UNCLASSrTMD it rACSECURITY CLASSIFICATIUN Or THIS PACE (When, Data EtonieeQ (I nV ~ J I

REPORT DOCUMENTATION PAGEREDISUCONI. RPC~rMU~ER ~. nVY ACCESSION NO. 3. RECIPIENT'S CATALOG NUMBER

4. TITLE (and ubt fhle) ý

, COMPUTER PROGRAM FOR ANALYZING PROJ ECTI11111FLIGHT TRAJECTORY. a. PERFRINGftl ORGo. REPORT Mrp

7. AUTH9WA)_ 11. CONTRACT OR GRANT NUMISER(s)

'AI John MIFerriter:7 John J.1JReba

IS. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRA M 1T."PRJECT, TASK

/Director, Chemical Systems Laboratory AREA A N UERs

Attn: DRDAR-CLN-DAberdeen Proving Ground, Maryland 21010 Projec UI~62=2255

11. CONTROLLING OFFICE NAME AND ADDRESS I ODirector, Chemical Systems Laboratory fha =7

Attn: DRDAR-CLJ-RAberdeen Proving Ground, Maryland 2 1010 2

14. -MONITORING AGENCY NAME 6 ADORZSS(lI different frwom Controlling Office) IS. SECURITY CLASS. (of thirport.)

UNCLASSIFIED16a. DECLASSIFICATIONIDOWNGRAOING

SCHEDULE NAIs. DISTRIBUTION STATEMENT (of this Report)

Approved for public release; distribution unlimited.17. DISTRIBUTION STATEMENT (of th. abstract onfored in Blck..20 If Effatst broa Report)

1S. SUPPLEMENTARY NOTES

19. KEY WORDS (Cotinwae on, reverse side flneceoomar mWidenartify by Weak5 nmuber)

(U) Gyroscopic stabilityDynamic stabilityEquilibrium roll rateResonance roll rate

\$imple particle trajectory20. ABSTINAN!,motmfha misrveresif V n aomsinY And Idet r~ Or Slek as-600

(U) -The report describes a computer program that predicts the flight trajectory, spindecay, and gyroscopic and dynamic stability factors for spin- or fin-stabilized cannon-launchedprojectiles with liquid or solid payloads..

JAN 13 Emo FNVSSSOL~ UNCLASSEFIEDSECURATY CLKWIPICATION OF THrS PAGE (Man Dete Entered)'/J ¾ 1__ __

PREFACE

The work described in this report was accomplished as support effort for severalprojectile research and development programs being conducted at Chemical Systems Laboratory.The work was started in September 1976 and completed in September 1977. The computerprogram is general in nature and should be applicable to any study of a projectile's trajectory.

Work was authorized under Project 1L162622A554-1, Lethal Chemical WeaponsTechnology.

Reproduction of this document in whole or in part is prohibited except withpermission of the Director, Chemical Systems Laboratory, Attn: DRDAR-CLJ-R, AberdeenProving Ground, Maryland 21010; however, DDC and the National Technical InformationService are authorized to reproduce the document for US Government purposes.

3

. -A

SUMMARY

This report describes a computer program that predicts the flight trajectory, spindecay, and gyroscopic and dynamic stability factors for spin- or fin-stabilized cannon-launchedprojectiles with solid or liquid payloads. The program provides a fast, accurate, and efficientmethod of evaluating projectile trajectories. A short introduction provides the mechanics oftrajectory theory. However, no effort is made to give a complete mathematical analysis of thetheory. The theory may be found in the literature cited (given as footnotes in the report).

5

III I i L

~Im

CONTENTS

1. INTRODUCTION .. ...... ..... .. .... .. . ... . 9

II. THEORY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

A. Simple Particle Trajectory .............. ..................... 9

B. Spin Decay for Liquid-Filled Projectile .......... ................ 10

C. Roll Rate For Fin-Stabilized Munitions ....... ................. I I

Ill. THE PROGRAM ............. ........................... ... 12

IV. CONCLUSIONS ............. ........................... ... 24

DISTRIBUTION LIST .............. ........................ .. 25

#

A COMPUTER PROGRAM FOR ANALYZING PROJECTILE FLIGHT TRAJECTORY

1. INTRODUCTION.

The purpose of this report is to present a computer program that assists designpersonnel in analyzing projectile flight. After aerodynamic coefficients for a proposed munitionshape are derived from wind tunnel tests, a prediction of projectile stability, range, and accuracymust be made. In addition, the effect on projectile flight of a liquid payload or shift incenter-of-gravity location may be required. This program can be used as a design tool inanalyzing projectile flight.

II. THEORY.

A. Simple Particle Trajectory.

As in any trajectory, simple particle trajectory is the curve traced by the center ofgravity of a projectile with respect to a horizontal surface when fired at a particularcharge/elevation combination. However, simple particle trajectory uses velocity and aerodynamicdrag to calculate the horizontal and vertical velocity components.

The fundamental equations used in the computer program are:

AV ( -drag s gsin0) At (1)A=projectile mass

A = - C At (2)

AX (V cos 0) At (3)

AZ = (Vsin 0) At (4)

where

V = projectile velocity

0 = acute angle between a horizontal plane and the tangentto the trajectory at the projectile center of mass

g = gravitational constant

t = time

X = horizontal distance

Z = height above horizontal plane

9

00-" N A #

B. Spin Decay for liquid-Filled Projectiles.

When a projectile is fired from a gun, the liquid, initially, is not rotating with theprojectile. During the down-range flight, the liquid acquires angular momentum from theprojectile and the liquid spin rate approaches that of the projectile. This process of the liquidacquiring angular momentum is referred to as the spinup process. This process, whereby theliquid acquires angular momentum from an initial condition of zero rotation, was explained byWedemeyer.* Wedemeyer showed that for the case of a completely filled cylinder, viscous regions,known as Ekman layers, near the end walls act as centrifugal fans sucking non-rotating liquidfrom the inviscid core and throwing the liquid outwards.

To incorporate liquid effects (spinup process) on rigid body spin decay, thedifference between rigid body rotation and zero liquid rotation at the muzzle is calculated. Thetheoretical spin decay assumes a percentage of liquid rotating w;th the projectile at muzzle exit.The particular decay curve (see the figure) for the percentage of liquid rotating with theprojectile at muzzle exit is:

y = at (5)

where

a = percentage of liquid rotating -,';-th the projectile at muzzle exit.

t = time after launch

y = spin decay correction factor.

The decay curve asymptotically approaches the t-axis. The value of y (equation 5) i2 multipliedby the difference between rigid body payload rotation and zero payload rotation at muzzle exitto determine projectile spin decay due to liquid effects.

0.0

y-at0.8 t - TIME (SEC)

0.8 - PERCENT LIQUID SPINUP

IN THE PROJECTILE AT0.7 MUZZLE EXIT

y - SPIN DECAY CORRECTION0I 0.8 FACTOR

-- 0.5

0.4

0.3

0.2-

0.1*

0 .0 1 2 3 4 6 7 8 9, 10 11 12 13 14 IS Is

t (SEC)

Figure. Spin Decay Curves for Liquid-FilledSpin-Stabilized Projectiles

* Wedemeyer, F. H. BRL Report 1252. The Unsteady Flow Within a Spinning Cylinder. Aberdeen ProvingGround, MD 21005. 1963. 10

C. Roll Rate For Fin-Stabilized Munitions.*

Unlike spin-stabilized projectiles whose spin is generated by the gun tube rifling,fin-stabilized munitions generate spin by the air flowing over the canted fin blades. The spinequilibrium roll rate, Pe, for fin munitions is:

-CIS VSfcPe = d (6)Clp d

where

CIS = roll moment coefficient due to fin cant (at zero spin)

Clp = roll damping-moment coefficient

Sfc = fin cant angle, radians

V = velocity, ft/sec

d = maximum projectile body diameter, ft

Theoretically, resonance instabilities can occur in spin-stabilized projectiles due tothe coincidence of spin and yaw frequencies, however, this phenomenon is more likely to occur

with fim-stabilized projectiles. The spin is most likely to coincide with nutational frequency ,given by:

p p2 )0 5 P(I + 0-/S)0"5 (7)

where

Sg = gyroscopic stability factor

M= pSd3 CMa21y

CMa = static moment coefficient, per radian

d = maximum body diameter, ft

p = air density, slug/ft3

S = projectile cross-sectional area, ft2

Engineering Design Handbook AMCP 706-242. Design for Control of Projectile Flight Characteristics.Headquarters, US Army Materiel Conmnand, Waabington, D.C. 1966.

III

P Ix pdP = and 1 -

u = static moment factor (per radian)

p = spin in radian per caliber of travel

Ix = axial moment of inertia, slugs - ft 2

ly = transverse moment of inertia, slugs - ft2

This reduces to a resonance roll rate, Pr, represented as:

It has been suggested that the roll rate at exit for a fIn munition fired from a rifledtube should be three times resonance roll rate. A fm munition fired from a smooth-bore tubeexits with zero spin. Theory states that munition roll rate will pass through resonance roll rateprior to equilibrium roll rate. The greater the equilibrium roll rate/resonance roll rate ratio theshorter -ime the projectile is in the vicinity of resonance roll rate, thus temporary growth in yawdue to resonance will be insignificant.

III. THE PROGRAM.

The program given in Fortran symbols on pages 13 through 20 calculates the flighttrajectories of spin- and fin-stabilized projectiles with liquid or solid payloads. The inputparameters (i.e., launch conditions, aerodynamic coefficients, projectile physical characteristics)required are listed at the beginning of the program. The program consists of three parts (1) themain program calculates trajectory and stability, (2) a subroutine calculates the liquid effects onprojectile spin, and (3) a subroutine calcula*es equilibrium and resonance roll rates for afin-stabilized munition. Sample outputs for solid and liquid spin-stabilized projectiles are shownin tables 1 and 2. Table 3 shows an output for fin-stabilized projectiles.

12

1* C LINEAR INTERPOLATION INPU~t

20 C 04N ,RN DEtSISH 1ANDBOOK &1MCoO76*Z4

3s C CALC FLESHY TRAJECTORY OF PROJECTILE

s4 C DATA CARD I1 IE RGImE(CTI

5* C li - NUNBER OFTIqSPOA' XCEJ

6' C K= NUMSER OF COEFFICIENT CARDS N0.2F

7' C INC= 'l"E INCREt'qEI4 FOR PRINT OUT VNCSOZSCIT9RG*1

q. C i: = 0 - ALL AERO COEFFICIENTS*I-vFOIVOR~'0- SDLID PAVLOADO I - LIQUID PAYLOAfl

10' ~ c B:0 STABILITY FACTOR CAI:Cs I TA ?*NO T~LT AT 9 C

Ii' CD:,IN STABNUN- I _FINSTpU1 *C JDT -AP .2 TO N

130 C COT :DRAG COEFFICIETFRV

l~s C VT : rLOCIT'V

IS# C 04* CofPFICIENT

Ilo C SLAZ LIF~T~ COEFFICIENT

IQ* C. CAM= D1'P!PG ?401AENT CA.EFFICIENT

C LA: RLLF C0EN CEFFICETIF Ft/C

21* c 3ATA CAPD

23* C Vt') = 1141 IAL VELOMFNT oFT *

:14 C Ztv I~TT TISJ4T FT

32' C A~RT*FA~ C F SH HELL. FT

* C :-,NG L wEIT~IA RANGE- S1 LT L.

34 C V774NA Z Q 4ER%- MC!OENT -F S,'4-LL, L3-ASf)FT

P37/XA!L2~COPY

13

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16

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ý13* AZSAVEtAZý t.0 * C INCREMENTING TRAJECTORY

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297* 3'?1 IF(X0PT.EGQ-.l) GO TO 370

17

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271' YA2.AENSDAC**3

272* YAW3:IYAWl/YAW2i.*180./3.1f&15,32730 YAW4:ISA*SPRC.DIA)I/Ce4.Vl274' YAW5:I YAW3*YAW41 Il80./3.j4159~275* SP RClI:=CM PLX (Y &W39 YA WS?76* IFIOPT.GT*01 6O TO 3S277. C UZ STATIC MOMENT FACTOR, L~t-FT/QADIAN278. U:.3l269.AOEN*DIA..3..Vss2.*CH279' IF(JB.GT.0) GO TO 35'800 IFIJA.ST.01 GO TO 3f;2810 C SnLIio FTL1.Ef PROJECTILE

'1820 C GYROSCflPIC STABILITY FACTOR283' SG:(AXMS*.2.*SPRC., 2. )/(4.*TRAN.UI?F40 C flYNAMIV STABILITY ESTIMATE2c5o SD1:2..I CL*RGA.Sh I

2b6* S02=rL-CD+1-0Q3T.DAI287' GO To 37

?E80 C LIQUID FILLED PROJECTILE361 SESIfXS*.SRC*./4*QNU

291* SG?:AX0MQ/AXMS291' SG:SrIA.C2..2.292. RGA0=(WR*OIA**..)/AKMq293' RGTQ:IWw*DIA*..l./TRAN294' SO1:2.sfCL+RGAR.l;A)2950 SD2=CL-CD-(RGTR*CA)296* 37 S0O:SDl/SO2'37* SG1:1./SG298' SD=SnOO.2.-sflo299' 35 OPT:1300s GO TO 16301* C DETFR'4INE POINT OF TI4PACT3C02 50 RATIO=-ZSAVE/OEL7333' XFINAL:QATIO*OELX*XSAVF304* XMFINL=XFINAL/3 .2813050 ZFINAL:P.ATIO*OELZ.ZSAVF3'n6e Z.HFTNL='FINAL/3.281307' TFTNAL=:?ATIO' IT-TSAvE)+.YSAVr''1080 VXFNL=QATIO.OELVX*VXSAVE309s VZFNL=RATIO*OELVZ*VSAVE310' VFINAL:SQRT(VXFNL*VXFNL.VZFNLOV?FNL)311. T4EF14L=ATAN21VZFNLiPVXFNL)312s AXFNL =RATIO*( AX -AX SAVE) +AX SAVE313s AZFNL:RATIO.(AZ-AZSAVEI.AZ?'AVE3144' AFINAL=SQRT(AYFNL.AXFN4LAZFIJL.AZFNLI315o TI4ACFL=ATANZE AZFNL' AXFNLl316' OXFNL=RA TIOef DX-0X SAVE) +DX SAVE317' 0!FNL=RATIO.IOZ-DZSAVEIOZSAVE318' OFTNAL =SORT (DXFNL*OKFNL*OZFNL*DZFNL I31q. THACFL=THACFL*18U./3.14159

18

320 o TH F.L=T HE FWN;I1BO.1 21 . WRITEt6931 TFXNAL.THEFNM.XMFINL.ZNFTW#L.VFINAL.AFINALP3220 ITHACFL90FIN*L3236 3 FORNATfIXt15HPOINT OF IMPACT* /w3X98F9).2152*4 C COMPARF S63 TO SO0

,:?,; 0IF(JD.EQ.O)GO TO 379

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IFIJA.F3.11 6o TO 106

133. 121 FORMATtloIX.2314SOLID FILLEOD ROJECTILEIT3& 60 TO 122

333o 126 hIRITE(691131'3bo 113 F09MATI/vlX924HLI3UIO FILLrii PROJECTTLF)

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33!. dRITE(691021 SOO

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1. C T41c, SURROUTINE CALCULATES TH4E -ROJECTILý -,-IN

?o C DECAY ASSUmIN6 VARIOUS LIO SPI'IJP IN THE TURE.99

3. C w. IS THE PERCENT DECAY AT TlMEvTI9 FOR9 A GTVEN

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* 150 20 IFIW.GT.O.DOII 1GO TO TO16o THAX=TI17. 70 RETURN19. ENDO

19

?~ESIAVKAt~COPY

I. C SUBR-OUTINE CALCULATES SPIN FOR A FIN MUNITION2* C PC IS THE EQUILIBRIUM ROLL IATE.3* C PR IS THE RESONANCE ROLL RATE

40 SUBROUTINE FIN5. COMMON/BLK IICSL*SFC*CLIP*OPT*Po To

i; *COMMOt4/RLM2/0ENvV9S*0IA9DELTIs COOqWONIULK3/CY4.SPINPRATIOAXMS.TRAN

6* RE AL MU90 DOUBLE PRECISION SPIvE

11 : 2. TIAZ8..*T11* 01=-CSL/CLOP

D2 = V * VSF C I/ 01A13* SPIN=D3.02

140IFIT*MS.5. 60 TO 501;* IFIP.EO.SPINI 60 TO SO

IFIDLT*SPIN3 60 TO %a0

lq* 60 TO 4e513. '.0 SPI=0,(l.-(l./EI1.(SPV4-Pl

2 4.5 SPIN:SPI.3 SO MU=.S*DEN*Vo.2.*S*DIA.C?4

2?. IFIOPT.GT.G.I GO TO 3023* IFICW.LEe0OeO GO TO 10

Z4* TE (6. 20125. e'0 FORMATt/91X.'.H SUBROUTINE IEGUIRES NES3ATIVE SIATIC MOM COEF)

* STOP7.10 PR:fSORT(-MU/fTRAN-AXMSI)/I2.03.1'.16)

23 PR PAT TO=SPIN/Pv29* 30 RETURN

31) END

20

9C n 9O

4)r

.5 0 in AD inF- f -

a 0 p-0a n P

In in

442 Maon pn .

~~~ 4r m~~c

30 %A 1 1 I

a-0 to 4r00nP

LI %~A aq @ 0

an on Wlef@'~

5-r r-I~

~~~ N0u~

w --- l4)~~ L* q

- 0' 21

ID C

2 0 0-.n~

4 0,

0-

be jh 0. * *

C000f, .4

f) W# , DF N N.'

4)~~ N Coc 0 M~~e~~

j .j N 1P.f10$. 0 4"I #~.~E l

10 a

C' in S0N 0 V

0 is. hi Vl P..0W , N c;

04 1- 'No w ~ e, 4.0 00, 1

01- m I ; 0 9 7

U 4 N f . * N,4 *a

'be -be hi -

X .J a p~~tp 22

KOCOCC•OQO

"G 9999999•

09Wf we F B• or%a. I * - so $

t• ~ ~ C 0lll, 0 t CitI

w w,. I .l" 1. *O 4 ,,, * , 9,S

io l •e • i i

0, L-t 0 % IL& WIW I- W ,

~Cs!-9 04- M m.* 4 a a

4) 0

2. ' a. A..

GAD 'a y ia' in 0 toe

ON0

o~~~0 aj 0%C ea-pIb WN4 Nri~n.Qn N

g P" • I n U •

40, -, F W

j 0

~i.A* IWI NtI"4I WI

- a-

-g23

IV. CONCLUSIONS.

The program analyzes projectile flight as shown by the sample outputs. Thesepredictions for spin- and fin-stabilized projectiles will assist design personnel in evaluating aprojectile flight. However, it should be noted that since the program does not take into accountmeteorological conditions, other than air density, and that it adapts simple particle trajectorytheory, the output provides a good trajectory estimate for a projectile fired under normalconditions.

j i24

DISTRIBUTION LIST 8

Names Copies Names Copies

CHEMICAL SYSTEMS LABORATORY Project Manage Smoke/ObscuranceAttn: DRCPM-SMK-M I

SAFETY OFFICE Aberdeen Proving Ground, MD 21005Attn: DRDAR-CLF I

PLANS & PROGRAMS OFFICE Human Engineering Laboratory HFE DetachmentAttn: DRDAR-CLR-L 4 Attn: DRXHE-EA 1

Bulding E3220AUTHORS COPIES: Munitions D n to APG-Edgewood Area

DEVELOPMENTAL SUPPORT DIVISION CommanderAtm: DRDAR-CLJ.R 3 US Army Foreign Science & Tedmcology CentsAttn: DRDAR-CLJ-L 3 Attn: DRXST-CX2 1

220 Seventh St.. NEMUNITIONS DIVISION Charlottesvile, VA 22901

Attm: DRDAR-CLN 5Commander

RESEARCH DIVISION US Army Missile Research and Development CommandAttn: D: ,AR.CLB 1 Redstone Scientific Information CenterAtm: DiWAR-CLB-P 1 Attn: DRDMI-TBD 2Attn: DRDAR-CLB-R I Redstone Arsenal, AL 35809

SYSTEMS ASSESSMENTS OFFICE DirectorAttn: DRDAR-CLY-R 1 DARCOM Field Safety Activity

Attn: DRXOS-C IDEPARTMENT OF DEFENSE Charletown, IN 47111

Administrator CommanderDefense Documentation Center US Army Materiel Development and Readiness Command

Atn: Accesions Division (DDC-TC) 12 Installations and Services ActivityCameron Station Atn: DRCIS-R-I-U 1Alexandria, VA 22314 Rock Island, IL 61299

Director US ARMY ARMAMENT RESEARCH ANDDefense Intelligence Agency DEVELOPMENT COMMAND

Attn: DB-4GI 1Washington, DC 20301 Commander

US Army Armament Research and Development CommandDEPARTMENT OF THE ARMY Atn: DRDAR-LCA 1

Atn: DRDAR-LCE 2HQDA (DAMOSSC) Attn: DRDAR-LCE-M IWASH DC 20310 Attn: DRDAR-LCF I

Attn: DRDAR-LCU 1Deputy Chief of Staff for Research, Attn: DRDAR-SCA-C 1

Development & Acquisition Atn: DRDAR-SCA-C 1Atn: DAMA-CSM-CM I Attn: DRDAR-SCi 1Attn: DAMA-ARZ-D 1 Atn: DRDAR-SCM 1

Washington. DC 20310 Attn: DRDAR-SCP-A IAttn: DRDAR-SCW 1

US ARMY MATERIEL DEVELOPMENT AND Attn: DRDAR-SER 1READINESS COMMAND Attn: DRDAR-TSS 2

Atn: DRCPM-SA 1Commander Dover, NJ 07801US Army Materiel Development and Readiness Command

Atn: DRCLDC I DirectorAttn: DRCSF-P 1 alistic Research laboratory

5001 Eisenhower Ave Atn: DRDAR-TS- 2Alexandria, VA 22333 Buiding 328

Aberdeen Proving Ground, MD 2100O

25

DISTRIBUTION LIST 8 (Contd)

Names Copies Names Copies

CDR, APG US ARMY TEST & EVALUATION COMMANDUSA ARRADCOM

Atm: DRDAR-GCL 1 CommanderAberdeen Proving Ground, MD 21010 US Army Test & Evaluation Command

Attn: DRSTE-FACommander Aberdeen Proving Ground, MD 21005US Army Technical DetachmentUS Naval EOD Facility 1 CommanderIndian Head. MD 20640 US Army Cold Regions Test Center

Attn: STECR-TDUS ARMY ARMAMENT MATERIEL READINESS COMMAND APO Seattle, WA 98733

Commander DEPARTMENT OF THE NAVYUS Army Armament Materiel Readine Command

Attn: DRSAR-ASN I CommanderAtm: DRSAR-IMB.C I Naval Explosive Ordnance Disposal FacilityAttn: DRSAR-LC 1 Attn: Army Chemical Officer, Code 604Attn: DRSAR-PDM 1 Indian Head, MD 20640Attn: DRSAR-SA IAttn: DRSAR-SF 1 Commander

Rock Island, IL 61299 Naval Surface Weapons CenterWhite Oak LaboratoryCommander Attn: Tech Lib & Info Svcs Br

US Army Dugway Proving Ground Silver Spring, MD 20910Attn: Technical Library, Docu Sect I

Dugway, UT 84022 CommanderNuclear Weapons Training Group, AtlanticCommander Naval Air Station

Pine Bluff Arsenal Attn: Code 21Attn: SARPB-ETA I Norfolk, VA 23511Pine Bluff, AR 71611

US MARINE CORPSUS ARMY TRAINING & DOCTRINE COMMAND

CommandantCommandant HQ, US Marine CorpsUS Army Infantry School Attn: Code LMW/20

Attn: NBC Division I Washington, DC 20380Fort Benning, GA 31905

Director, Development CenterCommandant Marine Corps Development & Education CommandUS Army Misile & Munitions Center & School Attn: Fire Power DivisionAttn: ATSK-CD-MD I

Redstone Arsenal, AL 35809 DEPARTMENT OF THE AIR FORCE

Commander HQ Forein Technology Division (AFSC)US Army Logistics Center Attn: PDRR

Attn: ATCL-MM I Wright-Patterson AFB, OH 45433Fort Lee, VA 23801

OUTSIDE AGENCIESCommandant

US Army Military Police Schoolfrratnlng Center Battelle, Cohumbus LaboratoriesAttn: ATZN-CDM 1 Attn: TACTECAttn: ATZN-TDP.C 1 505 King AvenueFort Mclellan, AL 36205 Columbus, OR 43201

Commander Director of ToxicologyUS Army Infantry Center National Research Council

Attn: ATSHCD-MS.C 1 2101 Constitution Ave, NWFort Benning, GA 31905 Washington, DC 20418

"j 26

DISTRIBUTION UST 8 (Contd)

Names Copies Names Copies

ADDITIONAL ADDIESSEES

Commander CommanderUS Army Envitromental Hygiene Agency US Army Science & Technology Center-Far East Office I

Atn: Lfrarian, Bldg 2100 1 APO San Francisco 96328Aberdeen Proving Ground. MD 21010

7 27