k D-RI52 654 MULTIZONE NODULAR ARTILLERY PROPELLING CHARGE STUDIES 1/2I (U) ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUNDI MD C R RUTH ET AL. FEB 85 BRL-TR-2636 SAI-RD-F316 597

UNCLSSIFIED F/G 19/6 NL

1 0 jjj8 2-B5

IIIII 11o4 3 6

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AD-A152 654 ID

TECHNICAL REPORT BRL-TR-2636* 0L* 0

MULTIZONE MODULAR ARTILLERY PROPELLINGCHARGE STUDIES *

Carl R. Ruth .

Thomas C. Minor DTICF a 1ELECTE

cl. February 1985 _ APR 16 Q85

APPROVED FOR PUBUC RELEASE; DISTRIBUTION UNLIMITED.

US ARMY BALLISTIC RESEARCH LABORATORYABERDEEN PROVING GROUND, MARYLAND

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Destroy this report when it is no longer needed.Do not return it to the originator.

Additional copies of this report may be obtainedfrom the National Technical Information Service,U. S. Department of Commerce, Springfield, Virginia22161.

*I

The findings in this report are not to be construed as an officialDepartment of the Army position, unless so designated by otherauthorized documents.

The use of trade names or manufacturers' names in this reportdoes not .'onstitute indorsement of any commercial product.

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READ INSTRUCTIONSREPORT DOCUMENTATION PAGE BEFORE COMPLETING FORMI. REPORT NUMBER 2. GOVT ACCESSION No. 3. RECIPIENT'S CATALOG NUMBER

TECHNICAL REPORT BRL-TR-2636 - 3.. 94. TITLE (and Subtitle) 5. TYPE OF REPORT & PERIOD COVERED

MITLTIZONE MODULAR ARTILLERY PROPELLING Technical ReportCHARGE STUDIES Qyt R1 - Till Rj

6. PERFORMING ORG. REPORT NUMBER

7. AUTHOR(a) 8. CONTRACT OR GRANT NUMBER(e).

Carl R. Ruth and Thomas C. Minor

9. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ELEMENT, PROJECT. TASKAREA & WORK UNIT NUMBERS

US Army Ballistic Research Laboratory 1121A8ATTN: AMXRR-ThD 1628A0Aberdeen Proving G~round. MD 21005-506611,~ CCNTROLLImG.OF.FLCE NAME AND ADDRESS 12. REPORT DATE

US Army Ballistic Research Laboratory February 1985ATTN: AMXBR-OD-ST 13. NUMBER OF PAGESAberdeen Proving Ground, MD 21005-5066 11814. MONITORING AGENCY NAME & ADDRESS(il different from, Controlling Office) 1S. SECURITY CLASS. (of this report)

ISe. DECLASIFICTI ON/ DOWN GRADINGSCHEDULE

16. DISTRIBUTION STATEMENT (of this Report)

Approved for public release; distribution unlimited

17. DISTRIBUTION STATEMENT (of the abstract entered In Block 20, It different from. Report)

IS. SUPPLEMENTARY NOTES

Presented at 1983 JANNAF Propulsion Meeting

19. KEY WORDS (Continue on reverse aide it necessary end Identify by block number)

Interior Ballistics Charge Geometry Modular ChargesPressure Waves Multizone Propelling ChargesIowters Stick Propellant,rain Geometry Combustible Cases

20. A36TRACT (Caintbue eeree eit~ if necesay and Identity by block number)

many of the requirements for the design of a multizone, Combustible-cased, modular charge for howitzer applications that will minimize pressurewayes at all zone levels without compromising performance are essentially un-cnown at the present time. An unsuccessful development program for a 155-mm,nultizone bagged charge (XN21I) highlighted the need for careful selection3f the Interrelated components that comprise a multizone charge. In thatievelopment program, severe pressure waves In high-temperature firings at

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intermediate zone levels were noted. As a forerunner of the studies reporte

here, investigations of a similar charge at the Ballistic Research Laboratorydemonstrated that severe pressure waves in high-temperature firings could beincreased or somewhat mitigated by a change in the charge/chamberconfixuration and/or ignition stimulus.

Multizone, combustible-cased modular artillery propelling charges werefabricated with both granular and stick propellants and were used in thisstudy to investigate the influence of charge interzone permeability,propellant bed permeability, distribution of ullage, and igniter brisance onthe two-phase flow, interior ballistic process, in particular, on theformation of pressure waves. Test charges used to study these phenomena werefabricated to resemble the modular charge configurations proposed for futureartillery applications. Gun tests with these charges were conducted usingM549 Projectiles fired from an M199 Cannon instrumented to measure chamber and

differential pressures. Representative data for each series fired in thestandard gun are presented in detail. For the situations investigated here,in which a wide range of loading configurations, boundary permeabilities, andignition stimuli were studied, the results demonstrated the superiority of

stick propellant over granular propellant for this modular-charge application.

To better understand the events occurring early in the ignition cycle

with these charges, and their relationship to the formation of pressure waves,multizone combustible-cased charges were fired in a 155-mm howitzer simulatorwhich used plastic tubes in place of the M199 chamber. The simulatorpermitted direct visualization of the events transpiring within the chamber.Data obtained included pressures measured by gages at the spindle andprojectile base; total force on the projectile base; flamefront movement,recorded by high-speed photography; and solid-phase motion, monitored via

flash radiography. One granular- and one stick-propellant chargeconfiguration, which were dramatically different in the levels of pressurewaves produced in the gun firings, were selected for testing in thesimulator.

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TABLE OF CONTENTS

Page

LIST OF ILLUSTRATIONS ....................................*.... 5

LIST OF TABLES .................................... 7

I. INTRODUCTION ....... ........ ........ .... * ..... 9

II. TEST SETUP ............................. ... ... .. .. ..... 12A. Weapon........................................ 12B. Instrumentation. . ............................ 13C. Firing Components ...................... ........- 13

III. RESULTS .... ..................................... 1

A. Preliminary Firings for Selectioq ofGranular Propellant ...................... ...... 15

B. Modular Case/Granular Propellant ... o........ %......... 181. Baseline Series/Granular Propellant.... ......... ...182. Ignition Variations/Granular Propellant ............. 183. Ullage Variations/Granular Propellant ............... 24

C. Modular Case/Stick Propellant ........................... 261. Baseline Series/Stick Propellant............... 262. Ullage Variations/Stick Propellant .................. 273. Ignition Variations/Stick Propellant ........... 29

D. 155-mm Howeimulatr Teust or..................32..32

IV. CONCLUSIONS.......................................... 35

ACKNOWLEGEMETS. ... ....... . .. .. ... ... .. . ... ... .36

REFERENCES ........................................ ... ..37

APPENDIX A- Propellant Description Sheets ............. 3

APPENDIX B - Tabulation of Firing Data for ModularCase/Granular Propellant and Modular Case/StickPropellant for all Series Configurations ................ 45

APPENDIX C - Plots of Spindle Pressure (Solid Line),Forward Chamber Pressure (Dashed Line),and Pressure Difference Versus Ti.. e..............53

DISTRIBUTION LIST...................................... ... 109

3

LIST OF ILLUSTRATIONS

Figure Page

1. Granular-Propellant, Multiple-Increment, BaggedCharge ................................ ............ . .. 9

2. Stick-Propellant, Multiple-Increment, ModularChrg......... ..oooo...oo.. ... oooo...... .1 1~e

3. Comparison of Modular and Bagged Charges....................11

4. M198 Howitzer System...

5. Locations of Pressure Transducers in M199Chamber-....... ..................................13 -

6. Granular Propellant, MIMP, and Slotted-StickPropellant, M31EI ............... ....................... 14

7. NC Container, Type 2 ...................................... 15

8.* NC Container, Type 1.........o............... esooool

9. Charge/Chamber Configuration for Modular Case/Granular Propellant with Ignition Variations ...... . .19

10. Spindle and Forward Chamber Pressure andPressure Difference versus Time for LargePressure Waves ..................................21

11. Spindle and Forward Chamber Pressure andPressure Difference versus Time for Very LargePressure Waves .............................................. 22

12. Spindle and Forward Chamber Pressure andPressure Difference versus Time for Medium

Pressure Waves........................................ 23

13. Spindle and Forward Chamber Pressure andPressure Difference versus Time for SmallPressure Waves .............................. .... 23

14. Charge/Chamber Configuration for ModularCase/Granular Propellant with Ullage Variations.............. 25

15. Charge/Chamber Configuration for Modular

Case/Stick Propellant with Ullage Variations ................. 28

5

7............,

7-.T 7 -. "

LIST OF ILLUSTRATIONS (CON'T)

16. Charge/Chamber Configuration for ModularCase/Stick Propellant with Ignition Variations ............ 30

17. 155-mm Howitzer Simulator, Plastic Chamber ................... 33

18. System for Experiment Control, Data Acquisition,and Data Reduction, 155-mm Howitzer Simulator......... 34

6

o1

. . ~ . .

LIST OF TABLES

Table Page

1. Granular Multi-Perforated Propellant Available

for Tests.............................................. 16

2. Preliminary Firings with Granular Propellants ................ 17

3. Firing Results for Ignition Variations/GranularPropellant ................................................... 20

4. Firing Results for Ullage Variations/GranularPropellant ................................. .......... 26

5. Firing Results for Ullage Variations/StickPropellant ................................................... 29

6. Firing Results for Ignition Variations/StickPropellant ...................................................31

Accessiconl'or -

IDTIC NPTSELECT Eo

B I yCodes6T b.d/or

7

I. INTRODUCTION

A charge configuration that is frequently employed in Army howitzersis the multizone, artillery propelling charge. This type of charge,schematically illustrated in Figure 1, consists of several discretepackages of propellant bound together in some fashion, as with tiestraps. The principal rationale for this charge design is that aparticular velocity can be achieved dependent on the number of packagesloaded into the weapon chamber, and this selectable velocity, coupled withthe permitted variation of weapon launch angle, allows a wide rangecoverage by indirect fire weapons.

PRIMER BASE PAD CHAMBER PROJECTILE

Figure 1. Granular-Propellant, Multiple-Increment, Bagged Charge

The requirements on the design of a multizone charge are demanding.The charge must exhibit reliable performance at ih low-zone end withoutcompromising performance at any other zone level. A case in point is ,the no -t4erminated dev.lopment program for the 155-mm, XM211 , PropellingCharge. ' The XM211 employed a small-web, single-perforation propellantin the base increment and a large-web, seven-perforation propellant in the

upper-zone increments. Coupling a very rapidly burning localized-ignition

1. W. May, "The Role of Ignition and Combustion: A Survey of

Developmental Efforts," 13th JANNAF Combustion Meeting,CPIA Publication 281, Vol. I, pp. 315-340, September 1976.

2 1. W. May and A. W. Horst, "Charge Design Considerations and

Their Effect on Pressure Waves in Guns," ARBRL-TR-02277,Ballistic Research Laboratory, USA ARRADmOM, Aberdeen ProvingGround, MD, December 1980 (AD A095342).

T. C. Minor and J. DeLorenzo, "Charge Design Approaches to theReduction of Low Zone Stickers," 1976 JANNAF PropulsionMeeting, CPIA Publication 280, Vol. 11T, pp. 403-434,

December 1976.

R. J. DeKleine, "155-mm XM211 Propelling charge Zones 3-6Design Review Minutes," Office of Project Manager, CannonArtillery Weapons Systems, Dover, NJ, April 1980.

9

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

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source to forward packages of less rapidly burning propellant in the XM211led to the formation of axial pressure waves, particularly at the Zone-5level with charges conditioned to 630 C. From this program, we once againlearned that it is necessary to consider all the interrelated componentsthat make up the charge in order to obtain satisfactory performance at allzone levels.

The phenomenology of a multiple-increment, bagie charge similar tothat of Figure I was considered in detail previously. ' It was shown thatin addition to well-documented problems usually associated with pressurewaves in high-loading-density M203 charges, the deleterious effect in low-loading-density charges of the impact of large quantities of propellant onthe projectile base on the projectile's safety and performance is also ofconcern. Even though pressure waves themselves in this-low-loading-densitycharge were not a hazard to tube or breech integrity, they have adverselyaffected more delicate weapon mechanisms.

To eliminate many, if not all, the aforementioned problems, the chargedesign community is seriously considering modular, energetic packagingconfigurations for both granular and stick propellants with specialemphasis being placed on the stick configuration. The use of stickpropellant in both high- anl medium-performance artillery charges isfinding increased application. The Army is currently introducing stickpropellant into the product-improved 155-mm, M203 (Zone 8S) charge. Asfuture advanced artillery weapons systems come along, the use of stickpropellant is virtually assured.

The main advantages of charges made with stick propellant are:reduced pressure-wave generation leading to improved safety; increasedloading density, permitting the use of lower flame temperature propellantsthat may reduce wear, flash, and blast; simplicity'of the ignition systemwith reduced ignition delay; and simplified loading, assembling andpackaging procedures. In Figure 2, a multizone, modular charge consistingof three zones is shown.

As illustrated in Figure 3, one of the main advantages of modular-charge configurations over bag-charge configurations is a rigid packageconsisting of interlocking components, thus facilitating automatic loadingin new weapons systems planned for the 1990s to augment the M198 Howitzer

T. C. Minor and A. W. Horst, "Experimental Studies of IgnitionPhenomena in One-Dimensional Propelling Charges," ARBRL-TR-02315,Ballistic Research Laboratory, USA ARRADWOM, Aberdeen ProvingGround, MD, April 1981 (AD A100298).

C. R. Ruth and T. C. Minor, "Multizone Artillery Propelling Charge

Studies," ARBRL-TR-02486, Ballistic Research Laboratory, USA ARRADOM,-Aberdeen Proving Ground, MD, May 1983 (AD A128285).

T. C. Minor, "Mitigation of Ignition-Induced, Two-Phase FlowDynamics in Guns Through the Use of S~ick Propellant," ARBRL-TR-02508, pBallistic Research Laboratory, USA ARRADCOM, Aberdeen Proving Ground, MD,August 1983 (AD A133685).

10

shown in Figure 4. Furthermore, since the modular-charge system willconsist of a small number of discrete module types, the propelling chargecorresponding to a desired performance level can be built up from theincrements at firing time, rather than discarding bags of propellant as iscurrently done with multizone artillery charges, resulting in a propellantand cost savings. New processing techniques might allow for theincorporation of additives such as wear-reducing, decoppering, flash-reducing, etc., directly into the case, and the increased strength ofloaded, rigidized combustible cartridge cases, as compared to bag charges, -

will minimize handling and transportation problems.

-, . V. t iI

Figure 2. Stick-Propellant, Multiple-Increment, Modular Charge

Figure 3. Comparison of Modular Figure 4. M198 Howitzerand Bagged Charges System

Let us now examine, with reference to Figure 2, some of the potentialevents in the early portion of the interior ballistic cvcle with acombustible-cased, modular propelling charge. The output of a primerimpinges on a basepad, and the burning bast-pad ignites the rear case wallof the module. Upon burn-through of the rear case wall, the rear of the-propellant bed is exposed to hot igniter gases, and is heated toignition. These hot gases then join those from the igniter and case toproduce a convectively driven ignition wave, resulting in flamespreadthrough the charge. In the situation of granular propellant, resistance tothe gas f low may lead to the formation of a pressure gradient in thepropellant bed, and perhaps even movement of the solid phase, as we havepreviously seen for bagged granular charges. 5 With the use of stickpropellant yielding a much smaller resistance to gas flow, essentially nopressure gradient is forne.1 in the propellant bed, and we would not expect

the solid phase to experience much movement. However, even with the stickpropellant, there will be substantial resistance to the flow of the gasesoffered by the relatively impermeable interzone barriers presented by thecase end walls, possibly leading to the acceleration of entire packages ofpropellant toward the projectile base. Complicating characterization ofthese phenomena, but perhaps resulting in better ignition of the charge,the igniter gases may take the path of least resistance and flow into theannular ullage surrounding the charge, which will almost certainly bepresent in order to facilitate loading. We have noted such 8behavior inother combustible-cased charges employing stick propellant. In this

manner, the case may begin to burn along its length, and if the casecollapses due tc pressurization of the ullage, the propellant bed itselfmay be exposed to these hot gases along a substantial portion of its axialextent, promoting uniform ignition of the charge. Lastly, we cannotoverlook the potential for fracture of the propellant, either granular orstick. Such fracture may occur not only as a result of impact of a packageof propellant on the projectile base, but also due to attack of an overlybri;ant igniter on the rear of the charge. Furthermore, stick propellantmay rupture due to a pressure differential established between the interiorand exterior of the long grain. All of these processes serve to createunprogrammed burning surfaces, which may lead to high local pressurizationand the formation of pressure waves, should even the natural flow channelspresented by stick propellant he obstructed.

The experimental investigations reported herein attempted to assessthe influence of loading conditions and variations of the interrelatedcomponents which comprise a medium-performance, large-caliber, combustible-cased, multizone propelling charge on pressure-wave formation. Theseinvestigations were conducted via test firings of the charges in both awell-instrumented 155-mm howitzer and a howitzer simulator.

II. TEST SETUP

A. Weapon

A 155-mm, M199 tube modified with pressure ports at thirteen axiallocations was the test weapon for all the firings. The standard muzzlebrake was replaced with a special pressure-gage adapter used in support ofa muzzle-pressure program that was conducted concurrently with the multi-zone firings. For this weapon, the standard, lanyard-operated spring-driven firing pin was replaced by a gas-activated firing pin.9 The gasnecessary to drive the modified firing pin into the M82 percussion primer

T. C. Minor and A. W. Horst, "Ignition Phenomena in Developmental Stick-

Propellant, Combustible-Cased, 155-mm, M203E2 Propelling Charges,"ARBRI-TR-02568, Ballistic Research Laboratory, USA ARRADCOM, AberdeenProving Ground, MD, July 1984.

J. J. Rocchio, R. A. Hartman, and N. J. Gerri, "An Electric Primer-Operated Firing Pin Actuator for Large Caliber Guns," ARBRL-MR-02897,Ballistic Research Laboratory, USA ARRADCOM, Aberdeen Proving Ground,MD, January 1979 (AD A069109).

12

p

FABLIE 4. FIRING RESULTS FOR LJLLAGE VARIATIONS/GRANULAR PROPELLANT*

cries Charge Variations Spindle No. Ign.No. Pressure -AP Velocity Rds. Del.

(Mea) (MPa) (m/8) (ms)

8. CBT basepad on Module A/ 281 23 695 3 51Hole of endcaps on Modules (5.5) (18.2) (2.6) (19.1)A, B, and A" opened from 22to 51 rm/ Hotes of fronts of

Nodules A and B opened from 22to 5L rim/ Vent holes (5.6-mmdiain) put in Modules A and A"(50 holes) and in Module B (40holes),' NC spacers connected toModules A and B, and to B and A"

L. Similar to Series 8 except 283** 34** 696 3 40

that vent holes 3.8-mm in (2.1) (5.5)0 i ame t . r

Sam., a, Baseline Series I 276** 26** 696** 2 47except that modules sepa-

rated in chamber with nospacers keeping them fromm r v 04n

S1. i . ,s Seris 1 except 322 65 701 1 56tlit drodul,,s were placed,it m[)I:i rn standoff - 10

' Pr(m spindle face

I. l it , are given in parentheses for series with 3 or wore

**A, or ,, ,i two roi ds I

ht,'rlinl, th,' etfect.s oif maximilm standoff, another Baseline Series I,),j' ,i hr ic i tod and test-fired (Series 11, Figure 14). The results''I ' 'it ri' i, il Ii ring are shown In 'Fable 4. The peak presc;ure and -AP.

0, M'a, respectively, were much higher than observed with tfle,Tri ,. The (,)ange in standoff from 2 to 10 cm apparently alters

, , t ,' ,iitr and initial combustion gases significantly. Though onlyr, *' ,,,,~ ,, ired, thii configuration gave the highest level of pressure

, . tt, sri's tested using a one-basepad ignition source.

.n i1>'S irk Pro)pti l;int

I i Srie;,/St irk Propellant. To fabricate the baseline-"-,N c, int ii ntrs were used. Two of the long A modules and

,' : , P m ii' were' loaded with 2.9 kg and 2.0 kg, respectively,

K I, *>tted-titk propellant. Endcaps were placed on all threettr,' t -v wer,. fitted together into a charge consisting of

.. , i', ' , B/ dule A" (Figur, 15). As in the previous tcst s,

!it th hi-,pad and 4bd itlo A" was at the front o)f the

.1

A A"1~~

ComE"0"MU 11- ZONE MODULAR CHARGE

obk0- 51 m OMA-22 USA0

rMIGAPS A. By: A UtOIA[ FRONET A'MODULE FROI4J A 0

( priesR)

A ( 3 8 MU DRAM IiNES) A"

MUSAiC LI -- ZONC MODUI AR CHARGE

DM5 U OM-22 MM -

(EOCWAS A. 0 & A' MODUJLE FRONT A*WOOL~F FR(X4IS A &0

(S,7ri' p)

Aj :A

ce "P., LII ZONE MODULAR CHARGE

DA 51 IMIAM-22 MM- -00 L

(PDCAP A (EDCAPS 8 & A"VMAE f"#IdS A. 0 AT A-

cm; BSPA DL r-ZONJE MODULAR -HAt G[

A 2 2 um

(PDCAP A (IBICAPS 3* A AMFZA* FROHIS k. a a A-

Fgure 14. (Iii gc/'fmhmnhir ( ml Kmmramtion for ModmiLir ms,(rim~Propellanmt k%ith II 1o~'' \kmriatmolls

vent-hole size from 5.6 mm to 2.8 m produced a four-fold reduction inaccess area of igniter and early combustion gases to propellant surfaces.Such a reduction impeded uniform axial ignition of the charge, and, asexpected, resulted in a higher level of pressure waves.

3. Ullage Variations /Granular Propellant. Since the length of thecharge and that of the chamber differed by only 10 cm, there could be nodramatic altering of the charge/chamber interface. Two basicconfigurations, charge at maximum standoff and charge modules equallyseparated with NC spacers interconnecting the modules in the chamber, wereselected. Perturbations on each of these two series were also fired.Results are noted in Table 4.

Series 8 was similar to Series 5, except that NC spacers made it almostfull-chamber length (Figure 14). As in Series 5, the holes in the threeendcaps and the f ront of Modules A and B were opened f rom 22 to 51 mm, and50 vent holes in Modules A and A" and 40 vent holes in Module B, all 5.6 mmin diameter, were added to insure maximum axial and radial penetration ofigniter gases into the propellant bed. After the charge was fabricated, twoNC spacers, one connected to Modules A and B, the other connected to ModulesB and A", were inserted. This increase in charge length reduced thepossible axial movement of the charge f rom 10 to 2 cm. The results (Table4) of this restriction on charge movement did little to peak pressure incomparison to Series 5 (281 MPa versus 277 MPa), but substantially increasedthe level of pressure waves (23 versus 8 Ml's). The large standard deviationin -AP of 18 MPa and in ignition delay of 19 ms attested to the largevariation within the three rounds. Charge integrity was weakened by thefive-module system (Module A/NC spacer/Module B/NC spacer/Module A") sincethe two 5-cm long spacers, fabricated from an existing module, did notinterlock as tightly as the modules. This could have contributed to erraticignition and flow of igniter and combustion gases through the system.

To determine the effect of reduced radial penetration of igniter gasesinto a charge that had the saiae overall axial and radial dimensions as thoseof Series 83, Series 9 (Figure 14) was fabricated with vent holes 3.8 Mm indiameter, all other characteristics of the charge being the same as Series8. This reduced the radial, initial vent area by a factor of two. ThA-results (Table 4) were essentially the same as Series 8 for pressure,velocity and ignition delay. The -AP Iwas about 30 percent higher, again, anot-surprising result.i

In Series 10 (Figure 14), the effect of Initial increment position onpressure-wave formation was addressed. The charge fabrication usedunmodified NC modules as in the baseline series, wherein the hole in theendcap of only Module A was opened up from 22 to 51 mm. The increments werepositioned so that Module A" was forward against the base of the projectile;Module B was mid-chamber approximately 5 cm from the base of Module A"; andModule A was 2 cm from the spindle face, approximately 5 cm from Module B3.No spacers were positioned between modules to keep them from moving afterignition occurred. The averaged results (Table 4) for a two-round seriesgave a peak pressure of 276 MPa and a -AP of 26 MPa which were similar tothose observed in Series 8 and 9. Althoug4 peak pressure was about the sameas the baseline series, the level of pressure waves was considerably less,indicating a more uniform ignition of the charge.

24

-7 2

T .z I H

i ,,I; / * -

Figure 12. Spindle and Forward Chamber Pressure and Pressure Difference

versus Time for Medium Pressure Waves

.. o4

Figure 13. Spindle and Forward Chamber Pressure and Pressure Differenceversus Time for Small Pressure Waves

versus 279 MPa) but a dramatic drop in the -AP (8 versus 46 MPa). ThisCombination of both axial and radial enhancement of igniter gas flow intothe charge reduced pressure-wave levels sixfold. Examples of both mediumpressure waves (10 to 20 MPa) and small pressure waves (0 to 10 MPa) areshown, respectively, in Figures 12 and 13.

In each series, it was necessary to place a thin cloth covering overeither the 22-mm or 51-mm hole to prevent propellant from moving from onemodule to another. In those series with 51-mm openings, the integrity ofthe cloth in preventing propellant from moving from one module to anotherwas suspect. In Series 6 (Figure 9), we kept the small 22-mm opening andye t still maintained the large radial and axial flow of igniter gases as inSeries 5. This was done by altering the three endcaps and fronts ofModules A and B with 150 holes 5.6 im In diameter, rather than opening the22-mm hole to 51 mm. The results (Table 3) for the one round agreed wellwith those from the Series 5 firings. Peak pressure was 281 MPaand -AP i was 10 MPa, only slightly higher than the 8 MPa of Series S.

To further clarify the Importance of the radial and axial vent holesIn the charge, another round similar to Series 6 was fabricated and test-fired. In Series 7, the holes In both the module sides, fronts and endcapswere reduced from 5.6 mm to 2.8 mm in diameter (Figure 9). Peak pressurewas about the same as Series 6 (Table 3). The Initial reverse-pressuregradient at 16 MPa was higher than the 10 MPa of Series 6. The change In

23

. ................................. .......mmnl~~ ml~lm I....."."......."..".

i"i

"'0 36 '9 4

"-"I,

Figure 11. Spindle and Forward Chamber Pressure and Pressure Differenceversus Time for Very Large Pressure Waves

To maximize the flow of igniter gases through the charge, rounds wereconstructed which minimized interior boundaries between modules. In Series3 (Figure 9), not only was the hole of the endcap on Module A opened f rom 22to 51 mm, but the endcaps on Modules B and A" were eliminated. in addition, "the holes on the front of Modules A and B were also opened up to 51 mn. The .

results (Table 3) indicate a more uniform ignition of the propellant. Peak -"pressure was about the same as in the baseline ,,!ries, but the -&P i war, much --lower, 17 MPa versus 46 MPa. Velocity and ignition delay were in the same

range as the baseline series. -

In an effort to further enhance the rapid ignition of all propellant ,grains in the modular charges, NC centercore tubes were added in Series 4(Figure 9). The 22-mam hole in both the three endcaps and the f ront of themodules was maintained so as to hold the centercore tubes in place. To have.similar axial flow of igniter gases as in Series 3, several small cutouts

were made in the three endcaps and the f ronts of Modules A, B and A". Theaddition of the centercore tubes not only changed the flow characteristics-of the ignition gases but somewhat redistributed the propellant in relatiorto both the charge and initial combustion gases. There was no improvement"

in the results (Table 3) of this configuration over that of Series 3. Thepeak pressure at 288 MPa was slightly higher while the-AP i of 14 MPa wasslightly lower than in Series 3. Both the increase in pressure and thelower -AP i resulted in a higher muzzle velocity for Series 4 of 698 m/s.

In Series 5 (Figure 9), the charge design was a further modification ofSeries 3. Endcaps with 51-mn rather than 22-mm holes were on each of themodules. The holes in the front of Modules A and B were also opened up from .22 to 51 mam. A layer of cloth was placed over each of these holes to keep .propellant from moving between modules. To increase radial flow of igniter ' ''gases Into the charge, vent holes 5.6 mm in diameter were placed in :!ach of .the modules. Fif ty holes in Modules A and A", and 40 holes in Module B were '

symmetrically placed around the cylindrical walls. The results (Table 3),when compared with the baseline series, show no change in peak pressure (277 .

22.

--] .- -i ..- -. . . . 9,. . r 4 ' ' ' " " " " . ' ' ' ' ' ' i ' i ' ' ' ' ' ' . " "" " . " ' " . " ' . , ' i " i " ' " . ' : ' . ' ' L / "

TABLE 3. FIRING RESULTS FOR IGNITION VARIATIONS/GRANULAR PROPELLANT* (CON'T)

Series Charge Variations Spindle No. Ign.

No. Pressure -AP Velocity Rds. Del.

(KPa) (MPa) (m/s) (ms)

6. CBI basepad on Module A/ 281 10 694 1 45

Endcaps and fronts of Mod-

ules A and B both have 150

holes (5.6-mm diam) and

standard 22-mm hole/ Vent

holes (5.6-mm diam) put inModules A and A" (50 holes)

and in Module B (40 holes)

7. Similar to Series 6 279 16 694 1 40

except the holes in

sides, fronts, and end-

caps are 2.8-mm diam

*Standard deviations are given in parentheses for series with 3 or more

rounds.

.. . ... .

Fiur 10. Spnl an owr

•

hme rsur n rsueDfeec

I"

,o[

'i "t

2 21

- s ' tI ' J0' I - %

Figure 10. Spindle and Forward Chamber Pressure and Pressure Difference

versus Time for Large Pressure Waves

21 %

. i-.i.

5

TABLE 3. FIRING RESULTS FOR IGNITION VARIATIONS/GRANULAR PROPELLANT*

Series Charge Variations Spindle No. Ign.

No. Pressure -AP Velocity Rds. Del.

(MPa) (MPa) (m/s) (ms)

1. CBI basepad on Module A/ 279 46 686 4 28

Hole in endcap of Module (5.3) (5.5) (0.8) (1.9)

A opened from 22 to 51 mm/Modules A, B, and A" andEndcaps B and A" unmodified

(Baseline Series)

2. Three CBI basepads - one 402 115 717 1 25

each at base of Modules of

A, B, and A"/ Hole in end-caps A, B, and A" opened

from 22 to 51 mm

3. CBI basepad and one endcap 282 17 690 3 31

on Module A/ No endcaps (1.0) (5.1) (1.5) (3.1)

on Modules B and A"/ Holesin endcap of Module A and

front of Modules A andB opened from 22 to 51 mm

4. CBI basepad on Module A/ 288 14 698 3 32

Endcaps and fronts of (2.6) (8.4) (0.6) (0.6)

modules had 22-mm hole

unmodified to supportcentercore tubes/Cutouts on endcaps andfronts of Modules A, B andA" to mimic 51-mm holein Series 1, 2, and 3

5. CBI basepad on Module A/ 277 8 693 3 34

Holes of endcaps on (2.5) (3.5) (1.7) (2.0)Modules A, B, and A"

opened from 22 to 51 mm/Holes of fronts of Modules

A and B opened from 22 to

51 mm/ Vent holes (5.6-mmdiam) put in Modules A and

A" (50 holes) and inModule B (40 holes)

*Standard deviations are given in parenthesis for series with 3 or more

rounds.

20

MUl~OEMDLRCHARGE _MULTI-ZONE MODULAR CHARGE

DLAM-51 Mm0 OMA& -22 MU IM2

INDCA A DWXPS Sb A, FNDCAwM A. I e MOUL uomr #045

(Series 1) MOUEFWSA "(Series 2) A

A_ B A

A B A "I __________ __ 7

M__ ULTI- ZONE MODULAR CHARGE MULTI- ZONC MODtJI AR CHARGEC9 RASEPAO WaAEA

0. DMA-22 MM --- ~ DIAM -22 MM

e ~CENIERCORE TUBES IN

ENOW Al MaCM~r FROedS A 8ODL MOOLIfAS A.S 6&A" ENDPPS A. A"

NO 0 A A' ENOCAPS FUwh? v MODUJLE FRACIS A. 0 &A-

(.S-eries 3) (Series A)

( 6- W DOAU ~I IS) \ 5s-i OSmI IML(S)

-A IBj A" A BA-

\MULTI-ZONE MODULAR CH ARGE -MULTI -zouE MOOULAR CHAlGFca SakuPAO, CA BA ILP

DLA 005 0A * CAI--5.6 -WJ(ASOUI OI AIS)

0**~0 0" -22 MD O -22 mMtIQCAPS A. 0 & A' MODUL.E FONT A- (NLJCAPS A. 9 & A-"" M O N 04 A-MODULE fR00153 A & 9 IM &I fw Ros A A IS

( ris 5)(Seri s F)

A 8 A"

MULrI-7ONE MODWlAR CHARGE*Cm 814AP00

OW*MU- 25 0 M(ABOUI ISO IOIIS)

0 DLAM-22: MM

EDCAPS A, N A A" MODULE FRONT A"LWOUa FPONfS A A 8

(',ric~s 7)I.i gore 9. Chargc/Chjamlhcr Con1 f i gtlrat i on for Modular Case/Granlular

Propellant w ith I griit ion Vari at ions

In inventory was some 1.14-mm web MIMP propellant which was calculatedto give a peak pressure substantially less than the 0.91-mm web MIMP.Since peak pressure and perhaps the level of pressure waves would be lower,and thus less threatening to the integrity of the gun, this propellant wasselected as the candidate propellant pending outcome of the initial firing 5tests.

B. Modular Case/Granular Propellant

1. Baseline Series/Granular Propellant. To fabricate the baselineseries, two of the long A modules were each loaded with 2.9 kg ofpropellant and one of the short B modules was loaded with 2.0 kg ofpropellant. Endcaps were placed on all three containers before they werefitted together into a charge consisting of Basepad/Module A/ModuleB/Module A". Although modules A and A" were identical, the module at thefront of the charge will be referred to as A" and the module next to thebasepad as A. The total weight of the charge was 7.8 kg of the 1.14-mmweb, MIMP propellant, 85 g Clean Burning Igniter (CBI) in a basepad, andapproximately 0.84-kg Type-I, NC container. The hole in the endcap betweenthe basepad and Module A was opened up from 22 to 51 mm to enhance ignitergas flow through the charge. Standoff for all four charges in Series I was25 mm (Figure 9). The results from this baseline series are given in the --

first entry in Table 3. The peak pressure of 279 MPa and -AP of 46 MPawere well within the acceptable limits of gun safety for continuation offurther tests with this propellant. Typical plots of spindle and forwardchamber pressure and pressure difference versus time for large pressurewaves (20 to 60 Wa) are shown in Figure 10. Coil velocity and ignitiondelay were 686 m/s and 28 ms, respectively.

2. Ignition Variations/Granular Propellant. Limited availability ofType-i NC modular components required limiting series size to three rounds.For three of the six ignition variations, only one round was fired, eitherto simply establish a trend or because of gun safety considerations.

Series 2 fabrication (Figure 9) paralleled that of Series I exceptthat three basepads were used instead of one. The three basepads, one eachat the base of Modules A, B, and A", were all on the outside of the modulewith the base endcap located between basepad and propellant. The openingin the Series 2 endcaps all were enlarged to 51 nun. Thus, the chargeconsisted of Basepad/Module A/Basepad/Module B/Basepad/Module A". Again,the charge standoff was 25mm. Propellant was restrained in each module byplacing a thin cloth covering over the vent openings. Results weredramatically different from Series 1. Peak pressure and -AP. rose from

279 and 46 MPa, respectively to 402 and 115 MPa. The average pressuredifference for the second and third negative excursions were 97 and 43 MWa,respectively, indicating an extremely severe pressure-wave phenomenon.

This very large reverse pressure difference (greater thail 60 MWa) is shown "graphically in Figure 11. The effect of the two additional basepads behindModules B and A" did not enhance ignition of the granular propellant in allmodules as intended, but rather reinforced the vigorous, localized ignitionof the cha ge, perhaps at several sites. Firings were discontinued afterone shot since both peak pressure and pressure-wave levels were largeenough to damage the tube and/or related components. All further testingwas done using one basepad.

18

-0 -' "q

to by a substantial increase in -AP (Series E) which was accompanied by aslight increase in peak pressure. iSince this large -AP in conjunctionwith a large peak pressure posed serious safety problems 1 or the variousparts of the howitzer, either another web of MIMP or another type ofpropellant had to be considered. The influence of case confinement onpressure-wave formation (Series C thru E) prompted retesting of the M31EIMPin modular containers (Series F). Although pressure waves were present,their feedback into peak pressure was not apparent in this limited testing.

TABLE 2. PRELIMINARY FIRINGS WITH GRANULAR PROPFLLANTS*

Charge Rationale Spindle No.Pressure -APti Rds. Series(MPa) (MPa)

M31EIMP Effect of 7.8-kg 132 0 4 Abagged propellant on pressure (1.3) (0.0)charges and -APi

MiMP Effect of 7.8-kg 341 21 4 Bbagged propellant on pressure (2.9) (12.9)

charges and -

MIMP Effect of 7.8-kg 379 14 4 Csub- propellant on pressure (2.9) (5.6)caliber and -AP / Effect of noNC- axial inhibition of gassleeved flow, radial ullagecylinder

MIMP Effect of 7.8-kg 381 26 3 Dfull- propellant on pressure (7.2) (10.3)bore and -AP / Effect of noNC- axial inhibition of gassleeved flow, reduced radialcylinder ullage

MIMP Effect of 7.8-kg 387 50 2 Efull- propellant in modularbore case on pressure andmodular -AP1 / Effect of fullycase combustible-cased(Type 1) packaging

M31EIMP Effect of 7.8-kg propel- 130 12 3 Ffull- lant in modular case (1.6) (3.9)bore on pressure and -APi/modular Effect of fully combus-

case tible-cased packaging(Type 1)

*Standard deviations are given in parentheses for series with 3 or more

rounds

17

.............. *.."

TABLE 1. GRANULAR MULTI-PERFORATED PROPELLANT AVAILABLE FOR TESTS

Propellant Web Length Diameter Diameter Perf(mm) (mm) (mm) (mm)

MISP 0.33 4.04 1.75 0.10

MiMP 0.91 11.20 4.83 0.38

M31EMP 1.52 20.20 8.15 0.69

MiMP 1.14 13.49 5.92 0.43

Interior ballistic calculations for each of these available granularpropellant charges were perforeld using an updated version of the Baer-Frankle lumped parameter code. The calculation for 7.8 kg of MISPpropellant indicated that it would give pressures too high for reasonablesafety. Charges with two different webs of MiMP and one web of M31EIMPwere predicted to give a wide range of peak pressures well within thesafety limits of the gun, and thus were selected for initial testing.Pertinent data from the initial tests with MIMP (0.91-mm web) and M31ElMP(1.52-mm web) are listed in Table 2 along with a rationale for eachparticular test.

Although the M31EIMP would have brought a continuity of propellantformulation to the program in going from initial tests with granularpropellant to final tests with stick propellant, the web of the readilyavailable M31EIMP granular propellant was too large as reflected by thepeak pressure (Series A). The MIMP seemed promising since both the peakpressure and the pressure difference were at acceptable levels formanipulating conditions within both the charge and charge/chamber interface(Series B).

Since rigid, NC-cased modules loaded with granular propellant mightalter peak pressure and -AP,, an increasingly more stringent set of NC-case-confinement conditions was imposed on the propellant. The initial changefrom bag to NC-cyllnder confinement with no change in axial or radialcharge/chamber configuration, but with some change in radial flow ofinitial combustion gases because of the difference in bag versus casepermeability, increased peak pressure while reducing -AP (Series C). Whenradial ullage was reduced by increasing the NC cylinder diameter toapproximately that of the modular cases to be used later in the program,the peak pressure remained unchanged, but the level of -APi rosesubstantially (Series D), surpassing that of the bag charges (Series B).When modular charges with front and rear NC surfaces were used in place ofNC-sleeved cylinders, the passage of igniter and initial combustion gasesthrough the granular bed of propellant was further restricted as attested

P. G. Baer and J. M. Frankle, "Simulation of the InteriorBallistics of Guns by Digital Computer Program," R1183,Ballistic Research Laboratories, Aberdeen Proving Ground,MD, December 1962 (AD299980).

16

°-' """ "'-",'° ','"-" % ."-""-"." - -" ""' '.''.' '....""-,.-"-.."...."..--..."-."."."....".-......."...-4-.- " -.- '.- .". -,

Figure 7. NC Container, Type 2 Figure 8. NC Container, Type I

I11. RESULTS

Preliminary firings were done with the Type-i, NC modules 10 and

several granular propellant formulations and webs under consideration for

t-;t ing,. After selection of the baseline granular propellant, variationscharge/chamber interface, ullage distribution, ignition intensity, etc.,

*tr, made in both the granular and the follow-on stick propellants to

ascrtain the extent to which they influenced pressure-wave formation as

indicated by the initial reverse pressure gradients, -AP. . Additionaltcsts on the more interesting cases, as determined from t~e gun firings,Swa.r-e repeated in the 155-mm howitzer simulator.

.N. _PreLiminary Firings for Selection of Cranular Propellant

The modular, 7one-3 charge used for all these tests contained 7.8 kg) prope I lant , a substantial increase in propellant weight over our' 6

t)t-,vious work on mul t izone combtistion phenomena. To ascertain thei nteractive affects of different propellant weights and types withdi tftrent packaging configurations, several granular prope I [antf i)rlpulations, locally available, were used for initial testin g whileiwai Ling the fabrication of the M3IE1 slotted-stick propellant. TheirSphvsic it characteristics are shown in Table I.

S. Einstein, B. Pe ling ton, S. Westley, "Charge DesignTechnol ogv," Large Caliber Weapon Systems Laborator-, USAARRADCflM, September 1980.

. . . . ." " ". " . -. i . . . . .. .- . . . . . . . . , . . . . , , ... -

.i . I IE lHE* * *. W I I I I U U I U U - q *qq~-. - ! | -. '.-. ,

velocities required for the 155-mm, M198 and ?1109A2/A3 Howitzers. Thecharge is built from two combustible-cased increments, one with apropellant weight of 2.9 kg (Module A) and the other with a weight of 2.0kg (Module B). The 1.3-mm web, slotted-stick propellant consisted of twodifferent lengths, 24 cm for the Module . and 17 cm for the Module Bunits. For our tests, the 24-cm and 17-cm long stick propellants werereduced in length to 23 cm and 16 cm, respectively, so that the moduleendcaps could be firmly snapped in place. In this concept, the two basicincrements, one 27-cm long, the other 21-cm long both being 15 cm indiameter and having wall thicknesses of 3 mm, would be added together toobtain the required velocities rather than discarding increments as is donewith the present standard, bagged, multizone charge. The propelling chargemay be fired as a Zone 1 (Module A), a Zone 2 (Modules A and B), or a Zone3 (Modules A, B, and A). A photograph of the granular MiMP and theslotted-stick M31EI propellants used for these tests is shown in Figure6. Copies of the Propellant Description Sheets for these propellants aregiven in Appendix A.

Figure 6. Granular Propellant, MlMP, and Slotted-StickPropellant, M31E1

Two types of nitrocellulose (NC) modules were used for the tests. Thepresent version (Type 2) is a molded NC cylindrical container (72-percentNC) open at one end to allow for loading of propellant. An unvented endcapfits snugly into the open end of the cylinder. This version, shown inFigure 7, was used for all testb with stick propellant. The previousversion (Type 1), shown in Figure 8, was a molded NC cylindrical colitainer(55-percent NC) which had a 22-mm vent hole in both the base of thecylinder and in the endcap. Extensions were structurally designed intoboth the base and endcap to allow for the placement of an NC centercoretube. When the tube was not used, a thin cloth covering was placed overthe fore and aft holes to contain the propellant. Since this early versionwas readily available, it was used for all tests with granular propellant 5while awaiting the manufacture and shipment of both the modular containersand M31EL slotted-stick propellant. Depending on the test condition,modifications were made to the NC modular structure and/or thecharge/chamber interface. The modular NC containers were purchased fromthe EFMC Corporation, CA. The stick propellant was purchased undercontract from Radford Army Ammunition Plant, Radford, VA, whereas the MlMPwas obtained on post from available lots at Aberdeen Proving Ground, MD.

0All charges were conditioned at 63 C for at least 24 hours prior to firing.

14

"' " '" -. " -" -" .'. " ., -' -' -' ' '. ". -.'' ' ' '' ' '" .> ' ' '' -' ' ', " -.' .' ."• '' ' .' , " '" '" ' ,' . '. " • ", i " -" " . ' " ."' '" " '" '" '

was obtained from an M52A3B1 electric detonating cap. The rapid andreproducible functioning of the M52A3B1 enabled instrumentation to beaccurately timed by this firing system. After the M52A3B1 cap wasdetonated, there was approximately a 1-ms delay until the M82 primerlunctioned. An M158 recoil mechanism in conjunction with the upper

Scarriage from a 155-mm, M59 gun was used to mount the APG Medium B Sleighwhich housed the 155-mm, M199 Cannon. All tests with this system were doneat the Sandy Point Firing Facility (Range 18) located at the Ballistic

Research Laboratory.

B. Instrumentation

Instrumentation on all tests consisted of six Kistler 607Cpiezoelectric pressure transducers housed in the gun chamber: two each,

side-by-side in the spindle; two each, 180 degrees apart at mid chamber;and two each, 30 degrees apart at a forward chamber location (Figure 5).

These six gages were sufficient to yield a measure of the pressure profilein the chamber. By differencing either of the spindle and forward-chambergages (PI-P5, PI-P6, P2-P5, P2-P6), the initial negative pressuredifference, -AP., was determined. Projectile velocity was calculated usingthe distance between and the projectile arrival times at two solenoid coilslocated approximately 20 and 35 meters, respectively, forward of the gunmuzzle. Ignition delay was defined as the time interval between the firingpulse and a spindle pressure of 7 MPa.

Generally, the data were recorded in real time by the Ballistic DataAcquisition System under the control of a PDP 11/45 mini-computer. If thedata were not recorded on-line because of an unusually long ignition delayor a computer malfunction, they were later digitized from an analog

recording made of each test firing.

Pi. P

r

P5~

Figure 5. Locations of Pressure Transducers in M199 Chamber

C. Firing Components

M549A1 Projectiles from Lot 10878E001S066, inert loaded with wax to43.6 kg, were used for all tests. Projectile weight and rotating band

condition (burrs, indentations, etc.) were ascertained prior to loadinginto the howitzer; projectile seating distance was measured prior toloading the propelling charge.

The XM216 Propelling Charge, a version of which is shown in Figure 3,is currently under development by the Large Caliber Weapon Systems

Laboratory to serve as the next-generation zoning solution for the midrange

13

.-

r.-

charge. The total weight of the charge was 7.8 kg of propellant, 85 g ofCB1 igniter, and approximately 0.84 kg of Type-2, NC container. Standofffor the three rounds in the series was 2.5 cm. Combustion irregularitieswere almost nonexistent as attested by the small -APi of 2 MPa (Table 5).Ioth spindle and forward chamber pressure traces were smooth with only aslight pressure-wave undulation superimposed on the pressure. Coil velocity

for the series was 699 m/s. Ignition delay at 40 ms was slightly larger

than for the baseline series with granular propellant.

Since pressure-wave phenomena were almost nonexistent, modifications tothe modules as in the earlier tests with granular propellant to change theflow of igniter and early combustion gases into the charge were deemed notnecessary. Therefore, ullage rather than igniter variations were examinedfirst to see if pressure-wave phenomena of a serious nature could bei ndu ced.

2. Ullage Variations/Stick Propellant. Variations in charge/chamber

configuration were limited because the charge was radially almost as largeas the chamber (14.7 cm versus 16.5 cm for the chamber), and axially only13.6 cm shorter than the chamber. Within these limited confines, three

additional series were tested.

Series 2 was fabricated exactly like the baseline series. The chargewas positioned at maximum (13.6-cm) rather than standard (2.5-cm) standoff

(Figure 15). Firing results are shown in Table 5. Both peak pressureand -APi increased substantially from the baseline series. Spindle pressure

and -AP. were, respectively, 276 and 12 MPa. Although there was a six-foldi

increase in -AP it was still low in relation to those encountered with

granular propellants. The increase in peak pressure was manifested also in

a coil velocity of 704 m/s, which was considerably higher than Series 1.

Ignition delay at 46 ms was about the same as the baseline series.

For Series 3, the modules were spaced in the chamber so that Module Awas at 2.5-cm standoff, Module B was approximately 6 cm forward of Module A,and Module A" was 6 cm forward of Module B, just touching the base of theprojectile. There were no spacers between the three modules to preventmovement after Initial ignition of the charge (Figure 15). Results (Table5) were essentially midway between Series I and 2 with a peak pressureand -AP., respectively, of 266 and 8 MPa. Again, slight changes In thecharge/ chamber configuration made noticeable changes in the combustioncharacteristics of the charge. Coll velocity and ignition delay were 695m/s and 43 ms, respectively.

To ascertain whether initial increment placement rather than incrementmovement could induce large pressure waves, a slight variation on Series 3was made. Series 4 was similar to Series 3, except that 6-cm long,cardboard spacers were inserted between Modules A and B and between ModulesB and A" to impede Increment movement after initial ignition of the charge(Figure 15). Results, which are listed in Table 5, Indicate that pressure,velocity, and ignition delay were essentially the same as Series 3.The -AP1 was reduced somewhat from S MPa In Series 3 to 5 MPa in thisseries. The lower standard deviation on all variables except ignition delaymay be an indication of slightly more stability for the restricted modulesover the unrestricted ones.

27

A 1ries A"

MULTI-ZONE MODULAR CHIARGE-

0 STICK PROPELLANTENCAPS AMO MODlIC FRONISMIT A 0 a A-(14 VENTS)

(Serips 2)

Co&POIU IAA(.-

MULTI-ZONE MODULAR CHAR\GE -

0 STICK PROPELLANTOiOCAS "MOM FdOR RONS

FO A 8 A(HO VENTS)

(Series 2)

MULTI-ZONE MODUAR CHARGE\STICK PROPELANT

CNIAP AI~ OCA FftOTSFOR A. Sb A(HO VIS)

(Spries 4)

I~~~ ~ B~z' A" ~ir/hmc 5lf ua o orMdlrCs ~ l rjc nwith U] lage A .- in

CH 28EA z Okf SPRVD

.. ... ... ... .... ... ... ... .... ... ... . .. . .*...QM SACR

TABLE 5. FIRING RESULTS FOR ULLAGE VARIATIONS/STICK PROPELLANT*

Series Charge Variations Spindle No. Ign.No. Pressure -AP Velocity Rds. Del.

(MPa) (MPa) (m/s) (ms)

1. CBI basepad on Module A/ 260 2 699 3 40Endcaps on Modules A, B, (3.8) (1.0) (2.1) (5.5)and A"/ 2.5-cm standoff/Baseline Series

2. Charge configuration same 276 12 704 3 46as Series 1/ Charge at (7.0) (3.6) (3.1) (4.0)maximum standoff (13.6 cm)

3. Module loading same as 266 8 695 3 43Series I/ Modules (8.5) (3.8) (10.4) (1.5)separated by 5 cm/ ModuleA at 2-cm standoff/ ModuleA" touching base ofproject lie

4. Charge configuration same 268 5 698 3 38as Series 3/ Cardboard (1.5) (1.7) (2.9) (5.5)spacers used to keepmodules separated

*Standard deviations are given in parentheses for series with 3 or more

rou ods

3. Ignition Variations/Stick Propellant. Five basepad variationswere tested to determine the effect of initial ignition stimulus on chargeperformance. The intent was to dramatically change the ignitioncLardzturistic of the charge so as to induce, if possible, Ignit ion

variations leading to pressure-wave formation.

Series 5 (Figure 16) was fabricated exactly like the baseline seriesexcept that the basepad was 85 g, of Class I Black Powder instead of CHI.Charge standoff was 2.5 cm. The results are shown in Table t. Peakpressure at 268 MPa, -AP at 2 MPa and coil velocity at 697 m/s, werk,os-sntlally the same as the baseline series. As expected, ignition delavwas reduced substantially over the baseline series.

To create a more brisant ignition source, 85 g of Class 5 Black Powderwas used In Series 6. All other characteristics of the system were the sameas In Series 5 (Figure 16). Peak pressure and velocity were about the sameas in Series 5 (Table 6). Although -APi at 7 MPa was threefold higher than

Series 5, it was still much lower than that observed with most of thegranular charges. The ignition delay of 16 ms was the lowest observed for

any series tested In this project.

With the advent of modular charges that are to be loaded Into howitzersby automatic mechanisms, the possibility exists that modules could be

29

.............................................L -........ ." ................ "

CLS 1 LCK( POWDER CLSSSUBAK POWDE(RGAMPAO GASEPAW

MULTI-ZONE MODUtAR CHARGEMUT OE ODLRCAE-STICK PROPELLANI STICK PROI'ULLANI

NDC AMUOOtf FRfONTS (?E2CAPS AND MOXMI ITIS

,OR A, S & A-(NO VENTS) (Srp )FOR A. 0 & Ai(NO IdIS) rsF

AL A" Afla A"

NOSASEPAD C1SMA

MULTI-ZONE MODULAR CNHARGE - MULTI-ZONE MODULAR CHA\RGE

0S TICK PROPELLAN r 0STICK PROPELLANT

EICCAPS AND UOOU E FROHTS DOCAPS AM MOCKAE FRONTSFr* A. 9 A-(NO VENTS) FORt A. 0 A(140 VENTS)

A A"' A , VA

rC 3C.~ct HAEAO OI8SEPAO

MULTI-ZONE MODULAR CI 1ARGE "'MULTI-ZONE MODULAR CHARGE-\STICK PROP[LLANT STICK PROPELLANT

O4OCWS ANC MacFPLE FRONTS NO CNDCAPS / MOoui FRONTSFOR A. 8 A A-(IO V111TS) FOR A. 9 & A-C'(NrS)

CI ASEPAO

MULTI-ZO14E MODULAR CIIARGE -

STICK PROPELLANT

NO WC WVAIES /STIC PRFV'I)T IN MAW3 S

Fijgurec In. Chr ihrConfub r;itirm [o r Moduir'US/tIc1)rnpol i t i t h f[gu1i t Iu \TI V 7i 'It 1011S

30

7.- 7.

misloaded with the basepad at a mid- or forward-chamber position or possiblynot in the system at all. To ascertain the effects on ignition andcombustion of charges with no basepad, Series 7 was constructed exactly asSeries 5 except that the basepad was eliminated (Figure 16). Results, asshown in Table 6 indicate no change in peak pressure or velocity. Theinitial reverse pressure gradient at I MPa was reduced twofold over Series5; sevenfold over Series 6 and, thus, was one of the lowest recorded for anyseries tested in this project. As expected, the ignition delay increased --substantially to 200 ms.

TABLE 6. FIRING RESULTS FOR IGNITION VARIATIONS/STICK PROPELLANT*

Series Charge Variations Spindle No. Ign.No. Pressure -AP Velocity Rds. Del.

(MPa) (MPa) (m/s) (ms)

5. Class I Black Powder 268 2 697 3 29basepad on Modules A/ (5.5) (0.6) (1.5) (3.1)Endcaps on Modules A, B,and A"/ 2.5-cm standoff

6. Charge configuration same 266 7 698 3 16as Series 5/Class 5 Black (7.2) (5.1) (2.9) (1.5)Powder basepad

7. Charge configuration same 266 1 698 3 200as Series 5/ No basepad (3.2) (2.3) (3.8) (57.1)

8. Charge configuration same 275 0 706 1 342as Series I except CBIbasepad on front ofModule A"

9. Three CBI basepads - one 259 4 704 3 38each at base of Modules (6.8) (3.2) (3.6) (7.2)A, B, and A"/ Modules andendcaps unmodified

10. CBI basepad on Module A/ 264** 2** 698** 2 32**No endcap on Module A, B,and A"/ Fronts of ModulesA, B, and A" opened up with

11-cm hole

11. No NC module/ Stick 232** 0"* 670** 2 66**Propellant tied inbundles/ CBI basepad

*Standard deviations are given in parentheses for series with 3 or morerounds**Average of two rounds

31

.,

The single firing for Series 8 depicts the effect of having the CBIbasepad at the front of the charge. Pressure and velocity at 275 MPa and706 m/s, respectively, were similar to Series 2 where the charge was atmaximum standoff. Unlike Series 2, -APi did not increase but was 0 MPa.

Ignition delay at 342 ms was the longest for any series fired evensurpassing that of Series 7 where no basepad was used. Series 9 shows theopposite extreme from Series 7 wherein 3 basepads, one each at the base ofModules A, B, and A", were loaded into the howitzer (Figure 16). Theresults (Table 6) of this test, simulating another case of misloading thehowitzer, again suggest a very safe and forgiving charge. Pressure,ignition delay and -AP at 259 MPa, 38 ms and 4 MPa, respectively, weresimilar to Series I, t~e baseline configuration. Velocity at 704 m/s was 5in/s higher than the baseline series thus being more comparable to Series 2(charge at maximum standoff) and Series 8 (CBI basepad in front of ModuleA").

As suggested by the very low -APi for all of the series tested, nearsimultaneous ignition of the stick propellant charges appears to heoccurring even though the propellant is packaged in unvented NC modules. InSeries 10, rapid axial flow of igniter gases over the propellant iticks wasenhanced by eliminating both the endcaps and opening up the fronts ofModules A, B, and A" with an 11-cm hole (Figure 16). These results (Table6), when compared to those from Series 1, suggest that the effects of axialconfinement preventing rapid flow of igniter gases into a stick propellantcharge that is not tightly constrained within the NC tube are minimal. Whenthe NC container was completely eliminated (Series I, Figure 16) thereduced energy of the system in conjunction with a slightly larger freevolume reduced, substantially, the peak pressure and thus the velocity(Table 6), a result corroborated by lumped-parameter interior ballisticcalculations. Ignition delay increased 30 percent over the baseline seriesto 66 ms. Not only were pressure-wave phenomena nonexistent, the pressure-time profile was the smoothest for any series fired. Apparently, even togenerate the small pressure waves noted in most of the series, the stickpropellant has to either be confined in the NC module or tightly constrainedin bundles thus reducing the radial flow , f igniter gases through thecharge. Neither condition was present for the two rounds in Series 11.

D. 155-mm Howitzer Simulator Tests

The apparatus used to conduct a variety of studies at the BRL of thedetailed phenomenology of propelling charges is shown in Figure 17. Themassive mount, constructed of armor plate, accepts either plastic chambersor axially reinforced, filament-wound fiberglass chambers. The plasticchambers used were commercially available cast acrylic tubing with inner andouter diameters of 165 nmm and 191 mm, respectively. Although the clearplastic fractures at significantly lower pressures than the fiberglasschambers, they offer a much better view of the events transpiring within,

and thus were used for this study. The muzzle end of the chamber was closedby a projectile seated in a section of gun tube machined to the dimensionsof the M199 Cannon. The breech end of the chamber was closed by a spindlesimilar to the mushroom configuration of the M185 Cannon with the centrall" -venting primer spithole. The spinile accepted three piezoelectric pressuretransdticers. An instrumented projectile permitted gas pressure, totalforce, and acceleration measurements to be made at the projectile base.

32

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

.. ~--- --- . . .1%[. L ...~n . ,

Figure 17. 155-mm Howitzer Simulator, Plastic Chamber

Photographic data were recorded with a high-speed 16-mm camera. Datawere recorded at a framing rate of approximately 5000 pictures per second.

A one-kHz timing signal was placed on the film by electronics internal tothe camera, and the firing fiducial (time at which the firing voltage wasapplied to the gun) was also placed on the films to aid in correlation ofthe film data with other data.

Flash X-rays were used on these tests to monitor the movement of thesolid phase. For one shot, a total of four, 300-kV X-ray heads was used,two at one axial location, separated by approximately twenty degrees (seeFigure 18), and another two at a further axial location, similarlyseparated, to cover the length of the tube. The overlapping images from thetwo sets of heads were rec rded on a single sheet of film, yet it was

possible to determine the X-ray source of each image. One image was createdby X-rays triggered at a predetermined spindle pressure, and the secondimage was made by the X-ray heads triggered at a predetermined time delayafter the first. For the stick-propellant test, only one image was recorded

using two X-ray heads to improve the clarity of the radiograph. Theradiographs were recorded on Kodak XR-5 tilm using Dupont Lightning Plusintensifier screens. The film was protected from the blast of the

disposable chamber by a wooden cassette, with the forward face composed oflayers of air spaces and saciriticil wooden plates.

The two charges selected for testinp, in the fixture were the baselineconfigurations for both the modular/ranil ar (Series 1 , Table 3) and

modular/stick (Series 1, Table ') propellat . These charges represented a

infold variation in -AP. and ai threefold variation in ignition delay. An(vetview of the data is presented hel, w.

Data were obtained for the Yrlniuliar-propel lant charget up to a spindle

pressure of 17 MPa. The hih-speed film showed the functioning of the W82Primer at about 1.5 ms after appli cat i(n of the firing voltage. At 2 ms,

the rear ullage was full of flame. By 5 ms, a 1luminous front traversed thelength of the chamber in the top ainotilar i] l age, and was then reflected

. .~ . . .

toward the spindle. After arrival of this reflection in the spindle region,all luminosity disappeared, and several oscillations of smoke in the annular

ullage were seen. The chamber remained dark until after 50 ma, but by 55 msthere was a very bright luminosity at the spindle end of the charge. At 58

ms, a plume of flame escaped from the front of the charge in the area of thehole in the forward end of Module A". The luminosity increased such that itwas very inteuse at both ends of the chamber at 60 ms, and the flame started

moving into the annular ullage from the rear of the charge at about 61 ms.The flame then continued to fill the chamber until the plastic tuberuptured, without any obvious indication of combustible case fracture orsubstantial movement of the charge. The flash X-ray recorded at about 4 MPa

showed that the charge had moved forward approximately 50 mm. The rear ofthe charge was lifted off the bottom of the chamber so that it touched thetop of the chamber. The "A" module was raised slightly off the bottom ofthe chamber. The granular propellant was seen to fill nearly the entirevolume of the modules, and the walls of the cases appeared to be intact,including the endcap of Module A which was next to the basepad igniter.There were no obvious traces remaining of the igniter itself. A flash X-rayrecorded at a pressure of approxiamtely 8 MPa showed the same features asthe one shot at 4 MPa, except that the charge had moved forward an

additional 5 mm.

BALDAS

EXPERIMENTCONTROL

DATA ACQUISITION Y

DATA REDUCTION TRIGGER

HIGH SPEEDI j -- CAMERA

X-RAY ---.. pHCASSETTE I .:;:

LI

X-RAY HEADS

Figure 18. System for Experiment Control, Data Acquisition,

and Data Reduction, 155-mm Howitzer Simulator

34

Data were obtained for the stick-propellant charge up to a spindlepressure of 16 MPa. As with the granular charge, the high-speed movieshowed the functioning of the primer, ignition of the basepad, and an'scillation of luminous gases in the annular ullage, at about the sametimes. However, the intensity of the luminosity of the combustion of thebas-pad appeared to be much less intense than with the previous shot. AgainIfter the luminous oscillation, the chamber became dark with only smokevisible. At 38 ms, luminosity appeared at the spindle and front of theThamber, without traversing the annular ullage in view of the camera. By 40ms, the flame at the front of the chamber was very bright, and startedmoving through the annular ullage toward the rear of the chamber. At 42 ms,the rear of the charge was lifted from the bottom of the chamber, and thetop casewall of Module A perhaps was ruptured. By 44 ms, luminous gaseswere swirling into the annular ullage from the rear of the charge, and itappeared that the case of Module B perhaps was collapsed. Just prior tofailure of the plastic chamber, it appeared that the casewall of Module Awas blown out to the wall of the chamber through the top annular ullage.Also prior to the failure of the chamber, the intense luminosity inside themodul, illuminated them from within, and t 1hough propellant grains could notl>o seen, the reinforced areas of the modules at their overlap points werereadily discernible. Due to a test failure, a radiograph was not recordedfor the shot just described, but a second test firing of an identical chargein the sirnul.itor provided a flash X-ray recorded at about 7 MPa. It showedrhat the rear of the charge was elevated well off the bottom of the chamberand the forward end was slightly lifted. The charge moved axially about 50mm fron the initial loading position. The top of the case of Module A waspushed out into the annular ullage, the case of Module B remained intact,and the top sidewall of Module A" was collapsed down upon the stick-propellant bed. There were some twists of either propellant or casematerial in the annular ullage in the region of the juncture of Modules Band A". The endwall of Module A, initially next to the basepad, was not inevi~dence.

IV. CONCLUSIONS

In this study, the influence of charge interzone permeability,distribution of ullage, charge increment movement, igniter brisance and/orplacement on the formation of pressure waves for modular charges employingboth granular and stick propellant was investigated. These parameters werenoted as those likely to cause ignition and early combustion problems, basedon our previous work with bagged, multizone configurations.

Within the range of parameters studied and sample sizes of the series,the results indicate a distinct performance difference between modularcharges employing granular and stick propellants. The modular chargesfabricated with granular propellant, regardless of the charge/chamberconfiguration, generally gave large pressure-wave levels. Only afterextensive modifications to the modular container to enhance both the radialand axial flow of igniter gases into the body of the granular-propellant beddid the level of pressure waves lessen from large to medium or smalllevels. The stick propellant, regardless of charge/chamber configuration,type of basepad igniter or, indeed, no igniter at all, gave pressure-wavelevels that were small without any modifications being made to the modularcontainer.

35

The overwhelming conclusion reached from this study is that themultizone, modular charge with stick propellant has good ignition andcombustion characteristics that are not affected, substantially, by thecharge/chamber interface or by ignition variations. Future studies willconcentrate on the effects of low temperature and parasitic components inthe module on ignition and combustion characteristics of the charge.

ACKNOWLEDGEMENTS

The authors wish to express their gratitude to Mr. Scott Westley of theLarge Caliber Weapon Systems Laboratory, USA ARRADCOM, Dover, NJ, forsupplying the combustion modules used in some of the tests and to the SandyPoint Firing Facility personnel (Messrs, J. Bowen, J. Hewitt, and J.Stabile) who conducted the test firings and recorded the data.

36

........................................ .- . ...

S. . . . . ,

REFERENCES

1. I. W. May, "The Role of Ignition and Combustion: A Survey ofDevelopmental Efforts," 13th JANNAF Combustion Meeting, CPIAPublication 281, Vol. 1, pp. 315-340, September 1976. p

2. 1. W. May and A. W. Horst, "Charge Design Considerations and TheirEffect on Pressure Waves in Guns," ARBRL-TR-02277, Ballistic

Research Laboratory, USA ARRADCOM, Aberdeen Proving Ground, MD,December 1980 (AD A095342).

3. T. C. Minor and J. DeLorenzo, "Charge Design Approaches to theReduction of Low Zone Stickers," 1976 JANNAF Propulsion Meeting,CPIA Publication 280, Vol. III, pp. 403-434, December 1976.

4. R. J. DeKleine, "155-mm XM211 Propelling Charge Zones 3-6 DesignReview Minutes," Office of Project Manager, Cannon ArtilleryWeapons Systems, Dover, NJ, April 1980.

5. T. C. Minor and A. W. Horst, "Experimental Studies of IgnitionPhenomena in One-Dimensional Propelling Charges," ARBRL-TR-02315,

Ballistic Research Laboratory, USA ARRADCOM, Aberdeen ProvingGround, MD, April 198t (AD A100298).

6. C. R. Ruth and T. C. Minor, "Multizone Artillery Propelling ChargeStudies," ARRRL-TR-02486, Ballistic Research Laboratory, USAARRADCOM, Aberdeen Proving Ground, MD, May 1983 (AD A128285).

7. T. C. Minor, "Mitigation of Ignition-Induzed, Two-Phase FlowDynamics in Guns Through the Use of Stic', Propellant," ARBRL-TR-02508, Ballistic Research Laboratory, USA ARRADCOM, AberdeenProving Ground, KD, August 1983 (AD A133685).

8. T. C. Minor and A. W. Horst, "Ignition Phenomena in Developmental,Stick-Propellant, Combustible-Cased, 155-mm, M203E2 PropellingCharges," ARBRL-TR-02568, Ballistic Research Laboratory, USAARRADCOM, Aberdeen Proving Ground, MD, July 1984.

9. J. J. Rocchio, R. A. Hartman, and N. J. Cerr, "An Electric Primer-Operated Firing Pin Actuator for Large Caliber Guns," ARBRL-TR-02897, Ballistic Research Laboratory, USA ARRAI)COM, AberdeenProving Ground, MD, January 1979 (AD A069109).

10. S. Einstein, B. Pellington, S. Westley, "Charge Design Technology,"Large Caliber Weapon Systems Laboratory, USA ARRADCOM, September

1980.

11. P. G. Baer and 1. M. Frankle, "Simulation of the InteriorBallistics of Guns by D-Lgital Computer Program," R1183, Ballistic

Research Laboratories, Aberdeen Proving Ground, MD, December1962 (AD 299980).

37

APPENDIX A

Propellant Description Sheets

P; PEiLANTDESCRIPTION SHEET EXPPTP.R7-2a

b A ,tO 1 N.Wfl&

'-.k TYP 11 (CTUAL L(T)__ PA'+ 2,00 5-wbt --t356 d td 14~ Jan 82 - - PCD-18,020 lbs. ---

C. ARMNY AY ,UNMTON PLANT, RADFORD, VA. A~C OAA9-77*4 007 _

h II RO G E [L L LOS E _______________

I 11,1I. 1N1ROGEl. CONTENT4 III $ &A(I SI At'LrI 134 C

65 S5Ci

* 21'!-~__________MAX_.139.. 1 __MIN

MIN 13.11 ___ __

AVG _13._15___+ MIN 30_WI

- x5 ~MN 30 _ W'

?I~NUAC1REOF SOLVENT PROPELLANT___.1 1 S No /D Y5. I~NZ.[MINI CIj' S'.NG 0Of POUN.DS ALCOHOL AND ____ POU?4D5

s'L) .INI PERCENIAGE VEMIX IC -. OLF L-----TPROCESS-SOLVENT RECOVERY AND DRYING c)AT

7: ;AnRE F24__

TET F 1NiSHED PROPE1.LANT STA8IUIY AND PHYSICAL TESTS

4 iPUL ACTUAL

1 o iol ;__ E s ERs. TL'. NF 5 hrsI~ Ufl 1PR~. O ELANY FmaET

.~~~~(. E DEFOTN1 IMNON Iinc.. es)

oil ___ DATES

PACKED

4~~1 - - - - ----

A~~~ *. .-

*Tfl,.~j,5 5~ * I ~~V~e~~l~t 0~d.I A ~,@ACE I'IE IT IVI"

A: I F. f--83

13FRIES 1, MODULAR CHARGFI/GRANLLR PROP.. MODOL. On

20-

260d

10

I14 icrn

211

'100

I-IF~ tl'

SERIES 1. MODULAR CHARGE/GRANULAR PROP., MODUL.28BASELINE SERIES

300

280-

260

Pie

226-209

- ISO

IllZ

-. 100'/"" 1 0

,;s' T I f-.0H S) Il G-

II ~

SERIES 1, MODULAR CHARGE/GRANULAR PROP., MODUL.028BASELINE SERIES

60)

CL 40.

30-

LJ 20-

* --10.

w -20-

ILL

-so.

, ,, - @ .

2S 30 3s 40 4s5 '.5

T111E (MS)

56

SERIES 1. MODULAR CHARGE/GRANULAR PROP.. MODUL.027BASELINE SERIES

30 0

260I '

2GQ-

220]

S 200-'

Cc 140Ina.

I ,I I

TI-ME (M ))

SERIES 1, MODULAR CHARGE/GRANULAR PROP., MODUI.027BASELINE SERIES

3I0

-30

',' 2 ;4

TIM ( )

iii

-C.O -.

TIME (MS)

.... . :.... ,iI ,, , ,,-.. ... . ..... - -..... ........... ............... .. ,,

APPENDIX C

Plots of Spindle Pressure (Solid Line), Forward Chamber Pressure(Dashed Line), and Pressure Difference Versus Time

(A O N co C14 co0 U

0 dE r-.LrC'.D I

W

(A -x

u 4 w ~ Q.c)C 4C

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a) r,00a C4 .Z)

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"C~~~Q rC C C. ~ .4

(UCC<0 U C '-

w.. 47" 4c~"Zt " " )U bC.tC C rn0C

APPENDIX B

Tabulation of Firing Data f or Modular Case/Granular Propellant andModular Case/Stick Propellant for all Series Configurations

45

PROPELLANT DESCRIPTION SHEET _EEMPT-PRA_7-2

___ ___ ___ ___ ___ ___ ___ ___ ___ ___ ___ ___ ___ ____I AR 335-15COMPOSITION M31AlE1 Slotted Stick(NoMTNAI.T rn'r DALTNMI A-E409SPKIFiCAON COR lttr SARRA-EN dtd 10/6/82 & 11/29/82 PAKDAON 10,200 Pounds

MF TRA DFORD ARMY AMMUNITION PLANT, RAOFORO, VA. jCONTRACT NUMBER OAAAO97C-4O07

NITRO CELLIJLOSE _______________

ACCETEDBLID NMBES HllROGEN-+CONTENT- KI STANCH- STABiLIT 11314.510

12.58 MIN(

B30963 B30964 B30966 AVG 12.52 % 45+!MIN1 30 MIN

_____________ xPEOS1ON we

MANUFACTURE GF.S SOLVENT. PROP ELLANT:...:*:. .: :.. :::.:::": ::

-0. 1 78 POUNDS SOLVENT PER POUND NC/DRY WEIGHT INGREDIENTS CONSISTING OF 60L... POUNDS ALCOHOL AND 4n POUNDS

Acrionp plit 100 POUNDS SOLVENT PERCENTAGE ETMIX TO WHOLE

ItE.PE TUNl~ES I A. TIMEFE M .... PROCESS-SOLVENT RECOVERY:AN DRYING:DAS~_UR

Gxbien Ambiend Ambient Conditioning ___48

Amie 120 1 Increase at 5" per Hour___

FRCPFLLANT COMPOSITION TESTS.O.F. f INISHEODPELNT . STASIUTY AND PHYSICAL TESTS

CONSTITUENT FCIMULA -TOLERANCE MEASURED FORMULA_______ ACTUAL___

____H_ EAT TEST NO CC 40' 0(+Nitrocellulose 22.20 ±1.3 21.91 No Fumes 60' 60Nitroglvcerin 19.00 ±1.0 19./48 FRM Of POPELLANT

Nitroeuanidine 53.70 ±1.0 53.28 ____________

____________HOE cal/gm n/a Si.50

Dibutvlohthalate 2___70_ ±0____3 2.98______

Ethyl Centralite 1.40 ±0. 1.3 Avg Stick wt-I!ms n/a 30.00

Potassium Sulfate 1.00 ±0.3 1.03 Std Dev -?_MS n/a 0.931

Total 100.00 - ___No Trials n/a 100

Total Volatiles (TV) /a n/a I c Absolute Densityl 1.63__ ____

Carbon Black 0.09 ±0.01 I* L.jgcCLOSED IOM ... . PROPELLANT -IMENSIONS 4ET 83c

_______I LOT NUMBER I TEMP *Pj_____ oeF______ ________ ____ RELATIVE ID li...;,....

TSPECIFIC.ATION DIE FINISH4ED SPEC ACTUAL

____ _______________ _ LE_ NGTH ILI 292 28.81 n a 03

_______ 90___ 90_103.161 120.95 DIAMETER (0) 0.234 0.259 02.32 n/a 11,2

I_ IfF _ _ _ _ (d) 0.07 0.086 _ _, DAE

REMARKSWe0.7 0.8 0 ACI1/33

W. TIU- OF% PAC INFCOTAND

TYPECOF FORMKIP4R 10NAUGNER

REMARKS

inclue.a.

. . . . . . . . . S "tA. tl OF CC. 011' RERSNTTV s . Of GOVERNMENT CVAUI A SUAC REPRESEN.t *. TATIVE .

2IEL1 V1-3 '623 ______

54153-2. 53472-2, rAN 70 .SeS-2 ~ TVX s.r~"B:za

,.,7Y;252YI 253Y: 256Y C1UOE .t.t -

. 263Y;__ 2 6 8y_, 282Y;_ 28FY ;-295.y;, 3 +

13. 11 30gS-16 30 ..

IkA u;-AC;TUi-E OF PROPELLANJT

-- - -,;PFOCESS-3OLVENT RECOVER~Y AND DRYING ---

- E SCLVENT PECO'.L.YT.JZR __ ___________ ___ 1

_ CYCLE________ __

TESTS OF FiNIS-CD PROPELLANT '" ____

__ - C *'lC - - S O ~ .4 - - 3 4 , 5 0

120.00 +,,.00 9. 73 'to i -.osmo ___ _ HS ~ . MIN 5 hrs.5.0 _-5. ____ _ _ ___

1.00-- _ _ _

0 60 - Q0 [4 5 1-- -

i 1.32 - ___ ____ _

- -. CA.., PC-..SIUrM 4. TAIAU i I A~ 1 _____

-A. Q- _4 1 6.25 ,:x 1.7* ~ ________0.2 79 0. 19L3 2.66

0.0535 O 06 '4/22/74

~ r~rn ~ 10.0515 J10. 0337 Is 4/22/74-~ ~~~~~~~~~~~oo 0 .*--. T.'~- --- .55J._03727'.

* 4--------1 - ~'' jl '\x.J __ 7.1 4t. 4-30-74- - ------ - t~ ~ I.2.22 .,t

1 . s. C to 52_ 5-2-74

7C PM. P 14 '%A IT -, F.7jF CA I

.............................................................................4

- .- . .

CGRTIrICATE OF COMPLIANCE AND ANALYSIS

B3LACK PWEOSIUM NITRATE (Nominal Lot) OATH PACKED_______

SPECIFICATIONm;/PLTNtRNOIA

GRaA/DEASS C S-

CH.MICAL AND PHYSICAL REQUXREbMNTS

SPECI-ICATION LIMITS ANALYTICAL RESULTSMAXIMUM MINIMUM SAWLE I SAMPLE 2

X-1S TUR oSc t , t.1

ANALYSIS - DRY BASIBsPotassium Nitrate 72f0 ?A 720_ 1Sodium NitrateSualfur -0 5CharcoalCalcium CarbonateSemi-BitumLnoum Coal x

Total xx XX T

ASH 0.8iSa6a,

SPECIFIC GRAVITY 1.8o ,77 /. 781

APPARENT DENSITY M

GRITTY OR FIBROUS PARTICLES Ab"Mw. J

* GLAZE

GRANULATION,On U.S. Std. /S 3.0 S _ i,9 * /On U.S. Std.ThruU.S. Std. -.-

Thru U.S. Std. A/0 .00

Date Tested_________ _____

Book No.

Order No.

* Customer

Tested byt Ifle5 ).

42 .

i .. '-..''.i'-. ' ," ,''-?.."' - "'., . '. . .. . :. ."". , - .. - . - .- ., . . .. - - -"- .'- ,,. . " , . - .. - .

SERIES 1, MODULAR CHARGE/CR tJUL5l PROP., MODLIL'.03BflSELIU4' SERIES

300-2:.220

(. 200:

iJo-

S 120-I

30

710

sot

301 ---

20'- ISS

I ti HS ______ _____

~[RIF IHOULiRcWRG/GnNL~< RO. MDU5.83

rqI,IIS 2., 1 ODUI-_R C mRGE/GRZANULOR PROP.. IODUL.0,31ONE BASEI>FD AT 8RSE OF EACH MODULE

3120-

3100

380"

200"

ISO'160

610 IIl I

100

I r ; 30 3 - 4Q '-(

TII1[ (IS )

,PF SiEi 2. IIi0)'JLnR CIIRRGE/G " 4ULi-R PROP., ;.';OUi. .0 iON 6IlSLPAD AT BA'SE OF EAlCH MODULE

120

I Ii

I 20.21

-II

I

- II1I !,,,•.

T II1[ I MS).

59

.- .- .. .. ..:-..-.'.-..'..,.."--." .......-.-.- .... ..'.-'.... ....,. ."..'. -';- / , ., " ' " " " " " " " " " ' '

SERIES 3, MODULAR CPSE/GRANULAR PROP.. MODUL.032flODULE FRONT & BnCK SURFACES OPENED UP TO SI IH

300

289-

260 -

220

i.

-" 180.: * - ISO.

(o 120:r,

hI 100-

Go-

3 lto 11' so s60,TIME (MS)

^-RIES 3 .IciDULAR CASE/G, - UL I- PR P. [OOUL -2U)l.L L -IO' & -flCK SURi(C-S OPENED UP S$ Si

"- ' -0

30-

I 20-

SC SA,,. I 1 '

7 I

TIME (11S)

60

........................................................ ,..........._.:! :

q-' Mo I.

SLP i -S 3, IIODULniz C ISF/Gd-)i1ULAhR PROP., hC[O~UL .Wis

PMO)ULL FRONY A BO)CK SUR17ACES OPENED UP TO Si ilI

20

220-

L. 200

R '1100 o, 0',

I.

T I HI

5 "61

iiODULE FRONI' & 3LACK( SURFriCEC DPE' ED UP TO 5 1 l-A

280-

269 1

220-

, 160.

v-ri

Ld~

2630 3S Ito'ITIME (MS)

662

, ER [ES 4. MODtILF CI-IORGE/GROnVULflR PROP. M-ODUL.035MODULES HOiVE CENTERCORL TUBES

300-

280 1

260

2140-

22 0

I80

C)

2, 0

603

SERIES It, MODULAR CHARGE/ GRANULAR PROP., MOOUL.036"MODULES HAVE CENTERCORE TUBES

300

280-

2409

220

160

1409

120-

LL

-~1 -~ TIME (MS) S

SERIES 4, MODULAR CHARGE/ GRANULA~R PROP.. MODUL.036MODULES HAVE CENTERCORE TUBES

crCL

LLU30-

Ld

Ld~ 20-

le-

Ld

Le

25 '0364 Li5 s'o s

TIME (MS) ________

64

SERIES 4. MODULAR CHARGE/GRANULAR PROP... MODUL.037MODULES HAVE CENTERCORE TUBES

300

280

269

220

teseISO-

140-

(A 120

(ALii 190'Cr:0.. 80-

20

40

25 30 36 40 4s 50 5s

TIME (MS)

SERIES 4, MODULAR CHARGE/GRANULAR PROP.. MODUL.037MODULES HAVE CENTERCORE TUBES

S.,al:

40-

LUJ 30-

cl 20 -;

LLJLU

LULi. 0

. -20-30i

-302s 30 'q , ss

TIME (MS)

6S

. . . . . o

"" "" -"". '" -. . '." .,. -' ,,,,J 2" "."."' '._ -_ - -_" Z " "" -- '."- " : '" ,"," -.-. L ,,- ." .... ;"t- '"''-'""-" : "'" -'--- -

SERIES S. MODULAR CHARGE/GRANULlR PROP.., MODUL.038MODULES HAVE 5.6-M1M VENT HOLES

I- 270

I'l.

Lu-

4040SO 556

TIME (ms)

I SRIS . ODUORCHRG/GRNLLP POP. MDU63

SERIES S. MODULAlR CHARGE/GRPNULnp PROP., MODUL.03930 r ODULLS HARVE 5.6-MM VENT HOLES

200-

2GG -

249-

180-

L

UL 8

Ila-

29-

e 0

T IME HMS)

SFIE 5 ~Or'Jfl ClPC/GPNL~ POP, O67.3

Zam ~ 22V ~-* iDJ

SERIES 5, MODULAR CHARGE/GRANULAR PROP., MODUL.q0iHODULES HAVE 5.6-MM VENT HOLES ]

2r)03o0 1

260 I

0 2 0

(o) t 60"(Al

120110

20 "

(I)

25;30 3£ 4,0 6£, 5STIME (11S)

SER IES S , ODULAR C H AF,( / R AN lII AP PROP ., 1iODUL .O01 01-O0iULES HAVE 5;.6-Mil VENT HOLES =

;;7, 30

Y,

20

0 C 10 - 1,1-5- ~

i

/0 p ~ , r- '

I;

I ti s

TIE IS)

I

. . . . . . . .. . . . . . .-. ....

SERIES G. MODII AR CHnRc:F/GRANIft.PR PROP., MODUL.0117),',0' ES & kNldC(A2& N )iVL 5 hIVtL~ HOLEiS

* ".? l I I.

140-

C/)

40

FI IE (MS)

' FRIIES 6. moDjiLQR CHARGEM(RWAJULOR PROP., HODUL.c0tI7L)ULL & EiNOCfAPS FIU'VC 5.6-Mil VENT HOLES

Lii

Lii

LL 20-LL

IiMHE (His)

69

SERIES 7. MODULAR CHARGE/GRANULAR PROP.. MODUL.0q8i-,ULES & Ei'iPS HNiV,-- 2.8-M VENT hULES

2110260

120-5- too-

0 1 120.

C") IO-

CL 80-4'0

60

3 120 ,s so 6' 65

TIMIE (MS)

SERIES 7, MODULAR CHARGE/GRANULAR PROP., MODUL.048 .

MODULES &ENOCAPS HAVE 2.8-MM VENT HOLES

80 0

40-

t J

Lld 10-

20

TIME (MS)70

7O.r -

- 0 . . - - . - , - - .- . . . -- - . . - . - . . - . - - - " - - . . -. - " 5.: . - - . i - . .' -' . . . . . . - . - -• . - ., - , ' ' , . ' - - , " , , " , ' .t . " - ' " , " . - _ " : . ' - " * - " , .' . " , , --4 0 _ - , , ,

SERIES 8, MODULAR CHARGE/GRANULAR PROP. . MODUL.0415.6-MM HOLES IN MODULES(SEPPRPTED BY NC-SPACERS)

300-

280-

260-

240-

220-

0- 200

180-

140-

S 120

S 100-0-CL 80

608

'40

28 /

'i0 '5 05 60 6s 70

TIME (MS)

SERIES 8. MODULAR CHARGE/GRANULPR PROP., MODUL.041E.6-MM HOLES IN MODULES(SEPARATED BY NC-SPflCERS)

60

50-

20-

-3 01

L.J

L

120

'40 '45 6~ 55 60 ' 65 7 0

TIME (MS)

71

SERIES 2. MODULAR CHARGE/STICK PROP.. MODUL.061CHARGE AT MAXIMUM STANDOFF

260

240"

1,"

20

2110 so

E IL 2.MDLRIHRES IC RP , OU -6

140

,, 12(1

30-

10 1

110 s S 55 60 65

TIME (MS)

EPIEiS 2. MODULAR CHARGE/STICK PROP., MODUL.e61CHARGE RT MAXIMUM STANDOFF ;-

30- "

i0

' -I0

--o.2 ,, ' ' U --,---. "--._

TIME (MS)

85-..

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

SERIES 2, MODULAR CHARGE/STICK PROP., MODUL.060CHARGE AT MAXIMUM STANDOFF

300'

280'260.

220 -

(- 200/

.- ISO.

(o 160-

Co 120-

O0-

40

20.

o40 4IS 50 6 60 s 70TIME (MS)

SERIES 2. MODULAR CHARGE/STICK PROP., MODUL.060CHARGE AT MAXIMUM STANDOFF

40.

30-

20

"o.

0°

4,1S 0 S 6' 6s 7 0TIME (MS)

84

-_ I

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

SLRIES 2, MODULAR CHARGE/STICK PROP., MODUL.OS9CHARGE AT MAXIMUM STANDOFF

300

jiI. 'I

160-

40-

LL 8

60•

40-1

40 45 so 5 60 6s

TIME (MS)

SERIES 2, MODULAR CHARGE/STICK PROP.. MODUL.059CHARGE AT MAXIMUM STANDOFF

so2-.

" 40.

± 30.

20

L,

IME (M S)F

83 il2

. ... -. ' .- " : " ' . .' .. .'. ... ". " : ." '- " . -' .' . -- .' . - . -. . ' .? - .- . -. .. "- .i .iiS .. ... . . . . . - _" ' • ", , ", " _, " . , ". " ". "... " ', - _ _. " _ - • - . - .2 - -. . ,:

7.0

SERIES 1. MODULAR CHARGE/STICK PROP.. MODUL.079BASELINE SERIES

3806

269-

2606

240-x-

- 226 .

LLJ

cn 120-

40-

2:.

25 3364's ('IS soTIME (MS)

SERIES 1, MODULAR CHARGE/STICK PROP., MODUL.079BASELINE SERIES

4,-

a

L)z

C)

L

2-I,

25 36 54 4'0 0TIME (MIS)

82

7.- ,j 7*--S

. * ** **. . .

SERIES 1, MIODULAR CHARGE/ STICK PROP., MODUL.078BASELINE SERIES3,,-

200-

260-

240-

220 1

CL 200 /

Y') ISO Iuj 140-

S 120-

60-

I0~

0-40s 45 6066

TIME (MS)

SERIES 1. MODULAR CHARGE/ STICK PROP.. MODUL.078BASELINE SERIES

CL 30-

Lii 20-

Ix

L

81

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

SERIES 1. MODULAR CHARGE/STICK PROP., MODUL.077BASELINE SERIES

300

280 -

260-

240-

220 i

160-

6 10

60-

35 4'0 45 6S5 60- TIME (MS)

SERIES 1. MODULAR CHORGE/SUICK PROP., MODUL.077BASELINE SERIES

40

CL 0

LiJ 20-

Ld

LUj

IL

-280

SERIES 11, MODULAR CHPRGE/GRANULAR PROP.. MODUL.D54MAXIMUM STANDOFF/SPME AS BASELINE SERIES

340-

320-

300

280-

260 .

ci: 210-0L

S 220-

200

ISO

S 140-oo 120-C- IL-

80-

sO 5s 6 G's 70 75 80TIME (MS)

SERIES II. MODULAR CHARGE/GRANULAR PROP., MODUL.D54MAXIMUM STANDOFF/SAME AS BASELINE SERIES

190-

Lii 40-

zJJ

ce 20-LAJLL

wl -2'M(C)

-40Li J

Ci, -69

so s5 I' 6'5 o is o

TIME (MS)

79

..... .- -.-.--... ... . .. - "

SERIES 10. MODULAR CHARGE/GRANULAR PROP.. MODUL.D53MODULES SEPARATED/NO SPACERS/SAME AS BASELINE SERIES

266.

266.

8220

cr

20.

las

6 IO-

Li 60"

60'3

26

s o. iil i

49-- -

46 46 Be B5s 66 is is

TIME (MS)

SERIES 10. MODULAR CHARGE/GRANULAR PROP., MODUL.D53MODULES SEPARATED/NO SPACERS/SAME AS BASELINE SERIES

66

a

X8 its-i

3,-wZ 20-

LL

-20-LiiQ - I

CL -3:

40s 45 70TIME (MS)

78

SERIES 10, MODULAR CHARGE/GRANULAR PROP., MODUL.D52MODULES SEPARATED/NO SPACERS/SAME AS BASELINE SERIES

300-

280-

260

240-

220.

O ~200-" 180-

U) 160-Lii

U 120

Lw 100'

0. 80-60 I

'0 l6 0 5s 60 6 70TIME (MS)

SERIES 10, MODULAR CHARGE/GRANULAR PROP., MODUL.D52MODULES SEPARATED/NO SPACERS/SAME AS BASELINE SERIES

CE .

40-

LU 30-

C,

C) -.

z

tLjJ

e 20LU-

(J

LUj

0.. -20-

-30!•-

S 4 6 's o es 60 6 70TIME (MS)

SERIES 9, MODULAR CHIRGE/GRANULAR PROP., MODUL.0L63.8-MM HOLES IN MODULES(SEPARATED BY NC-SPACERS"

399-

280

269"

240 - Forward Chamh-r

229 Pr,?ssur onlv

a 200.

ISO I

L lU IIO0 14 ' I

ci:, I \

Z3

0 /80 I " .120-

Joe-

3S '40 ' 66 56 646 6 s

TIME CMS)

No Spindle Pressure---Therefore no PressureDifferencp could he calculated.

S

76

". . . . .-7 ,

SERIES 9. MODULR CHPRGE/GRPNULPR PROP., MODUL.04513.8-MM HOLES IN MODULES(SEPPRPTED BY'NC-SPPCERS)300-

280-

260-

240-

220-

(n 20

,a 180-

140-

0 0-

60-

z 20-

W -0-

30 35 4'0 45 0s56TIME (MS)

SERES9. ODLP CHRG/GRNUPRPRO..MODL754

3.8-MM HLES INlMdUL" SPRTI B CSPE

SERIES 9. MODULAR CHARGE/GRANULAR PROP., MODUL.044I3.8-MM HOLES IN MODULES(SEPARATED BY-NC-SPACERS)

390-

200-

260-

249-I

- 220-

0- 209-

w 149 I

1 20-

0.0.

40-

20 I

30 35 tie 45 so 66 soTIME (MS)

SERIES 9. MODULAR CHPRGE/GRANULPR PROP., MODUL.04LJ3.8-M HOLES IN MODULES(SEPARPTED BY NC-SPACERS)

E 40-

3,-LUC-)Z 20-

Li.

CA-20

30 36 tie 145 50 5 60

TIME (MS)

74

SERIES 8. MODULAR CHPRGE/GRPNULPR PROP.. MODUL.0435.6-MM HOLES IN MODULES(SEPPRATED BY'NC-SPPCERS)

286

2460-

- 220CE

126

(/)

LL 126 I

Go I

40-

d 20-

6n7 S 988 69

ce

CL

Lii 201LL70es9

TIELMS

w7

SERIES 8. MODULAR CHARGE/GRANULAR PROP., MODUL.0425.6-MM HOLES IN MODULES(SEPARATED BY NC-SPACERS)

299-h280-

269-

2409

220-

CL 299-180-

169-

9e 49

QI)

0

30 is0 45s

TIME (MS)

SERIES S. MODULAR CHARGE/GRANULAR PROP.., MOOUL.0425.6-MM HOLES IN MODULES(SEPARPTED BY'NC-SPACERS)

70

ci:Q_

48-

L 30-

z 29-LUJ

LUJLL

Li

ci -20-

S -30-

Lul c -40-

-50L

30 35 40 45 so ss 6oTIME (MS)

72

I

SERIES 3. MODULAR CHARGE/STICK PROP., MODUL.062MODULES SEPARATED, NO SPACERS

300

260.240-

220,

180.

160-

Id I140-

S 120 I

adj 100-C- 80'

60

Ll

2o

-640 4 0E 0cETIME (MS)

SERIES 3, MODULAR CHARGE/STICK PROP., MODUL.062MODULES SEPARATED, NO SPACERS

so-

40-

20-IL.

I,

a a

10ILL -1O0

t i e 4s s o 6 s

TIME (MS)

86

I' .: .. .-o -..- .. ..-.. -.- .. . ....-- ..- ..l.p. , ..- -- -.. , .. . . .. . .: , - -

SERIES 3. MODULAR CHARGE/STICK PROP., MODUL.063MODULES SEPARATED, NO SPACERS

300-

2140-

12U

( I.. I -

60'

244'"'

643

Y4(1

TIME (MS)

6087

GO

44--

I i"

liii

_____ _____ ____TIME (MS)

. rn* ~. *.* -o

U. -- --.- -- o.4

SERIES 3. MODULAR CHARGE/STICK PROP.. MODUL.064MODULES SEPARATED, NO SPACERS

308

280.

260-

240-/ Q.. .

220-Cl 200 ' .''

0 160'LI

I' 14

60 -10-

40 45 so ss 6o Gs

TIME (MS)

SERIES 3. MODULAR CHARGE/STICK PROP., MODUL.064MODULES SEPARATED, NO SPACERS

40

- oi

-..- 30

20-I I

-30J

-: -Io

TIME (MS)

88

SERIES 4, MODULAR CHARGE/STICK PROP., MODUL.071CARDBOARD SPACERS BETWEEN SEPARATED MODULES300-

26-

240 *CA 200

(Go I9J

60

40

<135 '(0 45 60

TIME (MS)

SERIES q, MODULAR CHARGE/STICK PROP.. MODUL.071CARDBOARD SPACERS BETWEEN SEPARATED MODULES60-

r 50-

- 40

'2 30-I--

Io

(I.' - -

11 IF (Hu.

89

IJ I .. " ,.-.

SERIES 4j, MODULAR CHARGE/STICK PROP., MODUL.072CARDBOARD SPACERS BETWEEN SEPARATED MODULES

2609

200-

v) 160.

J ~ 129 1

69-

;o04

____ TIME (MS)

SERIES '4, MODULAR CHARGE/STICK PROP., MODUL.072CARDBOARD SPACERS BETWEEN SEPARATED MODULES

60-

300

SERIES 4. MODULAR CHARGE/STICK PROP.. MODUL.073CnRDBOARD SPACERS BETWEEN SEPARATED MODULES

280

260-

- 220-

0. 200

100

?:* S1606

TIE MS

30-

Li

TIME (11S)

SERES'4. MDUARCHRGESTCKPRP.,MOUL91

I - .,

SERIES 5, MODULAR CHARGE/STICK PROP., MODUL.065CLASS 1, BLACK POWDER BASEPAD3,

286'

260.

2140

220aCL 200.Is,

LuJ

C 1206

"-" 180.

60 /

22630 is 4a 420 26 TIME (11S).

SERIES 5. MODULAR CHARGE/STICK PROP., MODUL.065CLASS 1. BLACK POWDER BASEPAD

66U

30-Lii

'J 0

243

I S 20 26 30 3 40 46

TiME (MS)

92

SERIES S. MODULAR CHARGE/STICK PROP., MODUL.066CLASS 1. BLACK POWDER BASEPAD

260

240.

220

Ci. 200"

180-

160-

Li,

0 120-

I,1 100"

S 80-

Be-

60

'40 45* SO 5TIME (MS)

SERIES 5. MODULAR CHARGE/STICK PROP., MODUL.066CLASS 1, BLACK POWDER BASEPAD

60

Lii30-

LLUc-lLi 20,

10

204

I,I

20 2is0 3 40 45 5s5TIME (MS).

9.3

93 ..* *.*.... ....---

SERIES 5. MODULAR CHARGE/STICK PROP., MODUL.067CLASS 1. BLACK POWDER BASEPAD

300-

280-

260-

240-

220 /

-~ ISO.I

x_ 140 I

ce 120-

IJ 100-(L 80-

60-

44-

TIME (MS)

SERIES 5. MODULAR CHARGE/STICK PROP., MODUL.067CLASS 1. BLACK POWDER BASEPAD

60

60

C) 30-zLi

I-I-i

IA

P026 3 s '40 4'sSTIME (MS)

94

SERIES S. MODULAR CI-lRGE/STICK PROP.. MODUL-08CLOSS S. BLACK POWDER BPSEPAD

300-

280-

260-

200

?0 /

108

'I. I M (1S

40-

3I0

6 2 263036 11 c

IE (HL1S)

CRIFES 6, MODULAR CHARGE/STICK PROP. , MODUL.069CLASS S. BLACK POWDER BASEPAD

skI0

2uu

ISO.

II

I is io TIME A(MS It

SERIFS 6. MODULAR CRPRGE/STIC( PROP.,' MODUL-069CLA~SS 5. BLACK POWDER BASEPPD

606

SERIES 6, HODULAR CHARGE/STICK PROP., MODUL.070CLASS 5, BLACK POWDER RASEPAD

300

289

260

220-

(I 206

1 146

('6

IL. . .. . 1

., 20 r 3o0 3S

TIME (Hr,)

SLI-ES (. MOuULAR CHARGE/STICK PROP., MODUL.070CLASS 5, BLACK POWDER BASEPAD

I0 I -. PS303s4

f I I 11£97

38"

IL

Ii

' II'

4,' I P0 2. 3 3S '40--

97 -22i

w . -°. . . .. . . . . . . ....:,'-' "- -. . .""""'' '

'; ; '." "" "-- , - "" - "" - - ""' -"-"- " "-" ," - -

SERIES 7, MODULAR CHPRGE/STICK PROP., MODUL e074NO BPSEPAD ON CHARGE

289,

200.

260 .

2U))

1.. 20

10-

(,? 120'

60II -

P-9 190 200 IO

TI1E (IS)

SERIES 7, MODULAR CHARGE/STICI( PROP., MODUL.0741NO BPSEPAD ON CHARGE

401

10I I

"

I I 190 2iO 0

98

. . .

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

SERIES 7. MODULAR CHARGE/STICK PROP., MODUL.075NO BASEPAD ON CHARGE

300

280-

260-

24I0

220

Cl 200-

180

190

IHe-

II PM

:21

P ; 2 ~ 270 2is 280 AS 290 2qs

TIE (MS)

SERIES 7, 11ODULAR CHfARGE/STICK PROP., MODUL.075NO BA.SEPAD ON CHARGE

30

20-

I;fl

10

toI

;-, , ;'F~2, 270 21E 2(0 205 2oo ;5",I I l-i[ (113)

99

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

RD-AR152 654 MULTIZONE MODULAR ARTILLERY PROPELN HRESUIS 2'(U) ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND"D C R RUTH ET AL. FEB 85 BRL-TR-2636 SBI-AD-F300 597

NCASFE / 96 M

1-0 12 _ 5

12-0

11125 14 11116

SERIES 7, MODULAR CHARGE/STICK PROP., MODUL.076NO BASEPAD O,' CHARGE

30

280-

260-

249-

220 '

-20

' ISO-A

E. la.

.- e.,

lip

-- +

TIME (MS)

SERIES 7, MODULAR CHARGE/STICK PROP., MODUL.076NO BASEPAD ON CHARGE

60-I

I-'l

.... 8

111 1 6 170 le2TIME IMS)

100

-(++I

SERIES 8. MODULAR CHARGE/STICK PROP.. MODUL.083CBl B~iSEPAD ON FRONTEND OF MODULE Am.

280-

C,.. :.

~~- .o"

2110-. '-•

, 3110 3115 3S9 355 360 395

TIME (MS)

SERIES 8, MODULAR CHARGE/STICIK PROP.,. MODUL.083CBI BASEPOD ON FRONTEND OF MODULE Am

30

Lii- 20

31S 31031 6 I 6 6

ci

-1101

I -.

3'' 315 "036636

TItlE (MS)

101 L

SERIES 9. MODULAR CHARGE/STICK PROP., MODUL.eeeCSI RrSEPnD flT BACKEND OF EACH MODULE--3 BaSRpfCs

-~220

,

CL PAO-

120*

c.-

24.

SERIE 9,MDLR00G/TIKPO. OU-8

40-)

30-~

20-

25i s'I' 4'G1

TIME (MS)

410

.1 20 . . . .. . . . . . .

SERIES 9, MODULAR CHARGE/STICK PROP.. MODUL.081CBI BASEPAD AT BACKEND OF EACH MODULE--3 BASEPADS

300-

280-

260-

240-

-~ 220-L _ 200 1 -

' 180.

Cr II

e 40-

120

25 30 3,5 '9 45 60 SSTIME (MS) """.

SERIES 9, iMODULAR CHARGE/STICK PROP., MODUI..081 ...:CaI B3SEPAD AT BACKEND OF EACH MODULE-,-3 BASEPA'DS"-..

Oi-

40-.4

303. s

Id 0

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u - -

-20-25 Io is ,0 i's s. "

TIME (MS)

103

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SERIES 9. MODULAR CHARGE/STICK PROP.,. MODUL.082CBI BASEPAD AT BACKEND OF EACH MODULE--3 BASEPADS

300- . . . -

289-

260-

-'.22,

0- 20-lee. I.] .

14 2 0--'-.-

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0 120-

L:J IG@-

LI'

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TIME (MS) 6-

SERIFS 9, MODULAR CHARGE/STICK PROP., MODUL.082C ,-, SEPAD fnl BnCKEND OF EACH MODULE--2 BASEPAI)S

30-

29-C,. e•

10

- 0 7 _+

... " : i

35 is fig sTIME (MS)

104

,l l li~ll mu~t '"'" "0

SERIES 10, MODULAR CHARGE/STICK PROP., MODUL.08qNO ENDCAPS OR FRONTS ON MODULES A. B. AND Am300-

280-

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25 2200 -3'4.so

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TIM (MS)

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SERIE 10 OULR00-ESIK RP.MOU.8

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Li 20

25I' 311 0 i 0 5s

TIME (MS)

SERIES 10, MODULAR CHARGE/STICK PROP.. MODUL.08 u

NO [NDCAPS OR FRONTS ON MODULES A. 8. AND Am li

Q_ 30

hi 20" '

Ii-

()l

.)-(I

TIME (MS)

105

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

SERIES 10, MODULAR CHARGE/STICK PROP., MODUL.08SNO ENDCAPS OR FRONTS ON MODULES A, B, OR ml-"

2R

2' i - ",

-' 220-

r" 200 '. "

toIGO

ti.le. ""

Igo

iV I GO.. 20-

a-

rio 303 i 4 os

TIME (MS)

SERIES 10, MODULAR CHARGE/STICK PROP., MODUL.08SNO ENDCAPS OR FRONTS ON MODULES A, 'B, OR Am

Cr.II.

l

.,J

C I

-j -

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SERIES 11, MODULAR CHARGE/STICK PROP., MODUL.086BUNDLES OF STICK PROP./ NO NC ;-;ODULES/ CBI BnSiD

28O

Z " -.

I kil

r, l - -- -- ---..-- - --rI - -

C-

vs; Rlf 0s 95 9

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SERIES 11, MODULAR CHARGE/STICK PROP.. MODUL.0862~DLFSOF STICK PROP./ NO NC ;-ODULEs/' CBI BflSIZ-i'fD

30 I

?fl

16107

IA 112

g6#

.. I( 7 n 5 90 95 I .o

Title (MS)

107%

SERIES 11. MODULAR CHARGE/STICK PROP.., MODUL.087BUNDLES OF STICK PROP./ NO NC KuDULES/ CBI BASEPAD

300

266-

266-

2'I0-' 220-

0_ 200,

I l" I, -, 169- /:.,-) 120

I. 80.

Ito

20

I5 5 O5 60 65 70 7 80

TIME (MS)

SFRIES 11, MODULAR CHARGE/STICK PROP... MODUL.087L',riOLS OF STICK PROP./ NO NC MODULES/ C81 BAISEPAD

30-

U. 20-lo."

$I t; s4. e Gs i 5 0

IAp

LI - Io

,IS , ' 55. 6'0 65; "9 "75 0o

TIME (MS)1

108:i

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