ITI] FILE COPY

MEMORANDUM REPORT BRL-MR-3840

EXPERIMENTAL STUDY OF FLAMESPREADING PROCESSES

IN 155-MM, XM216 MODULAR PROPELLING CHARGES

L.ELECTE 0JUL 2 5 IS90

CARL R. RUTH( 1 cTHOMAS C. MNOR

JUNE 1990

APMOVED XOR PUBL[C R LFASE, DISTRYBUMTION UNL.frlED.

U.S. ARMY LABORATORY COMMAND

BALLISTIC RESEARCH LABORATORYABERDEEN PROVING GROUND, MARYLAND

iQ 2

UNCLASSIFIED

REPORT DOCUMENTATION PAGEp~~~~~~ewq~~~~~~~ - OWNmmm Na - 1 W n.bSS0 "w1 eiwS .Om 8gg

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Experimental Study of Flamespreading Processes in155-mm, XM216 Modular Propelling Charges P: lM463628D007

AUTNOX(S)

Carl R. Ruth and Thomas C. Minor

7PtRFORMING ORGANIZATION NAME(S) AND AOORESS(ES) I. PERFORMING ORGANIZATION41E1,OR1T NUMOER

9. SPONSORING/ MONITORING AGENCY NAME(S) AND AOORESS(ES) I0. SOSORING / MONITORINGAGENCY R111111011 NUMIER

USA Ballistic Research LaboratoryATT'N: SLCBR-DD-T BRL-NR-3840Aberdeen Proving Ground, MD 21005-56

11. SUPPLEMENTARY NOTES

Ila. DISTRIOUTION/IAVAILABILITY STATEMENT 12b. DISTRIBUTION CO0E

Approved for public release; distribution is unlimited.

L13. ABSTRACT (kfaximum 200 wok)

,-The 155-mm, )34216 is a modular, combustible-cased, stick-propellant charge developed by the Armament Research,Development and Engineering Center (ARDEC3~and recently type classified to provide the Zones 2-4 range coverage for the M198

owitzer should another advanced propulsion option not be fielded. The propellant granulation and casing characteristics of thecharge are unlike those of multiple-increment charges that have been fielded previously by the US Army. Past investigations ofsingle-increment, combustible-cased, stick-propellant configurations which produced ballistic anomalies have indicated a substantialinfluence of particular igniter and charge attributes on ignition and flamespread, and by extrapolation, on the overall interiorballistic cycle. The charge developer, in order to assure that similar problems did not arise with the XM216, requested acharacterization of the early, ignition and flamespread processes of the nearly final configuration charge.

Testing to provide such data was accomplished in~he -Ballitc Research Laboratory's- 155-mm howitzer simulator. Firings wereconducted for all zones at ambient and temperature extremes to characterize ignition transfer, flamespread, propellant-bed mobility,and pressure-wave development during the early portion of the interior ballistic cycle. From these and similar earlier tests,conclusions are drawn regarding the influence of initial charge temperature, ullage, propellant granulation, and charge casing onflamespread processes and the remainder of the ballistic cycle. -~ -

14 SUINCT farm 1. NUNRR OF PAGES

Interior Ballistics, Pressure Waves; Modular Charges; Stick Propellant. 14 40 oo

It. UO*Y CLASWATION It. IrIy CLASIWCATION 13. SCWV CLASSPCA1O 30. UIMITATMO : A$EUCof REPO"T 40O THIS PAGEM OF ABSTRACTI

UNCLASSIFIED UNCLASSIFIED UNCLASSIFIED SAR

7s"1Mmic UNCLASSIFIED Stondaid pfnr Zoe (Rev 249)prwre LliI U'no-lt

Imrer.JomuLy LEFr BLANK.

TABLE OF CONTENTS

Page

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

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

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

II. EXPERIMENTAL TECHNIQUES ............................................. 12

III. RESULTS AND DISCUSSION .............................................. 13

A . Firings at 21 C ................................................ 14

B. Firings at 63 C ................................................ 21

C. Firings at -53 C ............................................... 23

IV . CONCLUSIONS ......................................................... 26

ACKNOWLEDGMENTS ..................................................... 27

REFERENCES .......................................................... 28

DISTRIBUTION LIST ................................................... 29

Acceion For

NTIS CRA&IDTIC TAB 0Unannounced 0Justification

By______A0 Distribution I

'd 4, Avilbility Codes

Avad andorDist Special

3i-I _

3

INUENTIONALLY LEFT BLUNK.

LIST OF ILLUSTRATIONS

Figure Page

1. Schematic of 155-mm, XM216 Propelling Charge ........................ 9

2. Phenomenology, Modular, Combustible-Cased, StickPropelling Charge ............................................... 10

3. 155-mm Howitzer Simulator ........................................... 12

4. Instrumented Projectile Baseplate ................................... 13

5. Breech and Forward Chamber Pressures, XM216 PropellingCharge , 21 °C ................................................... 15

6. Breech and Forward Chamber Pressures, XM216 PropellingCharge , 63 °C ................................................... 16

7. Breech and Forward Chamber Pressures, XM216 Propelling

Charge , -53 °C .................................................. 17

8. Annotated Breech and Forward Chamber Pressures, XM216Propelling Charge, Zone 4, 21 °C, Round 40913 ................... 19

9. Schematic of Flamespread, XM216 Propelling Charge,Zone 4, 21 °C, Round 40913 ...................................... 20

10. Annotated Breech and Forward Chamber Pressures, XM216Propelling Charge, Zone 4, 63 °C, Round 41002 ................... 22

11. Schematic of X-ray, XM216 Propelling Charge, Zone 4,63 °C, Round 41002 .............................................. 22

12. Annotated Breech and Forward Chamber Pressures, XM216Propelling Charge, Zone 4, -53 °C, Round 41017 .................. 24

13. Annotated Breech and Forward Chamber Pressures, XM216Propelling Charge, Zone 4, -53 °C, Round 41018 .................. 25

5

INTENTIONALLY LEFT BLANK.

LIST OF TABLES

Table Page

1. Test Matrix for Firings ............................................. 14

2. Experimental Firing Data ............................................ 18

7

IMrENIONALLY LEFT BUANK.

I. INTRODUCTION

The XM216 Propelling Charge, developed by the Armament Research, Develop-ment, and Engineering Center (ARDEC), was recently type classified to providethe Zones 2-4 range coverage in the 155-mm, M198 Howitzer, but will be pro-duced only if the US Army does not either pursue the universal-incrementcharge for this howitzer or field the Advanced Field Artillery System (AFAS).If produced, the XH216 would become part of the family that includes the alsorecently type-classified, stand-alone, Zone 1, XM215 Propelling Charge and thestandard, top-zone, M203AI Propelling Charge.

A schematic of the XM216 is shown in Figure 1. The charge consists ofindividual modules: Zone 2, Module A; Zone 3, Module A plus one Module B; andZone 4, Module A plus two Module Bs. A basepad consisting of 28 g of CBI witha 20-g black powder spot is placed only on the A Module. The propellant isM31Al slotted-stick propellant, with the webs and lengths of the sticks beingdifferent between the A and B Modules. One of the main advantages of modularcharge configurations is a rigid package consisting of interlockingcomponents, thus facilitating automatic loading in future weapon systems.Furthermore, since the modular charge system will consist of a small number ofdiscrete module types, the propelling charge corresponding to a desired per-formance level can be built up from the increments at firing time, rather thanby discarding bags of propellant as is currently done with multizone artillerycharges, resulting in a propellant and cost savings and a reduced logisticsburden. New processing techniques allow for the use of additives, and theincreased strength of loaded, rigidized combustible cartridge cases, as com-pared to bag charges, minimizes handling and transportation problems.

Let us now examine, with reference to Figure 2, some of the potentialevents in the early portion of the interior ballistic cycle with acombustible-cased, modular propelling charge. The output of a primer impingeson a basepad, and the burning basepad ignites the rear case wall of themodule. Upon burn through of the rear case wall, the rear of the propellantbed is exposed to hot igniter gases and is 'heated to ignition. These hot

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Figure 1. Schematic of 155-mm, XH216 Propelling Charge

9

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__________ ___ Wall-

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Sca*-Module

[~ ~ropEllPopant _____

Figure 2. Phenomenology, Modular, Combustible-Case,Stick Propelling Charge

gases then join those from the igniter to produce flamespread through thecharge. In the situation of granular propellant, resistance to the gas flowmay lead to the formation of a pressure gradient in the propellant bed, andperhaps even movement of the solid phase, as we have previously discussed forbagged granular charges. However, with the use of stick propellant yielding amuch smaller resistance to gas flow, essentially no pressure gradient isformed in the propellant bed, and we would not expect the solid phase toexperience much movement. Yet, even with stick propellant, there will besubstantial resistance to flow of the gases offered by the relatively imper-meable interzone barriers presented by the case end walls, possibly leading tothe propulsion of entire packages of propellant toward the projectile base.Complicating characterization of these phenomena, but perhaps leading tobetter ignition of the charge, the igniter gases may take the path of leastresistance and flow into the annular ullage surrounding the charge, whichalmost certainly will be present in order to facilitate loading. We havenoted such behavior in other combustible-cased charges employing stick propel-lant. 1 In this manner, the case may begin to burn along its entire length,and if the case collapses due to pressurization of the ullage, the propellantbed itself may be exposed to ignition gases along a substantial portion of itsaxial extent, promoting uniform ignition of the charge. Lastly, we cannotoverlook the potential for fracture of the propellant. Such fracture mayoccur not only as a result of impact of a package of propellant on the projec-tile base but also due to attack of an overly brissant igniter on the rear ofthe charge. Furthermore, stick propellant may rupture due to a pressuredifferential established between the interior and exterior of the long grain.All of these processes serve to create additional, unprogrammed burning sur-faces, which may lead to high local pressurization and the formation of pres-sure waves, should the natural flow channels presented by the stick propellantbe obstructed.

1T.C. Minor and A.W. Horst, "Ignition Phenomena in Developmental, Stick-Propellant, Combustible-Cased, 155-mm, M203E2 Propelling Charges," ARBRL-TR-02568, Ballistic Research Laboratory, USA ARRADCOM, Aberdeen Proving Ground,MD, July 1984.

10

Several previous experimental studies also helped to motivate this study.In an earlier test in the BRL 155-mm howitzer simulator with a granular,bagged, multizone charge with a relatively brissant base increment and slow-burning forward increments, it was found that the forward fncrement could bepropelled toward the base of the projectile at a high speed. While the XM216Charge employs stick propellant, as noted above the barriers presented by thecombustible case may present sufficient resistance to gas flow to result inpropulsion of substantial quantities of propellant. In another study, it wasseen that the method of ignition of the charge is often not as intended. Infact, rather than the igniter gases entering the propellant bed as desired,they have been seen to flow into the ullage, sometimes pressurizing it andseverely compressing the case and propellant bed radially. Alteration of theignition system to remove some of the blockages to igniter gas flow maycorrect the magnitude of the problem, but igniter gases still may not easilypenetrate the end of the stick bundle.

Earlier ARDEC testing with a candidate for the XM216 in which the forwardmodules were full of propellant showed the fopmation of pressure waves, whilea candidate that was partially empty did not. Testing of these two configu-rations in the BRL 155-mm Simulator showed that the full load of propellantsupported the the combustible case wall such that it did not collapse duringpressurization of the ullage surrounding the charge, keeping igniter gasesaway from the stick propellant bed. However, the partial propellant loadprovided no support to the combustible case, permitting it to collapse,allowing access of the ignition gases to the stick propellant, thus promotingmore uniform ignition of the propellant bed.

History has shown us that problems with ammunition malfunctions, such asbreech blows, originate in the early, ignition and flamespread portion of theinterior ballistic cycle. The charge developer, ARDEC, naturally wished acomplete characterization of the phenomenology of the charge before completingthe charge development. ARDEC thus requested that the BRL fire a matrix ofthese charges in the simulator to characterize the early portion of theinterior ballistic cycle.

2T.C. Minor, "Characterization of Ignition Systems for Bagged Artillery

Charges," ARBRL-TR-02377, Ballistic Research Laboratory, USA ARRADCOM, Aber-deen Proving Ground, MD, October 1981.

3T.C. Minor and A.W. Horst, "Theoretical and Experimental Investigation ofFlamespreading Processes in Combustible-Cased, Stick Propellant Charges,"BRL-TR-2710, Ballistic Research Laboratory, USA LABCOM, Aberdeen ProvingGround, MD, February, 1986.

4Private communication, R.S. Westley, ARDEC, Dover, NJ.

11

! _ _

II. EXPERIMENTAL TECHNIQUES

Figure 3 depicts the apparatus used at the Ballistic Research Laboratoryto conduct the experimental investigation. The illustration shows the mountwith a clear plastic simulator for the 155-mm chamber in place. Although themount also accepts higher-pressure, filament-wound fiberglass chambers, theplastic chambers were used in this study to a permit better view of the eventstranspiring within. The muzzle end of the chamber was closed by a projectileseated in a section of gun tube machined to the dimensions of the M199 Cannon.The breech end of the cbamber was closed by a spindle similar to the mushroomconfiguration of the M185 Cannon with the centrally venting primer spithole,housing three piezoelectric pressure transducers. An instrumented baseplate(Figur- 4) was attached to the base of the projectile; it permitted two gaspressure, three total force, and two acceleration measurements at the projec-tile base.

Photographic data were recorded with two high-speed, 16-mm cameras. Foreach shot, one camera was mounted with a wide angle lens to record the overallaspects of the event and another used a telephoto lens to allow detailedexamination of the critical base region of the charge. With all of thecameras, data were recorded at a framing rate of approximately 5000 picturesper second. One-kHz timing signals were placed on the films by electroniccircuits internal to the cameras, and the firing fiducial (time at which thefiring voltage is applied to the gun) was also placed on the films to aid incorrelation of the film data with other data.

Flash radiography was used to monitor the behavior of the solid phaseduring the interior ballistic cycle. Two 300-kV X-ray heads were employed,aligned perpendicular to the chamber axis and sufficiently separated from eachother to allow coverage of the entire chamber length. One image (a "static"

Figure 3. 155-mm Howitzer Simulator

12

FORCE (3)

ACCELERATIOi1 (2) "

PRESSURE (2)

X Z)

Figure 4. Instrumented Projectile Baseplate

shot) was taken of the charge in the chamber before firing, and a second, on aseparate film, was recorded during the event by X-rays triggered at a pre-determined spindle pressure (a "dynamic" shot). The X-ray film was protectedfrom the blast of the disposable chamber by a wooden cassette, with theforward face composed of layers of air spaces and sacrificial wooden plates.

III. RESULTS AND DISCUSSION

Test firings were done in the BRL 155-mm howitzer simulator using XM216Charges sent to us by the ARDEC, Dover, NJ. To maximize the amount of infor-mation from the limited number of charges available, firings were done atthree different temperature and zone levels and in the order as indicated inTable 1. The matrix was weighted to provide more data at the upper-zonelevel while at the same time giving some indication of the behavior of thecharge at the lower zones..

The measured maximum breech (spindle) pressure, P1, and forward chamber(projectile base) pressure, P2, the calculated pressure difference (P1 - P2),and the measured maximum charge motion before chamber rupture, from both filmand X-ray records, are listed in Table 2. Also listed are the times whenpertinent events occurred.

13

Table 1. Test Matrix

Charge Zone Temperature Number of(°C) Rounds

XM216 4 21 23 12 1

XM216 4 63 23 12 1

XM216 4 -53 23 12 1

Figures 5, 6, and 7 are plots, respectively, of all the pressure-timetraces for ambient (21 °C), hot (63 °C) and cold (-53 °C) firings at the Zone2 (Module A), the Zone 3 (Modules A and B) and the Zone 4 (Modules A, B, andB) levels. For clarity in discussing module movement in the Zone 4 charge,the Module B closest to the projectile will be referred to as Module B', thusmaking the Zone 4 charge consist of a Module A, B, and B'. In all the plotsof pressure, P1 is a solid line and P2 is a dotted line. In order to betterclarify the events occurring during the ignition and early combustion process,one of the Zone 4 charges fired at 21 C and 63 °C and both of the Zone 4charges fired at -53 °C will be examined in detail. Ignition and combustioncharacteristics of the Zone 3 and 2 will be related to the Zone 4 firings.All times on the plots and events described from film and X-rays are relatedto the same zero time when the firing voltage was applied to the M52A3BIelectric detonating cap. For all firings there was approximately a 1-ms delayfrom the application of firing voltage until the M82 percussion primerfunctioned.

A. Firings at 21 °C

The pressure-time plot of Round 40913, Zone 4, ambient, with detailsobtained from the film record are shown in Figure 8 and Table 2; no X-rayswere obtained for any of the ambient rounds. A schematic of the events takingplace during flamespread is shown in Figure 9. At approximately 1 ms, the M82primer ignited the basepad producing a 0.5-MPa pressure rise lasting for 4 ms.During this time interval, the rear cylindrical section of nitrocellulose (NC)contained within the basecap of Module A and the endcap enclosing the basepadwere distorted (Figure 5). The gray ignition gases from the M82 and basepadpushed the rear of Module A to the top of the chamber breaking the rear topportion of the NC cylinder. Within 2 ms, the rear portion of Module A waswell-ignited with bright orange-red gas covering the rear 3 cm of the chamber.By 8 ms, Module A was fully illuminated with luminous gases advancing forwardinto and around Modules B and B'. The rear upper portion of Module A brokeoff and burned separately. Parts of the Module A were pushed against thewalls of the plastic chamber and continued to burn as the luminous frontadvanced forward into and around Modules B and B'. Within 11 ms, the entireZone 4 charge was well-ignited even though the breech and forward chamberpressures were only 0.5 MPa. As the burning progressed, the forward

14

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Figure 8. Annotated Breech and Forward Chamber Pressures,XM216 Propelling Charge, Zone 4, 21 0C, Round 40913

ullage in the chamber became illuminated (15 ins) as burning gases swirled intothis region. This caused a 0.5-MPa pressure difference to develop from 18 mnsto 25 ms after which the two pressures became coincident until the chamberbroke at approximately 29 ins. During the entire combustion cycle, there wasno indication of large movement of the charge. Just before the slightpressure gradient developed at 18 ins, Modules B and B' moved away slightlyfrom the Module A component. Without X-rays, it was impossible to determineif the movement near chamber breakup was significant. With the exceptionsthat the peak chamber pressure was less and the corresponding event timeshorter for the second Zone 4 shot, Round 40917, the events described aboveaccurately reflect both Zone 4 firings.

The ignition and early combustion for the Zone 3, ambient charge, Round40926, was as described for the Zone 4 round. Primer and basepad ignitiontimes were essentially the same. As the ignition front and early combustiongases proceeded axially into and around the charge, pieces of the NC case werepushed against the chamber wall and proceeded to burn just as in the Zone 4tests. As the gases flowed into the forward ullage, illuminating it withintense white, hot gas, no pressure gradient developed and no indication ofmodule or charge motion was observed. The total event time was longer than for

19

- INITIAL CONDITION, 0 NS

r BASEPAD IGNITION, 1 MS

MODULE A BREAKS AT TOP,i-BASE ULLAGE BRIGHT

yj.[, ORANGE-RED, 3 HS

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i. .'.-9.-MODULES BREAKING.t ~:I4 * 9, 4.INTO PIECES, 1516s

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Figure 9. Schematic of Flamespread, XM216 Propelling Charge,Zone 4, 21 0C, Round 40913

20

the Zone 4 round previously described because, with the reduced density ofloading, hot gases swirling into the larger forward ullage had less propellantand more ambient gas to heat during the combustion process.

For the ambient Zone 2 shot, Round 40927, ignition and early combustionwere the same as the three previously described rounds. At approximately 8ms, a small 0.25-MPa gradient developed corresponding to the charge movingforward 2-4 cm in the chamber. From 12 ms to 17 ms, the pressure tracesindicated no gradient in the chamber. During this time, the charge movedforward approximately 15 cm. By 20 ms, a pressure gradient developed whereinthe forward chamber gage became 0.5 MPa higher than the breech gage. Thiscondition continued until the chamber ruptured. It is possible that thecharge continued to move toward the projectile, but since the film was washedout by intense, white gases and X-rays were not obtained, further chargemovement could not be verified. Since the force gages in the projectile baseshowed only gas response and not propellant impact, the extent of the chargemovement was probably less than the space available in the forward axialullage. The event time was the same as the Zone 3 firing because the chamberruptured at a low 8 MPa rather than at the expected 11-12 MPa.

B. Firings at 63 °C

The pressure-time plots of Round 41002, Zone 4, hot, with detailsobtained both from film and X-ray are shown in Figure 10 and the data in Table2. All four rounds in this series obtained, approximately, the same peakpressure before chamber rupture and X-rays recorded the charge motion justprior to rupture. At I ms, the M82 primer functioned. Within 2 ms, thebasepad was well ignited causing a pressure rise of 0.50 MPa. Unlike theambient rounds, the initial ignition pressure (Figure 10) did not decay tonothing before ignition of the main charge, but only decayed to 0.25 MPa.Then very quickly the pressure increased as the main charge ignited. By 9 ms,Module A was fully ignited and there was intense yellow light in the ullage atthe rear of the charge. During the same time, the breech pressure increasedrapidly from 0.5 MPa at 9 ms to 1 MPa at 12 ms. The ullage between the chargeand projectile became very bright as combustion gases flowed into this region.Ignition proceeded so rapidly that a forward pressure gradient developed assoon as the charge ignited at 5 ms until near chamber rupture at 19 ms. Justprior to chamber rupture, there was no indication of charge motion from thefilm record. By this time, the film was almost completely washed out from thehot combustion gases in the ullage surrounding the charge.

The X-ray was triggered at 8.9 MPa just prior to chamber rupture. Itshowed large axial movement for the propellant and the NC case (Figure 11).The propellant in Module A was propelled forward &n masse through the front ofthe module, thus punching out a disc of NC. As the propellant moved forward,it moved Modules B and B' and their propellant forward as a unit into thechamber 6 cm. Parts of the NC case were visible throughout the chamber.

The ignition and early combustion for both the second Zone 4 charge,Round 41005, and the Zone 3 charge, Round 41004, as observed from the filmswere the same as just described. There was some indication, from the filmrecords, of minimal charge motion for the second Zone 4 round, but none forthe Zone 3 round. X-rays for these two rounds were triggered at 8.9 MPa as inthe previous test. For the Zone 4 firing, the propellant again moved =n massethrough the front of the NC module. Most of the module remained at its

21

41002 ZONE 4I, 63 C

w BASEPAD IGNITION

12-ZZ) MODULE A IGNITION0))DUL A IX-RAY TRIGGERED AT A

0w PRESSURE OF 8.9 MPA

C | BRIGHT YELLOW FLAME AT

" REAR OF MODULE A

ca 9 ZONE 4 IGNITION

6.- FOIWARD AXIAL ULLAGE ILLUMINATED

aU 4

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Figure 10. Annotated Breech and Forward Chamber Pressures,XH216 Propelling Charge, Zone 4, 63 °C, Round 4,1002

Initial Condi!tion, 0 as

II

X-ray taken at 8.9.H a pressure, 18 an

Figure 1 . Schematic of X-ray, X216 Propellng Charge,

Zone 4, 63 °C, Round 41002

22

initial location in the chamber throughout the burning cycle. The force ofthe Module A propellant against Module B completely collapsed the 2-cm spacebetween Modules B and B' and pushed the modules forward 6 cm in the chamber.This was larger than that noted on film; however, the X-ray event occurred ata time after events on film were washed out from the burning gases. The Zone3 charge configuratio, when the X-ray triggered was similar to that of Round41002, except that Module B moved 10 cm instead of 6 cm. In addition, thefront of Module A and the front of Module B were also punched out by the forceof the propellants from Modules A and propellant moving forward. In bothtests, pieces of NC container could be seen throughout the chamber prior torupture.

For Round 41010, Zone 2, hot, ignition and early combustion were similarto that described in the ambient Zone 2 round, albeit at a faster time. At 4ms, the base region was well lit with gases starting to stream into theforward ullage. By 5 ms, the NC case had developed several radial cracks, hotgases were moving axially and radially forward through and around the chargelighting up the forward ullage, and there was some forward movement of NC.Unlike the previous three rounds, there was no pressure gradient. By 5 ms,the spindle and forward pressure gages were coincident which continued untilthe chamber ruptured. At 9 ms charge motion began, with a total movement of 16cm before the chamber broke. One could see the Zone 2 module moving forwardinto the intense white light of the forward ullage. As before, the X-raytriggered at 8.9 MPa, recording the same charge motion as the film. Althoughthe X-ray showed that the propellant moved forward approximately 16 cm, thedetail was such that the condition of the NC module and parts could not bedetermined.

C. FLrings At -53 op

The pressure-time plot from Round 41017, Zone 4, cold, is given in Figure12; other firing data are presented in Table 2. X-rays were not obtainedbecause the chamber ruptured at a very low 6 MPa. At 1 ms, the basepad wasignited and dark smoke could be seen streaming forward along the radial ullageinto the forward axial ullage. By 10 ms, the base region was very bright fromignition of Module A. As burning gases streamed around the charge into theforward ullage, the charge began to move forward at 13 ms. At 27 ms, thecharge was still moving forward with the rear ullage becoming very luminousfrom the hot combustion gases. By 29 ms, the charge was completely forwardagainst the projectile with all the ullage located between the spindle and thecharge. Burning continued in this manner until the chamber ruptured at 38 ms.The forward chamber gage initially was slightly less than breech pressure, butafter the charge moved forward against the projectile at approximately 30 ms,the two pressure gages reversed with the forward chamber gage being higherthan the breech gage.

For the second Zone 4, Round 41018, the initial ignition sequence wascompletely different from any other round in all three series. The pzessure-time plot is shown in Figure 13 with both high-speed film and X-ray eventsindicated. At 2 ms, the spindle pressure rose to 0.25 MPa, indicating thatthe basepad had been ignited, even though the film record showed no smoke orflame present. As the rear of Module A broke circumferentially, it balloonedinto the chamber, channeling all the igniter gases forward through the charge.No ignition gases were visible in the radial ullage. The pressure remainedconstant until 12 ma when it slowly began to increase. The forward chamber

23

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I I.5 3 3 4 0!G 45

10,,TIME (MS)

Figure 12. Annotated Breech and Forward Chamber Pressures,XM216 Propelling Charge, Zone 4, -53 0C, Round 41017

pressure gage showed no response until 16 ms. At 18 ms into the event, flamewas present at the interface of Modules A and B. The flame began to spreadaxially both toward the projectile and the spindle. By 25 ms, when theforward chamber pressure was coincident with breech pressure, all threemodules were burning. At 35 ms, the charge started moving forward into theprojectile base and was still moving at 37 ms when the intense white flamewashed out the film. At 35 ms, the forward chamber pressure-time traceindicated a sharp pressure pulse, suggesting that the charge moved forward athigh velocity. This pulse, which was also noted by the force gage (notshown), damped out rapidly with the two chamber pressure traces beingcoincident before chamber rupture. That the gas-pressure gage respondedsimilarly to the force gage is likely an artifact of the design of the gageblock, in that a column of gas was trapped between the front of the charge andthe recessed gas-pressure gage face. Although the film record of the ignitionsequence appeared to be different from the first, Zone 4, cold firing, neitherthe total event time nor the time to pressurize the chamber to 1 MPa weredifferent. Apparently, the ignition gases from the basepad were transmittedinternally through the Module A component to the interface of Modules A and Bwith propellant burning inside the NC containers hidden from the view of thecamera.

24

41018 ZONE '4. -53 CCECL

X-RAY TRIGGERED AT A

wF BASEPAD IGNITION PRESSURE OF 5.1 10A

2FLAME PRESENT AT MODULE A/B() --INTERFACE

CL ZONE 4 IGNITION I

W8" CIARGE MOVING FORWARD IMPACTING03 ON PROJECTILE BASE CAUSING[

(PRESSURE PULSECK

O 6- CHARGE COMPLETELY FORWARD NINUtACER/ REAR AXIALULLAGECOMPLETELY ILLUMINATED

cr

0IL

C) 2-

Wi 0 S 19 Is 20 30 35 40 Its

co'TIME (MS)

Figure 13. Annotated Breech and Forward Chamber Pressures,

XM216 Propelling Charge, Zone 4, -53 °C, Round 41018

The X-ray for this Zone 4 firing, which was triggered fortuitously at 5MPa when the pressure pulse occurred on the pressure trace, showed substantialcharge motion. Module A propellant was propelled forward through the front ofits NC enclosure with sufficient velocity to push both Modules B and B'forward into the projectile base. The 2-cm spaces at both of -he interfaceswere eliminated, the propellant from Module B' was tightly foi ited around theprojectile base, and propellant from all three modules was axially compressedand radially expanded, so that no radial ullage existed around the forwardportion of the charge. Most of the Module A container remained in itsoriginal location in the chamber.

The Zone 3 firing, Round 41019, was similar to the first cold Zone 4firing in that the chamber broke early at 5 MPa. No film record was obtainedfor the firing. From the pressure-time traces, ignition of the basepadoccurred at 2-3 ms after which both the breech and forward chamber pressuresincreased with minimal difference. By 30 ms, the forward chamber gage startedto show a larger pressure than the breech gage and continued to do so untilthe chamber broke at 47 ms. Just prior to chamber rupture, the X-ray

25

triggered at 5.1 MPa. The X-ray indicated that Module B was propelled forwardby Module A about 7 cm. The charge, burning in the forward section of thechamber, could account for the shift in the pressure traces.

The Zone 2 firing, Round 41016, was similar to the Zone 3 firing. Afterbasepad ignition at 1-3 ms, the two coincident pressure traces remained at alow 0.1 MPa until 15 ms after which they both increased together. At 35 ms,the forward chamber pressure became slightly higher than the breech pressureand remained so until the chamber ruptured. During the 15 ms when thepressure was less than 0.1 MPa, most of the ignition and early charge motionoccurred. At 7 ms, the rear portion of the module holding the basepad wasburning rapidly with an intense flame and the charge was beginning to moveforward. By 10 ms, the charge was well-lit with gases swirling around theradial ullage into the forward portion of the chamber. By 17 ms, the forwardullage was well-lit and the charge was continuing to move forward; thismovement continued until the chamber broke at 65 ms. The X-ray triggered at1.7 MPa, which occurred at about the time when the forward chamber pressurebecame larger than the breech pressure. The X-ray showed that the ModuleA propellant had moved 25 cm forward into the chamber as a mass. Unlike theother rounds, the propellant did not punch through the NC container, leavingthe container in its original position in the chamber. In this firing, the NCcylinder was propelled into the forward section of the chamber well ahead ofthe propellant while parts of the basecap and endcap were left in the rear ofthe chamber.

IV. CONCLUSIONS

Within the constraints of a limited number of firings, -,- have examinedthe effects of conditioning temperature and charge zone levels on theflamespread portion of the interior ballistic cycle in the 155-mm, XM216Charge. To answer tbs question posed by the charge designer, ARDEC, noobvious detrimental effects on the ignition and early combustion processeswere observed for any of the three zones comprising the XM216 Charge at any ofthe three temperatures tested even though there was substantial separationbetween modules and between propellant and case at very low chamber pressures.The observed rapid pressurization and coincident breech and projectile basepressures just prior to chamber rupture suggest no propensity for thedevelopment of large pressure waves later in the ignition cycle. A cautionarynote must be raised however, by the impact of the bundle of stick propellanton the base of the projectile at the cold conditioning temperature. While wesaw no evidence of gross grain breakup in the high-speed films or flash X-rays, the possibility exists that some microscopic damage was imparted to thepropellant, which might result in unprogrammed burning surface, leading tohigher pressures that were beyond the range of the simulator tests performed.

Consistent with earlier tests with combustible-cased, stick propellantcharges, we have seen that ignition and flamespread processes are probably notthose which the charge designer, or even the charge design community, mightexpect. Once again, we have noted the great influence of the relativeimpermeability and mechanical strength of the packaging containers on theflamespreading path. We have noted the preferential flow of igniter gasesinto the ullage surrounding the charge rather than into the charge itself, thelack of well-defined flamespread within the stick propellant bed, and themovement of entire packages of propellant. We should emphasize, however, that

26

not all the resistance to gas entry into the main charge results from thebarrier imposed by the combustible case. While natural flow channels withinthe bundle of sticks offer little resistance to the axial flow of gases,entrance conditions at the end of a stick bundle can provide quite animpediment to the entering gases, as evidenced by the movement of wholeincrements of the stick propellant outside of the modular case. The challengeto the charge design community is to exploit these perhaps non-intuitiveaspects of the flamespread process to produce safe and reliable propellingcharges.

ACKNOWLEDGMENTS

The authors wish to express their gratitude to Mr. Scott Westley, ARDEC,Dover, NJ for supplying the XM216 Propelling Charges used in the tests, toMessrs. J. Bowen, J. Hewitt, and J. Stabile, who conducted the test firingsand recorded the data, and to Mr. A. Koszoru, who prepared artwork for thisreport.

27

REFERENCES

1. T.C. Minor and A.W. Horst, "Ignition Phenomena in Developmental, Stick-Propellant, Combustible-Cased, 155-mm, M203E2 Propelling Charges," ARBRL-TR-02568, Ballistic Research Laboratory, USA ARRADCOM, Aberdeen ProvingGround, MD, July 1984.

2. T.C. Minor, "Characterization of Ignition Systems for Bagged ArtilleryCharges," ARBRL-TR-02377, Ballistic Research Laboratory, USA ARRADCOM,Aberdeen Proving Ground, MD, October 1981.

3. T.C. Minor and A.W. Horst, "Theoretical and Experimental Investigation ofFlamespreading Processes in Combustible-Cased, Stick Propellant Charges,"BRL-TR-2710, Ballistic Research Laboratory, USA LABCOM, Aberdeen ProvingGround, MD, February, 1986.

4. Private communication, R.S. Westley, ARDEC, Dover, NJ.

28

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29

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