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SIrINATURF I Lh TI AI

~.U." 11,ANKLIN Hewa!, I' j lcations B~rand,,CODE -7 AT

FCommander -Naval Weapons Laboratory

LDahgraii, VIrgnIa 22448 1 UNLASSirin:

UNCLASSIPIEDW14r N rNCLOSUnr. I% Prufvrt!

NWL TECHNICAL R 4PORT TR-29143January 1973

SURVIVABILITY OF AIR LAUNCHED GUIDED WEAPONS IN A FIRE ENVIRONMENT

by

J. A. Robinson

Test and Evaluation Department

C

Distribution limited to U. S. Government agencies only; Test andEvaluation; January 1973. Other requests for this document mustbe referred to the Commander, Naval Weapons Laboratory, Dahlgren,Virginia 22448.

I

FOREWORD

This work was accomplished under AIRTASK No. A532-532D/291-2/1501-0000-02 by the Naval Weapons Laboratory, Dahlgrenp Virginia.

The report has been reviewed by the following personnel ofthe Test and Evaluation Department:

H. P. Caster, Head, Weapons Evaluation DivisionF. W. Kasdorf, Assistant Head, Test and Evaluation Department

Released by:

Head, Test andEvaluation Department

ABSTRACT

Tests were conducted to establish fast cook-off characteristicsof the following guided weapons: (a) SIDEWINDER (AIM-9), (b) WALL-EYE (MARK 1 MOD 0), (c) SPARROW III (AIM-7), and (d) SHRIKE (AGM-45A).The type of reaction that occurred, the time to reaction and time-temperature data were obtained for each guided weapon when engulfedin fire from burning JP-5 fuel. These data are applicable to thedesign of thermal protection systems and the development of safer

fire fighting procedures.

I

ii

V1

CONTENTS

Foreword ............................................... i

Abstract ......................... ii

Introduction .................... ................... 1

Purpose ................................................ 1Fast Cook-Off Test Facilities ......................... 1

Test Configuration and Procedures .................... .. 5

Instrumentation . ... .. . . . . . . . .. . . . .. .. .. .. ... * . .. . .. 5

Results ............ ... . .......... ... * .............. 5

SIDEWINDER (AIM-9) .......... ........... ........ 6WALLEYE (MARK 1 MOD 0) ..... .......... . ...... . . 6

SPARWI II (Ac4-LI ) o .. .. . .. * . . . . . . . . * . * . 6 ***SPARROWiE (AIm-) . ............................. 8

SHIEIN (AIM-) ............................... 7

SPARROW III (AIM-7) ..... 81 ~ ~~SHRIKE (AGM-45A) ....... :::::::::::::::: 8

Recommendations ................................. 8

References ...................... ... ..... ............... 9

Apendices:

A. Definitions of Reactions (for Guided Weapons) .. A-1B. Fast Cook-Off Data Summary ................... B-I

iii

CONTENTS -(CONTINUE)

C. Fast Coo&-Off Test Data Sheets, Photographsand Time-Temperatue Data

SIDE I DER (AIM-9) .......................... c-iWALLEYE (MARK 1 MOD 0) ....................

C 8

SPARRow III (AIM-7) ......................... C-12SHRIKE (AGM-45A) ........... . ...... • .... ..... C-20

D. Distribution ....... D-1i

iv

INTRODUCTION

The major aircraft carrier fires that occurred in recent yearsaboard the USS FORRESTAL and the USS ENTERPRISE exposed a deficiencyin the knowledge of hazards associated with flame envelopment ofnavy air launched weapons. Reference (a) tasked the Naval WeaponsLaboratory to investigate these hazards by subjecting fleet usedweapons to ,simulated carrier flight deck fires (fust cook-offtests). Under this task, two tests were conducted on each of thefollowing:

a. SIDEWMER (AIM-9)b. WALLEYE (MARK 1 MOD 0)c. SPARROW III (AIR-7)d. SHRIKE (AG4-45A)

PURPOSE

Fast cook-off tests were conducted to obtain the time toreaction, the type of reaction and time-temperature data forselected air launched weapons. The data were required for thedesign of thermal protection systems and the development of saferfire fighting procedures.

FAST COOK-OFF TEST FACILITIES

The tests were conducted in %he following facilities:

a. Fast cook-off test retainer cage:

Figure 1 is an overall view of the retainer cage. It wasussd to prevent missile fly-away in the -&vent of a design modereaction. The cage had a 30-foot square base and encaged a 20-footsquare test pit. Figure 2 shows the stand used to restrain themissiles during tests.

b. Fast cook-off test open pit:

Figure 3 is a view of the open pit. It was used to test theWALLEYE guided weapons which are not designed to react propulsively.The walls of the pit were barked to a height of approximately eightfeet, and the pit contained a 30-foot square burning surface.

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TEST CONFIGURATION AND PROCEDURES

Previous tests on air launched weapons, reported by-reference (b)

and (c), were conducted with active rocket motors and igniters and

simulated warheads, boosters and safe and arm devices; or with activewarheads, boosters, and safe and arm devices, and simulated rocketmotors and igniters. For these tests, all propulsive and explosivecomponents of the weapons were active. The weapons were n.ot equippedwith wing and fin assemblies due to difficulty in obtaining thesecomponents. Guidance and control units were simulated when notavailable.

The fuel pits were filled with approximately two inches of waterto provide a level surface on which to float the jet aircraft fuel.The weapons were placed in a horizontal attitude,.36 inches (at theweapon centerline) above the water surface..

The necessary amount of jet aircraft fuel (JP-5) to ensure anexplosive reaction was supplied to the fuel pit. To facilitate rapidfuel ignition, gasoline was poured over the fuel surface and thermitegrenades (one placed in each corner of thefuel pit) were electricallyinitiated to ignite the fuel.

The tests were designed to provide: (a) Flame engulfment within30 seconds (time to 1000'F average flame temperature), and (b) anaverage flame temperature of at least 1650 0F.

INSTRUMENTATION

The data acquisition system consistd of iron-constantan thermo-couples, an elw.tronic temperature reference junction and an oscil-lograph. The system was used to measure the temperature of the

flame environment about the missiles and the temperature of internalmissile components (when possible).

Documentary high speed movie cameras, a video recorder and ablack and white still camera were used on all tests.

RESULTS

Definitions of reactions used in this report are presented inAppendix A. A listing of the weapons tested and corresponding reactiontimes are provided in Appendix B. The detailed data, including time-temperature histories and pre-test and post-test photographs are

5

presented in Appendix C. Test results for each weapon ,tested

were:

SIDEWINDER (AIM-9)

The shortest time to reaction for the SIDEWINDER missiles was59 seconds. The most severe reaction was a motor explosion.

a. Test No. GM-I: The motor exploded in the vicinity of the afthanger, separating the motor at approximately 18 inches from the aftend. This initial reaction occurred at one minute seven seconds andwas immediately followed by propulsive burning which would haveallowed the missile to thrash about if it had not been restrained.At two minutes 58 seconds into the test, the warhead deflagratedthrough the forward closure. There was no other explosive reaction.

b. Test No. GM-2: The rocket motor deflagrated at 59 secondsof flame exposure. This initial reaction was immediately followedby a chuffing action. The warhead and the Safe and arm device werethrown off the test stand into the fuel pit. These items did notreact.

WALLEYE (MARK 1 MOD 0)

The most severe reaction observed during the WALLEYE tests ":asa partial detonation. The shortest reaction time was two minutes 57seconds.

a. Test No. GM-3: The warhead deflagrated at three minutes 30seconds. The warhead ruptured at the rear end and burned for twominutes 49 seconds before partially detonating. The blast from thedetonation caused considerable damage to the test stand. Burningpieces of explosive were thrown about the test site to a radius of1200 feet. A number of grass fires were started by the burningexplosive.

b. Test No. GM-4: The warhead deflagrated at two minutes 57seconds. The booster deflagrated at five minutes 30 seconds.

SPARROW III (AIM-?)

The shortest reaction time of the SPARROW III missiles was oneminute 31 seconds. The most severe reaction was a warhead detonation.

a. Test No. GM-5: The motor deflagrated at two minutes threeseconds and burned violently. The warhead, the safe and arm device

and the booster all deflagrated separately and very mildly at 16minutes three seconds, 20 minutes 54 seconds and 22 minutes sevenseconds, respectively.

b. Test No. GM-6: The motor deflagrated at one minute 31seconds after the start of the test. The warhead detonated at 15

* minutes 41 seconds.

SHRIKE (AGM-45A)

Both SHRIKE warheads tested exploded. The shortest time toreaction was one minute 17 seconds.

a. Test No. GM-7: The motor deflagrated at one minute 44seconds and the warhead exploded at one minute 57 seconds.

b. Test No. GM-8: The warhead exploded at,, one minute 17seconds. The motor deflagrated at one minute 29 seconds.

CONCLUSICKS

SIDEWINDER (AIM-9)

a. The missile will deflagrate or explde in a flight deck fire.

b. If unrestrained, the missile will thrash about as a resultof the MARK 36 MOD 0 motor reaction.

c. The motor and warhead will react in less time than the fiveminute minimum time requirement of reference (d).

WALLEYE (MARK 1 MOD 0)

When exposed in a flight deck fire, the MARK 1 MOD 0 WALLEYEguided weapon can be expected to react:

a. In less time than the five minute minimum time requirementof reference (d).

b. So as to create a major hazard to items in the immediate area.

c. So as to kindle new fires with burning explosive that isthrown about.

[ 7

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SPARROW III (AI9-7)

When the SPARROW III missile system is subjected to a fast cook-off environment, it can be expected to:

a. React in less time than the five minute minimum time require-ment of reference (d).

b. Cause extensive blast and fragment damage.

c. Enhance existing fires.

sai'n (A-45A)

It is concluded that when the SHRIKE AGM-45Amissile system, isexposed in a flight deck fire environment:

a. [Reaction will :occur in less time than the five minute minimumtime requirement of reference (d).

b, The MARK 68 MOD 0 warhead will explode.

c. Additional fires will be started by scattered fragments andburning explosive.

RECM4ENDATIONS

It is recommended that a retro-fix program be initiated for allfleet used air-toi.-air or air.to-ground guided weapons. The objective

4of the program would be to extend the minimum time to reaction to fiveminutes without increasing the severity of the reaction. It is recom-mended that the application of an insulating liner between theexplosive and the weapon's case and the application of an intumescentheat retardant paint on the external surface of each weapon be in-vestigated as possible fixes. The external thermal protection systemwould have to be extremely smooth, thin and tough to avoid adverseeffects on handling and aerodynamic performance.

It is further recommended that two of each type of these airlaunched guided weapons be thermally protected using the techniques

0 described above and subjected to fast cook-off tests. The weaponsshould be instrumented prior to being loaded. The data obtainedwould be used to verify the adequacy of the thermal protection system.

8

, , ,

a. AIRTASK, ,430-303/291-1/W46430-Oq, work request No. WR-l-8093.

b. Rocket Motor Survivability in Fire, :0. P. Hontgas, NWL Technical:Report !R-2508, November 1970.

c. Rocket and Missile Warhead Survivability in Fir , W. D. Smibh,NL Technical Report TR-28 0 8, October 1972.

d. Naval Weapons Cook-Off Program Plan, First Revision, September 1969.

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APPEDHA

DEFINITIONS OF REACTIONS (FOR GUIDED WEAPONS)*

Detonation (cookoff) - Munition performs in design mode. Maximumpossible air shock formed. Essentially all of case broken into smallfragments. Blast and fragment damage is at maximum. Severity ofblast causes maximum ground crater or flight-deck hole capable by themunition involved.

Partial Detonation (cook-off) - Only part of total explosive loadin.imunition detonates. Strong air shock and small as well as largecase fragments produced. Small fragments are similar to those in-normal munition detonation. Extensive blast and fragmentation damageto environment. Amount of damage and extent of breakup of case intosmall fragments increases with increasing amount of explosivedetonated. Severity of blast could cause large ground crater, orlarge flight-deck hole on carrier if munition is large bomb; hole,size depends on amount of explosive that detonates.

Eolosion (cook-off)- 4Violent pressure rupture and fragmentationof munition case with rVslting air shock. Most of metal case breaksinto large pieces which are thrown about with unreacted or burningexplosive. Some blast and fragmentation damage to environment. Fireand smoke damage as in deflagration. Severity of blast could causeminor ground crater, or small depression on flight-deck of carrierif munition is large bomb.

Deflagration (cook-off) - Explosive in munition burns. Casemay rupture or end-plates blow out; however, no fragmentation of thecase. No fragments are thrown about. Damage to environment due onlyto heat and smoke of fire. No discernible damage due to blast orfragmentation.

*Definitions from NAVORD OP.5, VOLUME 1 THIRD REVISION

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Test No. GM-I

Data Sheet

Item Tested: SIDEWINDER AIM-9 Missile

Components :, MARK 48 MOD 4 warhead containing 6 pounds ofPBXN-3 explosiveMARK 13 MOD 0 - Safe and Arm DeviceMARK 36 MOD 0 - Rocket MotorMARK 264 MOD 0 - Motor IgniterSimulated- Guidance and:,Control Sections

Date of Test: 28 August 1972

Weather Conditions: Cloudy, 2-4 knots wind, temperature 750F

Facility: 30' x 30' retainer cage with encaged fuel pitand test stand, Figure 4

Fuel: 200 gallons of JP-5

Test Fire: Flame temperature exceeded 1000OF at 30 secondsafter fire ignition and averaged 1810OF duringthe test.

Flame Duration: Six minutes

Results: A visual and audible reaction of the motor wasobserved at one minute seven seconds into thetest. This was followed by a propulsive burning

of the motor. At two minutes 58 seconds intothe test, the warhead deflagrated and burned.

Inspection of the missile, after the test, showedthat the missile had exploded near the aft hanger.Approximately 18 inches of the motor was missingas shown in Figure 5. The motor reaction forcedthe missile forward into the retainer stand.Figure 6 shows an indention on the retainer standthat was caused by this reaction. The center ofthe warhead section was bulged as shown in Figure 7.The safe and arm device burned.

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Test No. GM-2

Data, Sheet

Item Tested: SIDEWINDER AIM-9 Missile

Components: MARK 48 MOD 4 - Warhead containing 6 pounds ofPBXN-3 explosiveMARK 13 MOD 0 - Safe and Arm DeviceMARK 36 MOD 0 - Rocket MotorMARK 264 MOD 0 - Motor IgniterSimulated - Guidance and Control Sections

Date of Test: 8 September 197M

Weather Conditions: Cloudy, 6 knot wind, temperature 78OF

Facility: 30' x 30' retainer cage with encaged fuel pitand test stand

Fuel: 200 gallons of JP-5

Test Fire: Flame temperature exceeded 1000OF at 19 seconds

after start of fire and averaged 1720°F duringthe test.

Flame Duration: Seven minutes

Results: The rocket motor deflagrated at 59 seconds intothe test. The force of the reaction threw thewarhead and the safe and arm device into thefuel pit. These items did not react. Figure 8shows the forward section of the motor that re-mained in the test stand.

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WALLEYE GUIDED WEAPON FAST COOK-OFF

Test No, GM-3

Data Sheet

Item Tested: WALLEYE Guided Weapon MARK 1 MOD 0

Components: MARK 58 MOD 0 - Warhead containing 416 pounds-of Comp-B explosiveMARK 44 MOD 0 - BoosterMkRK 328 MOD 0- FuzeEX 5 MOD 0. - Control -UnitMARK 27 MOD 0 - Guidance Unit with, Nose Cover

Date of Test: 27 October 1972

Weather Conditions: Clear, 6-8 knots wind, temperature 550F

Facility: 30' x 30' open pit with test stand, Figuke 9

Fuel: 1000 gallons of JP-5

Test Fire: Flame. temperature exceeded 1000"F at 47 secondsafter start of fire and averaged 1720*F for theduration of the test.

Flame Duration: 11 minutes

Resul'4s: The warhead reacted by deflagrating at threeminutes 30 seconds into the test. The reactionruptured the rear of the warhead. A partial

detonation occurred at two minutes 49 secondsafter the initial reaction. The secondaryreaction was of such severity that burningexplosive was thrown about the test site to aradius of 1200 feet. A number of grass fireswere started by the burning explosive. Neitherthe booster, fuze nor any fragment samples wererecovered.

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Test No. GM-4

Data Sheet

Item Tested: WALLEYE Guided Weapon MARK 1 MOD 0

Components: MARK 58 MOD 0 - Warhead containing 416. poundsof 'Comp-B explosiveMARK 44 MOD 0 - BoosterMARK 328 MOD 0 - FuzeSEX 5- M-D 0 - 'Contrbl UnitMARK 27 MOD 0 - Guidance Unit without nose cover

Date of Tent: 3 November 1972

Weather Conditions: Clear, 8-10 knots, temperature 800 F

Facility: 30' x 30' open pit with test stand

Fuel: 1000 gallons of JP-5

Test Fire: Flame temperature at the weapon exceeded 10000 Fat 36 seconds after start of test and averaged1700°F during the test.

Flame Duration: 10 minutes

Results: At two minutes 57 seconds after the fire wasignited, the warhead deflagrated. Burningoccurred for three minutes 33 seconds, causingthe booster to deflagrate mildly. Figure 10shows some unburned Comp-B explosive and therupture in the warhead case caused by the initialreaction.

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SPARR( III MISSILE FAST, COOK-OFF

Test No. GM-5Data Sheet

Item Tested: SPARROW III AIM-7 Missile

Components: MARK 38 MOD 0 - Warhead containing 20 ,poundsof-PBXN-101 explosive-MARK 35 MOD 0 - Safe and Arm DeviceMARK 38 MOD,O - BoosterMARK 38 MOD 0 - Rocket Motor containing MARK 95_MOD-O propellant1&RK 265 MOD 0 - Motor IgniterBallast loaded Guidance and Control Sections

Date of Test: 11 December 1972

Weather Conditions: Partly cloudy, 2'knot wind, temperature 55PF

Facility: 30' x 30' retainer cage with encaged fuel pit:and test stand, Figure 141

Fuel: 200 gallons of JP-5

Test Fire: Flame temperature at the missile exceeded 1000OFat 29 seconds after the start of the test andaveraged 1800*F during the test.

Flame Duration: Nine minutes 30 seconds

Results: At two minutes 3 seconds after fire ignition,the motor started to burn violently. The war-head reacted by burning at 16 minutes threeseconds into the test. At four minutes 51seconds after the warhead began burning, thesafe and arm device deflagrated mildly. At oneminute 13 seconds after the safe and arm devicereacted, the booster deflagrated. Figures 11-13show the pre-test configuration and psl,.-testViews of the weapon remains.

Thermocouple locations are shown in Figure 14 andthe time-temperature data are presented in Figure 15.

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SPARROW III MISSILE FAST COOK-OFF

Test No. G4-6""ite Sheet

Item Tested: SPARROW AIM-7 Missile

Components: MARK 38 MOD 0 - Warhead containing 20 poundsof PBXN-1Ol explosiveMARK 35 MOD 0 - Safe and Arm DeviceMARK 38 MOD 0 -- BoosterMARK 28"MOD 0 - Rocket Motor containing MARK 75MOD 0 - PropellantMARK 265 MOD 0 - Motor IgniterBallast loaded Guidance and Control Sections

Dte of Test: 12 December 1972

Weather Conditions: Cloudy, 6-9 knots wind, temperature 58*F

Facility: 30' x 30' retainer cage with encaged test pit

and test stand

Fuel: 200 gallons of JP-5

Test Fire: Flame buildup was rapid, engulfing the missileat 17 second after start of fire

Flame Duration: 10 minutes

Results: The rocket motor deflagrated at one minute 31seconds after start of fire. At fourteen minutes

10 seconds after the initial reaction, the war-head detonated. Figure 16 shows a sample ofthe fragments and pieces of the motor recoveredafter the test.

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Data Sheet

Item Tested: SHRIKE AGM-45A Missile

Components: MARK 68 MOD 0 - Warhead Containing 50 pounds ofPBXN-1OI explosiveMARK 330 MOD 0 - FuzeMARK 44 MOD 0 - BoosterMARK 39 MOD 3 - Rocket Motor containing MARK 76MOD 2-propellant,MARK 265 MOD 0 - Motor IgniterSimulated - Guidance llit

Date of Test: 13 December 1972

Weather Conditions: Cloudy, 10 knot wind, temperature 520Ffacility: 30' x 30' retainer cage with encaged fuel pit

and test stand

Fuel: 200 gallons of JP,.5

Test Fire: Flame temperature at the missile exceeded 1000 Fat 23 seconds after start of the fire and averaged17550F during the test.

Flame Duration: Seven minutes 40 seconds

Results: At one minute 44 seconds after fire ignition,the rocket motor deflagrated. Thbe warhead

4exploded at 13 seconds after the motor reacted,throwing fragments and burning explosiveabout the cage. Figure 17 shows the pre-testconfiguration. Figures 18 and 19 show themotor and warhead remains. The;omocouplelocations are shown in Figure 20 and the time-temperature data are provided in Figure 21.

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SHRiKE MISSII FAST COOK-OFF

Test No. cm-8.

Data Sheet

Item Tested: SHRIKE AGM-.45A Missile VComponents: MARK 68 MOD 0 - Warhead containing 50 pounds

of PBXN-101 explosiveMARK 330 MOD 0 - FuizeMARK 44 MOD 0'- Booster

MARK 39 MOD 3 Rocket Motor containing MARK 76MOD 2 - PropellantMARK 265 MOD -0- Motor Igniter,Simulated - Guidance Unit

Date of Test: 14 December 1972

Weather Conditions: Cloudy, 3 knot wind, temperature 530F

Facility: 30' x 30' retainer cage with encaged fuel pitand test stand

Fuel: 150 gallons of JP-5

Test Fire: Flame temperature exceeded 1000°F at 16 secondsafter start of fire and averaged 1860OF duringthe test.

Flame Duration: Five minutes

Results: The warhead exploded at one minute 17 secondsafter the fire was started. The motor deflagrated

at one minute 29 seconds. Fragments from the war-head were thrown about the test site. Figure 22shows the warhead fragments that were recoveredfrom the test. The remains from the motor areshown in Figure 23. Thermocouple locations andthe time-temperature data are provided in

Figures 24 and 25.

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DISTRIBUTION

CommanderNaval Ordnance System CommandWashington, D. C. 20361Attn: ORD-00

ORD-o48ORD-9132ORD-5535

CoiAnder

Naval Ship Systems (-miandWashington, D. C. 20361Attn: XAVSHIPS-O!1G

SVS PS-2 52jAVSEC -2052X

CommanderNaval Ship Engineering CenterPrince George's Center BuildingHyattsville, Maryland 20782Attn: 6105

61

Chief of Naval OperationsWashington, D. C. 20350Attn: NOP-00

NOP-07NOP-07TNOP-01CNOP-09B93NOP- 098NoP-o982NOP-56NOP-823NOP- 722D2

Commander

Naval Air ForceU. S. Pacific FleetBox 1210, Naval Air StationSan Diego, California 92135

CommanderNaval Air 7orceU. S. Atlantic FleetNaval Air StationNorfolk, Virginia 23511

D-I

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DISTRIBUTION (CONTnWED)

DirectorNaval Weapons Engineering Support ActivityWashington,.Navy YardWashington, D. C. 20390

Chief-of Naval MaterialWashington, D. C. 20360Attn: NMAT-00

NMAT-09NMAT-O16NMAT-03NMAT-046

CommanderNaval Air Systems CommandWashington, D. C. 20361

Attn: AIR-03AIR-04

AIR-4104AIR-534AIR-05AIR-510AIR-537AIR-52043AAIR-632AIR-532DAIR-5323AIR-532AIR-5324AIR-5366

DirectorNaval Research LaboratoryWashington, D. C. 20390Attn: Technical Library

CommanderNaval Ordnance LaboratorySilver Spring, Maryland 20910Attn: Technical Library

D-2

DISTRIBUTION (CONTINUD)

CommanderNaval Weapon CenterChina Lake, California 93555kttn: 453

3022851445324561

Technical Library

Commanding OfficerNaval Ordnance StationIndian Head, Maryland 20640Attn: Technical Library

CommanderNaval Safety CenterNaval Air StationNorfolk, Virginia 23511 (2)

Commanding OfficerNaval Weapons StationYorktown, Virginia 23491

Commanding OfficerNaval Weapons StationsCharleston, South Carolina 29408

Commanding OfficerNaval Weapons StationConcord, California 94520

Commanding OfficerU. S. Naval Ammunition DepotCrane, Indiana 47522Attn: WPEC

CommanderNaval Missile CenterPoint Mugu, California 93041Attn: 5713 (2)

4718593-225710.10 (2)Technical Library 3

DISTRIBUTION (CONTIMluD)

Commanding OfficerNaval Weapons Evaluation FacilityKirtland. Air Force BaseAlbuquerque, New Mexico 87117

AdministratorDefense Documentation Center forScientific and Technical Information (DDC)Building No. 5, Cameron StationAlexandria, Virginia 22314 (2) ICommanding OfficerRobbins Air Force Base, Georgia 31093Attn: MNTBA

Commanding OfficerHill Air Force Base, Utah 84401Attn: NMNTA (2)

Air Proving Ground CenterEglin Air Force BaseEglin, Florida 32542

Commanding OfficerAberdeen Proving GroundAberdeen, Maryland 21005 (2)

Local:

T

TPETPB/JAR (2)ESEMIP-2MIP-3 5MIL •(2)

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JDISTIBJTION (cOaT ED

Commanding OfficerNaval Weapons Evaluation FacilityKirtland Air Force BaseAlbuquerque, New Mexico 8717il

AdministratorDefense Documentation Center forScientific and Technical Information (DDC)Building No. 5, Cameron StationAlexandria, Virginia 22314 (2)

Co6=ding OfficerRobbins Air Force Base, Georgia 31093Attn: IMNTBA

Commanding :Officer

Hill Air Force Base, Utah 8401Attn: M4!TA (2)

Air Proving Ground CenterEglin Air Force BaseEglin, Florida 32542

Commanding OfficerAberdeen Proving GroundAberdeen, Maryland1 21005 (2)

Local:

TTPTPEVPB/JAR (2)ESEMIP-2MIP-3 (5)

MIMMIL (2)

D-4)m

UNCLASSIFIEDJ

DOCUMENT CONTROL DATA. - & D -

(Scielly cl~asloln ol title, body o.61 ~~,Itret 10 i1douinif .01unllamR ffifixt In' eeloed whi'n th.' ovotall reportin De Cles-illegD)

IOF1G INA TING ACriviTy (Cotpoe oerf) a& M'ONT 91CIJRITY CI.ABIIICA [ION

UNCLASSIFIED4 Naval Weapons Laboratory its GROUP

T REPORT TITLtE

SURVIVABILITY OF AIR LAUNCHED GUIDED WEAPONS IN A FIRE ENVIRONMENT

4. C)~scRIPTIVIE NOTES (Type of reput and nlnCiive daleso)

S. AU THOft(S) (First o rnT~Ieniia, la,7t o

J. A. RobinsonG. REPORNT DATE 701, TOTAL NO. Of PAGES 7h. NO. orl RICrb

January 1973

b. PROJECT' KO.

C. 9h. OTNER R 01 ORT Nalol (Any other nhumbwre ta ay be .ede

* d.

10. DISTRIBUTION STATEMENT

Distribu tion limited to U.S. Gov't. agencies only; Test and Evaluation; January 1973.Other requests for this document must ba referred to the Commnander, Naval WeaponsLaboratory, Dahigren, Virginia 22448. I~SOSRNMLTNAVT

11. SUPPLEMENTARY NOTES IJ PNOIGML AYATVT

* ., 13. ABSTRACT

Tests were conducted to establish fast cook-off characteristics of t.'he followingguided weapons: (a) SIDEWINDER (AIM-9), (b) WALLEYE (MARK 1 MOD 0), (c) SPARROW III(AIM-7), and (d) SHRIKE (AGM-45A). The type of reaction that occurred, the time toreaction and time-temperature data were obtained for each guided weapon when engulfedin fire from burning JP-5 fuel. These data are applicable to the design of thermal

i protection systems and the development of safer fire fighting procedures.

681.,V 473 (PG )UNCLASSIIE