.)r LO> C)<

I x.

A--

LL

N44PAE49-LiIUR 2-

LL- V)

V -.- ,

18" O.D. x.030" STEEL 14" 0.0. x.020" STEEL 1" URETHANE FOAM

I I 20"1

SHROUD FOR 11-1/2", 0.D. 200-LB WARHEAD

TEST QN0'429AO

PAGE 429-6 FIGURE 429-3

IAli

I

TOTAL METAL REMAININGBETWEEN CIRCUMFEREN-TIAL GROOVES WAS TOOTHICKAS ILLUSTRATEDBY FRAGMENT LENGTHWISEPAIRING

INCHES t

QN0429AO

~III3RESULTINGFRAGMENTSHAPE

\I -

9

FRACTURE

LONGITUDINAL GROOVE

REDUCED-WEIGHT FRAGMENTS RESULTING WHEN THE METAL REMAINING BETWEENINSIDE AND OUTSIDE LONGITUDINAL GROOVES WAS 0.240" THROUGH 0.260"

EXAMPLE FRAGMENTS FROM TEST QN0429AO

V PAGE 429-7 FIGURE 429-4

.... '~ - - '-4I I

II

II ,

INCHESQN0429A0

RESULTINGFRAGMENTSHAPE

' /

H.E. SIDE

FRACTURE

LONGITUDINAL GROOVE

° REDUCED-WEIGHT FRAGMENTS RESULTING WHEN METAL REMAINING

BETWEEN INSIDE AND OUTSIDE LONGITUDINAL GROOVES WAS 0.280" OR MORE

EXAMPLE FRAGMENTS FROM TEST QN0429AO FU 49PAGE 429-8 FIGURE 429-5

ITARGETS 1-15 = CELOTEX PACKS

TARGETS A, B, C = .105" STEEL WITNESS SHEETS, 12' HIGH(NOTE: A, B DOUBLE SHEETS WITH 6" SPACING)

I p

I13 4 5- 6 7 8 9 10

2 11

1'112

1

Ii

1515 155'

900-grain 1 500-grainHEX HIBAL HEX HIBAL

j /700-grainHEX HIBAL

ITEST QN0429AO

I

I PAGE 429-9 FIGURE 429-6

t. 6 1!

TEST NO429AO

SUMMARY OF FRAGMENT VELOCITY AND POLAR EJECTION ANGLES FOR

THE HEX-HIBAL FRAGMENTS

FRAGMENT 500 GRAIN 700 GRAIN 900 GRAINROW POLAR POLAR VELOCITY AV. POLAR

ANGLE ANGLE AVG. 0-153') ANGLE

1 +12.00 + 9.50 4100 + 7.30

2 + 7.30 + 5.00 4200 + 3.40

3 + 4.20 + 2.50 4300 + 1.20

4 + 2.30 + 1.00 4500 - 1.00

5 + 1.30 - 0.30 4850 - 1.80

6 + 0.10 - 1.40 4500 - 2.30

7 + 0.30 - 2.00 5000 - 3.20

8 - 1.10 - 2.30 5000 - 3.60

9 - 1.40 - 2.20 5100 - 4.40

10 - 1.70 - 3.20 4850 - 4.20

11 - 2.10 - 3.10 5100 - 4.90

12 - 2.40 - 3.90 5100 - 5.00

13 - 2.90 - 3.80 5300 - 5.20

14 - 2.60 - 4.50 5100 - 5.70

15 - 3.50 - 4.30 5300 - 6.10

16 - 3.40 - 5.00 5450 - 5.20

17 - 3.80 - 4.60 5450 - 6.50

18 - 3.80 - 5.00 5450 - 5.70

19 - 3.50 - 4.40 5450

20 - 4.50 - 5.00 5450 - 5.30

21 - 3.80 - 4.50 5300

22 - 4.30 - 4.80 5300

23 - 4.40 - 4.90 5000

24 - 4.20

25 - 4.30

26 - 4.1 °

27 - 4.10

PAGE 429-10 FIGURE 429-7

co

C) -4J M 0-J j

w0 0 )C

0 U

Co - -Cc L- 2

ILLJ 0 5 cz

Li. -

1WJ LL- / )l

'4 LAJt

i-c' uiS- COL.

LLU

-j LLJJ

Cc Cl LL 7-1 L.cx a. -J <c

LA LiiC

PAE4910FGR 2-(DLL3

TEST ONO0429A0

VERTICAL MEASUREMENTS (INCHES)* OF FRAGMENT HIT LOCATIONSI ON WITNESS SHEET

FRAGMENT 700-gr FRAGMENT WITNESS SHEETROW NUMBER COLUMN 1 COLUMN 2 C OL UMN 3'

1 +29

2 +14 +14

3 +51-4 + 1-1

5 -5

6 -91 -9

7 12

8 -121 -141

10-18 :11-18

12 -201 -22

13 -22

14 -24 -26

15 -25

16 -28 -

17 -271

18 -29 -30

19 -28J

20 -30 -32

21 -301

22 -301 -331

23 -33

*Coordinates measured from the top of warhead aimline.

PAGE 429-12 FIGURE 429-9

I+

TEST QNO429AO

VERTICAL MEASUREMENTS (INCHES)* OF FRAGMENT HIT LOCATIONSON WITNESS SHEETS

FRAGMENT 500-r FRAGMENT WITNESS SHEETROW NUMBER COLUMN 1 COLUMN 2 COLUMN 3 COLUMN 4

1 +37 +371

2 +211

3 +11 +11 V4 +4- +45 + +

2 2

6 -4

7 -51- 6

8 -9

9 -I1 -10

10 -12

11 -141 -131

12 -151

13 -171 -18

14 -171

15 -211 -201

16 -21 -211

17 -24 -221

18 -23 -25

19 -24 -231

20 -27 -28

21 -26 -26

22 -271 -281

23 -291 -281

24 -29

25 -30 -30

26 30

27 -311 -30

h.. *Coordinates measured from the top of warhead aimline.

PAGE 429-13 FIGURE 429-10

* - .,,.a ,t- " _a.' ''3. "T = :,:m .:

I,IIK I

TEST QN0429AOVERTICAL MEASUREMENT (INCHES)* OF FRAGMENT HITS ON WITNESS SHEET

FRAGMENT 900-gr FRAGMENT WITNESS SHEET

ROW NUMBER COLUMN 1 COLUMN 2 COLUMN 3

1 +22

2 +9 +81

3 +1

4 - 6 -71

5 -10

6 -13 -121

7 -161

8 -191 -171

9 -22

10 -22 -221

11 -25

12 -271 -25

13 -28

14 -301 -30

15 -321

16 -31 -30

17 -351

18 -33 -341

19

20 -331 -35

*Vertical coordinates from top of warhead aimline.

PAGE 429-14 FIGURE 429-11

I TEST QNOI209AO

WARHEAD PRIOR TOI PLACEMENTOF SHROUD

ir

AII

LA

TEST ARENAPAGE 429-15 FIGURE 429-12

II

-k is

A 11W4

1

' 08

rIl ,.- -,50-RI HI AL

Alp r

00-GRAIN HIBALS

PAGE 29-1 FIGRE 49-1-

IIIII

4

I

TEST QNO514AO11.5", 135-LB PREFORMED FRAGMENT/FIREFORMED

FRAGMENT COMBINATION WARHEAD

III.IIIIIII

~

2.1.8 TEST 7, QNO514AO V

2.1.8.1 DESIGN SUMMARY AND RATIONALE

This warhead was partly firefonred fragments and partly prefoniielfragments. The basic design characteristics of the warhead (Figures514-1, 2, 3) were:

OUTSIDE DIAMETER: 11.5-inchINSIDE DIAMETER: 2.875-inchLENGTH: 14.0-inchCASE THICKNESS: 0.5-inchCASE MATERIAL:Prefomed fragments: SAE 4130, (RC40-42)Firefonned fragments: SSS 100, (RC-42), HY-80, (RC40-43)

WARHEAD WEIGHT: 135-lbSHROUD: Two steel skins, 0.020-inch inside,

0.030-inch outside, with 1-inch urethanefoam insulation between warhead andinner shroud

The preformed hex-HIBAL fragments were all 0.485-inch thick, and werethe following sizes: 13/16-inch across flats (500-grain); 15/16-inch acrossflats (700-grain); 1-1/16-inch across flats (900-grain). The fragments werepotted in laminac with a 0.015-inch outside skin.

The fireformed fragment case was grooved circumferentially to provide15 rows of equal-length fragments, each 0.867-inch long. The spacingbetween the longitudinal grooves was 0.625-inch, which provided for atheoretical fragment weight of 540-grains (before any weight loss due tofireforming).

Two different materials, SSS-100 and HY-80, were tested in thefireformed portion of the warhead to determine if the opposed groovingtechnique was sensitive to choice of alloy.*

For the HY-80, both the longitudinal and circumferential groove-depthswere selected which had been successful for the SAE 4130 alloy in test 5.

For the SSS-100, with the metal remaining between the longitudinalopposed grooves being held approximately constant, the internal andexternal groove depths were varied. Circumferential grooves for theSSS-100 were made slightly deeper on the non-booster end than the HY-80to fully insure that the resulting circumferential groove breakout atthat end of the warhead would avoid the creation of doublets. The grooves

* Flat plates of each material were circumferentially grooved,formed to the desired radius of curvature in a press, longitudinallygrooved, and then welded together to form the warhead case.

PAGE 514-1

at the booster end were made slightly. shallower than those used withHY-80, to determine if doublets would occur at the booster end of thewarhead.

HY-80 GROOVE DETAILS

LONGITUDINAL CIRCUMFERENTIALINSIDE OUTSIDE METAL GROOVE INSIDE OUTSIDE METALDEPTH DEPTH REMAINING NUMBER DEPTH DEPTH REMAINING(inch) (inch) (inch) (inch) (inch) (inch) (inch)

0.100 0.160 0.240 1,2 0.100 0.120-0.140 0.260-0.2800.100 0.170 0.230 3,4,5 0.100 0.180-0.200 0.200-0.220

6-16 0.100 0.220-0.240 0.160-0.180

SSS-100 GROOVE DETAILS

jONGITUDI NAL _ IRCUMFERENTIALINSIDE OUTSIDE METAL GROOVE INSIDE OUTSIDE METALDEPTH DEPTH REMAINING NUMBER DEPTH DEPTH REMAINING(inch) (inch) (inch) (inch) (inch) (inch) (inch)

0.130 0.130 0.240 1,2 0.100 0.100-0.120 0.280-0.3000.156 0.104 0.240 3-8 0.100 0.200-0.220 0.200-0.1800.104 0.156 0.240 9-16 0.100 0.240-0.260 0.140-0.1600.14n 0.140 0.2200.140 0.130 0.230

The shroud (Figure 514-4) is the same as was used in the previous 11.5-inchdiameter warheads.

2.1.8.2 DESCRIPTION OF TEST OBJECTIVES AND TEST ARENA

For the firefomed-fragment portion of the warhead the primaryobjective was fragment recovery. In addition, witness sheets were placedbetween each Celotex pack to provide evidence of fragment doubles, becauseprevious firings had indicated that some breakup of doublets into singlesmay have occurred during impact with the Celotex.

For the prefomed hex-HIBAL portion of the warhead, fragment velocityand pattern were the objectives.

The test arena is illustrated in Figure 514-8, and photographs ofthe arena are presented in Figures 514-14 and 514-15.

[PAGE 514-2

• At

2.1.8.3 DESCRIPTION OF TEST RESULTS.

A. Fragment Qjality

1. Firefonned Fragments

a. HY-80 Steel

The fragment breakout along the longitudinal grooves was good forboth choices of longitudinal grooving. However, breakout along thecircumferential grooves were not as good in that fragment nultiples(lengthwise) occasionally occurred everywhere except adjacent to thebooster end. (The booster-end row of fragments were good.) Examplefragments are presented in Figure 514-6.

b. SSS-100

The fragment breakout along the longitudinal grooves was excellentfor every choice but one - the choice which had 0.104-inch deep insidegrooves and 0.156-inch-deep outside grooves, wherein fragment scabbing andpartial fragments were prevalent, as shown in Figure 514-9. Somefragment lengthwise multiples were recovered for all choices of circum-ferential groove depths, indicating that depths of grooves were lessthan required. Examples are shown in Figure 514-15.

The fragments were not weighed because the weight of strings of

fragments are meaningless.

2. Preformed Fragments

Witness sheet data indicated that no breakup of the preformedfragments occurred.

B. Fragment Pattern and Velocity

1. Fireformed Fragments

This test was not designed to acquire pattern and velocity data forfi reformed fragment.

2. Prefomed Fragments

A summary of the hex-HIBAL-fragment polar-ejection angles andvelocities is presented in Figure 514-9. The hex-HIBAL fragment polarejection angles are plotted as a function of the fragment center-of-lengthdistance from the booster end of the warhead in Figure 514-10. Tablesof the fragment hit locations are presented in Figures 514-11, 12, 13.Photographs of the fragments pattern are presented in Figure 514-16.

PAGE 514-2aL-- 1

I C. Conclusions

1. Fireformed Fragment Warhead

a. The design requirements for achieving proper firefonning offragments with opposed longitudinal grooves have been well defined. Themetal remaining between the apexes of the longitudinal grooves should bebetween 0.200 and 0.240-inch.

b. The metal remaining between the apexes of the circumferentialgrooves must be less than 0.140-inch, probably about 0.100-inch, but theexact value remains to be demonstrated.

2. Preformed Fragment Warhead

There is no need fo further 11.5-inch diameter, 135-lb warhead tests.Fragment quality, velocity and pattern characteristics were all withinthe desired bounds.

PAGE 514-2b

OUT 0. 0104"IN 0~ 030 0 u

-v- [v - - I 0.104" Df PINH OFLOWUUTUM!'AL C.P'j).ESHEXIIfAL. F~RAMITS IN F lREI'V1*1D F;'(, VT'

90-ra in OUT 0.140"* ~1-1/16" ACROSS 010FLA'S VT 0. 1

23 RO IN 40"

700 raln 0700.gaI! I~ IIIIAL If')-N 0. 110

15/16" ACROsS 0TE 1 NOTE 3FLATS

16 ROWSJ OUT 010

IIN 0.100'

500-gra i.J-

FLATS r PT1g (l! TAIEP(0DIuls' CI MC.1 1[RF

112-/ 1O NOTES:

NOTES: tlRA. . 0.140" N 2r IfrCs:1. M~F0RMED KX~ H 1BAL 12"? 0 1 . '1 .IJ[-- E P.MNC

Sl i 4110 !'rl P00 W',' = S5S-T'l 1 0.KIPLAT(0 Oil. fr~fgTP[AI J r Oc, *A.l10 DRA,.i AT 8-Uii ta .-C p:-ACTUAl O~I P:IL 'C .:

'"~o~CO~MAStk~pM.EiuS - 40-4?.

TP t L 1-hrit610 0: 0 :*CzHE&.

T ._0 F0.041NISIAL

IMICNE 1 5. ALI,1% - S'lHIM f: .S71! . IIIff IC

3/16" *

11-112" 1

WARHEAD DESIGNTEST ON0514AO

PAGE 514-3 FIGURE 514-1

ML4

IC

c'.J

LLiixir

~00-t4

LLj~~~~: PAE54- IUR 1-

-. .$-t*',~ ~C4

CIC)CC\J to

II

uJuLJ

'N C)

C)00 C) O

LU -V) ClD

CD C) C/)cco

NN C) I

M 0a

C) w -L

LfJ (.0o

LU crzLC) U) K

0) LU

cm cm

PAGE 545FIE 51-3

o A,

18" 0.D. x.030" STEE 14" O.D. x.020" STEEL.' I" URETHANE FOAM

15"1

SHROUD FOR 11-1/2" O.D., 135-LB WARHEAD

TEST QN05ILAO

UPAGE 514- 6 FIGURE 514-4

- A,

i J0

INHE . .. '.

o 1 2INCHES

QNO514AO

RESULTINGFRAGMENTSHAPE

FRACTURE LINE

ONGITUDINAL GROOVE

H.E. SIDE

IFRAGMENT SHAPE RESULTING IN SSS-100 WHEN THE METAL REMAINING BETWEENLONGITUDINAL INSIDE AND OUTSIDE GROOVES IS .220", AND THE INSIDE

AND OUTSIDE GROOVE DEPTHS ARE EQUAL

PAGE 514-7 FIGURE 514-5

I1!

INCHES

QNO514AO

RESULTING.--- FRAGMENT

SHAPE

FRACTURE LINE

LONGITUDINAL GROOVE

H.E. SIDE

FRAGMENT SHAPE RESULTING IN HY-80 WHEN THE METAL REMAINING BETWEENLONGITUDINAL INSIDE AND OUTSIDE GROOVES WAS 0.230", AND THE

INSIDE LONGITUDINAL GROOVE WAS .100" DEEP

PAGE 514-8 FIGURE 514-6

L . . .. J

!I

THESE FRAGMENTS ___-.__._,_._.

WERE SCABBED

0 2

INCHES

OFSS1LTINGFRAGMENTSHAPE

H.E. SIDE

FRACTURE

LONGITUDINAL GROOVE

REDUCED-WEIGHT FRAGMENTS RESULTING IN SSS-100 WHEN METAL REMAINING

BETWEEN INSIDE AND OUTSIDE LONGITUDINAL GROOVES WAS 0.240", AND INSIDE

LONGITUDINAL GROOVE WAS 0.104" DEEP

EXAMPLE FRAGMENTS FROM TEST ON0514AOPAGE 514-9 F E

F FIGURE 514- 7.... -77,_... .

TARGETS AA -Fr 4Vx4'x8' CELOTEX PACKSTARGETS A - 0 4'x6' WITNESS SHEETS

SHEETS. 6" SPACING

TARGETS 2,4 4'x6' SINGLE STEEL WITNESS SHEETS

15'

15A STAXATA

ARNAFOTEST 1551'A

[I.HPAG 51- 1 FIURE51485I

S ... .~.15.

TEST QNO514AO

SUMMARY OF FRAGMENT POLAR EJECTION ANGLE AND VELOCITY RESULIS

AVERAGEFRAGMENT C.G. POLAR EJECTION ANGLES POLAR VELOCITY

FRAGMENT DISTANCE FROM ANGLE (9-15')ROW BOOSTER END (IN) 500-GR 700-GR 900-GR SUMMARY (ft/sec)

1 £.0 +5.9 +5.9 41001 1.2 +5.0 +5.01 1.2 +6.0 +6.0 41002 1.7 +1.2 +1.2 48002 2.0 +1.3 +1.32 2.2 +2.7 +2.7 47003 2.4 -0.5 -0.5 49003 2.8 -1.0 -1.03 3.1 0 0.0 50004 3.1 -1.9 -1.9 51004 3.6 -1.9 -1.95 3.8 -3.2 -3.2 54004 4.0 -0.3 -0.3 52005 4.4 -3.2 -3.26 4.5 -4.3 -4.3 54005 4.9 -2.3 -2.3 52007 5.2 -4.9 -4.9 54006 5.3 -3.8 -3.86 5.8 -2.4 -2.4 53008 5.9 -5.6 -5.6 54007 6.1 -4.6 -4.69 6.6 -5.7 -5.7 54007 6.8 -3.4 -3.4 53008 6.9 -6.1 -6.110 7.3 -6.1 -6.1 54008 7.7 -4.4 -4.4 55009 7.7 -4.7 -4.7

11 8.0 -6.2 -6.2 54009 8.5 -4.1 -4.1 5300

10 8.6 -7.0 -7.012 8.7 -7.0 -7.0 540011 9.3 -5.8 -5.813 9.4 -7.1 -7.1 540010 9.5 -5.4 -5.4 550012 10.1 -7.5 -7.514 10.1 -7.2 -7.2 540011 10.4 -5.8 -5.8 530015 10.8 -7.8 -7.8 540013 10.9 -7.2 -7.212 11.4 -5.1 -5.1 550016 11.5 -7.4 -7.4 540014 11.8 -7.3 -7.317 12.2 -8.0 -8.0 540013 12.3 -5.5 -5.5 530015 12.6 -7.0 -7.018 12.9 -7.7 -7.7 540014 13.2 -4.916 13.4 -7.7 -7.7

LPAGE 514-11 FIGURE 514-9

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PAGE 514-12 FIGURE 514-10

TEST QN051'4A0

500-GRAIN HEX HIBAL FRAGMENTSVERTICAL MEASUREMENTS OF FRAGMENT HIT LOCATION fINCHES)

RELATIVE TO THE TOP OF THE WARHEAD

____________ FRAGMENT COLUMN ______

FRAGMENTROW 1 2 3 4 AVERAGE

1 +21.0 +12.0 ______ +17.0

2 +____ +2.0 +__ _ +2.0 + 2.0

3 - 3.0 - 5.0 _____ - 4.0

4 _______ -10.0 - 8.0 - 9.0

5 -13.0 _____ -14.0 _____ -13.5

6 -18.0 -17.0 -17.5

7 -21.0 -19.0 _____ -20.0

8 _______ -24.0 -22.0 -23.0

9 -24.0 _____ -24.0 _____ -24.0

10 _______ -26.0 _____ -26.0 -26.0

11 -27.0 _____ -27.0 -27.0

12 _______ -31.0 _____ -29.0 -30.0

13 -30.0 _____ -32.0 -31.0

14 ______ -34 ______ -30.0 -32.0

15 -35.0 ______ -34.0 -34.5

16 _______ -35.0 ______ -33.0 -34.0

17 -37.0 _____ -36.0 ______ -36.5

18 _______ -37.0 _____ -36.0 -36.5

PAGE 514- 13 FIGURE 514-11

TEST 0N0514IAO

I 700-GRAIN HEX HIBAL FRAGMENTSVERTICAL MEASUREMENTS OF FRAGMENT HIT LOCATION (INCHES)

RELATIVE TO THE TOP OF T!!E WARHEAD

FRAGMENT COLUMNFRAGMENT

ROW 1 2 3 AVERAGE

1 _______ +14.0 +14.0

2 + 2.0 + 2.0 + 2.0 F3 -6.0 -6.0

4 - 9.0 _______ -10.0 - 9.5

5 -14.0 -14.0

6 -18.0 _______ -16.0 -17.0

7 -20.0 ______ -20.0

8 -24.0 ______ -27.0 -25.5

9 -22.0 _____ -22.0

10 -29.0 -31.0 -30.0

11 _______ -27.0 ______ -27.0

12 -33.0 ______ -33.0

13 -33.0 ______ -33.0

14 -34.0 _______ ____ -34.0

15 -34.0 ______ -34.0

16 -37.0 _______ ____ -37.0

PAGE 514-14 FIGURE 514-12

I,'TEST ONO51LAO

* 900-GRAIN HEX HIBAL FRAGMENTSVERTICAL MEASUREMENTS OF FRAGMENT HIT LOCATION (INCHES)

RELATIVE TO THE TOP OF THE WARHEAD

FRAGMENT COLTh 4FRAGMENT

ROW 1 2

1 +17.0

2 + 6.0

3 - 3.0

4 -5.0

5 -12.0

6 -13.0

7 -17.0

8 -21.0

9 -21.0

10 -26.0

11 -28.0

12 -27.0

PAGE 514- 15 FIGURE 514- 13

I16'b

WARHEAD BEFORE AND AFTER SHROUD IS PLACED IN POSITION

[ETQ014OFGRE541

III0

TEST RENA OR QN514A

PAG 51-1IUE541

r7C

1*-ri FAMN

500-grain FRAGMENT

FRAGMENT PATTERN WITNESS SHEETS FOR

500, 790, AND 900, GRAIN HEX HIBAL FRAGMENTS

TEST Q0514AO

[IPAGE 514- 18 FIGURE 514-16

II

2.2 SUMMARY OF WARHEAD TEST RESULTS

2.2.1 SUMMARY, PREFORMED-FRAGMENT WARHEADS

The comparison of predicted and measured fragment velocities andpolar ejection-angles for each of the tour warhead sizes are presentedin tables 2.2.1 thru 2.2.4.

2.2.1.1 VELOCITY

For the 8-inch diameter, 80-ib, and the 11.5-inch diameter, 135-lbwarheads the measured values were close to the predicted values, andslightly lower than the predicted values for the 11.5-inch diameter,200-lb warhead and the 19-inch diameter, 200-lb warhead. The fragmentvelocities from the 11.5-inch diameter, 200-lb warhead were stillwithin the range of desired fragment velocities (5000-5500-ft/sec), butthe velocities from the 19-inch diameter, 200-lb warhead were below thisrange.

2.2.1.2 POLAR ANGLE

For the 8-inch diameter, 80-lb warhead the measured polar ejection-angles were very close to the predicted values. For the 11.5-inch diameter,135-lb warhead, the measured ejection-angles were close to the predictedexcept for the two end-rows of fragments, which did not spread as muchas predicted. For the 11.5-inch diameter, 200-lb warhead the fragmentejection-angles near the booster-end of the warhead were very close topredicted, but the fragments near the non-booster end did not spread asmuch as predicted. For the 19-inch diameter, 200-lb warhead, the threerows of fragments nearest the booster-end, and the row of fragmentsfurthest from the booster-end did not spread as much as predicted. Therenaining 10 rows of fragments in this warhead were close to the predictedvalues.

2.2.1.3 FRAGMENT OUALITY

The preformed hex HIBAL fragments lost no fragment weight fromeither the detonation or from perforation of the shrouds or the recoverymedium. Minor fragment deformation, resulting from the explosive sweep,occurred in each of the tests.

.PAGE 9

2.2.2 SUMMARY, FIREFORMED-FRAGMENT WARHEADS

For the 8-inch, 80-1b; the 11.5-inch, 135-Ib; and the 11.5-inch,200-lb firefonned-fragment warheads; the comparison of predicted andmeasured polar ejection-angles and velocities are presented in tables2.2.5 thru 2.2.7. For the 19-inch diameter, 200-lb warhead, no tablecomparing actual vs predicted values was prepared because; (a) no usefulpolar angle data was acquired, and (b) Lhe velocity bounds establishedfrom the data did not permit a row-by-row comparison to be made.

2.2.2.1 VELOCITY

The fragment velocities for the 8-inch, 80-1b; 11.5-inch, 135-1b;and the 11.5-inch, 200-lb warheads, were close to the predicted values.For the 19-inch, 200-lb warhead, the highest fragment velocities wereabout five percent less than the predicted value* for this size warheadwithout shroud. The velocity bounds defined by the data from the 19-inchtest strongly suggest that the velocity of the fireformed fragments willconform to the preformed-fragment-velocity characterization, for thesame c.g. locations and shroud conditions.

2.2.2.2 POLAR ANGLE

The measured polar ejection-angles for the 8-inch diameter, 80-lbwarhead were close to the design values of polar ejection-angles.Improper lengthwise pairings of fragments occurred in the testsof the other three sizes of warheads, which altered the fragment polarejection-angles. Thus the resulting fragment patterns were narrower thanpredicted, a natural result of the unwanted, lengthwise pairings offragments. On the basis of comparative data from subsequent tests(QNO811AO and QNO819AO) it appears to be safe to assume that the polarangle distribution for the firefomed fragments will be essentially thesame as for preformed fragments having the same c.g. locations and endconf igu rations.

2.2.2.3 SUMMARY OF THE EFFECTS ON FRAGMENT QUALITY OF VARIATIONSIN OPPOSED-GROOVE DESIGNS

The data demonstrate that when the opposed grooves are designedproperly, loss of fragment weight in fireforming can be limited tobetween ten and fifteen percent.

* (Using the Brown-Modified Gurney Equation, see footnoteL in Appendix III.)

PAGE 10_J Li

A. Included Angle

The included angle of the grooves was maintained at 37 degrees forall the fireformed-fragment-warhead tests and, thus, the effects ofvariations in groove angle on resulting fragment quality cannot beascertained from the warhead test data. (NOTE: The mat firing data(Appendix I) indicated that relatively wide angle grooves (90'-120')require the presence of a relatively der.se inert filler material in theoutside grooves to achieve proper fragment fireforming.)

B. Longitudinal Grooves

The test results indicate that fragment quality is primarily afunction of the metal remaining between the apexes of the opposed grooves.Best results were obtained when the metal remaining between inside andoutside grooves was a maximum of 0.220-inch to 0.240-inch. When themetal remaining between the apexes of the grooves exceeds this value,

undesirable results such as partial fragments or fragment "borrowing"from its neighbor occur. Data from Test QN0514AO show that the resultingfragment quality is not sensitive to the ratio of the depths of theinside and outside grooves as long as the remaining metal value is0.220 to 0.240-inch; The loss of metal removed from the case by thegrooving process is minimized when the inside and outside grooves areof equal depth. Spacing between longitudinal grooves was varied from0.625-inch to 1.188-inch with no apparent effect on fragment quality.

C. Circumferential Grooves

The metal remaining between the apexes of the inside and outsidegrooves must not exceed "threshold" limits, to prevent fragmentlengthwise pairing. For the 8"-diameter, 80-lb warhead the opposedgroove design was adequate to achieve proper fragment breakout, (i.e.with no lengthwise pairings). For the other three warhead sizes, thedepths of the opposed grooves were not adequate (in that too much metalremained between the apexes of the grooves), and lengthwise pairings offragments resulted on the non-booster-end-half of the warhead. It isestimated that proper lengthwise breakout will be achieved when themetal remaining between the apexes of the grooves is 0.100-inch.

When the inside groove depth exceeds 0.120-inch, the inside non-booster-end edge of the fragment is broken off by the detonation.

[PAGE 11

. .... .. . ... . . . . . . ...... ~ ~ I . . . . . . . .-. r .,. .. . . . ..

2.2.2.4 SUMMARY OF THE DESIGN EVOLUTION FOR THE FIREFORMED FRAGMENT,OPPOSED GROOVE, WARHEADS

The results of the fragment mat tests were usei to design the firstfireformed warhead test, QN0225AO, which was 8-inch diameter, 0.488-inchcase thickness. Excellent firefoming results were achieved in thisfirst test.

The second and third tests, QNO311AO and QN0328AO represented achange in both warhead diameter and warhead case thickness. There wereseveral design approaches for opposed grooving which were possible.Proper firefoming of fragments could be dependent on:

1. The depths of the inside and outside grooves (orsum of the depths).

2. The ratio of the depths of the grooves to thecase thickness.

3. The metal thickness remaining between the apexesof the opposed grooved.

Design approaches 1 and 2 were pursued in tests QNO311AO andON0328AO. The results of these tests demonstrated that the designapproaches were not the correct ones to follow.

In test QN0409AO, the design approach was changed to provide forthe metal thickness remaining between opposed grooves to bracket thosevalues which were successful in the first test QN0225AO.

Excellent fragments were recovered in test QNO409AO; however, theCelotex recovery medium contributed to breaking the fragments at thecircumferential grooves (a fact which was not recognized until the resultsof the following test were obtained).

Test ON0429AO served Lo provide upper bounds on the metal thicknessremaining between longitudinal grooves for proper fireforming, anddemonstrated that too much metal remained between the opposed circuiferen-tial grooves.

In test QNO514AO, circumferential groove depths were significantlyincreased so as to reduce the metal remaining between opposed grooves.However, this increase in groove depth proved to be insufficient.

Subsequent tests (QNO811AO and QNO819AO) of 60-degree sectors of the19-inch annular warhead, using the groove depths and groove spacingsassociated with the follow-on warhead designs contained in this report,have yielded fragments that broke up as desired, had good shape charac-teristics, weighed within 2% of their design weight and had a polarejection pattern that was essentially identical to the pattern measuredfor the preformed fragments fired from this 19-inch warhead in testNo. QNO4O9AO.

k PAGE 12

!IITABLE 2.2. 1

COMPARISON OF PREDICTED AND MEASURED FRAGMENT VELOCITIES

AND POLAR EJECTION ANGLES FOR THE 8-INCH DIAMETER, 80-LBPREFORMED HEX HIBAL WARHEAD, FOR 700-GRAIN HEX HIBALS

FRAGIENT POLAR EJECTION ANGLE (degrees) FRAGiENT VELOCITY (ft/sec)

ROW PR ED IL IEl.l f'EASURELD PREP ICTED IMASURED

1* + 4.7 + 4.7 4100 4300

2 + 1.2 + 1.2 4300 4800

3 - 0.7 - 0.7 4600 5000

4 - 1.8 - 1.8 4800 5200

5 - 2.7 - 2.7 5000 5400

6 - 3.2 - 3.2 5100 5400

7 - 3.6 - 3.6 5200 5500

8 - 3.9 - 3.9 5300 5500

9 - 4.2 - 4.2 5400 5600

10 - 4.3 - 4.3 5500 5700

11 - 4.7 - 4.7 5500 5600

12 - 5.4 - 5.4 5500 5600

13 - 5.5 - 5.5 5500 5600

14 - 5.7 - 5.7 5400 5500

15 - 5.8 - 5.8 5300 5600

16 - 6.1 - 6.1 5000 5400

* Row of fragments closest to booster end of warhead

PAGE 13

TABLE 2.2.2

COMPARISON OF PREDICTED AND MEASURED FRAGMENT VELOCITIES

AND POLAR EJECTION ANGLES FOR THE 11.5-INCH DIAMETER, 135-LB

;PREFORMED HEX HIBAL WARHEAD, FOR 700-GRAIN HEX HIBALS

FRA ENT POLAR EJECTION ANGLE (degrees) FRAGM1ENT VELOCITY (ft/sec)

ROW PREDICTED MEASURED PREDICTED REASURED

1* +10.0 + 5.0 4450 4100

2 + 3.0 + 1.3 4900 4750

3 0 - 1.0 5000 4950

4 - 1.3 - 1.9 5350 5200

5 - 1.9 - 3.2 5550 5300

6 - 2.6 - 3.8 5600 5350

7 - 4.8 - 4.6 5650 5400

8 - 4.9 - 6.1 5650 5400

9 - 5.8 - 4.7 5700 5400

10 - 5.8 - 7.0 5700 5400

11 - 6.2 - 5.8 5700 5400

12 - 6.3 - 7.5 5700 5400

13 - 6.6 - 7.2 5650 5400

14 - 6.8 - 7.3 5550 5400

15 - 7.8 - 7.0 5350 5400

16 -11.0 - 7.7 5000 5400

* Row of fragments closest to booster end of warhead

PAGE 14

ITABLE 2.2.3

COMPARISON OF PREDICTED AND MEASURED FRAGMENT VELOCITIES

AND EJECTION ANGLES FOR THE 11.5-INCH DIAMETER, 200-LB PREFORMED

HEX HIBAL WARHEAD, FOR 700-GRAIN HEX HIBALS

FRAGMENT POLAR EJECTIOI ANGLE (degrees) FRAGMENT VELOCITY (ft/secROW PREDICTED MEASURED PREDICTED MEASURED

1* +10.0 + 9.5 4300 4100

2 + 5.0 + 5.0 4600 4200

3 0 + 2.5 5200 4300

4 - 1.0 + 1.0 5300 4500

5 - 2.0 - 0.3 5400 4850

6 - 3.0 - 1.4 5500 4500

7 - 3.5 - 2.0 5600 5000

8 - 4.0 - 2.3 5700 5000

9 - 4.5 - 2.2 5700 5100

10 - 5.0 - 3.2 5700 4850

11 - 5.8 - 3.1 5800 5100

12 - 6.0 - 3.9 5800 5100

13 - 6.2 - 3.8 5800 5300

14 - 6.3 - 4.5 5900 5100

15 - 6.6 - 4.3 5900 5300

16 - 6.8 - 5.0 5900 5450

17 - 7.0 - 4.6 5900 5450

18 - 7.0 - 5.0 5800 5450

19 - 7.0 - 4.4 5800 5450

20 - 7.5 - 5.0 5600 5450

21 - 8.0 - 4.5 5500 5300

22 - 9.0 - 4.8 5400 5300

23 -11.0 - 4.9 5200 5000

* Row of fragments closest of booster end of warhead

PAGE 15

U'i ,,2

I,TABLE 2.2,4

COMPARISON OF PREDICTED AND MEASURED FRAGMENT VELOCITIESAND POLAR EJECTION ANGLES FOR THE 19-INCH DIAMETER, 200-LB PREFORMED

HEX HIBAL WARHEAD, FOR 700-GRAIN HEX HIBALS

FRAGiENT POLAR EJECTION ANGLE (degrees) FRAGMENT VELOCITY (ft/sec)ROW PREDICTED MEASURED PREDICTED MEASURED

1* +25.0 +15.0 4600 3500

2 + 8.8 + 4.9 4850 3900

3 + 5.0 + 0.8 5050 4300

4 0 - 0.7 5250 4500

5 - 1.5 - 2.6 5400 4600

6 - 2.5 - 3.5 5500 4700

7 - 3.0 - 4.6 5600 4800

8 - 4.0 - 4.2 5600 4900

9 - 4.5 - 5.5 5600 4900

10 - 5.0 - 5.3 5600 4900

11 - 5.5 - 6.1 5500 4900

12 - 5.5 - 6.0 5400 4800

13 - 8.0 - 7.6 5200 4600

14 -15.0 -10.3 5000 4500

*Row of fragments closest to booster end of warhead

PAGE 16

TABLE 2.2.5

COMPARISON OF PREDICTED AND MEASURED FRAGMENT VELOCITIESAND POLAR EJECTION ANGLES FOR THE 8-INCH DIAMETER, 80-LB

FIREFORMED HIBAL WARHEAD

FRAGM1ENT POLAR EJECTIONJ ANIGLE (degrees) FRAGM1ENT VELOCITY (ft/sec)ROW PREDICTED - MEASURED IPREDICTED T EASURED

1* + 5.1 + 8.5 4100 4500

2 - 1.0 + 4.1 4300 4300

3 - 1.3 - 1.0 4600 4800

4 - 1.9 - 1.9 4800 5300

5 - 2.6 - 3.6 5000 5300

6 - 4.8 - 4.2 5100 5300

7 - 4.9 - 5.0 5200 5300

8 - 5.8 - 5.6 5300 5300

9 - 5.8 - 5.6 5400 5500

10 - 6.2 - 5.8 5500 5500

11 - 6.3 - 6.3 5500 5500

12 - 6.6 - 6.7 5500 5500

13 - 6.8 - 6.3 5400 5300

14 - 7.2 - 6.2 5300 5300

15 - 7.8 - 5.6 500 5300

*Row of fragments closest to booster end of warhead.

PAGE 17

i

TABLE 2.2.6

COMPARISON OF PREDICTED AND MEASURED FR.\GMENT VELOCITIESAND POLAR EJECTION ANGLES FOR THE ij.5-INCH O.D., 135-LB

FIREFORMED HIBAL WARHE,4D

FRAGMENT POLAR EJECTION ANGLE (degrees) FRAG .ThT VELOCITY (ft/sec)R O PREDICTED HEASUIRED* PRLDICTED tIEASURD[

1+ +20.0 + 7.6 4450 4800

2 - 1.0 - 1.0 5150 5200

3 - 1.3 + 3.3 5350 5500

4 - 1.9 - 0.4 5550 5500

5 - 2.6 - 2.5 5600 5500

6 - 4.8 5650 5500

7 - 4.9 5650 5500

8 - 5.8 5700 5500

9 - 5.8 5700 5500

10 - 6.2 5700 5500

11 - 6.3 5700 5500

12 - 6.6 5650 5500

13 - 6.8 5550 5500

14 - 7.8 5350 5200

15 -11.0 - 7.1 5000 5200

+ Row of fragments closest to the booster end of warhead.

* Fragment lengthwise pairs made it impossible to provide specific

values for fragment rows 3 through 14. All hits fell between -2.5*and -7.10, however.

[ PAGE 1

17! TABLE 2.2.7

COMPARISON OF PREDICTED AND MEASURED FRAGMENT VELOCITIESAND POLAR EJECTION ANGLES FOR THE 11,5-INCH DIAMETER,

FRAGMIENT POLAR EJECTION ANJGLE (.r e) FRAGHENT VELOCITY (ft/sec)R0OW PREDICTED MESU~RD PREDICTED t E#SURLD

1+ + 7.0 + 9.5 4600 4500

2 - 1.0 + 4.5 5200 4700

3 - 1.3 + 1.9 5400 4800

4 - 1.9 - 0.5 5500 5000-5300

5 - 2.6 - 4.0 5600 5000-5300

6 - 48 570 500-530

6 -4.8 5700 5200-5700

7 -45.9 5700 5200-5700

9 -5.8 5700 5200-5700

90 -5.8 5800 5200-5700

10 - 6.2 5800 5200-5700

12 - 6.3 5800 5200-5700

13 - 6.6 5900 5200-5700

13 -67.8 5900 5200-5700

14 - 7.0 5800 5200-5700

15 -78.5 5800 5200-5700

16 - 8.0 5600 5200-5700

18 - 9.0 5400 5200-5700

19 -11.0 -7.5 5000 5200-5700

+ Row of fragments closest to the booster end of warhead.

* Because some fragment lengthwise pairing and some breakup occurred,specific values of polar ejection angle cannot be assigned fragment rows6 through 19. All hits occurred between -4.00 and -750 however.

PAGE 19

I 3.0 CONCLUSIONS

In general, the Preliminary Warhead tests have demonstrated that theoriginal design criteria can be satisfied by both preformed and firefon: edwarhead designs.

3.1 CONCERNING FRAGMENT EJECTION CHARACTERISTICS

3.1.1 FRAGMENT VELOCITY (Fireformed vs Preformed)

For equal charge-to-metal ratios and equal shroud conditions thereis no significant difference between the fragment velocities achieved witha fireformed fragment case and the fragment velocities achieved with apreformed fragment case.

Ejection velocities can be accurately predicted, as described inSection 3.4.

3.1.2 POLAR ANGLE

Polar ejection angles can be accurately predicted for both thefireformed and preformed fragments with the methodologies presented inSection 3.4 and in Appendix III, with the exception of the row of fragmentsnearest each end of the warhead. The end row of fragments is verysensitive to the end configuration, and changes in the polar ejection angleas a function of the end configuration cannot, at this time, be predictedwith confidence.

3.2 CONCERNING THE OPPOSED GROOVE FIREFORMING TECHNIQUE FOR GENERATINGHIBAL FRAGMENTS

The results summarized in Section 2.2.2 demonstrate the feasibilityof generating fireformed fragments with the shape and toughness needed toqualify as HIBAL-type fragments, from all four warhead sizes.

3.3. WARHEAD MODELS FORMULATED FOR USE IN END GAME ANALYSES

The warhead models which were formulated for use in the end gameanalysis during the next phase of HIBAL effort are presented inTables 3.3.1 through 3.3.8. A high level of confidence is placed inthe ability of the warhead designs described in Tables 3.3.9 and 3.3.10to generate fragments having the characteristics given in Tables 3.3.1through 3.3.8.

PAGE 20

3.4 GUIDELINES FOR THE DESIGN OF FUTURE WARHEADS

3.4.1 WARHEAD CHARACTERIZATION

Curves presented in Figures 3.4.1 through 3.4.4 can be used topredict fragment ejection-angles and velocities for each of the fourwarhead sizes presented herein, and are deemed adequate for predictingeither preformed or fireformed fragments.

It should be noted that changes in the design of the ends of thewarhead can significantly alter the fragment ejection characterizationnear the ends.

3.4.2 OPPOSED-GROOVE DESIGN

When designing warheads utilizing the opposed groove technique,caution should be exercised when designing fragment sizes. The metalweight removed in the both the grooving process and fireforming processmust be planned for.

3.4.3 Structural Strength

Because of the deep grooves required to produce good breakup ofthe warhead case, there is no structural advantage of the solid-case,opposed-groove design, over a preformed fragment design having innerand outer stress skins.

pE

L PAGE 21

- . . . . -1

* K!V

4.0 EVALUATION OF UNCERTAINTIESn ii4.1 FOR BOTH PREFORMED AND FIREFORMED FRAGMENT WARHEADS

I ,4.1.1 END CONFIGURATION

Missile attachment structural details are likely to have a signifi-cant effect on the velocity and polar ejection angles of the fragmentslocated closest to the ends of the warhead.

4.1.2 SHROUD DETAILS

The missile shroud used in any given application may differ franthe simulations used in these tests and this may significantly alterthe effect on fragment velocity, ejection angles, shape and weight.

4.2 PREFORMED FRAGMENT WARHEADS

4.2.1 SKIN THICKNESS

The skin thickness (both inside and outside) necessary to meetenvironmental and/or structural requirements in any given applicationmay differ significantly fran the thickness used in these tests. The useof different skin thicknesses may significantly affect fragment polarejection angle, velocity, shape and weight.

4.3 FIREFORMED FRAGMENT WARHEADS

4.3.1 FRAGMENT CASE ALLOY

Opposed groove designs may change, in terms of the metal thicknessbetween the apexes of the opposed grooves, for differing alloys. Noproblem is foreseen in developing an opposed groove design which willproperly fireform fragments for most alloy steels, or mild steels.

PAGE 22

- .,-

I

TABLE 3.3.1

WARHEAD CIIARACTERIZATIONS

PREDICTED FOR 8-irtc'i DIAMETER x 80-1-B WARHEADSCONIAINING PRLFOR'IED HEX IIIAL FRAGMENIS

(BASED ON DATA OBTAINED FRON, TEST NO. QN0319AO)

FRAGMENT DEYAI LSFRAG. WI. 4 500-qrain 7---700- a ini . 900-(Irdi nT OlAl. NO. 4I0 352 _

WID1'611 ACROSSFLATS 7/8 1 1-1/8

THICrYNLSS0.42 0.42 0.42

FRAGMENT EJECTION CHARACTERISTICS (1)

ROOLNAO 0 N G L E V E LO C I TY -O AR -- iN-G - I -C -- - - - A T L -F L I T YS (deres) (ft/secL (decqrees) (ft/sec) (degrCes) I (ft/g.CcA (2) (3)

1 ___ +4.5 4300 44.0 4300 43.5 044002 +1.0 4700 +1.0 4700 40.5 4 03 0.0 5000 -1.0 5000 -1.5b 51004 -1.5 5200 -2.0 5300 -2.5 1 5300--5 -2.5 5300 -3.0 5400 -3.5 55006 -3.0 5400 -3.5 5500 -4.0 -56007 -3.5 5500 -4.0 5600 -4.5 56008 -4.0 5600 -4.5 5600 -5.0 57009 -4.0 5600 -5.0 5700 -5.0 5700

10 -4.5 5700 -5.0 5700 -5.5 570011 -5.0 5700 -5.5 5700 -5.5 5700b]12 -5.0 5700 -5.5 5700 -6.0 570013 -5.5 5700 -5.5 5700 -6.0 5600-14 -5.5 5700 -6.0 560 -6.0 550015 -6.0 5700 -6.0 560016 -6.0 5600 -6.0 550017 -6.0 560018 -6.0 5500

NOTES:

(1) Polar angle is given from the fragment c.g. relative to a normal to the warheadaxis through that c.g. Plus angles are toward the booster end. Velocity is theestimated average velocity measured over the first fifteen feet of travel in astatic arena test. including losses through shroud(s) and insulation.

(2) A and B are end-ring rows.(3) Booster end.

L

~~PAGE 23 * I.4

I

TABLE 3.3.2

WARHEAD CHARACTERI ZAT IONS

PREDICTED FOR 8-iriiC DIAMETER x 80-L.i WARHEADSCONTAINING FIRLFORCED HIBAL I-RAGMLNIS

(BASE) ON DATA OBTAINED IN TEST NO, QN0225AO)

rR PkGT -IUTATTFRAG. W(. 500-qrain 700-(cra n 900-orainTOTAL NO. 504 35 286

C IROCUMFL RLEN[ f-AL-'

WIDTH:S MNSIDE 0.799 0.895 1.017tS-- 0.898 1.005 1.142 -

-' W!(N A 0.833 1.0 1.154WIDTH: .T _ U SS 0 4 37 5 ' _ __ O!-4375_ !L 0 . 4315 b . .. . . .

-AE RW LAR ALE VELOCITY - Aw- -l- VELOCITY-POA-,L[ 'LOCYFRAGMENT ROW Potep )_ fle)l _.de~es_ .. t sc___ e res ]f..,,)_i

T_ degr es t/cJg res) ftI/s 'I cereesl _j~c1 (3) 414.0 4300 13.5 - 4400 13.0 I. 442 + 8.0 4600 + 6.0. 4600 + 5.0 47003 + 3.0 4800 + 1.5 j 40-- 0.0 -4QJ

4 + 0.0 490 -. 0 J 5000 -2.0 51'

5 - 1.5 5100 1 .0 - 5200 -4.0

6 - 3.0 5200 - 4.0 5300 - 5.0 53J007 - 4.0 5300 - 5.0 54001 - 5.5 54008 - 5.0 5400 - 5.5 500 - 6.0 55 Gr9 - 5.5 5400 - 6.0 5500 1 - 6.5

10 - 6.0 5400 - 6.5 5500 1 - 6.5 550)11 - 6.0 5500 - 6.5 5500 1 - 6.5- .546T_12 - 6.5 5500 - 6.5 5400 ] - 6.0 54(013 - 6.5 5500 - 6.5 5400 - 5.5 5300-14 - 6.5 5500 - 6.0 530015 - 6.5 5400 - 5.5 5300 -

16 - 6.5 5400 _17 - 6.0 5300I18 - 5.5 5300

NOTES:

11) All linear dimensions are in inches.2) Polar angle is given from the fragment c.g. relative to a normal to the warhead

axis through that c.g. Plus angles are toward the booster end. Velocity is theestimated average velocity measured over the first fifteen feet of travel in astatic arena test, including losses through shroud(s) and insulation.

(3) Booster end.

PAGE 24

'I

TABLE 3.3,3

WARHEAD CHARACTERIZATIONS

PREDICTED FOR 11,5-INCH DIAMETFR x 135-LB WARHEADSCONTAINING PREFORIED HEX HIBAL FRAGPIENIS

(BASED ON DATA OBTAINED IN TEST NO. QNO514AO)

_______________________ - FRAGMENT 1)LTAI LS

FRAG. WT. 500-grain - 00-grain _900-grain___TOTAL NO. 720 560 403

WI I'DTH 'AU SSFLATS 13/16 15/16 1-1/16

__tr h)_ __ ___________________________

THICK1ESS 0.485 0.485 0.485(inch) OA_485 _O._485. O._485

FRAGM4ENT EJECTION CHARACTERISTICS (1)

POLAR ANGLE VELOCITY POLAR ANGLE VELOCITY POLAR ANGLE VELOCITYROW NO. (degrees) (ft/sec) (degrees) (ft/sec) (degrees) (fl/seclA (2) 31 +6.0 4100 +5.0 4100 +5.5 41502 +1.0 4800 +1.5 4750 +2.0 46003 -0.5 4900 -1.0 4950 0.0 49004 -2.0 5100 -2.0 5200 5-.01 51505 -3.0 5400 -3.5 5300 -2.0 53006 -4.0 5400 -4.0 5350 1 -3.0 5407 -5.0 5400 -5.0 5400 54-3.5 _450

8 -5.5 5400 -5.5 5400 1 -4.0 55008 -6.0 5400 -6.0 5400 -4.5_55-__----

10 -6.0 5400 -6.5 5400 1 -5.0 550011 -6.5 5400 ' -7.0 5400 -5.0 5450-'12 -7.0 5400 -7.0 1 o5400 1 -5.5 540013 -7.0 5400 -7.0 5400 1 -6.0 535014 -7.5 5400 -7.5 540015 -7.5 5400 -7.5 540016 -8.0 5400 -8.0 540017 -8.0 5400 -18 -8.0 5400B (2)

NOTES:

(1) Polar angle is given from the fragment e.g. relative to a nomal to the warheadaxis through that e.g. Plus angles are toward the booster end. Velocity is theestimated average velocity measured over the first fifteen feet of travel in astatic arena test, including losses through shroud(s) and insulation.

(2) A and 8 are end-ring rows.(3) Booster end.

PAGE 25

TABLE 3,3,4

WARHEAD CHARACTRIZATIONS (4)PREDICTED FOR 31 .5-INCH DIAp rEPR x 135-i 1i WARHEADS

CONi AI Ni NG F IREFUOHrI) HI BAL FtRAG[ENTS(BASED ON DATA OBTAINED IN lEST NO. QNO514AO)

FRAGM0 NT ((HA_ . . . .F RAG. 1 T. 500-qra in 709-- ra n 900- cira i n

. TOlAt .. 7AL N_. 55- 49I-C RCUW,- I RLN Il

WIDIH:I INSIDE 0.707 0. 89? 1.000

--- Q )R(,- - -~ ------ --- ;

W 1)ITH: 0.824 0.933 1.077

101 (. "SS0.5 - .---0- X) , 0_ _ O. 500

FRAGIET [JEC1 10N CHAACTERI STICS (,)FRAM.N ROW I 0(40 AT I UulA- -T 1O/, / W i Y -- ro gpiV,.'S Li VE1 rIr

..._ - _(.s)_.... (ft/;c) J (eue- ) _(f_/e _) v e f f4L/u C1 (3) U' , 3 4,(. ] ,-

3 0_0 4 1u -- -. ' - X -4- - L--5. . .. I, .. . . .- -2 U .. . . 51'. 1,. . . 5.. . I0' ...... 2 . . .... ... l i .... .. _ I_ ... 3. 1. . : . ._q . .. ,

5 -2.5 *,]I -4. .5 W3.

9 ~ ~~~~ ~ . 5 ..... ?,(;j I -5 : :..., -. 5<40 6~I 4 ( I44

9 o0 I. __,. - -- ,.. - - . 5

1-6.0 5! i0 60 -t. 1 5; 6--- - . ,

13 __ _ - 6.5 ;5 ',-- i .. .- 7/ ... . .5411 .. . - 7- 0- .. . .. 350i4 -6. _ _ '.50 -7.0 50 110:

15 -7.0 5400 -7.0 5470

16 -7 .0 ..... .. _____4 _____ ___17___ -7.0 5300 _

NOTES:

(1) All linear dimensions are in inches.(2) Polar angle is given from the fragnient c,9. relative to a norital to the warhead

axis throuqh that c.q. P'us anqles are toward the booster end. Velocity is theestinlted average velocity measured over the first fifteen leet of travel in astatic arena test, including losses through shroud(s) and insulation.

(3) Beoster end.

(4) Thtu har a(teri;'ations shown on this ptage reflect the oata fro,tlhe P4IOVvlnt te~ts repoirt d hi'reiin, hut are lOUt to Iie ui.ed our

the. second phase IIII;AL ed-gaa, analysis. See Nute 4 on page26A.

PAGE 26

1 },4I € .,< i

" ,,, S *..<' .'',' 1 '-z". . -': "

I4

TABLE 3.3.'4A

J ~ ~WARHEAD CflAfACTER1 ZAT IONSPKED ICTED FOR 11.5-I OCH DI N~i TER X 335- Lli ,,.AxjjADS

COHl Al DING I1:1 WEVONV) 1I IBAL FRA(;VLDTS(BASED ON DATA OlA I DL) IN TEST NO, Q1NOG32GAO) (4)

10lA! ! 0.131-C1C U: 11 Li I I AC ---

I0s 1'i* ); 0. /0 8P_LOG R i p 1 /b--

LUN 111I: 0. 8'- 0. 933 1 .07/

FkAIl NI I E1EC 10.1 ___ I! rppA T E!I.J

iii~' Vi t3CTP N~~c Y~~

ANGIJ A\(. 0-i 1 ! 'I L AVG 0- A"'' L AV(. --HIM11LFrOT C (den(. (1- /S') _ _(P-.. (f- I 0~ ~

3 ~ ~~ ~ 6 7 5JO '' I(

4~ 1) 0Y0

6 3 100i 34

84 530 4 iU9 4 !,no 5400 4

10 '*01) o

3 -11 41) -- ~( - - 'I-

14 6 5410 / bi k)

167 0-U -----(

NOTES:

(1) All linear diosioris are in) incfrs.(2) Polar angl e is q iven frcont the fragmenot c q. rel atiye to at nr mi to thle %-: Iiea

axis thrOUI lit c) C.g Pl! angles arei towird the bomor o ed Velocity i theestimated 'I i.'r-pc velocity i'ea 0 oP over Ote first filtuel leot of travul inl asta tic arenO Lust, i ilcl dill tig ls!eS ttiiULiIi hio' I-( s) anld IoSolut ion.

(3) Ileoster efid.(4) lhie chai-acteii,alioTs (liven oil this page(Ic at-e b)aSed upon t10

results obta id from Test No. Q1109'26A1 whicht is not reportedherein. The I 3i-1b v-,artiad I tuLd in QNOWCAO inrorponi te(dthe recomiir'itled d'-sign dtai is li ven onl pous 40 of thi,.rposfor the 7OXp-voin vorsiion of it I 3-l firot i'iro HIMlA ua od.Theroolt obla Pied from QGUU'?iArO will be r1-pfo-t d fully ill aSubiseque!nt. rep-It. The chli roe rizdtion005 on t hiis pine! il hlused in the second phase110 enit-imn anil,J since. tti-yreflect tte poi-foriiance oif the recotiincnti, de,,i go'

PAGE 26A

TABLE 3,3.5

3 IWARHEAD CHARACTERIZATIONSPREDICTED FOR 11.5-NCH DJAMETER x 200-ti WARHEADS

CONTAINING PREFORMED IX HIB3AL FRAGMNI S

j(BASED ON DATA OBTAINED IN TEST NO. QNO429AO)

FRETIS7 -- _-_T-AILS

FRAG. WT. 500-grain 700-.9rain 900-1raiTOTAL-UN. .1161 85] 640

WIDIH ACROSSFLATS 3/4 7/8 1

(inch)-THilCKNESS0.40.40.4(inch) O.______48_____.__5_______O.___5___8

FRAGMENT EJECTION CHARACTERISlICS (1)

ROW NO. POLAR ANGLE VELOCITY POLAR A0!6LE V-LOC-Y -- LOR ANIGLE VELOCITY(degrees) (ft/sec) (degrees) (ft/sec) (deqrees) (ft/sec)

1 +11.5 4100 +10.0 4100 +7.5 41002 + 7.0 4200 + 5.0 4200 +4.5 4?503 + 4.0 4300 + 2.5 4350 42.0 44004 + 2.5 4400 + 1.0 4500 0.0 45505 4 1.0 4500 - 1.0 4600 -1.0 47i00-6 + 0.5 4650 - .0 4700 -2.0 ----__1 . ...7 - 0.5 4200 - 2.0 4850 -2.5' 49508" - 1.0 4800 - 2.5 4950 -3.0 51009 - 1.5 4900 - 3.0 5050 -3.0 520020 - 2.0 5000 - 3.0 5150 -3.5 530011 - 2.0 5100 - 3.5 5250 -4.0 535012 - 2.5 5200 - 3.5 5300 -4.0 545013 - 3.0 5250 - 4.0 5400 -4.0 550014 - 3.0 5300 I -4.0 5450 -4.5 550015 - 3.0 5400 - 4,0 _ 5500 -4.5 1 550016 - 3.5 5450 - 4.0 1 5500 -4.5 1 550017 - 3.5 5500 - 4.0 1 5500 -4.5 545018 - 4.0 5500 - 4.5 T 5500 -5.0 535019 - 4.0 5500 -_4.5 5500 -5.0 520020 - 4.0 5500 - 4.5 5400 -5.0 495021 - 4.0 5500 - 5.0 5300-22 - 4.0 5500 - 5.0 5150 123 - 4.0 5450 - 5.0 495024 - 4.0 535025 - 4.0 5250'-26 - 4.0 510027 - 4.0 4950

NOTES:

(1) Polar angle is given from the fragment c.g. relative to a normal to the warheadaxis through that c.g. Plus angles are toward the booster end. Velocity is theestimated average velocity measured over the first fifteen feet of travel in astatic arena test. including losses through shroud(s) and insulation.

2i A and 8 are end-ring rows.3 Booster end.

LPPAGE 27

.. . " :... . . . ." ., + . , ,, . -.', ,.- -.- ;

II

U TABLE 3.3,6

WARHEAD CHARACTERIZAT IONS (4)

PREDICT[D FOR 1 ,5-1NCH DIAMEI FR x 200-t.! AEIWADSCONTA]NING F UI LFORNLE) HI -AJ iAU-LNIS

(BASED ON DATA OBTAINED IN TEST NOS, QN0328AO AID UNO29AO)

______ _____WC tN OAu ( .- .

FRAG. WT. I00- Ca n . /0O--, i100 NO._ - ]14 - 836 .................

,CICU L, , 1 ' f,L .... . ..-. . . . . ... . . . .. . .

WIDTH: PL- l- - 0.741 0. '.5,8 0 9r)

NII D I: NL. 769 0.909 . _000

Til C tl; S ". .. ..... 0 L -,, .... .. . . O:!C3 . . . .. . . . 0. {)-. ,, t "t . . . .

FRAG!ENT EJECTION CI!AR(CTL[IS1ICS (2)FRA. F NT RON41;!;i i- -V OC- 1 Y- - T , AA ;- - ] J Y --- S- IL - - L- ,i 1-

(deor(F,) i (ft/snc) (o eer) ( isec) (.,<r... j t ,3 j 0 _4 04..] I3 .- ".2. 0 , 4] 0 3H .i Cl ] ! 4 iU I 40.Ii I ,!](.

4 .. 41 ., 4400 )0 1 . i . 4 - ,-544

;0 . -I 0 . 0 -

-- L - 4

9 -20 4901) / U .. 0010 - -- -3-0 j s J)f -[- -3 - -- -',it,,. . - - . ' - -- - ->''

__ _ - 3.0 51"9] )J / -[~ ., , -,. ',' 119 4 9U 0.. " ....3.0.

1 ) 1 , .J t 44- 0 4 0 -- - -i- - ,

15 ' - -4J 4 0 540 1 4 I . .. ., 0I

17 -r4 .5C)' - 4:., ?

18-4 it 0 - 0 , - 0 1 < '519 4. 5 5500 .........- 5.0 . ,..20 4. 5 ( 1 -5.0 b -.. - ] U

21 -5 0 . 0 .. .,22 -5.05 .. . - 500

4 -5.0 _24 -5.0 530) _ _ _._

26 -5.0 4900 - --_"

NOTES:

i All linear dimensions are in inches.Polar angle is given from the irdqinonft c.g. relative to a normal to the warheadaxis throuch that c.q. Plus dnjles are toward the booster end. Velocity is theestimated average velocity rm.:-ured over the first fifteen feet of tradve1 in astatic arena test, includiitg losses through shroud(s) arnd insulatioi.

(3) Booster end.

(4) The characterit tion. '.tho:n in thi-, page reflect. the ditla fromthe vlrViltnt. It-',(,. ti,'(trt ut h rtirt itl. ite Itol. to t)e t:. , forthe second :hii i HAL td-giurditt lysi!. See Note 4 on page28A.

PAGE 28

TABLE 3.3.6A

WAMIL AD CIIARACIIR IZAl IONSPRED ICTED FOR .11. '>- ICH Dl A~TI'- FR X 20,'O-1I HFD

CONTAIN rN I- I k F. 1 RHii1) 11 1iA Ar[.~I(BASED ON DAMA 001 Al ID IN1 UEST NO, uNDj6') 4

TOTAL 11' ;:) I> -8A),C t i I' ___ U'- i 1. U 1 1,t L

W ti 1.76 190')- I -(t

0 1 ) L)/- U - r' . -

PI 1PVAVG 0- 1 A IA.(.0

/ A

.3

104

i J I

b - - -' -

NOTRI S() All 1 1 i orit dit'tttt'jim; a ' in ill( hL-..

ax i s tiuri''ilt thint 'rl . j I'u (.. a ' i r no titi how'' i . V~ It) i I',' ,

'tilt i 'l '1atciqe t 't i t-. i t ''0 Ii till f st tilt.Il ' u .r' i t i t t i tv. oil L

(3) LUowttIer end.O(4) The Chit am I t ilaltins tii t tn iii' Iji t' ,-' has it ulocii Owc

lvycO' in til't ntln i', 11(o ityi~. ONI'rtr t'10 YB'. fitt I i'

th r(flco.t - de" it ti lu l it- i i c. ('11r it 'd 0 il At-,- Ip

PAGE ?8A

TABLE 3,3.7

WARHEAD CHARACTERIZATIONS

PREDICTED FOR 19-INCH DIAMFTER X 200-LB ANNUIAR WARHEADSCONTAINING PREFORMED HEX HIBAL FRAGMENTS

(BASED ON DATA OBTAINED IN TEST NO. QNO4O9AO)

FRAGMENT DETAI LSFRAG. WT. 50E0-ra _i 700-qra i 900- rainTOTAL NO. 975 741 55

-I_-I1 ACROi SS-FLATS 7/8 1 1-1/8

(_inch) dTICKNESS 0.42 0.42 0.42(inch)

"K" VALUE(in fuel.) 70 74 71

FRAGMENT EJECTION CHARACTERISTICS (1)

N POA AGLE VELOCITY A NL E VELOCITY- P-0LM-A[E-VEOCROW NO. (degrees) jft/sec) ede.rees (_ft/sec) __deqrees) (ft/ec)__ _ (T +17.0 3600 +15.0 3650 -36S(0 . 3702 +12.5 3950 + 5.0 4000 - 3.5 41 13 + 2.0 + 1.0 4300 -0-7-- 45004 0.0 4450 - .0: 00 o480015 - 2.0 4650 - 2.5 4750 3.5 5000 I6 - 3.0 4800 - 3. 5 -4950 o 5.0 | 51007 - 4.0 4950 - 4.5' 5050 5.h-- ---51-O8 - 4.5 5050 - 5.0 51-1 -o --9 - 5.0 5100 - 5.0 5100 -6.0 48()0

10 - 5.0 5100 - 6.0 5000 - 9. Q - 4700---11 - 5.5 5050 - 6.0 4900 -10.0 4012 -_6.0 4950 - 7.0 475013 - 6.0 4850 -10.5 460014 - 7.0 4700 ]1

15 -11.0 4600 I

(1) Polar angle is given from the fra(ynent c.q. relative to a normal to the warheadaxis through that c.g. Plus angles are toward the booster end. Velocity is theestimated average velocity measured over the first fifteen feet of travel in astatic arena test, including losses through shroud(s) and insulation.

(2) Booster end.

L PAGE 29

TABLE 3.3.8WAR EAD CHARACTER1 ZATIONS

PREDICTED FOR 19-incii DIAMETER x 200-1 B WARHEADSCONTAINING FIREFORMED HIBAL FRAGMLNTS

(EXTRAPOLATED FROM DATA OBTAINED IN TEST NO. ONO'iO9AO)

-- FR-A-G-MN-T-0-I Tf is-(.iFRAG. WT. 500-grain 700- ra in 9OO-or~iiri

"-- o-IA! NO. 980 720 540;CIRCUMIDRNTIAL 70/row 60/row 54/row

1 _NSI-E 0.808 O____DE 0.942 1.047OUTSIDE U.653 0.995 1.1Gb

NGI10INAL 0.786 0.917 1.100WIDTH: ____ ____ _____ ____ ____ ___

TICKNESS 0.5 0.5 0.5

FRAGMENT EJECTION CHARACTERISTICS (2)

ROW NO.VWUCITY POLAR ANGLE VELOCITY POLAR ANGLE VELOCiT-(deqrees) (ft/sec) (degrees) (ft/sec) (deorces) (ft/sec)

l__ _.(3) 417.0 3600 -16.0 6-O- - .(j i 370--2 + 6.0 390 - ---- 0 -4-000 --- -3.4----0---4-1.5003 + 2.0 - 4?O .. 0.5 4300 0.. 4 50044 - . 5o --1.5 -46 -00 -- 3.- 406 2.0 4 47o0 - 3.0-(4 ' - 4)- O -0--4-- "- tO -

3.5 (4) ,1900 - 4.0 -4) 5000 -- 5.0 T 5h P ---7 - (4. 5005.(4) 50.0 -.- - --8 5.L(4) 5200 --.0-(4) .. 5200 -5.5 -4. 51009 5.0- (4-) 5>200- --5.5 (4) __5- /.00 1 - .0- - . . 00re0- (4 - ).4 - --000 4)-H.-(D 76-11 - 6.0 (4) 5i-O - 7.5 4_- 4900 _ .. _

12 5--(4) 5-- oJ -11 5 i4 _

13 -18.0 (4) 4600-__14 -13(Y-(41 00 ______ _____ ___

1718

202122 .23-24

, , 25

NOTES :llA linear dimensions are in inches.2 Polar angle is given from the fragment c.g. relative to a normal to the warhead

axis through that c.g. Plus an(Iles are toward the booster end. Velocity is theestimated average velocity measured over the first fifteen feet of travel in astatic arena test, including losses through shroud(s) and insulation.

(3) Booster end.(4) These values conform to data for preformed fragments. Values for fireformled fragments

may differ when proper fireforning is achieved.

PAGE 30

16 _____ ________ ___________ ________ _____Y _

I'

" | V

+10| Io

+ 5 POLAR ANGLE VELOCITY -00

POLAREJECTION _ANGLE

MEASURED FROM .5000 FRAGMENTFRAGMENT C-g. VELOCITY

(PLUS IS (ft/sec)TOWARD

BOOSTER-END -

(degrees) - 5 -

-10-

I I I I I i I I I I i I I I I01 2 3 4 5 6 7 8 9 10 11 12 13 14 15

FRAGMENT c.g. DISTANCE FROM THEBOOSTER-END OF THE WARHEAD (inch)

PREDICTED FRAGMENT EJECTION CHARACTERISTICS(POLAR ANGLE & VELOCITY)

FOR AN 80-LB SOLID WARHEAD

Having an 8-inch O.D. x 2-inch I.D. x 15-inch long x 0.460-inch case thickness,and containing preformed hex-HIBAL fragments sandwiched between an outer skin of0.030-inch thick steel and an inner skin of 0.010-inch thick steel.

Prediction is based upon the data acquired in Test No. QN0319AO.

L P 1IGURE 3.4.1PAGE 31

.......I !

I

|II

I

+10

POLAR + 5 VELOCITY

EJECTION

MEASURED FROMFRAGMENT c.g. 000

(PLUS IS FRAGMENTOWAR-D) 000 VELOCITY

(degrees) (ft/sec)

-500

.0 POLAR ANGLE

-10

I i i I i i i i i I i -10 14

FRAGMENT c.g. DISTANCE FROM THEBOOSTER-END OF THE WARHEAD (inch)

PREDICTED FRAGMENT EJECTION CHARACTERISTICS(POLAR ANGLE & VELOCITY)

FOR A 135-LB SOLID WARHEAD

Having an 11.5-inch O.D. x 2.88-inch I.D. x 14-inch long x 0.51-inch casethickness, and containing preformed hex HIBAL fragments sandwiched between anouter skin of 0.015-inch thick steel and an inner skin of 0.010-inch thick steel.

Prediction is based upon the data acquired in Test No. QNO514AO.

PAGE 32

BFIGURE 3.4.2,,o°, . I>

I

EI

+10-

POLAREJECTION + 57POLAR ANGLEANGLE VELOCITY 7000

MEASURED FROM 6000FRAGMENT c.g.

(PLUS IS FRAGMENTTOWARD 0 5000 VELOCITY

BOOSTER-END) 0 (ft/sec)

(degrees) 4000

-3000

-5

-10

0 5 10 15 18FRAGMENT c.g. DISTANCE FROM THE

BOOSTER-END OF THE WARHEAD (inch)

PREDICTED FRAGMENT EJECTION CHARACTERISTICS(POLAR ANGLE & VELOCITY)

FOR A 200-LB SOLID WARHEAD

Having an 11.5-inch O.D. x 2.88-inch I.D. x 18.38-inch long x 0.573-inch casethickness and containing preformed hex HIBAL fragments sandwiched between an outerskin of 0.015-inch thick steel and an inner skin of 0.010-inch steel.

Prediction is based upon the data acquired in Test No. QN0429AO.LPAGE 33

FIGURE 3.4.3

I

+15 K

+10 POLAR ANGLE

+ 5VEO5T 7000

POLAREJECTION

ANGLE FRAGMENTMEASURED FROM 0 VELOCITYFRAGMENT C.G. (ft/sec)

(PLUS IS -4000TOWARD

BOOSTER-END) 3

(degrees) - 5

-10

II I I I I I I0 1 2 3 4 5 6 7 8 9 10 11

FRAGMENT C.G. DISTANCE FROM THEBOOSTER-END OF THE WARHEAD (inch)

PREDICTED FRAGMENT EJECTION CHARACTERISTICS(POLAR ANGLE & VELOCITY)

FOR A 200-LB ANNULAR WARHEADHaving a 19-inch O.D. x 10.6-inch I.D. x 11.5-inch long x 0.46-inch case

thickness and containing preformed hex-HIBAL fragments sandwiched between an outerskin of 0.030-inch thick steel and an inner skin of 0.010-inch thick steel.

Prediction is based upon an extrapolation of the preformed fragment data inTest No. QNO4O9AO.

PAGE 34 FIGURE 3.4.4

II

I

+10 KI

POLAR ANGLE

POLAR +5EJECTIONANGLE 7000

MEASURED FROM V

FRAGMENT c.g. -6000(PLUS IS FRAGMENTTOWARD 0 -5000 VELOCITY

BOOSTER-END) 0(ft/sec)

(degrees) 4000

- 3000

I I I I I I I 1 I iII

-

-10

0 5 10 15FRAGMENT c.g. DISTANCE FROM THE

BOOSTER-END OF THE WARHEAD (inch)

FRAGMENT EJECTION CHARACTERISTICS(POLAR ANGLE & VELOCITY)

FOR AN 80-LB SOLID (FIREFORMED FRAGMENT) WARHEAD1.Having an 8-inch O.D. x 2-inch I.D. x 15-inch long x 0.438-inch

Lcase thickness. Prediction is based upon data acquired in TestQN0225A0.

PAGE 35

FIGURE 3.4.5

III

SI

+10 VELOCITY 7000

POLAR + 5 000EJECTIONANGLE FRAGMENT

MEASURED FROMFRAGMENT c.g. 0 - -5000 VELOCITY

(PLUS IS (ft/sec)TOWARD

BOOSTER-END) -4000

(degrees) -

POLAR-10 ANGLE 3000

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14

FRAGMENT c.g. DISTANCE FROM THEBOOSTER-END OF THE WARHEAD (INCH)

FRAGMENT EJECTION CHARACTERISTICS(POLAR ANGLE & VELOCITY)

FOR A 135-LB FIREFORMED FRAGMENT WARHEAD

Having a 11.5-inch O.D. x 14-inch long x 2.88-inchI.D. x 0.5-inch case thickness.Prediction is based on data acquired in Test QNO311AO

PAGE 36

FIGURE 3.4.6

III

II

+15[

POLAR +10 VLCTEJECTIONANGLE 6000

MEASURED FROMFRAGMENT c.g. FAM000

(PLUS IS FRAGMENTTOWARD VELOCITY

BOOSTER-END) - 5 000 (ft/sec)

(degrees) -10POLARANGLE

0 1 2 3 4 5 6 7 8 9 10

FRAGMENT c.g. DISTANCE FROM THEBOOSTER-END OF THE WARHEAD (inch)

FRAGMENT EJECTION CHARACTERISTICS(POLAR ANGLE & VELOCITY)

FOR A 200-LB (FIREFORMED FRAGMENT) SOLID WARHEAD

Having a 11.5-inch O.D. x 2.88-inch I.D. x 20-inches long x0.563-inch case thickness.Prediction is based on an extrapolation of the data fromTest QN0328AO

[FIGURE 3.4.7

PAGE 37

.:.-,>

k AD-A92 071 NEW MEXCO INST OF ININNG AND TECHNOLOYSOORRO TER--ETC F/69/1

I ISAL PROGRAM PRELIMINARY WARHEAD-DESIGN. VOLUME 1.1 U)ISEP So N0002479-C5333I UNCLASSF7ED NMT/TERA-T-8013S-U-VOL- NL

I1

POLAR ANGLE

POLAR + 5EJECTION VELOCITY 7000ANGLE

MEASURED FROM 6000FRAGMENT c.g. FRAGMENT

(PLUS IS RAMNTOWARD 0 -5000 VELOCITY

BOOSTER-END) (ft/sec)

(degrees) 4000

- -3000

-5

-10-

1 2 3 4 5 6 7 8 9 10 11FRAGMENT c.g. DISTANCE FROM THE

BOOSTER-END OF THE WARHEAD (inch)

FRAGMENT EJECTION CHARACTERISTICS(POLAR ANGLE & VELOCITY)

FOR A 200-LB ANNULAR WARHEAD

L With a 19-inch O.D., 10.6-Inch I.D., 11-inches long anda 0.5-inch case thickness, curves are extrapolated fromdata obtained in Test QNO4O9AO

PAGE 38 FIGURE 3.4.8

TABLE 3.3.9DESIGN FOR WARHEADS

USINGPREFORMED HEX HIBAL FRAGMENTS

ITEM 8-inch x 11.5-inch x 11.5-inch x 19-inch x [80-lb 135-lb 200-_b 200,-1b_

DIMENSIONS

O.D. 8.0 11.5 11.5 19.0I.D. 2.0 2-7/8 2-7/8 10.5

LENGTH 15.2 14.0 18-3/8 11.5OUTER SKIN THK. 0.025 0.015 0.015 0.030INNER SKIN THK. 0.010 0.010 0.010 0.010S & A TUBE THK. 0.063 0.063 0.063 N/A

"END-PLATE THK. 0.125 0.125 0.125 0.125

FRAGMENT DETAILS

THICKNESS 0.42 0.485 0.548 0.42WIDTH 0.875 0.813 0.75 0.875

500- NO. PER ROW 25.0 40.0 43.0 65.0grain NO. OF ROWS 18.0 18.0 27.0 15.0

TOTAL NO. 450.0 720.0 1161.0 975.0THICKNESS 0.42 0.485 0.548 0.42

WIDTH 1.0 0.938 0.875 1.0700- NO. PER ROW 22.0 35.0 37.0 57.0grain NO. OF ROWS 16.0 16.0 23.0 13.0

TOTAL NO. 352.0 560.0 851.0 741.0THICKNESS 0.42 0.485 0.548 0.42

900__WIDTH 1.125 _ _1.063 1.0 1.125900- NO. PER ROW 19.0 31.0 32.0 50.0grain NO. OF ROWS 14.0 13.0 20.0 11.0

TOTAL NO. 266.0 403.0 640.0 550.0

MATERIALS

OUTER SKININNER SKINS & A TUBEEND PLATES

HIGH EXPLOSIVE TO BE DETERMINEDFRAGMENTS SAE 4130 ALLOY STEEL, OIL QUENCHED FROM 1550 0F,

DRAW AT 800'F to RC42

BOOSTER DETAILS

LOCATION AT ONE ENDOMPOSITION TO BE DETERMINEDSIZE

END-RING HOOPS

(EA. WIDTH 0.5 0.5 0.375 0.25EAD RADIAL THK. 0.44 0.5 0.56 0.44END) MATERIAL MILD STEEL

L ALL DIMENSIONS ARE IN INCHES.

PAGE 39

A&A.Ai

TABLE 3.3.10DESIGN FOR WARHEADS

USINGFIREFORMED HIBA. FRAGMIENTS

ITEM 8-inch x 11.5-inch x 11.5-inch x 19-inch x80-lb 135-lb 200-lb 200-lb

DIMENSIONS

O.D. 8.0 11.5 11.5 19.0,,__I.D. 2.0 2.88 2 .

CASE THK. 0438 0.500 0.563 0,_50_S & A TUBE THK. 0063 0.063 0.063NIAEND-PLATE THK. 0. 125-- 0.125 O.125 0125

FRAGMENT DETAILS*

INTENDEDWEIGHT LONGITUDINAL GROOVES

DEPTH, INSIDE 0.110 0.140 __ 0.170 fL.14D_OUTSIDE 0.110 0_.14Q 0., 170 0__14_0_

SPACING INSIDE) 0.799 0.767 0.741 .0 _OB500- CIRCUMFERENTIAL GROOVES

grain DEPTH, INSIDE 0. 115 0.115 15 0_.115_OUTSIDE 0.205 0.285 0.350 O.285

SPACIN SIE[ 0.833 0.824 0.769 0.786FRAGMENTS PER ROW 28.0 43.0 44.0 70.0NUMBER OF ROWS 18.0 17.0 26.0 14.0

TOTAL NO. OF FRAGMENTS 504.0 731.0 1144.0 980.01TNTEDWEIGHT LONGITUDINAL GROOVES

DEPTH, INSIDE 0.110 0.140 0.170 0.140OUTSIDE ____O.110 0.140 O.170 0.140

SPACiNG INS IDE. 0.895 0.892 0.858 0.942700- CIRCUMFERENTIAL GROOVES VC R__0_ 0_VS

grain DEPTH, INSIDE 0.115 0.115 0.115 0.115OUTS I DE 0.205 0.285 0.350 0.285

SPACING -INS --E - 1.0 0.933 0.909 0.917FRAGMENTS PER ROW 25.0 37.0 38.0 60.0

NUMOER-OF ROWS 15.0 15.0 22.0 12.0TOTAL NO. OF FRAGMENTS 375.0 555.0 836.0 720.0

INTENDED

WEIGHT LONGITUDINAL GROOVESD- 11H -] f O. 10 0.140 O. 170 0. 140

U1TSI 0D. 0. 110 0.-140 0.170 0.140]--- AcTI- T -- 1.017 1.000___ 0.959 __ 04Z

900- CT-IJM-R-' FtRIi EN-TI AL-G RO-V E __

grain - E-T14W,11N S-I E- 0 0.115_ 0.115 O11OUTSI DE 0.205 0.285 0.350 .Q-285_

1.154 1.077 1.000 _ , __R FGMENTS-I E-R -RO'CW 22.0 ... 33.0 34.0 . . 54t0

UitEffk0F ROWS__ 10 _13.0 -- 20.0 ._,0__TOT-Al- O O76F FRAGMLNTS 2 6.0 2.0_ 680.0 540..0-

MATERIALS

WARHEAD CASE ALL FIREFORMED FRAGMENTS MADE OF 4130 STEEL,_QUENCHED__.AND DRAWN TO RC42L S & A TIUDE

_ _._ _ &_ _ __l-_ __ _.... END-P] ATrFS MILD STEELI Gil rxpI.(}S1VE I

* THE INCLUDED ANGLE OF ALL GROOVES IS TO BE 370, ALL DIMENSIONS ARE IN INCHES.

PAGE 40

Distribution

CommanderNaval Sea Systems Command

Washington, DC 20362

Attn : SEA-62RSEA-62R54

SEA-62 Z3SEA-62Z5PMS-400M

Assistant Secretary of the NavyAttn: (RE&S) R. RumpfWashington, DC 20362

Chief of Naval OperationsDepartment of the NavyWashington, DC 20362Attn: OP352L (CDR Webb)

OP982F31 (CDR Fricke)

CommanderNaval Air Systems CommandWashington, DC 20362Attn: AIR-5413 (J. Newquist)

AIR-350 (H. Benefiel)PMA-241PMA-262

CommanderNaval Surface Weapons CenterDahlgren, VA 22448Attn: Code G34

G34(A. Hales)G35(S. Waggener)G13(T. Wasmund)

CommanderNaval Weapons CenterChina Lake, CA 93555Attn: Code 3261 (T. Zulkoski)

Code 383 (J. Pearson)Code 338 (K. Grant)

Applied Physics Laboratory/Johns Hopkins UniversityJohns Hopkins RoadLaurel, MD 20810Attn: B. Woodford

C. Brown-Group BFD

DirectorUSA Ballistic Research Laboratories (DRDAR-DLV)Attn: D. MowrerAberdeen Proving Ground[ Aberqeen, MD 21005

41

IDistribution (Cont'd)

CommanderUSA Missile Research & Development CommandAttn: E. Atkins, Adv. Concepts Group

LTCOL R. Kelly, Code DRSMI-ODHuntsville, Alabama

CommanderArmaments Research and Development CommandDover, NJ 07801Attn: DRDAR-LCE-M (T. Stevens)

DRDAR-LCA-L

CommanderAir Force Armaments LaboratoryEglin AFB, Fl 32542

7 Attn: AFATL/DLOW (D. Glendenning)AFATL/DLYD (K. McArdle)ADTC/SD7ED (P. Buckley)

CommanderNaval Postgraduate SchoolMonterey, CAAttn: Professor Ball

McDonnell DouglasP.O. Box 516St. Louis, MO 63166Attn: J. Riley Dept E241, Bldg 106

Martin Marietta Corp.Mail Point 159 P.O. Box 5837Orlando, FL 32855Attn: F. Malatesta

General DynamicsPomona, CA 91766Attn: J. Stamper

Boeing Aerospace CompanyPO Box 3999Seattle, WAAttn: E. Wilhelm

Vought CorporationP0 Box 225907Dallas, TX 75265Attn: J. Craddock

42

1

U Distribution (Cont'd)

Northrup Corporation500 East OrangethorpeAnaheim, CA 92801J Attn: Code &20 (R. Lawther)

Raytheon CorporationMissile Systems Division

Hartwell RoadBedford, MA 10730Attn: T. Cullinane

Hughes Aircraft Co.Missile Systems Group8433 Fallbrook Ave

Canoga Park, CAAttn: Mr. Buhnan

Bldg CT-10Mail Stop T94

Defense Technical Information Center (2)

Cameron StationAlexandria, VA 22314

43U