TECHNICAL REPORT BRL-TR-2996

B R ... AD-A2O8 104BRL 0

THE EFFECTS OF OBTL -,ATORS ON GUN TUBE WEAR

D. L. KRUCZYNSKIIRVIN C. STOBIE

MAY 1989

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U.S. ARMY LABORATORY COMMAND

BALLISTIC RESEARCH LABORATORYABERDEEN PROVING GROUND, MARYLAND

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Aberdeen Proving Ground, MD 21005-5066

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Picatinny Arsenal, NJ 07806-5000 64693A 1N4646930385 00 0011. TITLE (Include Security Classification)

The Effects of Obturators on Gun Tube Wear12. PERSONAL AUTHOR(S)

David L. Kruczynski and Irvin C. Stobie13a. TYPE OF REPORT I3b. TIME COVERED 14. DATE OF REPORT (Year, Month,Day) 15. PAGE COUNT

Technical Report FROM Dec 87 TO Dec 8816. SUPPLEMENTARY NOTATION

17. COSATI CODES 18. SUBJECT TERMS (Continue an reverse if necessary and identify by block number)

FIELD GROUP SUB-GROUP19 06 - Gun Wear, Obturators, 155-mm Howitzer Wear,

19, ABSTRACT (Continue on reverse if necessary and identify by block number)- Modern US projectiles incorporate plastic obturator bands to reduce the ill effects of high temperature gas escaping from

behind the projectile. Not all NATO countries use obturators on their projectiles. Currently several of these countries areconsidering introducing obturators to their projectile inventory. This study was conducted primarily to assess the effects ofsuch a change on previously quantified ammunition interchangeability and gun wear. Of particular interest are poter:ta!effects on nuclear projectiles.

Instrumentation employed included embedded gun tube wall thermocouples. These thermocouples were located atselected circumferential and axial locations. The axial locations were selected to measure charge temperature input to the guntube wall at locations reflecting various countries' current choices of gun tube condemnation measurement points. Thecircumferential separation of thermocouples allowed continued studies of asymmetric wear effects of stick propellants.

Data comparing US and other NATO propelling charges and projectiles, with and without obturators, are presented andanalyzed. Additional data on asymmetric heating effects of stick propelling charges are examined. .

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22a. NAME OF RESPONSIBLE INDIVIDUAL 22b TELEPHONE (Include Area Code) 22c. OFFICE SYMBOLDavid L. Kruczynski 301) 278-6202 SLCBR-IB-A

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TABLE OF CONTENTS

I. INTRO D UCTIO N ........................................................................................ 1

I1. BAC KG RO U N D ........................................................................................... 1

II1. DESCRIPTION OF MATERIAL, INSTRUMENTATION, AND TECHNIQUES .... 2

A . A m m unition .......................................................................................... 2

B . Test M atrix ........................................................................................... 4

C. Experimental Techniques and Instrumentation ..................................... 5

IV. EXPERIMENTAL RESULTS AND OBSERVATIONS ................................... 7

V. CONCLUSIONS ...................................................................................... 10

ACKNOWLEDGMENTS ................................................................................ 10

REFERENC ES ............................................................................................... 10

Dst"

i I'Ad t

LIST OF FIGURES

Figure 1. Typical Projectile Rotating Band/Obturator ................................ 1

Figure 2. M549 and L15A1 Projectiles ..................................................... 2

Figure 3. M203A1 Propelling Charge ....................................................... 3

Figure 4. L1OA1 Propelling Charge ........................................................... 3

Figure 5. L8A1 Propelling Charge .............................................................. 4

Figure 6. Thermocouple Locations in Gun Tube ....................................... 5

Figure 7. Relative Thermocouple Locations .............................................. 5

Figure 8. Close-Up of Thermocouple Design ............................................ 6

Figure 9. Controlled Load Ramming Device .............................................. 6

Figure 10. Multi-Angle Downbore Photography Acquisition Device ........... 6

Figure 11. Typical Thermocouple Responses ............................................ 7

LIST OF TABLES

Table 1. Test Matrix .................................................................................... 4

Table 2. Pressure-1ime and Velocity Data ................................................... 7

Table 3. Effect of Obturators at 41.75 Inches from RFT .............................. 8

Table 4. Effect of Obturator at 42.10 Inches from RFT ................................ 8

Table 5. Relative Thermocouple Depths ..................................................... 9

Table 6. Effect of Obturators at 42.60 Inches from RFT ............................. 9

Table 7. Asymmetric Tube Heating ............................................................ 9

I. INTRODUcMION

Considerable effort has been expended by the US to qualify 155-mm NATOmunitions and howitzers in terms of compatibility with US conventional and nuclearmunitions. Recently it has become apparent that some NATO countries are consideringadopting the use of obturator bands on their projectiles. Concern exists that this modifica-tion could significant:y alter previously determined parameters, primarily gun tube wear lifepredictions.

This study was initiated to address this issue by making experimental measure-ments of heat input imparted to a 155-mm howitzer when firing various combinations ofUS and NATO munitions with and without obturators. The data were then analyzed in aneffort to predict potential consequences to the system from the addition of the obturator.Additional analysis of this data allowed comparisons of the propelling charges employedin terms of total heat input and potential for producing asymmetric tube heating .

II. BACKGROUND

Obturators serve as a backup tothe copper rotating band in retainingpropulsive gases behind the projectile.Figure 1 depicts a typical rotatingband/obturator configuration. While thecopper rotating band is retained on theprojectile throughout its flight, the plasticobturator is designed to fragment uponmuzzle exit, thereby reducing drag onthe projectile. This characteristic has inthe past made its use unacceptable tosome countries. It was felt that these Figure 1. Typical Projectile Rotatingexpelled obturator pieces could present Band/Obturatora hazard to personnel near the howitzer.Recently it became apparent that some NATO countries are now considering the use ofobturators to extend gun tube life. Since obturators are easily installed on existingprojectiles, this change could affect current and future foreign ammunition inventories.

In theory, the contribution of the obturator in sealing of propulsion gases behindthe projectile increases as the gun tube wear increases. This results from the ability of thepliable band to flex radially when loaded from behind by propulsive gases. Thus unlike thestiffer copper rotating band which is primarily designed to spin up the projectile in rifledtubes, the obturator can conform more efficiently to irregular and highly worn tubes whererifling lands may be worn or nonexistent. Ideally then, obturator performance would bestbe measured in a worn tube. For this study, a worn tube which could be modified for

thermocouple instrumentation was not available. A relatively new (88 rounds) 155-mm,M199 gun tube instrumented from previous gun wear studies ' was available. It was feltby the authors that if slight changes in heat input could be detected with and withoutobturators in this new tube, the effects in a highly worn gun tube could be assumed to begreatly magnified.

III. DESCRIPTION OF MATERIAL, INSTRUMENTATION, AND

TECHNIQUES

A. Ammunition

The projectiles used in this study were the US M549 and the UK L15A1. Theseprojectiles are compared and contrasted in Figure 2. Note the lack of a rocket assist in theL15A1 projectile. The other difference of particular interest isthe lack of an obturator on the L15A1. Figure 2. M549 (Left)

The propelling charges employed in the study were the and Li5A1 Projectiles

US and UK top zone charges, the M203A1 and the L10A1(charge 3) respectively. In addition, the UK L8A1 (charge 2) wasalso fired. The two UK charges were employed because theywere the primary charges used during US testing of the UK FH70 5howitzer. The US M203A1 charge was used since it is the roughequivalent of the Li 0Ai. These charges are shown in Figures 3through 5.

A

CHARGE, PROPELLIN'G, 155MM, M203A1(TC-STD)

(COMMENCE PRODUCTION FY86)

COMBUSTIBLE CARTRIDGE CASE18% TALC WEAR REDUCING ADDiTIVEi

07 OZ BLACK POWDER CLASS 3

I OZ Cal

- (DECOPPERING AGENTI

28 LBS. STICK PROPELLANTM31AlE1 SLOTTED. OUOWEB

625 IN MAX

CLOTH IGNITER BASE PAD

COMBUSTIBLE END CAP 3 T.ACMC

OCTOBER 9MSWICAR Aff SP

Figure 3. M203A1 Propelling Charge

CHARGE PROPELLING155mm HOW CARTRIDGE 3 CHARGES

Figure 4. L1OA1 Propelling Charge

3

0*41 PFfloptluNG -

IGNITER L20 AlGunpowder G20 18grammes,propellant NC1 200 809ramrnes

CHARGE PROPELLING155mm HOW CARTRIDGE 2 CHARGE 3-7

Figure 5. L8A1 Propelling Charge

B. Test Matrix

The basic consideration in the test matrix was to investigate as many variations ofobturator/charge/projectile interplay as feasible. To ensure test uniformity all obturatorswere first removed. New standard obturatorswere then emplaced on both M549 (normal Table 1. Test Matrixcondition) and L15A1 projectiles (test condi-tion). A separate group of both projectiles PmJaJm Charg Obltuoiwas left unbanded. In addition, a third groupof M549 projectiles was banded with double M549 M203A1 StandardM54g M203A1 Nonewidth obturators. Limited testing of these M549 M203A1 WideM549 L10A1 Standarddouble width bands had in the past indicated M549 LOA1 Standardthat these bands had a propensity to extend L15At M203A1 Standard

Li 5A1 M203A1 Nonesatisfactory system performance in highly L15AI M20A1 NoneL15A1 L10A1 Standardworn tubes beyond that seen with the standard L15A1 L10A1 NoneLSA1 L8A1 Standardwidth band. L15A1 L8A1 None

roup consisted of five rounds (total 55 rounds),Table 1 details the test matrix. taard obturator is 549AI obturator.

4

C. Experimental Techniques and Instrumentation

The primary instrumentation used to evaluate wear propensities was ther-mocouples embedded in the gun tube wall. These thermocouples were installed at fouraxially separated locations near the origin of rifling in a US 155-mm, M199 gun tube. Thethermocouple locations are detailed in Figure 6. Except for the furthermost downbore

gage, each axially location

60.00 INCHES TOP OF TUBE had at least two circum-41.75 INCHES -1/16 INCH ferentially separated ther-

0.060 INCMI Diameter mocouples, one at the top___ N and one at the bottom of

the gun tube. The fourthgage position containedonly one thermocouple at

0.oe J INC _i_...'/Ie INCH the top, while the first axial-42.10 INCHES Diameter ly location had additional

42.60 INCHES BOTTOM OF TUBE thermocouples in both sidewalls of the gun tube.

Thermocouples at top, sides, & bottom of tube at 41.75 inches from RFT.Thermocouples at top and bottom only at 42.10 and 42.60 inches from RFT.Thermocouple at top only at 60.00 inches from RFT. The axial ther-

mocouple locations wereFigure 6. Thermocouple Locations in Gun Tube chosen for the following

reasons. The first set fromthe breech was located at the point in the origin of rifling currently used by the US to makefield measurements (pullovers) of remaining tube life. The third set represented a cor-responding field condemnation measurement point used in the UK. The second set waslocated approximately midway between these sets. This midpoint location has beendiscussed as a possible unified measurement position. The fourth thermocouple waslocated where granular propellants have historically produced high secondary wear in thegun tube. Since only stick propellants were used in this study, this position is not one ofprimary interest. The relationship of these thermocouple positions to a seated projectile(M549) are shown in Figure 7.

42.60"42.10" r Distance from Rear

41.75" Face of Tube RFT

40.79" 1_

Also a thermocouple @ 60.001 Inches RIFT (Top Only)

Figure 7. Relative Thermocouple Locations

5

-UFRN,1,CO1PLE TJN 1 ,AI -11N The actual thermocouple design isshown in Figure 8. The thermocouple junc-

CCoa,,'s,,7,o--,--F tion formed is called a gun tube steel-con-p ac O,= go Weld-cOicor (75 Vol,,,0 MFD) stantan thermocouple and has been shown

un 06 to be reliable for near surface(gun tube wall)

lato Tocutemperature measurements. A calibrationInslaI¢ Therr cuple Hole

N 1/6 ,,,i D,, factor of 19.232 degrees C per millivolt out-oOo.rre, D , glance put was used for all thermocouples.

/ From inside Tube

In addition to the thermocouples,Figure 8. Close-Up of Thermocouple chamber pressure versus time data were

obtained using Kistler 607 gages located atthe front and rear of the gun tube chamber. Projectile ramming forces were keptcomparable, round to round, through the use of a projectile ramming device whichtranslates an applied torque load to a axial ramming force. This device is shown in Figure9. Observations of inbore obturator sealing were made through the use of a Multi AngleDownbore Photography Acquisi-tion Device (MAD-PAD). This in-house designed device allows "extreme close-up downborephotography at any gun eleva-tion. This device is shown in Fig-ure 10. In operation, a highspeed camera located behind orto the side of the weapon isequipped with a telephoto lensfocused on a mirror held by the Figure 9. Controlled Load Ramming DeviceMAD-PAD. With proper adjust-ment of the mirror, which canpivot on two axes, the camera "looks" directly downbore. Projectile muzzle velocities wereobtained with standard doppler radar techniques.

4

_ . ' ,.

' . -- ; r , , _

Figure 10. Multi-Angle Downbore Photography Acquistion Device

6

IV. EXPERIMENTAL RESULTS AND OBSERVATIONS

Pressure-time and velocity data are summarized in Table 2.

Note from Table 2 that Table 2. Pressure-Time and Velocity Datawith the exception of the last

two groups, there was a slight PrmWt veoaty,

increase in pressure and Si d,,m dwt,,,

velocity as the obturator band pmvmule CbarV Obturator (PressiveI) (MPa) _l

is added or enlarged. As will Mi M , sT W4i, =4.2 a21/1.0

be seen, this correlated well M54 WOW NONE 5 351/3.4 819/2.2

with temperature increases M549 M4203AI WDE 5/5 35712A 822/25

measured. M549 L,,A, sM 5/5 338.3 27/2.9

M549 LMA1 ST 4/5 330/3.1 883/.9

L1S 1 M21,3.i ST) 5/5 35 1 821/3.4

Downbore camera L15AI M203A1 NONE 5/5 356/3.7 821/3.4

L15AI L10AI 570 5/5 344/2.3 832/1.3

data showed no visually dis- L15AI L10AI NONE 45 3"12 8331.9

cernible difference in projec- LISA, La I 5/5 334/12 8212 5

tile obturation. These data L15AI LAI NONE 5/ 3353 4/0.8

were not surprising sinceblowby probably would not have been apparent until the gun tube was highly worn.

Before analyzing temperature data, all pressure time curves were examined toensure that for the various conditions tested the basic pressure profiles and resultantenergy release conditions were basically uniform and comparable round to round. Peaktemperatures recorded at each thermocouple location were then used for comparativeanalysis. Typical temperature profiles are shown in Figure 11.

ISOl

,40

TIA - Top @ 4L75 inches RFT

T1B-Rgbt ide @41.75 inces FT 1 20TIC - Bottom @ 4L75 inces RFT

TID - LeftSde @ 4L75 inches RIFT

TZA- Top @ 42.10mnchesRFT 100

TB - Bottom @42. 10 incbes RFT

TIA- Top @ 42.60 inChes RFT 90 -

T1B - Bottom @42.160 inches RETT4- Top @ 60100 incte RFT 6 -

40

Temprature ?2

(Degrees C) 0

3.aI 10S. am 2ee. am .0040O

TIME (m=)

Figure 11. Typical Thermocouple Responses

7

Table 3. Effect of Obturators at 41.75 Temperature data did show slight dis-Inches from RFT cernible trends. Table 3 shows the effects of

adding or removing obturators as measuredObturator Effects at 41.75 inches from RFT. Although some

Temperature Rise Degree. C differences are within the standard deviations

Projectlile/ With Without With of the data, all firings show increased peakCharge Obturator Obturator Wide temperature without obturators. The US

Obturator charge in particular, shows this effect. As

M5_______ "38 1 13 mentioned previously this temperature riseM540.IOAl 12 should be much more pronounced in a wornML55AJA1 131 tube as the obturator may not fully compen-L15A1/M2OAl 1325 148 ______

L15A1,L1OA1 1652 i sate for the additional propelling gas sealingL,5,,8, 12t t22 required. Note also that under these newPe" tempratures mmurd fa top of tube, 41.75 I fhtso RFT.Standard de.raions wy from 2 to4 degr s. tube conditions, the wider obturator appears

to have no significant further temperaturereduction effect.

Table 4 presents data from the second thermocouple position. Note that whilethese numbers are lower in magnitude, the same increases in temperature withoutobturators as seen at the first thermocoupleposition are apparent with the exception of Table 4. Effect of Obturator at 42.10the lower zone L8A1 charge firings. It is Inches from RFTprobable that the lower gas volumesproduced by this charge produce much more Obturator Effectssubtle changes in temperature effects which Temperature Ris Degrees Care not detectable in this new gun tube.

Projectile/ With Without WideCharge Obturator Obturator Obturator

The overall much lower temperaturesat the second measurement position were w4wm1 74 7 74

not expected since all thermocouples were o7 f

within one inch of each other axially. It was ,1,,IoMI 72 8,

theorized that the significantly lower tempera- L15AI- LoA 85 87 --

ture magnitudes at the second (and third) L15AIAA1 0 3Peak tempesatures nmesud at top of tube at 42.10 inches from FT.

measurement positions were mostly artifacts Stdwod ve.f 2 to,.4

of different gage distances from the innerland surface. Although great care was takenin the drilling of these gage holes (including through tube wall pilot holes), some variabilitydue to machining, differences in tube wall thickness, and differences in inbore surfaceremoval made exact depth matching impossible. Post test measurements of relativethermocouple depths were taken and are shown in Table 5. Note that these measure-ments support this assumption. Using the measured relative thermocouple depths themeasured peak temperature values at the second and third thermocouple positions couldbe corrected to simular depth temperature values using standard heat transfer equations.It is not the intention of this paper, however, to compare axial positions to each other, butto use each axial position as a discrete measurement position and examine the changesat each position as a function of the charge/projectile/obturator combination.

Table 6 presents data fromTable 5. Relative Thermocouple Depths (Inches) the third thermocouple position,

Thermocouple location From Face of Tube where the same general trends41 75 Inches 42.10 Inches 42MInch.s described above are seen. All ther-

Top Bottom ToP Bottom T

op Bottom mocouple positions show greatlyincreased tube heating when the

.0625 .0625 .0980 .0824 .0940 .0755 UK L10A1 charge is fired, which isindicative of its use of higher flame

Thermocoup e set a141.75 Inches is the baseline thermocouple. Th temperature propellant formula-indiceated deph at is positlon Is assumed as a bas line as there is no

absolute depth checking mechanism available. T oope tions. Note also the expected dropdepths ar measured relative to this baseline., in tube temperature with the lower

zone L8A1 charge.

For brevity, only the top thermocouple positions have been used so far forcomparative purposes. The data from the bottom and side gages yield basically the sameobservations. One interesting use for the bot-tom gages, however, is to again look at the Table 6. Effect of Obturators at 42.60uneven heat distribution produced by stick Inches from RFTpropelling charges 1 2 . The first thermocoupleposition is used in an asymmetric heatinganalysis. This set of thermocouples is best Obturator Effectssuited for these measurements as it has been Temperature Rise Degrees C

calibrated with the gun tube inverted 180 Procile With Without With

degrees to distinguish thermocouple depth /Charge Obturator Obturator WideObturator

differences at the top and bottom of the guntube. M54/1.1 7? 1

M549/AMI1 7 _

M15A1_1_423.A1 as715Table 7 shows data for the ther- L___1L__A_ _ ,9mocouple temperature difference (top minus LISIAAA1 M

bottom thermocouple peak temperatures) eperureaset-opbe ,42.00 Inches from -r.

for all charge projectile combinations used in

this study. Note that while the effect of ob-turators on this phenomenon is unclear,

Table 7. Asymmetric Tube Heating there in conclusive evidence that the stickasymmetric wear propensity is evident for all

Temperature Difference the charges tested including the lower zoneTop minus bottom thermocoupepeak temperaur

Projectile/ With Without L8A1.Charge Obturator Obturator

M549/M203AI 3A I

M549/I10A1 48

M54G/tEA1 24

LI5A1/M203A1 30 45

LI5AIIOA1 43 45

L1SAI/.BAI 28 26

Temperatures taken 41.75 inches from RFT.Standard deviations vary from 2 to 4 degrees.

9

V. CONCLUSIONS

The following conclusions are drawn:

" Small decreases in heat input to the gun can be seen when obturators are added tothe projectile even in a new gun tube. Thus addition of obturators to some projectileinventories should extend useful gun life.

" The ability of the obturator to reduce gun tube wear may be less pronounced inlower zone propelling charges.

" Asymmetric wear effects arepresent in both top and lowerzone stick chargefiringsregardless of changes in other ammunition components such as projectile orobturator

ACKNOWLEDGMENTS

The authors wish to thank Mr. Kok Chung and the Nuclear Projectile Branch at theUS Army Armament Research Development and Engineering Center for their interest,support, and insight into this study. Also acknowledged are Mr. Joe Colburn of BRL forhis invaluable assistance in advanced data acquisition techniques and Mr. Jim Bowen andJohn Hewitt of BRL for their excellent experimentation support.

REFERENCES

1. D. L. Kruczynski and I.C. Stobie, "Parameters Involved in Asymmetric Gun TubeWear," 2 3 rd JANNAF Combustion Meeting, CPIA Publication 457, Volume II, pp. 287-297,October 1986.

2. D. L. Kruczynski, I.C. Stobie, and M. B. Krummerich "Gun Tube/Charge/ProjectileInteractions and Gun Tube Wear," 24 th JANNAF Combustion Meeting, CPIA Publication476, Volume III, pp. 121-131, October 1987.

3. T. L. Brosseau, "An Experimental Method for Accurately Determining theTemperature Distribution and Heat Transferred in Gun Barrels," BRL Report 1740, BallisticResearch Laboratory, Aberdeen Proving Ground, MD, September 1974.

4. David L. Kruczynski, "Final Report of Product Improvement Test of 155-mmPropelling Charge M203E2," Report No. USACSTA-6329, USA Combat Systems TestActivity, Aberdeen Proving Ground, MD, January 1986.

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