BRL-MR-3838
MEMORANDUM REPORT BRL-MR-3838
BRLNCOMPARISON OF 155-MM GUN TUBE HEAT INPUT
WITH SOLVENTLESS AND SOLVENT PROPELLANT
ARTHUR A. KOSZORUIRVIN C. STOBIE
JUNE 1990 J 2&i990
APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLLMITED.
U.S. ARMY LABORATORY COMMAND
BALLISTIC RESEARCH LABORATORYABERDEEN PROVING GROUND, MARYLAND
90 06 28 023
NOTICES
Destroy this report when it is no longer needed. DO NOT return it to the originator.
Additional copies of this report may be obtained from the National Technical Information Service,U.S. Department of Commerce, 5285 Port Royal Road, Springfield, VA 22161.
The findings of this report are not to be construed as an official Department of the Army position,unless so designated by other authorized documents.
The use of trade names or manufacturers' names in this report does not constitute indorsement ofany commercial product.
UNCLASSIFIED
REPORT DOCUMENTATION PAGEJ_______,~~gb~~f~ ~ ~i~ @ n~lmt . m.tS U Ud M'~ .d~ .~i~ wIwg OWgu~ of
1. AGENCY USE ONLY CL&W hilri) I2. 4111041T DATE 1*REPORT TYPE AND DATE$ OEEI June 1990 IFendl -len R- 87
.TTU AND SUITITU S. FUNDING is I~RS
Comparison of 155-mm G;un Tube Heat Input with P: IL162618AH80Solventless and Solvent Propellant
6. AUTHOR(S)
Arthur A. Koszoru and Irvin C. Stobie
7. PERFORMING ORGANIZATION NAME(S) AND ADORESS(ES) B. PERFORMING ORGANIZATIONREPORT NUMMER
9. SPONSORING I MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSORING 'MONIORINGUISA Ballistic Research Laboratorv AGENCY REPOT MUMMER
ATTN: SLCBR-DD-TBR- -3 8Aberdeen Proving GIround. MD 2 0W5-5066
11. SUPKIEMENTARY NOTES
I 2a. DISTRIBUTION / AVAILABILIT'Y STATEMENT 12b. DISTRIBUTION CODE
Appronced for public reledse, distribution is unlimited.
13. AM)ILACT (Maximum 200 wod)A test to measure wall temperatures of a 155-mm howitzer cannon was conducted at the Ballistic
Research Laboratory as part of a Product Improvement Program (PIP) which was formulated and conductedunder the auspices of the Armament Research, Development, and Engineering Center. The main objective ofthis ballistic study was to determine if the projected gun tube wear from an alternative, ballistically equivalent.155-mm, M203AI propelling charge containing solventless stick propellant is comparable to the wearproduced by the standard M203A1 containing M3IA1E1 solvent based propellant. The results of this studyindicate that the solventless propellant charge does not appear to be more erosive thanl the standard M203AIcharge. Additionally, the effects of several of the charge constituents on the amount of heat transferred to thetube were investigated, with a particularly dramatic increase seen in heat transferred to the tube when thecase was removed.)
14L SUBJECT TERAMS IL NUMMER OF PAGES
7 71155-mm; M199 Cannon, (jun Wear; Solventless Propellant (XM41), M203AI, Heait FI W mc ootInput; Erosiun f)'
17. SICJRIIY CLASSWICATIO 18. SECURITY CLASSICKAWN It. WNCW~t a.ASSON44CATON n0. : IATIOM OF ABSTRACTOF REPOR4T I Of THIS PAGE 1 OF ABISTRACT
UNCLASSIFIED IUNCLASSIFIED UNCLASSI FlED SARMSN 75404-1604500 UNCLASSIFIED Standard For 298 (111t 2-49)
fowe ow I lm% fig. II
INTENTIoNALLY LFT BLANK.
TABLE OF CONTENTS
Page
LIST O F FIG U R ES .................................................................................................................. v
I. INTRODUCTION ..................................................... 1
II. EXPERIMENTAL .....................................................
A. TEST MATRIX ....................................................
B. TEST FIRINGS .................................................... 4
III. RESULTS ....................................................... 5
IV. CONCLUSIONS ....................................................... 8
R E FE R E N C ES ......................................................................................................................... 10
ACKNOWLEDGEMENTS .............................................. 10
APPENDIX A - PROPELLANT DESCRIPTION SHEETS ........................................... 11
APPENDIX B - PRESSURE TIME CURVES .................................................................. 15
D ISTR IBU TIO N LIST ............................................................................................................ 63
* ~~~O Inr~ r.l I
'i/or
iii
INTNimoNALLY LEFr BLANK.
iv
LIST OF FIGURES
Fur Page
1 155-mm, M 203A 1 Propelling Charge ............................................................................ 2
2 155-mm, M203A1 Solvenfless PIP Propelling Charge .................................................. 3
3 Gage and Thermocouple Schematic ................................................................................ 4
4 Breech Pressure and Pressure Difference, Standard M203A1 ................. 6
5 Breech Pressure and Pressure Difference, Solventless M203A1 ................................ 6
6 Temperature Changes at Thermocouple Locations 1-4 ...................... 8
v
IMNTNONALLY LEFT' BUANK.
1. INTRODUCTION
The M203A1, shown in Figure 1, is a 155-mm, single increment, top zone propelling charge. Thecharge contains approximately 11.79 kg of M31A1E1 triple base, slotted single perforated stick propellantand a lead foil/wax/TiO2 liner which acts as a decoppering agent and wear reducing additive. Thepropellant and liner are contained An a rigid nitrocellulose combustible case which contains talc in itscomposition for wear reduction purposes. Ignition is accomplished with a CBI/black powder basepad heldin place by a combustible end cap. The M203A1 propelling charge was type classified on 29 March 1985to replace the granular M203 (bag) propelling charge. A PIP is currently being conducted on this 155-mm, stick propelling charge by the Armament Research, Development, and Engineering Center(ARDEC). This PIP would provide an alternate solventless stick propellant for the M203A1 propellingcharge. An ARDEC-developed solventless propellant, XM41, was selected as the candidate for the PIP,which will complete full scale evaluation and result in type classification of the alternative propellant in theM203A1 configuration. The charge expected to result from this PIP is shown in Figure 2.
ARDEC initiated several investigations to determine the applicability of solventless propellants to theM203A1 charge configuration and performance level. Such a charge, manufactured at currently under-utilized facilities, would significantly contribute to the number of charges available to support mobilizationrequirements. Additionally, solventless propellants retain their extruded dimensions with less distortionthan solvent propellants, leading to better physical uniformity, thus reducing the labor and cost of blendingpropellants to obtain the required ballistic uniformity. ARDEC-sponsored investigations includepropellant producibility, ballistic acceptability, safety and other charge design related areas. As part of thisseries of investigations, ARDEC requested that the Ballistic Research Laboratory (BRL) examine theeffect on wear of the substitution of the solventless propellant for the standard M31A1E1 propellant.
In the BRL portion of the evaluation of the M203A1 solventless stick propelling charge, gun tube walltemperatures were measured to determine if the heat input into the cannon with this charge wascomparable to that with the 155-mm, M203A1, stick propelling charge. From previous ballistic data, it wasdetermined that eliminating the combustible case i and duitlive liner io'wers pressure but increases theheat input into the cannon near the origin of rifling, thus increasing wear and erosion. Utilizing thisinformation, possible charge variations were developed to examine the effect of several charge componentson the heat transferred to the gun tube.
11. EXPEkIMENTAL
A charge test matrix was developed by ARDEC and BRL to compare heat input from a solventlesscharge with similar components to that from a standard M203A1 charge. Further, an attempt was madeto determine what effect the addition of flash-reducing agents and the removal of the wear-reducing lineror combustible case would have on the heat input to the gun wall.
A. Test Matrix
The ballistic test consisted of fourteen, control, M203A1, solvent stick propelling charges, LotIND85M738-1B-3 and twenty eight, experimental, M203A1, solventless stick propelling charges. ARDEC-
1
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39
developed XM41, solventless, slotted stick propellant, Lot RAD-PD-736-8C was used in all the solventlessexperimental charges. PXR6325 projectiles, Lot 1OP86D002S067, were used with both the solventless andsolvent charges. All charges were conditioned at twenty one degrees Celsius for twenty four hours prior tofiring.
The solventless charges were subdivided into five sets, consisting of the following components:
1. Variation 1. Seven charges contained 11.39 kg of solventless propellant, a combustible case,
basepad, and TiO2/wax liner.
2. Variation 2. Seven charges contained 11.39 kg of solventless propellant, a combustible case, and
basepad.
3. Variation 3. Six charges contained 11.39 kg of solventless propellant, a combustible case, basepad,TiO 2/wax liner, and a 0.113-kg KNO 3 flash reducer.
4. Variation 4. Seven charges contained 11.39 kg of solventless propellant, a combustible case,
basepad, TiO2/wax liner, and a 0.113-kg K2SO, flash reducer.
5. Variation 5. One charge contained 11.39 kg of solventless propellant and a basepad.
B. Test Firings
The gun fuings were conducted at the Ballistic Research Laboratory's Sandy Point Firing Facility (R-18), in a 155-mm, M199 cannon, serial no. 32000. The M199 cannon was modified to accept two Kistler
607C4 piezoelectric pressure transducers and five thermocouples. Chamber pressure measurements weremade by modifying the M199 cannon's spindle to accept one pressure transducer and machining a
thrcaded port 904.2 mm from the rear face of the tube (RFT) at the 12 o'clock position to accommodatethe second pressure transducer in the tube sidewall. A schematic showing the gage anA thermocouplelocations is given in Figure 3.
FOUR THE RMOCOUPLES 900 APART MOUNTED NEARORIGIIN OF RIFLING, .060 INCH FROM INSIDE LAND
PRESSURE GAGESONE AT PROJECIILE BASE.
ONE IN BREECH
Figure 3: Gage and Thermocouple Schematic
4
To obtain the heat input measurements, holes were drilled in the gun tube sidewall at the desired
thermocouple locations to a depth at 1.59 mm from the bore surface. Constantan wires 0.13 mm indiameter were welded to the bottoms6 of the holes using a capacitive discharge technique to formconstantan-gun steel thermocouples near the bore surface. Four thermocouples were located at 3, 6, 9,and 12 o'clock positions at a distance of 1060 mm from the RFT at the origin of rifling. An additionaldownbore thermocouple was located at 12 o'clock at 1524 mm from the RFT. This technique was initiallydeveloped by Brosseau3 to measure wall temperatures in 37-mm guns. The technique was modified forthis M199 cannon to determine the extent of asymmetric heating in a 155-mm howitzer.4 The asymmetricheating study provided a reasonable data base for the evaluation of solventless heating.
A calibration factor of 52 microvolts per degree Kelvin was used to compare known voltage calibrationsteps to the response of the thermocouples. The maximum temperature change for each thermocouplewas noted for each round. The heating effects of the various rounds in this study, as well as in Reference4, were expressed in the maximum temperature change. The maximum temperature change at each
thermocouple is a reasonable measure of heat input from the various charges since all the rounds hadsimilar maximum pressures and pressure durations. Given the pressure similarities, the assumption wasmade that the heat input took place in the same amount of time for all of the rounds.
A 15-GHz continuous wave doppler radar and discriminator were used to obtain on-line velocity/timerecords.
The maximum breech and forward pressures, differential pressure, projectile velocity and change intemperatures were recorded and reduced by the Ballistic Data Acquisition System (BALDAS) under thecontrol of a PDP 11/45 minicomputer.
III. RESULTS
The maximum pressures, muzzle velocities and sample sizes for all the firings are summarized in Table1. The maximum temperature changes for the thermocouples at three positions at the origin of rifling aresummarized in Table 2. The two other thermocople positions - origin of rifling at 9 o'clock and downbore- are not included due to the failure of the thermocouple junction at these positions for most of therounds.
5
Variation 1 was the substitution of solventless propellant for the standard M31AIE1 slick propcllant.Breech pressure-time and pressure difference (forward - rear gages) plots are given for the standardM203A1 and the solventless propellant M203A1 in Figures 4 and 5 respectively. A complete record of thepressure-time curves and thermocouple plots are contained in Appendix B. The maximum pressure andmuzzle velocity were higher for the solventless variation in comparison to the standard M203A1 charge.The cause of these higher values was attributed to the fact that the solventless charges were fired with 0.3kg more propellant than was required to ballistically match the M203A1 charge. The maximum change intemperatures with these charges agreed within the scatter of the data with the standard charge, indicatingno effect on thermal erosion produced by substitution of the solventless propellant for the solventpropellant. The temperature-time traces for a solventless M203A1 firing are given in Figure 6. Thesetraces are typical of all those obtained in this study.
BREECH, FORWARD & DELTA PRESSURE
00
35@
300
c3
U)
so-
_50 -1-
is 2030 .1 0I cI[ ( MS )
Figure 4: Breech Pressure and Pressure Difference, Standard M203AI
BREECH. FORWARD & DELTA PRESSURE
350
30
490
LAJr,
(I)
LUI
lea
IS 0 30TI I LI. (H I
Figure 5: Breech Pressure and Pressure Difference, Solventless M203AI
6
Sample Breech Forward MuzzleCharge Size Pressure Pressure Velocity
(MPa) (MPa) (m/s)
M203A1 14 366 325 827
Solventless/ liner 7 380 334 839
Solventless/ wo litver 7 364 321 835
Solventless/ KNO 3 6 384 350 844
Solventless/ K2SO4 7 382 340 841
Solventless/ no case 297 262 794
Table 1. Pressures and Velocity
Sample Max Temp Rise (°C) Avg atCharge Size 12 3 6 Origin
M203A1 14 113±8 81±3 108±3 101±5
Solventless/ liner 7 116±8 82±3 114±4 104±3
Solventless/ wo liner 7 119±6 87±2 120±3 110±4
Solventless/ KNO 3 6 115±5 83±2 113±2 105±3
Solventless/ K2SO4 7 116±8 82±2 111±2 105±5
Solventless/ no case 1 139 -- 138 133±10
Table 2. Thermocouple Data
7
2S5
l ogLU7
a
i- soLU
25
0 5 li0 Iso 200 250 300T ME iMs
Figure 6: Temperature Changes at Thermocouple Locations 1-4
Variation 2 was the solventless charge without the TiO2/wax/lead liner. As expected from previous
experience with the M203A1, this variation resulted in reduced pressures and velocities in comparison tothose from Variation 1. This reduction should be expected, since the elimination of the liner effectivelyincreased the chamber volume. The temperature measurements were slightly higher at all of thethermocouple positions. The temperature results indicate the minimal effect of the wear reducing additivein this charge.
Variations 3 and 4 were the solventless charges with flash reducers of KNO3 or K2SO4. Higherpressures and velocities were seen with the flash reducer shots when compared with other solventlessrounds due to the reduction of free chamber volume. The flash reducers produced no effect on thetemperature increases.
Variation 5 consisted of a solventless charge without the combustible cartridge case. The pressures andvelocities were less than the other solventless rounds due to reduction of the amount of energetic materialin the charge and the effective increase in chamber volume due to the elimination of the case and parasiticcomponents. The maximum temperature at the two measured positions increased dramatically over theother solventless charges. These results were anticipated because the combustible case has a flametemperature near 2200 K while the flame temperature of the solventless propellant is approximately 2737K. The combustible case not only reduces the effective flame temperature of the entire charge, but has anadded cooling effect in that gases from its combustion are produced near the boundary layer, thecharacteristics of which govern the heat input to the tube.
IV. CONCLUSIONS
From the data gathered in this study, we can draw several conclusions regarding the effect several ofthe charge constituents have on the amount of heat transferred to the gun tube during the interior ballisticcycle.
8
A combustible-cased charge containing solventless XM41 propellant does not appear to be moreerosive than the standard M203A1 charge containing M31A1E1 stick propellant, based on the amount ofheat input at the origin of rifling.
The wear reducing additive in the solventless charge reduces the maximum temperature change, andthus the heat input, at the origin of rifling. The magnitude of the reduction appears small; however,testing performed during the M203A1, product improvement program predicted a wear life significantlylower without the liner.
The addition of a flash reducer in the amount typical of that in a fielded charge (0.113 kg) does notaffect the amount of heat transferred to the gun tube. It does, however, increase the maximum chamberpressure to the degree expected.
The elimination of the combustible cartridge case significantly increases the heat input at the origin ofrifling, as expected. The cooling effect of the entrainment of the case gases, which are cooler than thoseof the propellant, into the boundary layer was dramatically demonstrated by the the comparison of thetemperature rise in the vicinity of the origin of rifling with cased and uncased charges.
9
REFERENCES
1. T.L. Brosseau, I.C. Stobie, J.R. Ward and R.W. Geene, "120-mm Gun Heat Input Measurements,"
BRL-TR-02413, US Army Ballistic Research Laboratory, Aberdeen Proving Ground, MD, July 1982.
2. F.A. Vassallo, "An Evaluation of Heat Transfer and Erosion in the 155-mm M 185 Cannon," Technical
Report No. VL-5337-5-1, Calspan Corporation, Buffalo, NY, July 1976.
3. T.L. Brosseau, "An Experimental Method of Accurately Determining the Temperature Distribution and
Heat Transferred in Gun Barrels," BRL-R-1740, US Army Ballistic Research Laboratory, AberdeenProving Ground, MD, September 1974.
4. D.L. Kruczynski, "Gun Tube/Charge/Projectile Interactions and Gun Tube Wear," BRL-TR-3004, US
Army Ballistic Research Laboratory, Aberdeen Proving Ground, MD, June 1989.
ACKNOWLEDGEMENTS
The authors wish to thank the crew at Range 18 - Messrs. J. Bowen, J. Hewitt, J. Stabile, R. May, J.Tuerk, D. Meier, and S. Little - for the experimental support in conducting the firing program.
10
APPENDIX A
Description Sheets for XM41 and M3AE1 Propellants
11
IM'ENTONALLY LXEFT BUANK.
12
XM41
P AF ROPELLYAMMNTO LNT .S RADFORD, SHA. DunO-7--4
CObv Cetr SMQtEN ae 101 /8 37.214 o PT1 0 mlb *~
MAX % ____m__
1131 - - 10ANU ACTURL OF .... !L...N! mc ACU
0.5 m/c oain Lodenist nte-- -08
700 cccleloa df 38
CONSWUNTPOROULAAD M A
uaiin- 200 ±10-- NoFue -Ih
Nitroglycri n manfacure by. RAA; Oirgaiiemfacue byOAN SnlWr A.AP
1.3
N131AIE1
'Aane allyOR AYMUuNITION PLANT, RAFRmm, VA.~ AAgUC40
AC Inn=as OUM Los MT91"Cwl .. atrC 1" 31C
so 12.92 -184p
-te.tooemueetu upeciftlonerequiren..,,:
McmUI 2a43 mbin hold 4
Incrase t A' n-rhour2514
APPENDIX B
Computer generated plots of breech, forward, and delta (breech minus forward) pressures, andthcrmocouple output.
(Plots are in order of firing).
15
INTnTimoNALLY LEVI BLANK.
16
PROPELLANT LINER FLASH
RD # TYPE Yes/No REDUCER
36 M31AIEI Y ---
37 XM41 Y ---
38 M31IE1 Y ---
39 XM41 N ---
40 M3AIEl Y ---
41 XM41 N ---
42 XM41 Y ---
43 M31IE1 Y ---
44 M31AIE1 Y ---
45 XM41 Y ---
46 XM41 N ---
47 M31A1E1 Y ---
48 XM41 Y K2so 449 XM41 Y KNO
50 M31AIE1 Y ---
51 XM41 Y KSO 4
52 XM41 Y KNO 3
53 M3IAIE1 Y ---
54 XM41 Y KSO4
55 XM41 Y KNO
56 M31IE1 Y ---
57 XM41 Y KSO 4
58 XM41 Y KNO
59 M31AIE1 Y
60 XM41 Y ---
61 XM41 N ---
62 M3lIAE1 Y ---
63 XM41 Y
64 XM41 N
65 XM41 Y ---
17
PROPELLANT LINER FLASHRD # TYPE Ycs/No REDUCER
66 XN141 N--
67 XM41 Y--
68 XN141 N--
69 N131AlEl Y--
70 XM41 Y
71 XM41 N--
72 XM41 Y K 2 S0 473 XM41 Y KNO 374 M31AlEl Y--
75 XM41 Y K 2 SO 476 XM141 Y KNO 377 M31A1E1 Y--
78 XM41 Y K 2S0 4
18
WEAR 36BREECH c. FORWORO PRESSURE
'Is,
389
0-
250
S 290-
Q Is*0-
.
TIME (M1S)
WEAlR 36DELTA P
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a-9
WEAR 37BREECH PRESSURE
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205-CA
01 7 2 .2 27 32 37 42TIME (MS)
DATA LOST
WEAR 37TC *0, 90. 180, 270 DEG
126
0. 765m
I
-AJ
25-
* so 5 le Is 209 210 3ioTIME (MS)
20
WEAR 38BREECH & FORWARD PRESSURE
-"
ties
35,
250
D 200
w M
too-
soi00
ii 23 28 i3 38 43TIME (MS)
WEAR 39DELTA P
IS'
75
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TIME (MS)
WEAR 38TC 0 , 90. 180. 270 DEG
126
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TIME (MS)
21
WEAR 39BREECH. & FORWARD PRESSURE
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259
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TIME (MS53
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TIME (MS)
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Iff
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22
WEAR 40499 BREECH & FORWARD PRESSURE
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LiS Is#
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68
16 21 62 1 ITIME (MS)
WEAR 40DELTA P
7S
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TIME (MS)
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CL 761
a Go
2S L
TIME (MS)
23
BREECH I FOrW11LR ITELCSIREI4se
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TIME (MS)
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(X so
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WEHR 4'BREECH & I-ORVPID 1CLS;UrE
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126
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BREECH & I-Oli! ILU
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hicn
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TIME (MS)
WLFR 43DELTA P
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26
CL.
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TIME (MS)
WEAR 43TC 6 0. 99, 190 DEG
ISO
129
hlo
75
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Si Ile IeO 2OO 2gi 3"
TIME (MS)
26
WEAR 44BREECH &FORWARD PRESSURE
360-
a~
20
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017 22 27 i2 37 412TIME 01S)
WEAR 414DELTA P
79
0.
so.
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- 7
as
DELTl TEMP (DE
27
WEAR 45B~REECH FORAR PRLESSURIE
360-
260-
Of ISO0.
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17 22 22 37 1TIME (MS)
WEAR '45DELTA P
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TIME (MS)
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LU
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BREECH & FORWARD PRSSURE
q gov .".-
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WEAR 46DELTA P
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TIME (MS)
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29
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a t
TIME (MS)
30
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: GO BREECH &FORWARD PRESSURE
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300
0) 20
u
20 No a035IsTIME (MS)
WEAR 48
____________DELTA P
75
26.
TIME (MS)
WEAR '49TC a 0, 90, 199 DEG
* 2
76
a
0
4 lid lie 20 no0 weTIME (MS)
31
WEAR 49BREECH & FORWARD PRESSURE
C 300
260iJi
200
Lu
0-
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20 lit 35 IS '1TIME (MS)
DATA LOST
WEAR 49TC *0, 90, 180 DEG
126I~ 110
LJ
m. 76
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26
a 4 40 tie gig 25e 39
TIME (MS)
32
WEAR 5eBREECH & FORWARD PRESSURE
3 p'
ca 300
2SeCd
206
LU
a. Is@CL
lea-
2026 3035 44S1TIME (MS)
WEAR 50DELTA P
I.S-
75
Ld
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-2 0 5is4 0 65TIME (MS)
WEAR 50TC 0 9. 9, 180 DEG
ise
1 2r
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0. 76X:
a
as
00 so lie do. Rio IN 300
TIME (MS)
33
WEAR 5!0 BREECH & FURWPRD PIESUkE
3S0
CE 300
260
L.A
200
Is@
20 es JJ UfI llIi ( H: )
DATA LOST
WEAR S1rC e 0. 90, 180 DEG
12.
too
X" 76,w
I-00a-
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a
THK 50s
34
WEAR 52BREECH PRESSURE
se
35S-
380
260
S200
CL.
14e
Sa3
[IME (MS)
DATA LOST
WEAR 52TC Q 0, 90. 180 DEG
76
I0-
80 so e IO ' .. . .2 AN
TIME (MS)
35
WEAR S3BREECH PREESSURE
35@
c 300
250LdD) 200-
(og
Li
29.
02 25 36 is 45TIME (MS)
DATA LOST
WEARP 53TC e 0. 90. 180 DEG
I GO .%'
12
LiJ
0 7
hat6'
2r
is lie IS iO i-s NTIME (MS)
36
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INT77D(fONALLY LMF BLANK.
62
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