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AD-A283 644
Characteristics of JAX Gun Propellant
Robert J. Lieb,Joseph M. Heimeri
ARL-TR-465 June 1994
S &94-26905
APPROVED FOR PUBLIC RELEASE; DISTRIBUTION IS UNLWIMIE.
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The findings of this report are not to be construed as an official Department of the Armyposition, unless so designated by other authorized documents.
The use of trade names or manufacturers' names In this report does not constituteIndorsement of any commercial products.
REPORT DOCUMENTATION PAGE@m W ftm bi . hemWa" m 0a00mmsm OWu i isimiae ft t9Mu o bm•w• m m im. hdmmag afW. he wm e" @ of so 1 u-~~- fte- -0a m -i -~ muge "*M" b V" embalm to Iftmlsa. bUmnsu"sg N uba Ou Rb 11g.s mf
1. AGIENCY USE[ ONLY (L"Ve b/ank) 2. REOTDT .REPORT TYPE AD ATSCOVERED
IJune 1994 Final Jan 88 - Jan 944. TITLE AMN mUBTITLE 5. FUNDING NUMERS.
PR: IL161102AH43Characteristics of JAX Gun Propellant
6. AUTHOR(S)
Robert J. Lieb and Joseph M. Heimeri
7. PERFORMING ORGANIZATION NAME(S) AND ADORESS(ES) S. PEFORMING ORGANIZATION
U.S. Army Research Laboratory REPORT NUMBER
ATTN: AMSRL-WT-PAAberdeen Proving Ground, MD 21005-5066
9. SPONSORINGIMONITORING AGENCY NAMES(S) AND ADDRESS(ES) 10SPONSORINGiMONITORINGAGENCY REPORT NUMBER
US Army Research LaboratoryATTN: AMSRL-OP-AP-LAberdeen Proving Ground, MD 21005-5066
11. SUPPLEMENTARY NOTES
12a. OISTRIBUTIONIAVAULABITY STATEMENT 12b. DISTRIBUTION CODE
Approved for public release; distribution is unlimited.
13. ABSTRACT (Maximum 200 words)
To increase the performance of 120-mm kinetic energy tank rounds, propellant made by adding up to 30% ground RDX toJA2 (JAX) has been manufactured and tested. While the performance goals of the JAX were met, its response to shapedcharge jet attack in several different vulnerability tests was much more violent than that of JA2 alone. This unexpectedviolent response of JAX propellants has been documented. In the attempt to understand the mechanism responsible forthis response, the deposition of dry crystalline RDX on exposed JAX surfaces was discovered. This crystalline formationwas detected during a routine morphological examination using a scanning electron microscope, and the crystals wereidentified by Fourier transform infrared (FTIR) surface Microreflectance. A wicking mechanism has been proposed toexplain this phenomenon. Thermal, chemical, aging, and morphological investigations were performed to substantiatethis mechanism. The information gathered indicates that the RDX deposition process occurs in all JAX propellant andmay occur in other JAX-like materials. Since JAX undergoes continuous morphological change with temperature andtime,there are important safety implications for he storat,' and handling of these materials, as well as questions concerningtheir subsequent suitability for use in weapon systems. It was also found that standard safety tests do not indicate thepresence of the deposited RDX. All of these findings are documented and the implications are discussed.
14. SUBJECT TERMS 15. NUMBER OF PAGES
85JA2, RDX, gun propellants, JAX, vulnerability, mechanical, response, morphology 16. PRICE CODE
17. SECUIRITY CLASSIRCArTON U. SECURITY CLASSICATION 19. SECURITY CLASSICTbON 20. UTATION OF ABSTRACTOF REPORT OF THIS PAGE OF ABSTRACT
UNCLASSIFIED UNCLASSIFIED UNCLASSIFIED
NSN 7540-01-28•-5500 Standard Form 29e. 2-89)Prescribd by AN 1 St.239-16 296-102
Intentionally Left Blank
ii
TABLE OF CONTENTS
LIST OF FIGURES .............................................................................................. v
LIST OF TABLES .............................................................................................. vi
ACKNOW LEDGM ENTS .................................................................................. vii
1. INTRODUCTION .................................................................................................. 1
2. THE FRACTURE RESPONSE OF JAX ............................................................. 2
2.1 Mechanical Response Testing ........................................................................ 2
2.2 JAX Fracture Response Conclusions ............................................................. 5
3. VULNERABILITY TESTS: DESCRIPTION AND RESULTS ......................... 6
3.1 The Primacord Shock Initiation Test .............................................................. 6
3.2 The Air Blast Test ......................................................................................... 6
3.3 The Shock Velocity Test ............................................................................... 9
3.4 The Impulse Pendulum Test .......................................................................... 11
3.5 The Staged Compartment Test ..................................................................... 13
3.6 Summary of JAX Vulnerability Testing ...................................................... 13
4. JAX M ORPHOLOGY ...................................................................................... 14
4.1 SEM Background ......................................................................................... 14
4.2 SEM 's of JA2 Grains .................................................................................... 14
4.3 SEM 's of JAX Grains ................................................................................. 15
4.4 Crystal Identification .................................................................................... 18
4.5 The Formation of Crystals on JAX Surfaces ................................................. 19
4.6 The Role of DEGDN .................................................................................... 20
4.7 The RDX Deposition Process ..................................................................... 21
5. SAFETY IMPLICATIONS ............................................................................... 22
iii
TABLE OF CONTENTS (Conunued)
6. OPTIONAL STRATEGIES TO RDX ADDITION ............................................ 24
6.1 Solid Fills ..................................................................................................... 24
6.2 Use of Less Volatile Plasticizer ................................................................... 24
7. SUMMARY ........................................................................................................ 25
8. REFERENCES ................................................................................................... 27
APPENDIX A JAX PROPELLANT DESCRIPTION SHEETS ....................... 29
DISTRIBUTION LIST ...................................................................................... 73
iv
LIST OF FIGURES
Figure
1 Mechanical Parameters Illustrated ............................................................................ 3
2 Illustration of the Total Deviation Parameter ........................................................... 3
3 Mechanical Response Results ................................................................................. 3
4 DMA Data for JA2 which Indicate Glass Transition Temperature Region ............ 4
5 Total Deviation vs Impact Velocity for Gas Gun Impact Test ................................ 4
6 PrimaCord Shock Initiation Test Seup ..................................................................... 6
7 Schematic Diagram of the Air Blast Experiment ................................................... 6
8 Air Blast Pressure at 3.0 m ...................................................................................... 7
9 Air Blast Pressure at 6.1 m ...................................................................................... 7
10 Air Blast Arrival Time at 3.0 m .............................................................................. 9
11 Air Blast Arrival Time at 6.1 m .............................................................................. 9
12 Schematic of the Shock Velocity Experiment ......................................................... 9
13 Schematic of Microphone Locations ..................................................................... 10
14 Shock Velocity Data for JA2 and JAX .................................................................. 11
15 Schematic of the Impulse Pendulum Test ............................................................. 11
16 Impulse Pendulum Data for 2.3-kg Quantities of JA2 and JAX ........................... 12
17 Impulse Pendulum Data for Various Amounts of JA2 and JAX ........................... 12
18 Schematic of the Ten-Round Staged Compartment Test ....................................... 13
19 Staged Compartment Test Results for 2.3-kg Quantities of JAX and JA2 ............ 14
20 Micrographs of the Cold-Fractured Surface of JA2 Propellant ............................ 15
21 Micrographs of the Cold-Fractured Surface of 2R-10 JAX Propellant ................. 15
22 Nitramine Base Propellant with RDX in the 2 - 20 Pim Particle Size Range ...... 16
23 Micrographs of the Cold-Fractured Surface of 2R-20 JAX Propellant ................. 16
24 Schematic of the Impulse Pendulum Test ............................................................. 17
25 Micrographs of the Inner Perforation Surface of JA2 and JAX- 1 Propellants ......... 17
V
LIST OF FIGURES (continued)
EigUM jag=
26 Micrographs of the Inner Perforation Surface of JAX- I Shown in Figure I IbCold-Fractured in the Radial Direction ................................................................ 18
27 Micrographs of the Exterior Surface of 2R-16 JAX Propellant afterSeven-Year Storage .............................................................................................. 19
28 Microreflectance FTIR Spectra of JAX Surfaces ................................................. 19
29 Micrographs of the Cut Surface of 2R- 16 JAX Propellant ................................... 20
LIST OF TABLES
I BLAKE Computations for JA2 and Selected JAXs ................................................. 1
2 3.0 and 6. 1-m Air Blast Data .................................................................................. 8
3 Shock Velocity Coefficients .................................................................................. 10
4 Shock Velocities (km/s) as a Function of Distance .............................................. 11
5 Impulse Pendulum Data ......................................................................................... 12
6 Staged Compartment Propellants .......................................................................... 14
7 Thermogravimetric Analysis for JA2, M30 and M43 at 600 C and 1000 C .......... 21
8 Vapor Pressures of Neat DEGDN and NG .......................................................... 21
9 Solubility of RDX and HMX in DEGDN at 250 C .............................................. 22
10 Sensitivity Initiation Characteristics for JAX, JA2 and Neat RDX ...................... 23
vi
ACKNOWLEDGMENTS
This report is the accumulation of many distinct items of information that were collected over aperiod of about 7 years.
We thank the following folks from whom we amassed the vulnerability information on the JAXpropellants: N. Gerri's very early PrimaCord test results; D. Devynck's air blast data;0. Lyman's shock velocity test results; T. Adkins, G. Gibbons, D. Serrano and J. Watson who
developed the impulse pendulum and staged compartment tests and accumulated the results; andG. Garcia who performed BLAKE calculations.
M. Leadore performed all mechanical properties testing of the propellants. C. Gillich used thescanning electron microscope to discover the white "powder" within the perforations of the JAXgrains, and produced, cataloged, and performed initial analysis for the recent micrographs used inthis study.
R. Pesce-Rodiriguez used her skill with the Fourier transform infrared (FTIR) microscope todetermine that the "powder" seen on the JAX propellant surface was a nitramine. In addition, sheperformed the solubility experiments of RDX and HMX in DEGDN. We extend many thanks to herfor allowing us to use her unpublished results. Thanks are also due to F. Robbins for allowing us toremark on his studies with PARAPLEX G59, and to W. J. Worrell and B. M. Riggleman of Hercules(Radford) for supplying information contained in Reference 21.
The reviewers, R. Frey, F. Robbins, and B. Strauss, are thanked for making this a more readablemanuscript.
vii
Intentionally Left Blank
viii
1. INTRODUCTION
Methods have been and are being sought to increase the lethality of a kinetic energy (KE) tankround. One approach is to increase the rod's velocity by increasing the energy available to the round.This is most readily accomplished, at least in principle, by increasing the energy of the propellant.
The propellant of choice in several prior tank ammunition applications has been JA2. It is madefrom nitrocellulose (NC), nitroglycerine (NG), and diethylene glycol dinitrate (DEGDN) in relativeamounts of roughly 60%, 15%, and 25%, respectively. JA2 has a nominal impetus of 1150 J/g, ascomputed from the BLAKE code.' To increase the energy, cyclotrimethylenetrinitramine (RDX)has been added to JA2 during manufacture.2', 3 The computed increase in the impetus, flametemperature, and the chemical energy, which is the impetus divided by (y - 1), is given in Table 1.The common, generic name for JA2 propellant with RDX added is JAX. A common name for aspecific amount of RDX added to JA2, say B%, is 2RB. For example, 10% RDX added is given thedesignation 2R10. This is the nomenclature used in Table 1.
JAX has been made with nominal RDX additions ranging from 6.5 to 30% by weighL The RDXused in the earlier manufacture of JAX was fluid energy milled and had particles with a meandiameter2 of 7.5 gim. The more recent manufacture used nominal 4-irm recrystallized RDX fromDupont Corporation. 3 The JAX referred to in this report is generally the earlier manufacturedmaterial. For the same propellant formulation, more stick propellant than granular propellant can beplaced into a fixed volume gun chamber; thus, the JAX had been made in both granular and partiallycut stick (PcS) geometries. The sticks were kerfed, or cut part way through at selected linear intervalsalong the stick, to relieve the internal pressure when the propellant began burning.
Performance increases were realized.2 However, the response of JAX to the unplanned stimulusof a shaped charge jet was violent, approaching, or, in some cases, perhaps sustaining a detonativeevent. Because JA2 itself usually just bums in such tests, the violent response was not anticipated.In addition, other propellants, e.g., XM39 and M43, have been formulated with several times theRDX loading of the JAXs and in similar tests, they responded less violently to the shaped charge
Table 1. BLAKE Computations for JA2 and Selected JAXs
Formula Impetus Flame Temp Impetus/(y -1)J/g K J/g
JA2 1153 3448 51302R6.5 1168 3489 51942R10 1175 3509 52252R12 1179 3520 52402R16 1187 3541 5273
2R17.5 1189 3548 52832R20 1194 3560 53022R30 1209 3602 5367
attacks.4 Thus, the question is raised: what happens to the JA2 when the addition of even smallamounts of RDX is observed to change the vulnerability response from burning to detonative?
In an effort to address this question, several test results are reviewed. First, the mechanicalfracture response of JAX relative to JA2 is discussed. Second, the results of a number of vulnerabilitytests that demonsi.ate the different vulnerability responses of JA2 and JAX are reviewed. Third, JAXis characterized by the now standard propellant characterization techniques, 5 the results were notanticipated and their interpretation consumes the latter half of this report.
2. THE FRACTURE RESPONSE OF JAX
2.1 Mechanical Response Testing.
Three lots of JAX propellant were produced in 1985 and had fracture response evaluationsperformed with methods that were in use during that period. 6 '7 8 ,9 The mechanical parametersreported are the results of those tests. These results have been shown to agree with results gatheredfrom improved procedures and equipment st' aquently developed to expand the scope and qualityof fracture response measurement. TI " section is based on an unpublished technology transferreport.10
Two methods of fracture evaluation were used to characterize the JAX materials. The first wasthe drop weight mechanical properties test (DWMPT)6,7 that provides high-rate, uniaxial, compres-sive loading to individual grains from which the propellant modulus, failure stress, failure strain, etc.,are determined at various temperatures (-500 C to 600 C). These parameters are illustrated inFigure 1. This test characterized the uniaxial response of standard test grains and can indicatefracture response differences in materials. The second method was the gas gun impact test (GGIT)8.9with surface area analysis performed using the damaged grains. In this latter test, a single grain isdamaged by a single impact at a controlled velocity, orientation, and temperature. After severalgrains are damaged, the grain and any of its shards are collected and burned in a small closed bomb.The pressure-time data is reduced using burning rates established for undamaged grains. From this,a surface area vs fraction burned profile is generated that reveals the nature and degree of the fracturedamage suffered during impact, as shown in Figure 2. The fracture susceptibility is quantified bysumming the difference between the damaged-grain fracture profile and the profile predicted for theundamaged grain, which is represented by the shaded area in the plot. These two procedures providemechanical and fracture response information that can be used to indicate propellant fracturesusceptibility.
DWMPT and GGIT procedures were performed using JAX propellant under conditions similarto those used for previously tested JA2 propellant. DWMPT procedures were conducted at 20, -10,and -32' C at a strain rate of about 200 s-. Modulus, failure stress, and failure strain vs temperatureresults are shown in Figure 3. The JA2 results (solid diamonds) are connected by a smooth curve.
The JAX data in Figures 3a and 3c tend to lie on or above the JA2 line. Also, the JAX data tendto be ranked at a given temperature, the larger values corresponding to specimens with more RDXfiller.
2
hbrnct d swo L"Om 4"
100 O @VW Li. Friamm Damaged
le Tota Deilio doLmis*
5.0 10.0 I$00.0 0.2 0.4 0.6 0.8 1.0Strain (PCt) Fraction Burned
Figure 1. Mechanical Parameters illustrated Figure 2. The Total Deviation Parameter
200-\ 5" 0 2R10
\2~ 4 ]22A 22R300
La
• , . , • , • -,. MEN , • , 2
-60 -40-20 020 4060 80 -60 -40-20 020 4060 80Temperature (°C) Temperature (0 C)
a. Failure Stress vs Temperature b. Failure Strain vs Temperature
6 A 0 2R30
soR~
JAM
-60 -40-20 0 20 40 60 80
Temperature (°C)
c. Modulus vs TemperatureFigure 3. Mechanical Response Results
A 2R30
The JA2 failure strain curve of Figure 3b Loss Modulusdecreases in both directions from 0* C. In the 0.8, 0.48
lower-temperature. direction, the increased brittle- -0.46ness causes failure at lower strain; in the higher- 0temperature direction, the rapidly increasing soft- 01 0.6 -0.44
ness causes plastic failure, also at lower strain. - 0.42(Results from dynamic mechanical analysis"1 0.5 0 Cindicate that glass transition occurs at or slightly O I0.40
below -20* C. See Figure 4.) -0.38
Figure 3b shows that the JAX propellants do . 0.36not soften as JA2 but maintain a brittle character 0.2 ,0.34over the temperature range tested. 2R10 and -60 -40 -20 0 20 402R20 exhibit similar slopes, while 2R30 has a Temperature (0C)much shallower one. Again, the magnitude of thestrain at failure tends to be ranked with the level Figure 4. DMA Data for JA2 Which Indicateof RDX filler used in the JAX. Looked at another Glass Transition Temperature Regionway, the addition of the RDX filler reduces (orpossibly eliminates) the gross thermoplastic-flow characteristics of the JA2 propellant at highertemperatures and extends the brittle characteristics of the JAX into the higher temperature regimes.
The GGIT procedure was carried out at three velocity-temperature matrix points for the threeJAX formulations. For JAX propellant at -200 C, grain fracture was observed to begin at about110 m/s, so velocities of 90 and 120 m/s were chosen as two of the matrix points. At -300 C, the thirdmatrix point was selected. The results of these tests and ones previously completed for JA2 are shownin Figure 5. The total deviation (defined earlier, see Figure 2) is an arbitrary scale that measures the
1200" 1200"U,,,m JA2 U JA2
1300 --- 2R11000_ - 2R20 1000" 2RI0' -- b- 2R30 2R30 A
800- 0800- ,
00Z 600"sS 600" -s
400) • 4)00- S
S200 •. 200"
0 40 80 120 0 40 80 120Velocity (m/s) Velocity (mis)
a. -20' C b. -300 C
Figure 5. Total Deviation vs Impact Velocity for Gas Gun Impact Test
4
degree that the damaged grain surface-area profile deviates from the profile predicted for undamagedgrains. Closed bomb results for undamaged grains, when subject to this analysis, produce totaldeviations that average about 45 with a range between 30 and about 100. Significant grain fractureis thought to have occurred when values near 200 result. The comparison of fracture damage andfracture susceptibility via the total deviation is made by noting differences in this parameter at similarimpact conditions.
Figure 5 shows several things that are evident:
1) As the RDX content of the JAX increases, the fracture susceptibility in-creases.
2) The fracture susceptibilities of the 10% and 20% RDX compositions of JAXare similar to each other and comparable to JA2. (The shaded area indicates therange of JA2-like behavior.)
3) The 30% RDX composition has a significantly greater fracture susceptibilitythan JA2 at both -20 and -300 C.
4) These results are self-consistent and consistent with DWMPT results.
2.2 JAX Fracture Response Conclusions.
The mechanical properties and fracture response of JAX were measured under conditions thatwere thought to show the greatest differences between JA2 and JAX. Measurements showed thatat RDX levels near or below 20%, JAX mechanical response was not significantly different fromJA2, and may, in fact, have been slightly better (see Figure 5a). At RDX levels near 30%, theDWMPT mechanical response indicated the increase in brittleness would result in the creation ofsignificant fracture-generated surface. This observation was confirmed in GGIT fracture suscepti-bility tests. JAX with 30% RDX had significantly greater fracture-induced surface area than did JA2,2R10, or 2R20 under similar impact conditions.
These tests indicate that JAX propellant up to an RDX content of about 20% should not sufferworse fracture-related performance loss or vulnerability susceptibility than JA2, as long as the stressenvironments are equivalent. At RDX levels of 30% and greater, JAX can be expected to havesignificantly worse fracture-related performance and vulnerability responses than does JA2 underthe conditions in these experiments. This does not say that a JAX propellant cannot be designed togive satisfactory performance under normal interior ballistic conditions. However, when conditionsdeviate from normal (such as localized ignition at low temperature, or shaped-charge jet interaction)and grain fracture occurs, a JAX propellant can be expected to have a more severe fracture responsethan JA2. Since JA2 has been shown to be a thermoplastic elastomer with time-temperatureequivalence,12 failure strain results indicate that as the strain rate of the deformation increases, thedivergence in mechanical response between JA2 and JAX should increase. That is, as the interactionrates increase, JAX should show an increasingly greater level of brittle response when compared toJA2 (see Figure 3b).
5
12cm 3. VULNERABILITY TESTS: DESCRIP-TION AND RESULTS
Propellant Bed Several vulnerability tests had been performedusing these early JAXs as the test propellant. Inthis section, these tests and their results are out-lined in rough chronological order: 1) the"Primacord shock initiation test, 2) the air blast
.......... test, 3) the shock velocity test, 4) the impulseSo t pendulum test, and 5) the staged compartment
S. test.
e V3.1 The Primacord Shock Initiation Test
This test has been designed to rank new propel-
Figure 6. PrimaCord Shock Initiation lant formulations by their relative response to
Test Setup explosive shock initiation. It is a simple "go" or"no-go" screening test designed to eliminate those
",,e-.--re. Gaugs , propellants with a demonstrably poor vulnerabil-ity response.
"3.0,m • I ,- Figure 6 shows a schematic of the Primacord3.0r m r•,
, ,I shock initiation test setup. A 250-mm section ofW11. a 120-mm combustible case is filled halfway
3.0 I ,n] with granular propellant. A predetermined lengthPropellatnt-Filed of Primacord, with a mass of about typicallyCase, 32 g, is coiled and placed on top of the propellant
- bed. A short length of cord extends through the
-Plate wall of the case to accommodate the igniter. TheShaped Sharge case is filled to the top with propellant that is held
in place by sealing the case with gun tape. Thecase is placed on a 305-mm by 610-mm section
Figure 7. Schematic Diagram of the of 10-mm rolled homogeneous armor (RHA)Air Blast Experiment plate supported by two plates of 51-mm RHA
which, in turn, rest upon a large 5 1-mm section ofRHA (not shown). The Primacord is ignited and the propellant reacts. If the 10-mm support plateis destroyed, a detonative event is indicated and usually indentations can be found in the base plate.2
These tests indicated a violent response for 2R30 and mild responses for 2R 10 and 2R20. 2 Theseresults are consistent with the findings of the fracture response tests of JAX discussed in Section 2.The JAX formulation 2R30 was eliminated from further consideration.
3.2 The Air Blast Test.
A schematic of the test configuration for the air blast measurements is found in Figure 7. An81-mm BRL precision shaped charge jet is conditioned by a 25-mm RHA plate at a distance of 2 cone
6
diameters (CD). (This standoff distance has been selected because the jet is thought to have well-defined characteristics [for example diameter, velocity, and length] at this distance.) The conditionedjet proceeds through and interacts with the propellant. The shock wave produced by the jet-propellantinteraction is detected by in-ground pressure gages that are located along radii 450 on either side ofthe jet center line. The pressure gages are situated in lead shields sunk into ground. The entire testarea had been graded and leveled. The data consists of time of arrival of the shock and the pressuremeasured at a given location. For comments on the difficulty of obtaining reliable data from this typeof test, see Reference 13.
Table 2 shows data for an inert material, JA2 in both granular and PcS geometries, and a numberof JAXs. The upper section of this table refers to the data taken at the 3.0-m locations while the lowersection refer to those data taken at the 6. 1-m locations. The left most column identifies the Range10 shot number; the second and third columns identify the propellant used; the fourth and fifthcolumns tell the geometry (granular or partially cut stick) and the perforation (7 or 19). The sixthcolumn shows the weight of each propellant in kilograms. The next columns display the results.Pressure values measured along the left (L) and right (R) legs, as well as the average (A) of both legsare show in columns 7, 8 and 9, respectively, in Table 2. The right most column shows the averagearrival time of the shock.
Figures 8 and 9 graphically display the average air blast results for the different propellants. TheJA2 responses are slightly greater than the inert material response. On the other hand, the JAXs givea more violent response.
Figures 10 and 11 show the air blast arrival times. The inert material exhibits the longest times(i.e., slowest shock wave, which in this case must be due only to the shaped charge jet itself). Thearrival time for the JA2 propellants is slightly faster. The JAXs, however, all show significantly
1000- 150
800°
100.
& 0. . X*.
600" Vo-,.•, l-•, %
'%"o ,• o -Z; ,Z% -Z"
400' Z % ."Z.",ol'Z, i 50 """ ""
200 o ;;' ••.
i ,.. ...., o o o, P Z , . o ,
Figure 8. Air Blast Pressure at 3.0 m Figure 9. Air Blast Pressure at 6.1 in
7
v t~~~~% S6 -OO 0 -44O O
C040 to'-%- 00 m v C
enm6
vi vi 4c~C c~s 0ý O N4 (7 Ch-
zE ~l C4 0 ) U
6lc. C: : :6c L
t9, 1C4C 4 qt E4 C4 C4 eq CSI e
C14 C4 0A C4
I- I, -b4
to .j T 6a*
s 88 s8 w'0c888
-- 4'0 0'0-0'0' -z 00i00' 00 -i' 000'0
.LS to- -r
8
6 15
5
__ 4 _ 104, ]0
3 3.1
00.
.11I
Figure 10. Air Blast Arrival Time Figure 11. Air Blast Arrival Timeat 3.0 m at 6.1 m
faster arrival times, again indicative of a more
violent reaction.
3.3 The Shock Velocity Test. . 81-mam Shaped Charge
Figure 12 shows a schematic of the shockvelocity test. 4 . 15 An 81-mm BRL precision Conditionins Block
shaped charge is aimed at the center of the box of • , ZeoTn Triggerpropellant. The shaped charge is fired, the jet is /Propellant Boi
formed, and is conditioned by 51 mm of RHA. It•
then strikes the trigger plate and interacts with thepropellant within the wooden box. Any residual :- Index Block
jet is captured by the stack of RHA blocks. At aposition 80 mm from the upper surface of the ".-Catcher Blockscatcher blocks, the upper surface of the third
* RHA block was indexed to obtain a measure ofthe actual center-line of the jet. The 2R16i ii m19-perforation stick JAX was broken at the kerfsto provide "grains" with an LID about unity.
The wooden propellant box is made 250-rmmsquare and 80-mam deep. In the vertical center Figure 12. Schematic of the Shockplane of this box (i.e., 40 mm below the trigger), Velocity Experiment
9
Table 3. Shock Velocity Coefficients
Shot Propellant Lot A B CNumber Name Number
16 INERT WEP -10.50 0.35 25.7017 INERT WEP -6.19 0.21 16.4036 2R16 HCL-87A-010-002 7.39 0.08 -10.6041 JA2-19p RADPE-792-11 -6.41 0.22 17.3043 JA2-19p RADPE-792-11 -7.61 0.26 19.6044 JA2-19p RADPE-792-11 -6.97 0.24 18.50
eight sacrificial microphones are positioned at progressively increasing radii from the center (seeFigure 13). The microphones are located on radii 28 mm to 102 mm from the center of the box. Theshock front from the propellant-jet interaction passes through the propellant bed and is sequentiallydetected by the microphones. Since the location of each microphone is known, the basic data consistsof time of arrival of the shock front vs location. Differentiation provides velocity vs time information.
Table 3 identifies the lot numbers for several propellants, their shot numbers, and theircoefficients in the empirical formula:
shock velocity (km/s) = A + Bd+°-5 + Cd-°.2s. (1)
8' 'Equation (1) has been used to compute the infor-mation in Table 4 for shots 16,17, 36,41,43, and44. The average of shots 16 and 17 (the inert"shots) and the average of 41, 43, and 44 (the JA2shots) are also shown in Table 4. The sigmacolumn is the standard deviation of the three JA2shots.
Figure 14 shows the shock velocity of theaverage inert, the average JA2 and the 2R16plotted against distance from the center of thebox. The inert material and JA2 propellant show
2 36 33 a shock with monotonically decreasing velocity.3 40 ,3 By contrast, the 2R 16 JAX exhibits an accelerat-4 60O 75 70 240 ing velocity with distance. These results clearly6 so 210 .7 9o iso indicate that the response of the JAX is mores 102 1o violent and of a different nature than the response
Figure 13. Schematic of Microphone Locations of the JA2.
10
Table 4. Shock Velocities (kWns) as a Function of Distance
Sbots
Ditamce 16 17 Average 36 41 43 44 Average Sigma(mM) 16,17 41,43,
20 3.21 2.50 2.85 2.75 2.75 2.82 2.85 2.81 0.0530 2.40 1.96 2.18 3.30 2.18 2.18 2.24 2.20 0.0440 1.93 1.66 1.79 3.69 1.86 1.82 1.89 1.86 0.0450 1.63 1.46 1.54 3.97 1.64 1.60 1.67 1.64 0.0460 1.44 1.33 1.38 4.21 1.50 1.44 1.54 1.49 0.0570 1.31 1.23 1.27 4.40 1.41 1.33 1.42 1.39 0.0580 1.22 1.17 1.19 4.56 1.34 1.26 1.36 1.32 0.0590 1.16 1.12 1.14 4.71 1.28 1.22 1.32 1.27 0.05100 1.12 1.10 1.11 4.84 1.26 1.18 1.28 1.24 0.05
3.4 The Impulse Pendulum Test.
Figure 15 shows a schematic of the impulse pendulum test apparatus.1 6 In this test, propellantsare placed in a cardboard shipping container, nominally 150 mm in diameter and 520 mm long. Theattack path is diagonally through the center of mass of the propellant and placed at a convenient angle(but constant) so that the jet will miss the pendulum bob. The attack is by unconditioned bare Viperplaced 2 cone diameters away from the propellant charge. The shock wave, produced by theinteraction of the Viper's jet and the candidate propellant, impinges upon the nearby pendulum bobof massive weight. The distance between the propellant tube and the pendulum face is 305 mm. Thedisplacement and the period of the pendulum are measured directly and the total impulse deliveredto the pendulum is calculated from the following formula:
Impulse = 2x [Mass x Displacement/Periodl. (2)
5"
4 Displacement X- FrictionleUS Peno Bearing
*A 2R16633
\ Period
2'
o 20 40 60 8o 1o0 120 (3200kg)
Distance (mmn)
Figure 14. Shock Velocity Data for Figure 15. Schematic of the Impulse
JA2 and JAX Pendulum Test
11
The contribution of the shaped charge itself is determined by shooting into a cardboard containerfilled with sand. This contribution is small and subtracted from the calculated impulse to obtain theimpulse due to the jet-propellant interaction alone. Results are ranked in a relative fashion.
Table 5 identifies the propellant, the shot number, and the net impulse in N-s. The table is dividedaccording to whether the weight of propellant tested was 2.3 kg or greater than 2.3 kg. Figure 16shows the results for the 2.3-kg tests. Again, it is evident that 2R20, either in the granular or stickgeometry, exhibits a greater response than the JA2. The results in Figure 17 are even more dramatic.Here JA2 at the 7.3-kg and 10-kg levels has about five times lower response than the 2R20 at the7.3-kg level. This is further evidence that the JAX responds in fundamentally different fashionrelative to JA2.
Table 5. Impulse Pendulum Data
opellant Mass Lot Shot ImpulseName (type) (kg) Number Number (N-s)
JA2 (7p) 2.3 RAD-84G-001-S176 88-10 612JA2 (19p) 2.3 RAD-PE-792-11 88-11 657
JA2 (19 PcS) 2.3 RAD-PE-792-33 88-30 843JAX 2R20 (7p PcS) 2.3 HCL-86C-006-004 88-27 1484
JAX 2R20 (19 p Hex) 2.3 HCL-86H-003-009 88-13 1618JAX 2R20 (19p PcS) 2.3 HCL-86C-004-001 88-14 1896
JA2 (7p) 4.5 RAD-84G-001-S176 88-25 872JA2 (19 PcS) 10. RAD-PE-792-33 88-28 1201
JA2 (19p) 7.3 RAD-PE-753-10 88-26 1208JAX 2R20 (7p PcS) 7.3 HCL-86C-006-004 88-29 5614
2000 6000'
22zA A A R 3022
120"
3.5 The Staged Compartment Test
These tests characterize the relative responseof candidate propellants in confined quarters thatsimulate the volume of the stowage compartmentof an M I tank. The apparatus used in this test isshown in Figure 18 and is capable of holding tenrounds of sleeved 105-mm ammunition. How-ever, in these experiments, 2.3 kg of propellantare placed in a cardboard tube and blocked withwood. This tube is then located within a standardaluminum stowage sleeve that is placed in the testapparatus on the second tier from the bottom, infront of the hole cut into the angled face of thearmor. Only the sleeved 2.3-kg propellant charge Figure 18. Schematic of the Ten-Roundis in the compartment. The threat is an 8 1-mm Staged Compartment TestBRL precision shaped charge located at standoff (The target round is darkened.)of 2 CDs (not shown). The jet passes through25 mm of RHA that is backed by 13 mm of Isodamp. The conditioning armor pack (not shown) islocated against the slant wall of the compartment and the jet is aimed at the center of mass of thepropellant. Two mounts for Kistler gages (calibrated to 13-MPa peak pressure) are located in bothend walls of the compartment, in a plane parallel to the direction of the shaped charge jet attack. Thesegages provide (duplicate) pressure vs time data. The pressure-time curve is integrated (up to 10 ms)to provide specific impulse vs time information.
Table 6 identifies the propellants tested in the staged compartment apparatus. The testing of JA2propellant took place on February 11, 1988, while the testing of 2R20 propellant took place onApril 12, 1988. Figure 19 shows the computed impulse plotted against time for the four propellantslisted in Table 6. It is obvious that the JA2 response is about five times lower than the JAX response.
3.6 Summary of JAX Vulnerability Testing.
The mechanical properties tests, even at low temperatures, did not show an obvious correlationwith the vulnerability tests that involved shaped charge jets interacting with the JAX propellant bed.This is not surprising since the role that mechanical properties play has been shown to be secondaryto that of chemistry. 17
All five tests discussed previously show that the response of JAX is fundamentally different fromthe response of JA2. Since JAX is manufactured by adding 30% RDX (or less) to JA2, the questionarises: What is the specific mechanism that causes JA2 to go from a low response propellant, one thatgenerally mimics the inert material response, to the violent response observed for the JAXs? Theremainder of this report discusses how we began to address this question and what was found.
13
15
Table 6. Staged Compartment Propellants.10
Propellant Lot#L 19psda
2R20 HCL-88C-006-004JA2 19P STICK RAD-PE-792-33 JA
JA2 19P GRAN RAD-PE-792-11JA2 7P GRAN RAD-PE-001-S 176
0
0 2 4 6 3 10
Time (MS)
4. JAX MORPHOLOGY Figure 19. Staged Compartment Test Results
for 2.3-kg Quantities of JAX and JA24.1 SEM Backgeround.
The physical arrangement of the processed material is very important to propellant performance.Defects such as voids, cracks, agglomerates, or foreign material can have a deleterious effect on theprogrammed burning of the charge by changing the mass generation rate of the propellant. This isdone by supplying augmented surface area directly or through the resulting fracture, or by simplychanging the intrinsic burning rate of the propellant. For this reason, scanning electron microscopy(SEM) has been adopted as a standard method of detecting these defects. Each propellant lotundergoing investigation is examined by SEM to ensure that the structure has its intended integrity.SEM micrographs are also used to assure that there are no processing problems, such as poor mixingof materials. Information may be uncovered during a routine SEM morphological screeningexamination that would alert researchers to potential performance problems and could eliminate orredirect subsequent testing. 5
Therefore, undamaged specimens of each type of JAX propellant were cold fractured at dry icetemperatures. The low-temperature fracture reduces the possibility of introducing artifacts into thestructure. Since cracks propagate through the material by a path of least resistance and defectsusually supply a lower resistance pathway, the likelihood that a crack will encounter a defect (if itexists) as it propagates is enhanced. This process results in more defects being exposed at the fracturesurface than would be represented in random sectioning of the specimen. Conversely, if no defectsare seen on the newly exposed surface, it is likely that the defect population is small.
4.2 SEM's of JA2 Grains.
Figure 20 shows micrographs of the cold-fractured surface of typical JA2 propellant and ispresented as a basis for comparison. JA2 is a thermoplastic elastomer that undergoes a transitionfrom mostly plastic to brittle behavior at about -20° C at deformation rates on the order of 100 s-1 (seeFigure 4). The typical JA2 cold-fracture surface is smooth, indicating brittle fracture. Somenitrocellulose (NC) is observed because the high nitration level (13.1%) of the NC prevents all of thefiber from dissolving in the plasticizer. Other propellants that use lower levels of nitration (12.6%)
14
10 Pm 10 Pm
a. -700X b. =200OXFigure 20. Micrographs of the Cold-Fractured Surface of JA2 Propellant
have the NC completely dissolved and do not show exposed fibers. The only other notable featurein typical JA2 propellant is the presence of very small (0.5 - 2 pim) particles distributed throughoutthe propellant. Their identity has not been established. They could be very fine carbon black, whichis an added ingredient, or they could be small particles of MgO that are added during mixing to aidin the extrusion process. In any case, they seem to be found throughout the material.
4.3 SEM's of JAX Grains.
Figure 21 shows micrographs of 2R 10, a JAX propellant. RDX particles that are less than 5 pmin diameter are observed in these micrographs. The surface is not as smooth as the JA2 surface inFigure 20, but other JA2-like features are present, such as NC fibers and very small particles. The
20pm 10 Ima. -400X b. =800X
Figure 21. Micrographs of the Cold-Fractured Surface of 2R- 10 JAX Propellant
15
only unusual feature is that the particle size of theRDX is considerably smaller than expected. Thedistribution of particle sizes that was added tomake JAX, and that typically appears in nitra-mine base propellants, has most of the particleswithin a range of 2 to 20 p.m. Figure 22 shows anexample of a nitramine base propellant. It has76% RDX filler that falls within the 2-20 pamrange. This range is representative of the RDXparticles size distribution expected in the JAXspecimen but was not observed.
. Micrographs of JAX propellant with 20%
10 P.M (-800X) RDX filler are found in Figure 23. As expected
Figure 22. Nitramine Ba. : Propellant with the number density of particles is greater, but the
RDX in the 2 - 20 p.m Particle Size Range particle size is still about 5 .tm. The fracturesurface is rougher than the 2R10 surface (see
Figure 21). This was caused by the greater number of particles (i.e., defect locations) diffusing thepath of the crack during the specimen preparation.
Micrographs of the 30% filled JAX propellant are presented in Figure 24. There are similarchanges due to the increased concentration of RDX as were noted in Figure 23. There are moreparticles present and an even rougher surface. The major difference noted here is that the RDX sizedistribution seems to be more in line with what was expected.
The observations made for these three lots of JAX propellant are significant and consistent whenconsidered in light of information that was gathered when a more recent production of JAXpropellant was made. The JAX micrographs presented in Figures 22, 23, and 24 were taken whenthe propellant was first delivered in the Spring of 1986. A more recent production was manufactured
20 pim 10 pAMa. -400X b. -800X
Figure 23. Micrographs of the Cold-Fractured Surface of 2R-20 JAX Propellant
16
20 gm 10 lima. -400X b. --800X
Figure 24. Micrographs of the Cold-Fractured Surface of 2R-30 JAX Propellant
at the Radford Army Ammunition Plant in February 1993.3 The objective in making the newer JAXhad been to test the effects of using recrystallized RDX rather than fluid-energy-milled RDX in a JAXcomposition. This lot was received for routine morphological testing and was cold fractured toinvestigae the structure. Crystals were observed covering the surfaces of the perforation walls.These observations had not been made with any previous lot of JAX. However, the only surfacesthat were investigated using the earlier propellant were cold-fracture surfaces. Micrographs of earlylots were inspected for similar observations, but there were no portions of micrographs that showedperforation surfaces of sufficient magnification to confirm the presence of crystals growth.Figure 25 shows a comparison between a JA2 perforation surface and the corresponding surface ofa 2R7.7 JAX grain. All perforations showed similar crystal structure. All areas of every perforationshowed evidence of crystal growth.
20 pim 20 gima. JA2 (-400X) b. JAX-1 with RDX Crystals (-400X)
Figure 25. Micrographs of the Inner Perforation Surface of JA2 and JAX-1 Propellants
17
To understand the physical nature of the deposition process, the specimen used in Figure 25 wascold fractured along the radial direction of the grain. This provided an orthogonal view from the onepresented in that figure, and provided an opportunity to observe the extent of the crystal growth.
Figure 26 shows the radial fracture surface. Attention is called to the whiter band of material thatsits on the gray bulk of the propellant grain. It is clear that the crystals reside only on the extrusionsurface. There is no extension of the crystals below a sharp line of demarcation, the extrudedperforation surface.
-0I...- lr20 pm a. =400X 10 ni b. =800X
Figure 26. Micrographs of the Inner Perforation Surface of JAX-1 Shown in Figure 1 lbCold-Fractured in the Radial Direction
The more recent lots of JAX were not the only ones to exhibit this crystallization phenomenon.The JAX propellant that was studied in 1986 (2R10, 2R20, 2R30, and 2R16) was still in storage inthe magazine. It had been undisturbed for 7 years and was retrieved to see if this crystal growth couldbe seen in the perforations. When the ungraphited 2R16 JAX propellant was brought to thelaboratory, a white "powder" was visible on its outside surfaces. Specimens of whole grains wereprepared for SEM analysis and micrographs of the outside surface of the grain appear in Figure 27.Since the crystals must have appeared after extrusion, and since the crystals seem to appear uponannealing or long-term storage, the deposition mechanism is likely to be precipitation aftertransportation to the surface by means of solution.
4.4 CLrystal Identification.
Positive identification of these crystals was needed and was obtained. The identification strategyconsisted of 1) examining the surface of the perforations, where the crystals had been detected; and2) examining the bulk material, away from external surfaces, as a control. The microreflectance-FTIR spectra of the JAX surfaces (see Figure 25b) were obtained using a Mattson Polaris FTIRspectrometer and a Spectra-Tech IR-Plan infrared microscope with a MCT detector.II The softwareincluded Kramers-Kronig transformations to correct spectral distortions. For both spectra, 32 scanswere collected with a resolution of 8 cm-'. The scans are shown in Figure 28.
18
100 jAm 20 pma. -80X b. =400X
Figure 27. Micrographs of the Exterior Surface of 2R- 16 JAX Propellant after 7-Year Storage
Attention is drawn to the ordinate of Figure 28 in the region between 1500 and 1700 cm-'. Fromother spectra (not shown), an RDX spectral signature lies at about 1600 cm-' and an NC spectralsignature lies at about 1660 cm-1. In the upper scan labeled "Bulk Surface of JAX" (Figure 28), wesee the NC spectral signature at 1660 cm-', but little or no indication of an RDX spectral signatureat 1600 cm-'. On the other hand, the lower scan, labeled "Perforation Surface of JAX" (Figure 28),we do find the RDX spectral signature at about 1600 cm-'. The shape of the derived NC spectralsignature at about 1660 cm 1 is distorted. This results from a failure of the Kramers-Kronigtransformation to perfectly compensate for the specular reflection of the crystals on the surface.
The crystals were positively identified as nitramines and we concluded that they were recrystal-lized RDX. With the information thus far it washypothesized that some type of migration pro- -cocess was occurring that resulted in the depositionof RDX on the exterior surfaces of JAX propel-lants.
4.5 The Formation of Crystals on ,Buk Surface olJAX
JAX Surfaces. - A DX
Processing records indicated that annealingof the propellant was performed for 6 hours at430 C after extrusion and cutting to relieve re- Perforaion Surface of JAX
sidual grain stress. Annealing is routinely per-formed as a part of JA2 processing, and was 2000 1800 1600 1400 1200 1000 800
included in the JAX processing. 3 Thus, if heating Wavenumber (cm-')were to accelerate the RDX deposition, all JAXmaterials should have RDX crystal growths on Figure 28. Microreflectance FTIR Spectratheir external surfaces after manufacture. of JAX Surfaces
19
After annealing, the grains are tumbled to apply a graphite coating that aids in loading operationsand increases packing density. We infer that the newer grains had the RDX removed from exposedoutside surfaces during the tumbling process. This explains why crystals were found only within theperforations for the recently produced JAX. Grains stored for extended periods of time either wereexposed to high temperatures (storage history is unknown) or the solution that transports the RDXto the surface had sufficient time to form these crystals after slowly evaporating.
As stated earlier, the annealing step in the processing of JAX suggests that heat might promotethe RDX formation. We devised a simple test of this proposal. Specimens of JAX (2R16) were cutat 2 10 C (not cold-fractured) to expose fresh surface area that contained no crystals. One half of thegrain was placed into an oven at 750 C for 65 hours. The other was placed within a laboratory hoodat room temperature. After 23 hours the propellant specimens were removed from the annealing ovenand inspected; crystals were observed on the surfaces. The control showed no sign of crystalformation. The samples were returned to the oven and the hood and after 65 hours they were againexamined using the SEM. There was about the same number density of RDX crystals on the heatedsamples as there was after 23 hours, but the crystals were larger. The SEM results for heated andcontrol samples after 65 hours are shown in Figure 29.
4.6 The Role of DEGDN.
Evidence from thermogravimetric analysis experiments shows large weight losses (13.5 to 19%)for JA2 upon exposure to elevated temperatures. Table 7 shows the weight loss observed for thepropellants JA2, M30, and M43 upon exposure to 600 C for 1000 minutes and upon exposure to1000 C for 360 minutes. 19
The candidates responsible for this relatively large weight loss observed for JA2 are theplasticizers DEGDN or NG. Table 8 shows the vapor pressure for these two neat materials2" over
50 pm 50 pim
a. Control, Unannealed (-160X) b. Annealed, 750 C for 65 hr. (=160X)
Figure 29. Micrographs of the Cut Surface of 2R-16 JAX Propellant
20
Table 7. Thermogravimetric Analysis for Table 8. Vapor Pressures of NeatJA2, M30 and M43 at 600 C and 1000 C DEGDN and NG
Temperature Vapor Pressure(%WL Loss) (0 C) (Pa)
Propellant T= 600 C T= 1000 C DEGDN NGSpecimen t = 1000 rin t- =360 min 20 0.48 0.20
JA2 13.5 19 25 0.78 0.2440 no data 1.00
M3 7.5 1 45 no data 1.7260 17.3 8.00
the temperature range 200 to 600 C. The neat vapor pressure of DEGDN is significantly greater thanthat of NG, a factor of 2 at 600 C, and the weight percentage of DEGDN is almost a factor of 2 greaterthan the weight percentage of NG in the formulation of JA2. These two ratios lead us to focus ourattention on DEGDN as the principal solvent for the transport of RDX in the JAXs.
The next question concerns the solubility of RDX in DEGDN itself. Table 9 shows the availabledata for the solubility of RDX and HMX 20 at 250 C. The data are ranked according to the value ofthe absolute solubility of RDX. This value ranges from a low of 2.3 g/100 g solvent to a high of41 g/100 g solvent. The absolute solubility of RDX in neat DEGDN has the lowest value.
Since DEGDN is about 25 wt% of JA2, and since 6 to 30 wt% of RDX is added to the JA2, the
solution of dissolved RDX in the DEGDN and NG within the JAX propellant is very likely saturated.
4.7 The RDX Deposition Process.
The measurable solubility of RDX in DEGDN and high vapor pressures for DEGDN stronglysupports the following deposition process.
When RDX is added to the JA2 propellant, it dissolves to form a saturated solution in thepropellant plasticizers. This accounts for smaller than expected particle sizes observed in morphol-ogy investigations, especially at lower concentrations of RDX. The high vapor pressure of DEGDNcauses rapid vaporization of the plasticizer at all exposed propellant surfaces. During annealing, thisprocess is accelerated (and the solubility of RDX may be greater) causing rapid loss of plasticizerand transport of RDX from the interior to the exterior surfaces. As the plasticizer vaporizes, thedissolved RDX precipitates and is deposited on the surface. Once crystals are formed on the surface,the tendency to enlarge existing crystals would take precedence over the creation of new sites, as isusually the case when solids precipitate from saturated solutions. This was observed in the mostrecent annealing experiments (see Section 4.5). The effect of this process is to remove RDX fromthe bulk of the grain and deposit RDX crystals on the exterior surfaces.
21
Table 9. Solubility of RDX and HMX in DEGDN at 250 C
Solvent RDX HMX Ref RDX/HMX
(g/100g Solvent)
DEGDN 2.3 <0.2 a >11
Acetonitrile 5.5 2.0 b 2.8
Cyclohexanone 7.7 1.0 b 7.7
Acetone 8.2 2.8 b 2.9
Butyrolactone 14 12 b 1.2
Hexamethyl 16 1.4 b 11phosphoramide
Dimethyl 33 c bacetamide
Dimethyl 37 c bformamide
Dimethyl 41 57 b 0.7sulfoxide
a) Reference 18
b) CPIA/M3 "Solid Propellant Ingredients Manual" Nov 1989. RDXvalues from Unit 16, p15 of 21; HMX values from Unit 15, p16 of 22.
c) Shortly after the HMX dissolves, precipitation of solvate crystalsoccurs.
5. SAFETY IMPLICATIONS
Some of the final processing steps in the manufacture of JAX are conducted at elevatedtemperatures.3 First, there is the "even-speed operation" conducted at 680 C that prepares the doughfor carpet rolling. Second, the carpet rolls are conditioned at 660 C for a minimum of 30 hours.Finally after extrusion, trays of cut propellant are annealed for 6 hours at a temperature of 430 C. Ifour proposed mechanism for the precipitation of RDX on exposed propellant surfaces is correct, thenit is likely that recrystallized RDX is formed in one or more of these processing steps. Thus, therecrystallized RDX constitutes a potential safety hazard even during its manufacture.
It is also noted 2' that "Microscopic examination of 2R12 and 2R16 propellant carpet rolls instorage at Radford (since 1986) confirmed the presence of unbound (recrystallized) RDX on thepropellant surface."
We have noted in section 4.5 that the recrystallized RDX is likely to be mechanically loosenedfrom the exposed exterior surfaces of JAX propellant. This was confirmed when recrystallized RDX
22
Table 10. Sensitivity Initiation Characteristics for JAX, JA2 and Neat RDX
Producti Total RDX Content Sample Sliding ThermalSample Date Volatiles Panicle Thickness Impact Friction* Dischrge Initiation
(M) Size (g) (%) (MM) (an) (MP) (M (C)
2R12 Apr-86 0.05 47 12 2.46 80 390 729.5 1982R16 Apr-86 <0.01 7.5 16 2.54 64 464 ,9.5 1942R20 Feb-86 0.14 100 20 2.41 80 503 ý9.5 no data
JA2 Oct-86 0.30 0 0 2.46 80 617 ;,9.5 195
neat RDX dry 7.5 100 0.18-0.38 13-26 200-293 0.026-0.065 no dataneat RDX dry 47 100 0.38-0.45 51 170 0.065 no dataneat RDX dry 100 100 0.28-0.36 26-64 170-345 0.13-0.26 no data
* at 244 cn/s
was easily removed from 2R12 and 2R16 carpet rolls in experiments at Radford by scraping thepropellant surfaces with a spatula. 21
"This RDX crystal growth and subsequent separation from the propellant introduce safetyconcerns during propellant moving and handling operations that are not well understood. Theseconcerns arise during sample inspection, the finishing phases in the JAX manufacturing process, andpropellant shipment and storage.
Recent safety testing of several JAXs, JA2, and neat RDX has been done.2' These results forthreshold initiation levels are presented in Table 10. (In the table, threshold initiation level is definedas that level above which initiation can occur, and is established by 20 consecutive failures at thestated level. Initiation was determined by infrared detection of decomposition gases.) These datashow little or no change in the initiation level among the JAXs as measured by electrostatic or thermalignition. The differences in the JAX initiation values for impact and sliding friction were judged notsignificant. The report concludes that for all practical purposes the JAX initiation levels arecomparable to the JA2 values. Table 10 also shows that dry, neat RDX is more easily initiated byimpact, friction, and electrostatic discharge than either JA2 or the JAX propellants listed.
There are two implications that can be drawn from these data. First, the recrystallized RDX, whenmechanically freed from the JAX, may either remain airborne and diffuse, or be convectivelytransported, thereby contaminating shipping or storage containers. The precise safety implicationshave not been quantified, but the data in Table 10 suggest a prudent caution since the loose RDX posesan increased safety hazard. Second, the fact that these safety tests showed no differences betweenJA2 and JAX (with or without surface RDX 21) suggests that these tests cannot be used to predict ordetermine the level of recrystallized RDX present. To make this determination, a time-temperaturestudy of the rate of formation of recrystallized RDX on the JAX propellant surfaces would have tobe undertaken, perhaps as a function of the weight percentage of RDX. Once this relationship isdetermined, the temperature history of the JAX propellants would have to be recorded and evaluatedto properly assess the current state of recrystallization. The increased hazard due to the evolution ofloose RDX would also have to be determined.
23
Two considerations raise questions that may be significant, but are currently not resolvable. Thefirst deals with the RDX deposition process at annealing and upper-extreme storage temperatures.The data in Table 8 show that the relationship between the vapor pressure and temperature isArrhenius in nature. Thus, at elevated temperatures, the vapor pressures will continue to rapidlyincrease. However, the solubility of RDX in the propellant plasticizers is not known at highertemperatures. If the solubility is significantly larger and works in concert with the higher vaporpressure, the deposition rate will be markedly increased as the temperature rises. The secondconsideration concerns the deposition rate and is chemical in nature. Our interest has been focusedon the role of DEGDN because of: 1) its higher vapor pressure (Table 8) and greater concentrationrelative to NG; and 2) the greater thermogravimetric weight loss experienced by JA2 relative to M30(Table 7). Nevertheless, the role that NG plays in the RDX transport process is not clear. In addition,the mixture of DEGDN and NG that forms the JA2 plasticizer may have properties different fromthe properties of the neat components. Most of the information needed to address these concerns isnot known. Two tacit assumptions were used throughout this analysis: 1) dramatic changes in thesolubility of RDX with temperature were not considered; and 2) the vapor pressure of the plasticizermixture would be an interpolation of the neat constituent values. If additional processes or chemicalchanges were introduced when the plasticizers were mixed, other explanations for these observationsbecome possible. However, the mechanism, as presented, is qualitatively consistent with theinformation and physical data contained in this report.
In conclusion, the mechanism for the precipitation of RDX discussed in section 4.7 produces adynamically changing structure on the surfaces of and within JAX propellants. Since JAXs canundergo morphological changes with time and temperature, and since the standard safety tests arenot predictors of the changing state of a JAX propellant, the continued manufacture and use of JAXsas they are currently formulated and processed is not recommended.
6. OPTIONAL STRATEGIES TO RDX ADDITION
6.1 Solid i.
RDX is not the only energetic solid oxidizer that could be tried in the manufacture ofa JAX-likepropellant. Table 9 shows that the relative solubility of HMX in neat DEGDN is more than an orderof magnitude lower than that of the RDX's solubility. While this is encouraging, this low value isno guarantee that HMX would not show a similar crystallization phenomenon. Recourse must bemade to experimentation. Other solid oxidizers could also be tried.
6.2 Use of Less Volatile Plasticizer.
The DEGDN could either be replaced with a less volatile plasticizer oran inhibitor could be addedto DEGDN to retard its migration. In this last regard, some experimentation with PARAPLEX G59,a viscous, high molecular weight hydrocarbon, has shown some success.22 Approximately 10 wt%of G59 had been added to a recently manufactured nominal 2R20 JAX. The grains were exposed totesting as described in section 4.5, except that the heating at 750 C was continued for 120 hours.These grains were examined by SEM, as described in section 4.3, and analyzed by FTIR, as describedin section 4.4. No crystalline RDX was observed on the exposed outer surfaces.
24
7. SUMMARY
The original goal of this investigation, to determine the mechanism(s) by which the vulnerabilityresponse of JAX was so much greater than that of JA2, was not reached. It may be that the rawcrystalline RDX observed on the external JAX surfaces contributes to this increased violent responsebut it is not the only possible mechanism, and in no way has it been demonstrated. For example, theimplication that RDX enters into solution in the DEGDN may also provide a mechanism for theincrease violent response of the JAXs observed in the vulnerability tests.
During the course of routine investigations on JAX propellant, raw RDX crystals were founddeposited on the external surfaces of all JAX grains examined. A mechanism for this deposition washypothesized and tested, and found to be consistent with all data at hand. Safety implications of thedeposition process were pointed out and some general approaches to mitigating or circumventing theRDX crystallization were suggested.
25
Intentionally Left Blank
26
8. REFERENCES
1. Freedman, E., "BLAKE- A Thermodynamics Code Based on Tiger: Users' Guide andManual," ARBRL-TR-02411, USA ARRADCOM Ballistic Research Laboratory, AberdeenProving Ground, Maryland, July 1982.
2. Nosan, F., F. M. Monteiro and J. Kennedy, "High Performance Propulsion System, FinalReport," BRL-CR-634, U. S. Army Ballistic Research Laboratory, Aberdeen Proving Ground,Maryland, June 1990.
3. Zeoli, D. "Production of JAX -Experimental Solventless Propellant," Hercules Inc., TechnicalReport for Project No. PD-090, Contract DAAA090-91-Z-0001, February 1993.
4. Heimerl,. J. M., "Hypervelocity Impact On Propellant Beds: Workshop Report," BRL-TR-3115, U. S. Army Ballistic Research Laboratory, Aberdeen Proving Ground, Maryland, June1990.
5. Kaste, P. J., J. Ceasar, R. J. Lieb, "Scanning Electron Microscopy (SEM) to Probe PropellantMorphology," ARL-TR-230, Army Research Laboratory, Aberdeen Proving Ground, Mary-land, October 1993.
6. Lieb, R. J., and J. J. Rocchio, "High Strain Rate Mechanical Properties Testing on Lots of SolidGun Propellant with Deviant Interior Ballistic Performance," 1982 JANNAF Structures andMechanical Behavior Subcommittee Meeting, CPIA Publication 368, pp 23-38, October 1982.
7. Lieb, R. J., and J. J. Rocchio, "Standardization of a Drop Weight Mechanical Properties Testerfor Gun Propellants," ARBRL-TR-02516, USA ARRADCOM Ballistic Research Laboratory,Aberdeen Proving Ground, Maryland, July 1983.
8. Lieb, R. J., D. Devynck, and J. J. Rocchio, "The Evaluation of High Rate Fracture Damage ofGun Propellant Grains," 1983 JANNAF Structures and Mechanical Behavior SubcommitteeMeeting, CPIA Publication 388, pp 177-185, November 1983.
9. Lieb, R. J. and J. J. Rocchio, "A Gas Gun Impact Tester for Solid Gun Propellants," BRL-MR-3399, ADA 149 712, USA ARRADCOM Ballistic Research Laboratory, Aberdeen ProvingGround, Maryland, October 1984.
10. Lieb, R. J., "Fracture Response Evaluation of JAX," unpublished Technology Transfer ReportPSB-TTR-86-06, Interior Ballistics Division, Ballistic Research Laboratory, Aberdeen Prov-ing Ground, Maryland, December 1985
11. Lieb, R. J., ed., Draft STANNAG, "Dynamic Mechanical Analysis of Explosive Materials toMeasure the Glass Transition Temperature," AOP-7 Test Number 102.01.025, Descriptionsof Tests Usedfor the Qualification and Documentation of Explosive Mate rials for Military Use,AOP-7, Annex II (Draft), Section 102.01, December 1993.
27
12. Lieb, R. J., and M. G. Leadore, "Mechanical Response Comparison of Gun PropellantsEvaluated under Equivalent Time-Temperature Conditions," ARL-TR-228, Army ResearchLaboratory, Aberdeen Proving Ground, Maryland, September 1993.
13. Wise, S. and W. 0. Ewing, " Shaped Charge Jet Direct Impact of Porous Granular PropellantBeds," JANNAF Propulsion Systems Hazards Subcommittee Meeting, CPIA Publication 582,Vol I, pp 51-64, April 1982.
14. Watson, J., "Response of Propellant Beds to Shaped Charge Attack," Proceeding of the NinthInternational Symposium on Ballistics, Part Two, pp (2-391)-(2-40 1), April-May 1986.
15. Lyman, 0. R. and J. T. McLaughlin, "Comments On Shock Velocity Measurements InPropellants Beds," BRL-TR-3284, U. S. Army Ballistic Research Laboratory, AberdeenProving Ground, Maryland October, 1991.
16. Waston, J., "The Response of Gun Propellant to External Stimuli," Proceeding of the TwelfthInternational Symposium on Ballistics, pp 62-71, October-November 1990.
17. Lu, P., J. Shin, B. Strauss, S. Moy, and R. Lieb, "Shaped Charge Jet Impact on Gun PropellantsStudy I -Temperature and Mechanical Properties Effects," 1991 JANNAF Propulsion SystemsHazards Subcommittee Meeting, CPIA Publication 562, pp 517-532, March 1991.
18. Pesce-Rodriguez, R., Private Communication, Army Research Laboratory, Aberdeen ProvingGround, Maryland, 1993.
19. Lieb, R. J., "Mechanical Properties and Thermal Analysis of HPLOVA," unpublishedTechnology Transfer Report PSB-TTR-86-07, Interior Ballistics Division, Ballistic ResearchLaboratory, Aberdeen Proving Ground, Maryland, March 1986.
20. TM-9-1300-214, Army Technical Manual: "Military Explosives," HQ Department of theArmy, Washington, DC, September 1984.
21. Kristoff, F. T., " Sensitivity Characteristics of Solventless Propellant with Unbound SurfaceRDX," internal Hercules Radford Memorandum, HI-93-M-033, October 1993.
22. Robbins, F., Private Communication, Army Research Laboratory, Aberdeen Proving Ground,Maryland, 1993.
28
APPENDIX A
JAX Propellant Description Sheets
Lot Numbers:
HCL86HO03-008 HCL86CO06-003 HCL87AO1O-006HCL86HO03-009 HCL86CO06-004 HCL87CO10-007HCL86HO03-010 HCL86CO06-005 HCL87CO10-008HCL86HO03-013 HCL87CO10-009HCL86HO03-014 HCL86HO08-001 HCL87CO10-010HCL86HO03-015 HCL86HO08-002 HCL87CO10-0 11
HCL86HO08-003 HCL87CO10-012HCL86CO04-001 HCL86H008-004 HCL87CO10-013HCL86CO04-002 HCL86HO08-005 HCL87CO10-014HCL86CO04-003 HCL86HO08-006 HCL87BO10-015HCL86CO04-004 HCL86H008-007HCL86CO04-005 HCL86H008-008 RAD-PD-090-1 (JA2)HCL86CO04-006 RAD-PD-090-2
HCL87A010-002 RAD-PD-090-3HCL86CO06-001 HCL87AO1O-004 RAD-PD-090-4HCL86CO06-002 HCL87A010-005
29
Intentionally Left Blank
30
- P/ACLSO Pounds
~ ,~J~ LadForedAirDrV . ' t? f l at . n y nv. tjI f S _ _
F kW Hold ato"k teIOwperatauamream395 89 F5 91 95092r Co l d v or p itl
noq.h~m¶ ~ TETS MFRIPI PP LAT PW~t -~?W400?
*~~~~g nv_________0 _
Pjc1~tuy _____________
527 foru f old a aint themp27ratundrd.e / 27700ccbomb, 0.1 smc oadng denit. L*""1x-s-r
N tro elluloselln N/A ouac "j, c 60aUrrnN ue FIh
DECD W/AK/AOftsof "a31
Akarit 1 NIA0.71 PF (alfgl W/ 116
PROPELLANT DESCRIPTION SHEET EI I!WdFPAWA 7.29
V2~0. 13 pert Nusagonal &ranulor =NcL*IOC)-Q0
=4m 11 5Mjltics-6113 W066- A !80" 1 48Poun~dsA' RADFORD ARUY AMMUNiTION PLANT, RADFORD. YA. k"Onleyvei Sulleentrect 947092. t!. TAS!v 110
momo~m Ii
UITIOILTIIIN~~AV AL-u I04 I / f4A.%ii ESP or Nliatiruluui~~~~~13ftM PikLDNTAt , ~wauawLw
MSH I A A PI T StA 1 j2...... ic j3jef / !ccA Tisw
AKN * -I -I I-/ 7 'AIN 1io
U 1S IT MA i I A PI AnIf N~ot C~a l/2) WAo1
ASH 0IA IAEN MIAMN ftt AISM IIS7 NZ- mCD11.6vai.Bs mMI i I nCuE4TRYLEN V SLBIT Y zi IA M/uriat Agra xrso n a rlm Step~latI rc
Mi.CO IORM 214R 10 AUG 7702 02
395089. 95091; 95092
*1 ANIIFACTURI If $fLVEfflLESS jOPttAiL1VJuim IT
-h Load Forced Air Dry
110 F 110 F Mold at temperatureT5F Amblen Coal down for samatine
NOPSAANnne N/A0%O .106 .0FF WS10 3/86f OM mOtwW
Nithoellulopelln WSn tMc @amountcs 91% it2 rnlvpi I 110 0Fmsm
* 'z IO"T-.A9 Perf. Rexaronal Graniular RCL36HO03-013 -
hultics GO* 086-31ý. %/77/mo 173 Pounds
I "SAnorm ARMY AEMURITION PLANT. RUMPOR. VA. Subcontract 973525. TasU TIT
595089% 195097 595092LJ.. _____
* ... **-MW~CTIRE I f SOLVEN1TLISS -PALIFUZtANT. U.
Nitrocellulose 'j NIA -NIA 55.09 iaWIY 120C ~P& I. N/A NIA No Fumes N NF 1 HT
DEGDN - NIA 20.99_____
hehlnes Cl SolubolP7 N/A NIA ________Den._-acc__1.6
______ N/ N/A~ 100.19 Cl3p to 10
* Ash N/Ae N/AA .00.010
.125"ur N/ .0I5A 1ie 0-ans 1h 42 ue . 7
iwieeP~uom~tuR Fibe Frumae52
t 01e proel0n in 9. trace 0mons N/ -63 -- 10
47-3 90IW Wam Webamr Ave.AWV N/ .088
- NAU .10 .09 8186X*c.£.W1 S R I AA
3 e4 A0
8
nKurtuA a W~ufto~r i onu en&& a~~210TN&9 Perf. Nexaconal GranulAr __CL56_______03 ____014__
- H ultics Czft 086-313. S/171RA 1A tauimn -
SAD ORDARMYAMMKITOK PAIT SAFDRD. A Subcontract 973525. Task TII
1 e950B 195091; 195092 13.13 ______
am 13.07 S m
1AANUfaPYTiRf Of SHVINtmtcc PCOVEMtNT
Pn R OCESS-;WN ..w.... TM
WitroceZlulose N/A N/A 55 09 WELaTw 15 200C er~ tjol cc r60'____ ____ ____ ____ __ NA /A
DEGDN N/A NIA 20.99 pe r01v~fAkardit 11NA NA 06 U ria1 NA 15
M~esUm 0Ovitde N/A N~/A U.U Abs. Dens. (icc '/ 1.60_______________ N/A N/A 0.05 Taliani: ____
_____________ N/A N/A 10.52 b.Lop@ OUi
Methvlene Cl Solubilitt N/A N/A 134.28 _______
*ul~. 7VL 119 Mn DE tcae S
-0an14 123-R I4 r 7 104 21 W6SIIUU / .710L
~SS5 lib Ave /A .. 2* ~ ~ ~ ~ 4 104.8 SR10 6a1nset om(." ld N/A .099 0796" 5~
. 125" z .085") fired against the ZH029 Outer N/A .0655 V i~uADUN
standard !P1 47 .2-138. /7.4 Ofa91/8
700cc bomb @ 0.10 gm/cc loading density.N/ IU
TwaP2 Wthmo onMmam Fiber Drum: 652D NA 1 .5t79
UAWM Candelilla wax was used as a lubricant during extrusion and may be present Inthe p~ropellant in trace amounts. The physical dimensions of this lot are a weight-
-ad average of sublots A and X.,.
D. W. KIRKPATRICK )p R L StOANS, PROGRAM MANAGER
35
riurrLuftI aIown anihirI uun
''2RI10~-4,9 Perf. Nexanonal Cranular H C.,86H003-015-
multcs rk 06-!3. %17/4 R&LADham 440 Found&
RADFORD AIRY AMMUNITION PLANT. RADFORD. VA. Subco*ntract" 973525. ý'ask *iT
595089: 995091 U9A09'a
____13_ 10_S_ _ 45__ + U'70
.~.. .*.....4UAtFACTIIRE Of SOLVENILESS ?IPREP ANT ______
11trocellulose NIA___ N/A 55.9____t_106cCC_0'7
______NIA___NIA_ 12.M8 No Fumes
AW3Wardit M 11be Drum: NI 61p52D/m /A 15
Crachdelil a a sd NA NuriAn durin exruionand aiepeen:nte-pRoplln inA tNIc amount2 lop 0 -C=.5
MisturS e I~I~1 NIAf AfV NAIA .
D. A......... ) wa. .
W136wag'7 7
NCLICCS44101 VoA ~ VIA Lo0d fortdadobr
.. ID.MIR. UNINIppg9 PLAN~wTP 9AD11 VA. t 0107
Hold atm ateamer#nture -
"bom
MANUFACURE____ 41*LIUS OIAT 6"
ma~~r 'tinsintu~~AU~ Candelild vati used asa ubricn uigstainn a epeeti
panalyi occaptaols
SignedA by . eeopmntEnineftrocelluloseDV /AirALkpatric@k20 b
9-1v37i 4A use 1FI h r
N/A
1111 AINT RVINITON KAVI. listM. VA. 111077
U49LNUOftem emewmi a Pam
2 a. t P qft1w _qmS!- 0! 1 a A a v"ft Io-sea
IL
NAW191111 If ISMINJISS OHU
d Air Ary
_"al"m Sm11024L startCAM wwL fgr
"Opubm CONSPOSSION INGMV AM mmis" amsmapraw miz M6-t _mMMI; 1
RtreciPlIUADSO MIA 1 142 12MIA I I hrMIAMIA M/A
n-m a. /cc /A
cararessure did reach
N 100 am atW/A
41-4..:W. "JUIM IREM IM off.INV SJUS11 I
AI-An 1169 11.*4n 1114n -SK Is WIA
1411% 1111-2 -ma-101 VIAOMGAW I I;dn I O&WIL VIA no,)
NIA PAN& 3/8600401 These are the closed bmb wasulte j4A -077 .10 "iftno 3/56for carpet rolls "t to gtr4m of mmumm __d1muslom 7.5"x.125"x.085". 3/86
700 cc bmb with a 0.1 jpfcc losdUg N/A 6.67 - us - '..dmalty. mw"919,
vm at tango - 33.33 29.75
w - %A lknw Win 7101 QURL.Nn- 32714fiCandelilla, am Is used a lubricant during extrusion and soy be present tothe propellant to trace sawints. Propellant coVositlon regultg are fromanalysis of caost rolls.
llsmd bo Development Ugin"TCoo4 -oo 2- D.V. lUrkpatri"
tuft 5
38
65 pow&*
U1F111 AINT 1111111IT111 PLANT. BAIFIRI. wanaywall 1%,brantreet
A- 4.1. qk
SLM I I Ig
W1 13, Ofave 11-11 S 304 100
"MomVANUUM11 SIL
Udd 10TULUT 1&VV v% SOFOBVITSINJO . 4
Cwl gMM fgr
MOT AM RM
ltroglluxoss MIA an 2 1
few 0 respaLonrdjj 11 MIA O.A& or (pal 1"I MIA
I MIA JR/A n-m ba. Dens. /cc N fAto I MIA IN/A n-n% allent: IjArgondy 20 MIA 12le 9 IUU=ftft
oressure did t reachW/A I OýO
10-10
=13 aim -tin alllov I Sw off mum =1
I --I a -1 WWWAIM an MamaI-Ln -jimp 071 Ik 1U MIA
I i a nfi. a IOIL OR
AM IPF;A72-11ft 144n I US"%- man MIA 111 _nV A 7 Mme 3186
OL"O' These STO the closed boob results N/A C77 "A& "AftO 3 /86for carpet rolls cut to staps of A "Nor,dUmnstons 7.5"s-125"a.08S"o 3LL6mM cc boob with a 0.1 P/CC loading 6.67 Owumdensity. 1 2-24 1 2.-32- 61LOWTION
33-33 t 29-75IM 0 POLUNS OWAAM RMA& %ftV Uft- tier RE& -Carton No. 1271J6
CandelIlls, wax is used as a lubricant during extrusion and my be present Inthe propellent in trace amounts. FCOPOllaRt COMpOCItIon results ore fneanalysis of carpet rolu.
Staved by "Velopeent i4ineor
- 4cL, 8vc oo-4-cw-i UstratrukP'114'04L J9. &. 14,44ý
39
VON- 21-20 7 ft t stlea ------
N/A 60 Pounds
fell Ally ANNINITION PLANT. tiff its. w. rt 012077
MNC= amw a Pam Pam"
-PýIr
lentItLVL UANT
7774ROUSS42YING
tin SOYSold at tammejejure
wn Or-
L000PULAW COMPONTift _.TUTS V m ill All
ORRALLUA
Iles& MIA K/A # 12 Of! Itr Wlewftal-_ýw MIA PIA S INV I hr
IDEGDN N/A OF PNPSLMTAkardit MIA I- DIA"Aw"004 -22m MIA MIA fral 10% 1166
n-ni Dan&- U/Ccj VIA 1.62Fr,&;;i t MIA Rik n -nit ffal lani: ILDX Jxroun 70 -in 151o" I 10OWN
1* vreseuTe016tuxe 10 0Ash INIA
lir
17 AMFWVjj ww"m
ind) a i via n 11S.0I I I WIA
+ MIA
Theme are the closed bomb results VIA .077 pmm 3/86
for carpet rolls cut to stripe of tiýA -062 .077 RE 3/8WA *3/86dlmnslons 7.5"z.125fix.085".
700 cc bomb v1th a 0.1 go/cc loading X/A .22density. - sigma/A 7 -97 AFL3
I!/A 15.8 114.65V PACONO WW&" WeIRA ILAN wn WLAQ_ 1271&fi
NAM" Candelilla wan La used as a lubricant during extrusion and say be, present If'the Propellant In trace swunto. Propellant composition results are fromanalysis of carpet coils.
Signed by elopment EnSIVAST
40
MYSI LINT UINITISE PLAIT. hAIhIS. Ua. v~a 1Aawr27
I :'~' A-. I~t Af II -" IV- to 4U U -Fre r&Ukrh~itn6
t PvrCLSITU
ftesluf NO lU---TS 4 FlWSIES "e smu" AM WTI"al
CadeWV a W L ~a m use a.0 a urcatdrngetuio n myb reeZ
Signed by DOVMIA MIA I& JO eetMIA. Iiketc
E C D NN / Av I -t m 0 M U M M I AI 1 f4 1
MJ./A U."y~u svtl.nta "alo
.* = I-U
densJIM 3 0+M
Uigne by Dvelopent "boomeWANirkpetiiFbI
ROCESS-42Y~
ft~~~~~e5~~~~as'~~9 gVss ' iTSS GlISW im igc gIM -_ _ __NIINPAT,11IO V.ucnrat927
Nlt~oc l~ulps .EJILJ....
in.2L..... RPM 11... LSL..I. ansem P" w m 1ANVls
of dmmnsous7. PROCES~0S'
loadi oal desi n
nooo CeMPNdeli Mr ~sesd IF FUA I luria t U me""n~ Alrso sdu e ptresn %as
-thoel lroells n Win Wrc I&ns rplatc~s~sarsl aefo
af n alysts oA cApe be-ort.ltis16
G~igned by. 3V. kkaanic
RADFSSP £131 £NUUUITWMk PLANT. 201111I. VA He"arvml1 Subcontract 932077
Ti P FSEUI PULP OFT
Witt tceelluloaEECI ____I___________j-n
of ~ ~ MT of~won 7."ItS".SS".e -u70 c ob ih dLmcloaiag0enit . __Is""_
jLL&_ 42 puug MEm o-00 c
AIa VO'r a . oge YIh
31 Pounds
F811 ARMY INNINITION FLANT. RAIFIRN. U. Honeywell Subcontract 932077
Winea "wool a a&" P"A" ""-a
Avg tons-80INUFACTURE 11 SILVIUMS FROPMANT
TUNU7.,
WTI 110U@
oad JjU-ed Air Drv*-- tin AIF
Hold at temBeralgro -gol down for mazling
NOPIUANT 900fterim I,,., M.TS OF FW9*91 *WrLLWTONSWU OMOA
luloal 42.68raffIsgarin JAJL--
DECDN =JL.kkarlýls w1k n-77 U-LAL
haeftmal a. Dens. feeGrapnlt* WI& liani: M
G-12fts TN 9i cps q a JIL 0.260
1 W/A VIA 0.10
I VIA VIA
TM
ROAMSVIA 11
I OVACM 01 VIA I -
IU6.2181 NMI. UL 40 W/A 1-ft7i n97a 0 N/A .113
eb N I N/A .106 -fiqn 0=0 3186 - IThese are the closed boob results ob, 0 1 N/A .. M "Afts3/86for carpet rolls cut to strips N/A 3186of dimensions 7.5"x.125"z.085". 1700 cc bomb with a 0.1 Sake It 111k 4.95 O"NO
N/A 2 eMbpraftloading density. _N/A 23-33 130. a POW"846
"Ps 40 !he NO COWAfts Wood Dow No. grie; Ila n 177IL6
UWAM Candelilla wax to used an a lubricant during extrusion and way be present tothe propellant in trace amounts. Propellant co W ditiOn T48uLtG Ara fromanalysis of carpet rolls.
signed by Development C"InserON. KIrkpattiCk
W.45
21-20 7 Fort
WA
1111 AM ANY911TIll PLANT. SAIF111. one"m1l subcontract 932077.............
41961PIM WhWW W41140M weem cam" a "am Stamm =-Q
not itAlý % 3ft
q. 'MIN "DICO
2 VA IT
ad Forged Atr.DrX
at tooveroture-dow A" aes"Iq1tv
"OPILUNT 901111jos"M U'?" Tun v 7MM M AW CAL IMS
250 Mal upr-delyt-OWL, ..... 11 -ILA IND FuMeA
W/A Ilkrdinir" WU n-77 1wr1w to-0 IýiI)esluft galdo Ln% Ubs. Dens. (a/cchit* JLML allani:
!Mae 2i A CBS I IRLUý U-263
UIRLINT MOW 091-I go? 0jawle I lot of
I
1493.010 -1971!145 1 126.55 106. Z3 -toup. a& le VIA
MAO&M -13B M0 I we saw&1111LAW VIA .091 Pam 3/86
These are the closed bomb results N/A- .077 "APIM 37116for carpet calls cut to strips VIA 77 Opole 3/86of dimensions 7.3"x.125"z. /A .22 -1.51 pus700 cc bomb with a 0. 1 SM/ce NIA 37.97 3U.-loading density, H/A 15.30 14.B
so owesie COMAPM U00, 11) 71 L 0.
1101ASKS C&ade1111a waz is used its a lubrIcaut during extrusion and wal be present tothe propellau in trace amounts. Propellant composition reou to are fconowlysts of carpet colU.
sun" by MgInserON. Kirkpatrick
W.46
U40 t Part $Uck ... ...
WA 65 PWAAS
UINF111 AINT ANNINITION PLINT. RA11821. VAL Voneywel2 Subcontract 93207711THIM113 7-T.-
SUMOON F4 a P&AM R&AX" ""*-Q
5fix I
so JIM. S
h
in'ýJ'-wrme'-IMNUFACTURE 1"OLVIVIESS FROPEILAIL.-;:
-DRYINGd d -Air-b-
11%rr - -Sold ON, ors"reiLlmCoal gmen for an;14vt:
of FORD FWETWTavow #WAWA
W.
AkArdit 11 MIA W A n-77 PIP (Pill /NMI "I& I I A Imagns2lum gildg n ni be. Done. (let/ccGrauhite aliani:
T% 218 tv 10
sturs I MIA VIA U.1U
I VIA
1 jrh IUP I
I Y
wZUiZ sonE 72-135 =0 1 2"!5 Users MIA -Ini P'MXO 3/86
?haae are the closed bomb results top VIA "A 3/86for carpet rolls cut to strips VIA furnaLwo; 1/86of dimensions 7.3"x.125"x.085". W/A sm -8-23 O*uOM cc bomb vith a 0.1 go/cc UCSFT1wloading density. W"910
H/A 18.57 1"MTM Is Wome CMI&WO wool -771Lfi
WOAW Cando.1111a wax Is usod as a lubric ne durInS extruslon andXlbe present Inthe propellant in trace amounts. Propellant coupooftlon T u a are from
analysis of carpet call@.
Signod by Development Ustnear
O.V. Kirkpatrick
29. W.4 7
2R-20 it Perf stick(TAO NCL16"008-001
W/A 700 PoundsNAP ME
ARVIT M ONITION PLANT. SAIIIII.. 1j, Sin 932077
off"686 Como" spasm 11"am a".%295089: 95091; 95092 IMA sea
11 Alis
-- LL12. %M01 ft
MANUFAMU'REIF SILVEMISS FROFELLAVT
Pus., - 4FROCLSS-11YING
itiinow c d Forced Air brv iin t S*F
110 F 11OWT lHold at tezveratureIF Amblen Cool down for sammlino
ftO"L6wCOftOQvvM TuTs or w1jas R FEMOT rMam Am MTOC" VMScoewflmv -066 ULA MM&
Nitrocellulose a!?= 0 120*c- cc 40, CC 601+KitrovIssyrin /A Fuses ELLU-DEGD% i m p 29.24 ofto of POOPUL"n
-Oardit 11 - N/A N/A 0.71 j1pr (gal /&a) V An e s i utb Ox-iAL-.. N/A _MLAý 0.05 _,Abs. Dens. (g/cc fi/A 1.61
Graphite N/A NIA 0,05 Ta"llani:-K/A NIA 17.79 51ope 9 100MMMME
AchI N/A NIA
sture 0.2 1D.S 20.3SolubiliLX 31.40 1
02a HIRELUTIMOIRS Inic UTWwwasse ivsw_-$
~1k JU A R-n
-If% n/._o 01 NfAAN A"of N A n7,,%
vaýftaft W Malls-231 90 W/A noo n
@Maas 1 8/86NIA .206 SAMPM 878ý6
The closed bomb test used 2R-20 In the par RLA__ .075 no ow827 form fired against the 827 standard. 4.4 M/ 8 6
F a ='% W/A .9.57700 cc bomb, 0.1 gm/cc loading density. Le JI/ .4
N/A 30.43 t 28.21 1
Wood Sox No. rrier lag N, :arton No. 327146
Candelills wax is used as a lubricant during extrusion and my be present inthe propellant In trace aviounts.
48
_______ VAUACUEI FSL(UESPBP-t
W iNW r Te~t .~VtI ~If
____ N/A______ 790F"s jh ~ .~k.
IA 1111iu OxId. 19171 FIT A11.V.92
_________________ ~1Oe UJONnfVWE*JLL,
&UPMSonXW"W U!99611 C0101 aPam aw"""t- _ _ _ _ 9591 959-400L
__________ msoma mj- _ _AU-
The closed Hom d t at us aed 1-0 nthre *.* .6 .B ~8
theD prpll ? in 1r.24 P04,unts.PLAW
41H9TOe.4
N/A Pounds
11OF111 ARKY ANNINITION PLANT. 201111. VIA. Haneywen sNbrcntr&_- 932077
- JUVM $do -W"ng 011601091 "NMI a O"GO SUMM95099. 95091 95092 Us Soo
sw lag 46k. It" 00
VANUFACTUR of ISUV 01 IOPILLANI I. -
sad Foued Is Drv
JHold at teaRerijure 4
Cool in f2r SýM"149%0
flo"U'w C800981"WA- -.7. TUTS of FOUSKI, FWUT I "Orin we ONVOCCAt It"S
KIW&A
Nitrocellul;,Se NIA, 0 1200C rc 40,'UroalUrarfm A". tieg .. ý XF I hrDEGDS .11L. GO "O"L"IAk r-dit /A MIA D_ 71 1 VIA lifil
-4 tA I W/A A G. fts. UftcGravhit* VIA 1.2"ý Tallani: -Rviv VIA 17-7a 0 a v 00=Y12A 4th NIA, - fiýnqM isture DS 18.1 0.2 1 1
_C1 ColubillevIN/A NIA 31.40 1
SLIM-NMI ART 912nm ft-LOT wimall IWO so I
for I -In - i -F 101 .69 1 Plow~ SO sallhe_1610101k IUall I In't A-14 too lu .6 1.6i ntA -24 a) MIA
to -
IS-231 1 90 WýW% MIA
NIk 41 VMS 8/86MIA "pas 87rbý
The closed bomb test used 2R-20 In the MIA -",&1?86827 form fired against 0 827 standard. Y/A 9.57 OWNS?700cc bomb. 0.2 to/cc lo&,.izg density. Ul I
.UL 2- _77.3N/A 30.43
TWW# so pace wbod ROK NO, rtan No. 227146
Candalilla wax is used as a Lubricant during extrusion sad Isay be pcosent inthe propellant in trace amounts.
OJEA
50
R AIF1IS ARIUT ANMDUITION PLANT. U1111211. IUA. *27
"d *.. .. !- -~~~~~~~~~ PamQ1. MAWe.ae tWrlpanv ,t1f
395089 95091 9od5t0e92atr
*T~~~h'~ov 13ie 10o 1ov for*an1r.-
- ý "NFMU=1MRS RPUN
mSWPMU~Cuut~mu Foocd Air Dry374,Brre aN.3701 atna
M-troenpropelln in trcIinn
DECD MIAVIA10" f 1906OL51
1*F1,11 AINT LUNhEIT1lI PLANT. OAD1133. VA. 927
009-~~~ 959;909 AO
~~ J **.4v 13W i10 10 CLhD...... £LW..US
1* 12*, , un tlai VT-
P'.~hy ubi. n Co al down-t T M 3.4 _________
N'tiddleas @il .07 .069zL WTh21e arI clse bobtsrues12 i h .. L..es. 7T~
527iu for fiA aUas thes Den7 standard.U
700NI 17.7 bombe 0. gm/c oain dnsty
N/A NI2.96g
-ithe pr2lln is tr.c 1mut.1w)
bylag ElSglu X/AXIA 152
f~illS HIT 15111IT11 FLAINT. SASFSS. VA. HIM "tat 32077
1*, - 4
TU't~m ITS Pw UMSMEN PWPLAXT POW" US PO UPS
62 frormll~ Iie atins 12he 627 -tnad 4, CLJ7,:l
thresU poxielln inA trac. amoDnsnts.
Grasht* 53
2R-20 7 pri-r Cranul.irramw wwý 209 Pounds
1A
gs(.11
932C771111011 AINY INNINITION FLIN1. 011111- VA-BIT lagiv
)89. 10800,00 COMMS 6 MANO M*JFJM ISUOU
9S(0)89- 95091; 95092 W fiean .LL13ý it 'Noso .JJAZ. 0 SO
CJS*§ Alt IDES
0 F Nold at t *=P*r U"Amblen coil 3gyn for GAP_-Q3ft&
N0004"I C0109109%ft I %ýF -MTS W FWSHEI-MOPELLM E EVIA Sir all 0 1
a TuResEGDS to" at PWII.MVkardit 11 W/A 0.71 Pr (Pal twal v U.
mid& VIA VIA a-OS AbS. DOM. (afCCM/A VIA Mllanl*MIA VIA
SIAO.S
;1txTz"O H talubIlArvINIA VIA --314.40- 1
MKILLUT IMMEXPA __Hft #1L
I -4n -1 00 -47 alsoAhas OU - N/A
04 In I n,& i % &*A Me 01 WIA 4
F I poll Ska. 10 IMM I20 1 IM&OK I SUNK eb Avs NIA .272-
N/A .0715 .066 8/86N/A .072r .077
The closed bomb test used 2R-20 in the A
627 fom fired against the $27 standard.700 cc bomb, 0.1 &=/cc loading density.. owns_,
w NIA
"'Ps v face%* CaRtAme- 652 DONSAM Candelills wax is used of a lubricant during extrusion and my be present to
the propellant In grace se"ritse
Air54
reala SUll ANKUINTISK PullU. Baxolot. VA. 1ttv=wuPar&t077
.4MANUFACTURE If SORiINUISS ROPUL131
~ ~ Load- F~rced Air brv
Hold at temperatureF Ambien Cool down for ganl~Iv. -
UJ. JLULS OF ..2. CAS)K 113LU &M am
OuterF I/ .02 .07 NT h
E27 VIAm fire aMane the 827 taard
700si cc id boIA 0.1hr gm/cc loedi. de(iy.lccj
ahiteTallni55
PEIL- 14-t4 PX I b zi.1;kkru ZM KC. 7J3369ýr-7 _____
PROPELLANT r SCRIPTION SHEET I Z~1P 1
*01~f 1-16 19 Pert Stick &ACA7OWw0
R ADFORD LINT AMUNITION PLANT, RADFlRD. VA. IKOD*Ywel, Subcontract 932077
119SWfl nQVV7 Q"flmf. Qafllt. obffl 00~wcwa e im .p~
T5~ T~ Extusio CarMusa
'rI IN- 1xtr0towoi
,,A~ur Igm I In_______________ -o o0 1af
&~~.LCSD Sb S f o.rpliIp ic a
13: -Ex .. truUE 87IC~~ o n - Dl
prop1SCSexist InA traA aao0tu
W/u&uU Xy. 019 off ealIre 07 -1
No. ofZrf 1 I
***O 11*O 2* 4 U IS a) VI56
PROPELLANT DESCRIPTION SHEET EIUMP PA, A 1.*W~!A1 49fl
7-nn~a672 Pounds
RW' AOFOD1 ARMY AMMUNITION PLANT, RADFORD, VA. HOfGYlywl Subcontract 932077
Canelila ax s ued s alubicat drin exru COn~ and maybpesent in the-propella; 959;_59 tr"c ainianta. NO
AIC50 OM 160 Axtusio 77 57peRl
I PROPELLANT DESCRIPTION SHEET TiuP . 116 RA '&Zf2R-20 19 Perf Stick wyA7Ainn
W~~v~~cwe1IWW &Mown ~W l7-lf7
RADFORD ARMY AMMUNITION PLANT, RADFORD, VA. j Moneyvli Subcontract 932077
wvoo CO~ W avmal 111"am 114w
T13.0 siss .xso i
VC OFST DFFNSNEDPRDELLtas Pk6m ewySGM IS
0.05 USE Extrusio - Die
n1 t 10 82 rmfiedagainst th 27 inr J.16 .
cad ng WM desiy Carto13709 0lrr6rla
U~SAINIISSP1 Devlopen IN/Aee Progam 0.Manseagern4
AVITAL FORM0 &I4 11111 18 1 1.658
PROPELLANT DESCRIPIIU bnri ,, I2R-20 7 Perf Stick 6H&WON LA010-006
VC)McOvll maj •r 175 PoundsUonny•u.1l MIu~ltre* t:.1U nlf7.f?Q .___-__ ........ _______
meM RADFORO ARMY AMMUNITION PLANT, RADFORD, VA. 0oneyvell Subcontrct 932077
' '- ' "1"d"€~ N1
B95089; 95091; 95092 .s -4 0,
.__4__&,_. [V013. 10 3D
145 155 E~evenspeed Ao1lInv - -
150 160 Extrusion - Carpet Roll i iT.3 155 Extrusion - Die110 110 Annealin. 24n•a -
noPr,,-.d, cOMoms,.o *.::.:•-TE.STS OF fINISIED PROPELLANTI.:.-, ' . m
________ Z14=1& VOLONC RMue* WoItS .OMULA At'U*L
NITA0C. LLU LISE N/A 181A 50.64 OuT cc 40' cc 60'+
111TROLTRINL N/A W/A 11.45 Be Fouts NF 1 11r -M uTI*II1TTLENE 6LICOL aiNITIITI N/A N/A 19.24 FORMof noaDeAM _yl___._
aKAIIIT 3• N/A NIA 0.71 "TALIANI 1.1 g/se .l l l l ~ g l l l' lN / A N I A 0 .O .5 s'e t il l la i
"' lPUITI .... N/A .NIA 0.05 all eroi / W 1163In/NA VIlA 17.78
TOTAL 10O.00 _I___ a1__1__ _, _ _A 1.61_ _!Moisture IN/A N/A I n•1nAsh 1 WI/A W/A~ 0-09
Methvlene C1 Snl"hbiItj ../A L1. 4llA__
L0USED BOW..,.-,I FROP MT IMENSIONS Ifi 631ahLOT NUMB2IE j IMPAP -F $eysAD.DIVI
n' SA* I=0.
-4 n-iin- PSRIAEIEI PIOPICASO -M on ImrU
-4n q7_47 I WA .A.1 U2NG W NIA _n "4IA I
- closed *.1h.5. qfR1 I. 5 OMM I. .395 .386 w/A 11.57
"I•OA- - 1 A- A .080 .077Outr NA .0B ,8 ~~m18umums The closed bomb test used 2R-20 t..oL P/0 n n=- 1/87'
the 827 form fired against the 827 .______standard. 700cc bomb vith 0.1 gm/cc ,/A 1.
oading density.
jDAd N/A 15.Ro 4. 70
ToMW#aect.T.w Carton 327049 ; Barrier 5ag327202; 00 x 327088
Candelilla wax Is used as a lubricant during extrusion and may be present In thepropellant in trace amounts.
seaUU op1 Developmentr
ARRCOM FORM 214 A 10 AUG 7759
" PKDPLLLAt( I VLbbKIr I lUn anr.r, &O"POblt4• ' ' 1181811+•llli ' a . o,• • oe
•ILeT.sIip,' 211-20 ... ]• p?:,+ •tlck e•a•wuso•,,iECLBTCOt.0-007
" •Q I• I ,mm•m53 Pounds•0" IIDFORD/tilT AMMUNITION PLINT, IADFOIO. Vi. Jione•el),Subcontrsct 9320??
• " i i'i:" """• flIT|0CELWLDSE !]"• .+' " ."" .... : • • m I• e• na'°, , ":'+:•, :•• -':"'• •'-'•"•<<:'• .4-.-: ..• -•-:•.. ....... ,+ . •+..
Emmooh LI• =I, IIMGm IIIL•TeT Pa4.1*T•i ii
|95089• 95093i 95092,, ;•. • ,, I•m___.• ,, , k.
im • IISL' ,,, ll•
l•S 155 £venspeed Roll•-, - - " I/
150 160 £xtruston - •rvet Roll , - " I
110 ' 110 Anneslln| ,,, •&O "•
m /
nlT||CELLOL|E[ NIA H/A SO.• m,,v cc &O' cc 60'+ IJ IITIli•TCElll I(/A ll/A 11.iS el lll(S INF I Rr ', NF 1 Br !
|I[IlTLEI[ |LTCIL illtTliTt R]A H(A 19.2& poel • peOelU,,mmr t ' . ,, CyZI|,l!ilt I• H/A N/A 0.71 . "TEUEil EI.I IllS" , .•9 iI
lllltSlgl l|ll[ Ilia •IA O.OS lille ltlllmm .|U, lrilt[ N/A •/• _0.0s ,act e.ll• n/, lz63 ..... ITrot NIA HIA 17. ?11 'I
'" 1111'11. 1• 20•0 lU ,[,Sllrl.lee °.1. 1.61
Hoisture " I Hl• IliA • ' I•sh p/A •/A ,, O.n9 iHeth'vlene C1 Sotub•it• N/A W/A •1 _In
I+. |
i i ° i i " " n
•-::::,.s?:::--:.-!.:::::-:.::-.:.::--::?•: :CLOSED, DOMG ,.":•.-•• .+': ............ | .•+ : PROPELLANT DIMENSIONS +".|mt•e$I ......I. +....: ,, •• II•LTIVl
to• ,w..u, J •u,, , I RQ '•';I +m my. ,, • I I.mr " .,'.n ranm? II•1 _mq t PllJ, lltll I mommm -.. m w mr.. " l,•e'm.LI
• l.qn q3.&7 ln'•./,• ummm ml• .•+Dt 4__7A m/• I N/AI
. ÷1,• q6_ml lrl&_Vr• a•ulnm ula . _6q• •la I N/Ai
i•*"=" - N/^ . _n• .]nL .m 1/87
imuM.s The closed bomb test used 2R-20 •,<aa•. •;1• - _•n• rmr, "••Ln the 827 form fLred ags:Lnst the 827 t .... •1, .• .10•!standard. 700cc bo• vlth 0.1 p/co -• 87•loadtlug i•mstty, i• T)!f[, P" Ilia }Ilk 7.9S o•nm
):d q/X •n • PzB.2! POlar-----,
meenoe0,•T,,oco4e•,n•n Carton 327310+ BaTtLer leg
Cande1431s vax :ILs used es s lubr•csnt durl•l extTusJLcm amd =my be present /n the |propellant •Ln trace 8=ounts. I
t u I I I n
III
I .,; ,.,]II I II I
IIBP•M [film $1d I 1fl IU• ?? 60
n n u i I I I I I I l I
rKurtLLAR I &9tmodrti oun n68a s.1k
w*j3Vwff M~~p l flfl,. 02967Pud
am W "Uamm" S 13m *II104.1
150 O~ 160 Y AMMUNIION PLNT MUM.e VARoll=1Sbcnrct92
T~mofh" 11aAnaln
IIITULEIESLICI IIUTIAT ORE OFA 38 19.2ti s a u ftpittaifl
-ehln %l £eluhf 20t 1~
150____ 16 Extrusio - ~ ,~ CarpetTE Rollao - un'
1 Cand llb l , Extrusiod -s a D rcnieligetuinedmy epeetI
propellat in trae a1%.9
US olouSI Dw lopuent L944ee? )UA M
A3IfMIEL 1 NIAM 0." cc 100 cc 061
601 Brim"
2R- 2(j 19 Pvrf Stirk ECL87CO10-009PALAW &WANWI
-0 54 Pounds_W"N ýIftw=
IRADFORD ARMY AMMUNITION PLANT. RADFORD. VA. Nontroall Subcontract 932077
W"oe" to~ aj 11"Lat 0 A"h Ww""I lak a 4.
a 395089; 95091; 95092 jd1&LL S 4"j M
95089- 91 ft"L
13.07 SML SMNL&V@ 13.10 30+ ON&
20 1
145 155 Evenspeed InI14"ole '
4-E5O5 in
110
160 Extrusion - Ca!Ret Roll-Extrusion - Die
110 1 01 mnealinit
$'screw ST&N&M AND "IT16c" UPSreorauAm compourtm ..---ý-.HSTS OF MISHICvi-"hl 0#4""1 . . OWAIULA MWALC060FINUM logamn "M
N/A -- N-7-k- NUT cc 40' cc 60'+W -I,- NY 2 IF
21711118LIC111111 NJA W/A 11 .45 Is tests RriýSW I A
r
1111151L1111 GLT91L 911171111 W/A X/A ý19.24 Poem Of NoMuff119AIIII 12 'N/A 10A 0.71 OTA1,19111 1.181/08111AIgn
- ;.y511NESINK situ N/A N/A 0.05611AFNITI H/A N/A 0.05 _101 pal Irs Trwany WIA 17,711
TOTAL 100.00 111111 1111111TV VIA 1.61Moisture N/AAsh N/AMerhylene
... CLOSED 810MG ... ....... NT 01MENSIONSto? "usaan I amp op RO
ACTUALUST -L" Qn-47 WM g47 -4 &-A UW&W luA7 Q1 -&A 2.10 -2- 'AQfi -rn I nL _,2 1; 191"Im M .6 0 IN/A
I Mo. am is AM- SAMWASNODAID inn-an me"% NIA noo _nQ7
VIA nirý P&a= 1/87usLA."$ The closed bamb test used 2R-20 VIA InR nQA I I
the 827 form fired against the 1127 VIA TLP " 7117tsudard. 700cc bamb with 0.1 Sake Diff W/A N/A 7.95 onumceding density. N/A 3.00 1 3.09 DUCRIP110"
0N/A .4n -%
"rimpacmeawumst Carton 327310; Barrier Rag 327041; woo, Dox UIJ
Candell.11a, wax is used as a lubricant during extrusion and my be present In thepropellant in trace amounts.
sonarveset Development Engineer
W k
sorrim room M I In Alit 7762
t'KUrtLLArII Ultbkoarsuun OflLL1
F o p atlf 24-ZU In Pe f stlE k hta " RC 8 r 1 -
~"RADFORD ARM! AMMUNITION PLANT. RADFORD. VA. Nne 112 Subocontract 932077
595089; 95091; 95092
~ COMI3U~ ...... :.:ý::.:TESTSFCtQ OFIISNDPDELNTAM1 Y5 Wl
___________ U*1 c4O' 211 '
IN .L .... ...4.. 007 1h1AU 4"am/a
150____ 160UTE Extrusion - Carpet Roll
Candelill Exruio -ame Dielbiatdrngetuin dmy epeeti h
110 110 Aznealines
*uirgnumiopu f~I IRIS HOE PAfiLL LUG" 107IFN a63UA M
PRDPLLLAN I Utbowur i un on., ac8C0021-20 19 Ter? Stick __CL87________10-0 ______1
UfM*yw~ W.ltpa W5 t*7O2Q62 Pounds
U11AOft ARMY AMMUNITION PLANT. UASUM, UA. moneyw12 subcontract 932077
_________________________________________ GO ~uM to 81*01. p~aikI 6"4414
595089; 95091; 95092 #"Jo -
~ .JLSL ± i..'m .......................w..
against 52 _____
o1d0 de0nAneali.
WPROP [email protected] Ca rton"ftST 3204 ; B1rrier SI.532720TWA
Candelilla~~ Swax; vsue malbiatdrn zraieuadma bemrsn" hPOp4llan Lu0 trcc amonts
__Ntfl 12-45 of4 fot FIaUIN ID AU9111I111 Rci 111110 WA VA 9.4 pem00PROI64I
Auti it- W/ W/ 0.1 *1111111 .1.0-0
* ~PKUI'LARI ULwIotrurwn emssi _20-f 19 P~vf Stick
w0ealnnaln
ftPLunCCMP1sANY ANNTESTS OFNT MIINHD- VA- PELLAKT Subonrat 93207
LtSA'4C; 00a9gp 5092 WS3,13
uIL ~ Extrsio -j Carpe It61oll eg
1 auelll Extrsusiod -s Diercn urn xrsonadmyb eeti h
propellnt in ~ace lmounts
w DevelVIAfi NIAN 50- cc 40' cI cr 65
rKurLLLAR I VL~komr asun on&.&. i
'It~~ ~ ~ ~ - o IIqf fcrCLe7C')10O!13watiwev.m¶ rli, tnVA7. 029 58 Pounds
R6 ADIfOil ARMY AMMUNITION PLANT. RA111OID. VA. INfbWVW22 Subconltract 932077
[395089; 925091; 95092 Wie' -......
rrrs 110 An0eit ng
SIUKYtUE SYCIL IEITITE ElAVIM OFA 19.24~-LO Paaae mottj ______
15_____ Ev line.AT IESIN lt
u~aN. 160 Exrso *a..~..- Cape Roll..*~~** 13
1.h5 coEdxobterusio d 2-2 Dier' ~
stndAd 7MIc bomr cct 401 cc 60cNadIA density.M F a
11INTLIEpaem Carton 327049 ;I W arie N/A 327.24 0011 FpCandlila w Isuse asa luricnt ar~g tusin an y e peset I th
11o4e1lait MIA traA a.7 01nt.WaI12ilm 9asiY'lS beeomeEIA MI 2.081311011 MIAl .0 -al Cal Aam */ 66
* :.rKUrLLLAR I &DL6%#Kr a wun onflL1
kaDFDRD &BUT AMMUNITION PLANT. RAAPR33. VA. 1fevllS~cnr
130D 160 alru~o -l DOW". 11o411
358;5C1;T 9502 S U 13. T1 ... *use ... 16
-e 131230
sad5n tensitn.
160u Ext wvs~Crtson 3204 ; arre Rlag32
41a.d0lilla Eaxtrusedn a- D urcn urn xrsoadmybepeeti h11 ropeellan ntceint.
uawwa me Deeompment ý---EngineerIHE PDPL"P LA'vr~
64CO cOR 40l1AU' 6c
*r~turLLj#n i urtvi~onor ov %Pi68b6he2A.I
2 R-20 Carpet Roll ECLS73010-015
*~n~.I11q,1t4a E~5 f57.02955 Pounds
RADFORD ARK! AMMUNITION PUNKT, RADFORD. VA. I Noneywell Subcontract 932077.4/.P 01"OILULS Maim. .-
MANUFACIVIE OF SSLVEIrILSS PIOPEL-LANT
14.5 155 Zverispeed InI I I. -
- - Extrusion - Carpet Roll
- - Extrusion - Die
*1ý-.TSTS OF "&MAU"~ wePLLM _______ sPI.;j..I p,..t.;e 9.*aG
Comma~_____________ 30wtt an~W slaN@ MI*L ac
BITU SCILLS LIH N/A____ __A42.0__40_c___ 0
6ITESULT911IU W/ A 13.12 as FINIS I_____FJAL_
1I115TL1UI 60ICUL 1IUITRATI WIA VIA 23.16_______ _____
SlAP~sv 331 NIA, Jj/A 0.0 0S in ea1116611WA __Aon _ca__1166
* hTAL ____.3__ US_____1.6
Moisture VIA___AIForm _f____v
Ash _________ _I_010 *Ddotrech1
-CIOSID sumE PRPELNTDMESIN_-_ctgY wUmeui I umIM I Ri2w IV
mnoaevS PE-.472..138 see Mo m d I /
C sdbomb vas shot using carpet roll &AP
cut Into strips (7.5"x.125"x .090")Tt#"Ifired against the 829 standard700 cc bomb using a 0.1 gm/cc, loading -W/NIdensIty. DdNA ~ ~Mi
Of PAamCI OOAWN r-~p ~I'n
Candelilla vax is used as a lubricant during extrusion and may be present In the
propellant in trace amounts.
61"TW0IDecvagup ent, Englineer
D.W ~rkwpatric4ARACOM FORM 214 A 10 A1C7 68
REPCRTS .OWFZ: SYSTEM
~ au~'u'~v' EME9P. PAOLA 'PROPEL DESCRIPTON HET AN 2,-,
TONPOSITION: PROPELlANT JA-2 19-PERF HEX GRANIJLAR .. ' T V•BER: RA-PD-:90-1
SPECZrICATIN.: OCC-P-64:353; ORDER RELEASE NO. 235-92, -11192 PACKEC AMOUNT 5.5 pounds
MANUFACTUREZ: RAZFOR, ARMY AMMUNITION ?:AT,, RADFORA. V:R5:NZA 24:4. :ZNTRACT NUMBER: ZAAA09-9:-Z-,•C:
K: STARCH STABILI.YACOEPTE: BLENZ NUMBERS %:-R3GEN CONTENT fsso"4.
BB 95S39, 69 95€54C. B9gE:54; HAX :." 4S* NINS W: INS
MIN .3: 45.. WINS ,-- NS
AV, ..i3. 4C- HINS 3C. WINSI EXPLOSION MRS
TEMPERATURE. OF PROCESS- DRYINGE
ram To DAYS HOURS
145 155 CARPET ROLL AT EXTRUSION
160 17% EXTRUSION DIE
I0S 11.5 ANNEAL 6
PRCPE.LA14T COMPOSITION STABILITY AND PHYSICAL TESTS
Percent Percent Percent
Constituent Formula Tolerance Measured Tests Formula Actua.
Nitrocellulose 59.50 1 2.00 58.89 Heat test B 1200
C MCC 60' CC 60'.
Nitroglycerin 14.90 2 1.00 1S.S4 No fumes NF 60' NF 6C'
Diethylene glycol dinitrote 24.80 2 1.50 24.78
Akardit IZ 0.70 2 0.20 0.71
Magnesium oxide 0.05 - 0.02 0.03 HOE Ical/9g 1120 Mom. 11S
Graphite 0.0S - 0.02 0.05 Absolute density. g/cc 1.56 min 1.56
Total 00-00100.00
Moisture content 0.5 t 0.3 0.3 Form hexagonal hexagonal
Ash content :.3 MAX 0.i Numfer ot perts
Methylene chloride solubles 40.4 1 3.0 41.4
Relative Relative amli@J4' byLot Humber Teamp OF Quickness Force 4wvmae
P0-090-1 .90 82.7 99.9 MW ", *z "uu
LENGTH i in 0.75 M --- 0.736 6.25 MAX 4.56
0.D. (in.) 0.789 NOm 0.834 0.811 6.25 MAX 0.33
PERF (in-. 0G.27 NMN 0.026 0.026
STD-71136 100.00 100.-C WEB Iavg! :.;09 NON --- 0.1:3 Dates
i WEB :inner. INFC --- 0.12? PACKEC 11-9:
REMARKS: FIRED 1N A 70C CC BOND AT C.20 G/CC LOADING WEB imiddle) INFO -- 0.11 SAMPLEC 11-92DENSITY WEB lou.er) INFO 0.106 TEST FINISHME :2-91
L/D INFO --- 0.908 CFFERED 1-93
D/d INFO --- 3C. 69 DESCRIPTION SHEETSFORWARDED
WEB iditft ) 15 MAX --- 4.04
TYPE OF PACKING CONTAINER: DOT 21-C FIBER DRUM
REMARKS: THIS DRUM CONTAINED NET PROPELLANT WEIGHT OF 75.5 POUNDS
THIS LOT MEETS SPECIFICATION REQUIREMENTS
SIGNATURE OF CONTRACTOR'S REPRESENTATIVE SIGNATURE OF GOVERNMENT QUALITY ASSURANCE REPRESENTATIVE
0. ZEOLI ~C. N. HALL
69
REPogTS Zw-acl S'gSV.ý
PROPELLANT DESCRIPTION SH EETE ,N , "-;:.MPCSIT:ZN: PRCPEL.LAN- ZAX-1 .- PERF HFX RAAMULAR L.- NUMBER: AA-F-i-
SPEC:F:CAT=., 3C-P-64CSSB: ZRCEP REL-ASE N., Z3S-92. ',-Y9 PACKEE AMCUNT: 92.5 pounaa
MANUFA=.'RED: RA:FGRP ARMY AMMUN:T:.:N P.AN. . RAZFCR. !:RZI:N:A .'4.4. =NRA- UNUMER: AA -- C
K: STARCH STABIL:TYACCrFTE= BLENZ NUMBERS NITROGEN C:NTENT 6- Soc' :134.SO°i
98 i5539. 8B9S54:. 9a.iZ4: MAX "-:1_% 4i. MINS 30. I•NS
""IN : 45.- INS 3^ W:NS
"AVG '13.13 45. MINS 30. MI NS
EXPLOSION MRS
WMAC3 0 @01 OUUT3U 3SOVEL1M
TEMPERATURE, OF PROCESS - DRYING TIME
FROM 0 DAYS HOURS
:45 155 CARPET ROLL AT EXTRUSION
160 i70 EXTRUS:ON DIE
105 115 ANNEAL
PROPELLANT COMPOSITION STABILITY AND PHYSICAL TESTS
Percent Percent PercentConstituent Formula Tolerance measured Tests Formula Actual
Nitrocellulose 5.33 NONe. 5S.73 eaet teat 0 1200C NCC 60' CC 60'.
Nitroglycerzn 13.86 NC1. 14.25 No fuHF 60" N? 60"
Diethylene glycol dinitrate 23.06 N1. 22.72
It= 1.-00 NON. 6.42
Akardi.t 1I .6 NON. 0.74 HOE Ical/g) info 1131
Magnesium oxide 0.0s NON. 0.06 Absolute density, g/cc Info 1.39
Graphite 0.05 NON. 0.08
Totai 100.00 100.00 Form hexagonal hexagonal
Ast, content 0.3 NON 0.1 Number of perts 19 19
Methylene chlor;.de solubles 40.4 NON 42.2
Moisture content 0.5 NON 0.3
-m.. . .: :.-. . .-.
RelatiVe Relstive &'~Lot Number Temp OF ucnes Force "
RAD-PD-090-2 -90 61.6 101.1 AMORL
LENGTH ([in. 0.7S NOR --- 0.746 . . . 4.42
-O.. (in.) 0.789 NOR 0.634 0.802- •- . -0.63
PERF in. 0.027 NON 0.026 0.0126g~ ~ .
STD-71136 100.00 100.00 WEB lavgl 0.109 ON --- 0.114 Dates
WEB (innerl INFO --- 0.123 PACKID 11-92
REMARKS: FIRED IN A 700 CC BONS AT 0.20 G/CC LOADING WIED middle) INFO -.- 0.111 SAMPLED 11-92DEMSITY WEB [outer) INFO --- 0.108 TEST FINISHED 12-9ý
L/D INFO --- 0.921 OFFERED 1-93
D/d INFO --- 30.94 DESCRIPTION SHEETS
WU E diff %) INFO --- 5.08
TYPE OF PACKING CONTAINER: DOT 21-C FIBER DRUM
REMARKS: THIS DRUM CONTAINED MET PROPELLANT WEIGHT OF 92.5 POUNDS
THIS LOT NUM SPECIFICATION REQUIREENTS
SIGNATURE OF CONTRACTOR S REPRISENTATrIV SIGNATURE OF GOVERNMET QUALITY ASSURANCZ REPRZS•ITATZVE
D. ZEOLI G C. N. HALL
70
II
REPORTS N!Z Y'E
PROPELLANT DESCRIPTION SHEET "EPT PARA
-CNPOSITIOI; PRCPEL.ANT jAX- .)-PERF HEX 3RANULAR L.T W.z MBER: A-Po-:;:-
SPECIFICATICN: =C-F-i4C35; 3R:ER RELEASE :. 23S-;:. 7'- 9Z PA:KEZ ANCUNT: ;•nuds
MANUFACTUREO: RA:F=RZ ARMY AMMUN:T:ZN PLANT. RAZFZRZ. V:RG:N:A ;14:4: ONTRA-T NUMBER: ZAAA39-9-Z-0CC!
K: STARCH $TAZ:.A-:EP7E: 8LEN? ýUJMBERS NITROGEN CNTE.N 65.50o :34 50:
80 95S39. 38 9554:, 38 9i54: MAX '% 45- MINS M-:15
M:% :3.:i 4i* MINS 3' NMNS
AVG !-•3 4S- MINS 3C- M:NS
EXPL=SION MRS
nIusutIa c1 uI m 0 I I3&3 mOUZIJIITEMPERATURE, OF PROCESS - DRYING TIME
FROM - DAYS HCLPS
145 1 CARPET RCLL AT EXTRUSION
6I'3 EXTRUSION D3E
105 ANNEAL
ITI? of VM =Z•EDIROlmd
PROPELLANT COMPCSITION STABIL.-1-Y AND PHYSICAL TESTS
Percent Percent PercentConstituent Formula Tolerance Measured Tests Formula Act-.al
Nitrocellulose 51.77 NON. 54.48 Heat test 0 1200C MCC 6:' CC 6,'-
Nitroglycerin 12.96 NON. 12.59 No fumes NF 60' NF 6-
Diethylene glycol dinitrate 21.58 NON. 20.37
ROX 13.C0 NON. 12.10
Akardit II 0.61 MON. 0.68 MOE Icai/gl Info 1144
Magnesium oxide 0.04 NON. 0.35 Absolute density. g/cc Info
Graphite 0.04 NON. 0.03
Total 10C.00 100.C: Form hexagonal hexagonal
Ash content 0.3 NOM 0. Nuber of perts 19 19
Methylene chloride solubles 40.4 MON 44.3
Moisture content 0.5 NOM 0.2
Relative Relative t.. ttormity byLot Number Temp OF QUIcKness Force St- Dviai•c•Ok,
RAD-PD-090-3 e.i 1 11.7 SP!• '1r 1.3IRS1 1 ACTUAL
LENGTH iin. :.75 NON --- 0.760 --- :.9
0.:. ,In.: C.789 MOM 0.834 0.810 --- C 1
PERF .n. 30327 NON 0.026 0.^2-
$TD-71136 lCC.OC 100.00 WEB avg. 0.109 NON --- 0.114 Dates
WEB inner, INFO --- 0.114 PACKE: ::-3^
REMARKS: F:RED 1N A 730 CC BOMB AT C.23 G.'O LOADING WEB imiddle INFC --- C.108 SAMPLE: 1:-;:DENSI'!*Y WEB outer. INFO --- 0.1:: TEST F:NISHEZ :--z:
L/C INFO --- 0.938 OFFERE: -3
D/d INFO --- 30.16 DES:RIPT:ON SHEETSFORWARDED
WEB idiff %j IMFC --- 3.12
TYPE OF PACKING CONTAINER: OCT 21-C FIBER DRUM
REMARKS: THIS DRUM CONTAINED NET PROPELLANT WEIGHT OF 100 POUNDS
THIS LOT MEETS SPECIFICATION REQUIREMENTS
SIGNATURE OF CONTRACTOR' S REPRESENTATIVE SIGNATURE OF GOVERNMENT QUALITY ASSURANCE REPRESENTATIVE
S414N iý Aw. 1, Z7-
71
PROPELLANT DESCRIPTION SHEETO'NIPCS:T:ON: PRCPELLANrT AAX-. "*-PERF kEX ;RAjNUAR L:7 NUMBEiA RA-P:-:iC-4
SPEC:F::AT,:ZN: DCL-P-4:3Ya: :P:E2 REL.EASE N:ý I3-:. PAZKE:Z AMC-NT: :.: po~na.
0AW.FA1---r*REZ: RACF:RZ ARMY AMM*::-:z% FLAN-. RAZF:R: ',:RZ:N:A 24:4. ::NT:A2 NUMBE6 rAAAC9-9:-:-...
A::E?7E: SLENr •NBERS NTROGEN ZNTEN: 65.so0 c34 500
96 i;1511. 08 95i4'. SB ý514- M AX 4ý- M:N4S MiNS
M�-�- 4- - ,MNS M•_-
AVG 12-:3 45- MINS 3,- MIN$
EXPLOSION MRS
TEMPERATURE. °F PROCESS - ZRY:N-, T:ME
FROM TC DAYS HOURS
145 I55 CARPET R:LL AT EXTRUS:7N I16C 17C EXTRUS::N DIE
105 :5 ANNEAL 6
PROPELLANT CZMPCSITION STABIL:TY AND PHYSICAL TESTS
Percent Percent PercentConstituent Formula Tolerance Measured Tests Formula ActwaL
Nitrocellwiose 46.35 NON. 46.65 keat test 4 12Co: NCC 6SC CC 60
Nitroglycerin 12.1.1 NON. 13.54 No fumes NF 60' NF 6C"
Diethylene glycol dinitrate 2C..6 NON. 21.60
RDX 16.7" NON. 17.42
Akardit II C.-7 NOM. 0.71 HOE ical/gi Info
Magnesium oxide 3.:4 NOM. .33 Absolute density. g'cc Infc .6:
Graphite C.:4 NON. 0.05
Total :CC.:: 100.00 Form hexagonal hexagon&.
Ash content M.0 NON 0.1 Number of perts 19 19
Methylene chloride solubies 4C.4 NOM 46.7
Moisture content 0.5 No" 0.2
Relative Reiative .. tomi.jlt~ y byLot Number Temp OF Quickness Force US Deviation. 4
RAC-PD-C90-4 .9" 79.8 103.1 2M • 12 VSUmý AC £CIAL
LENGTH in. .75 NON --- 0.762 --- -. 5;
C.D. tin.' 0.789 NON 0.834 0.818 --- .54
PERF itn.) 0.02' NOM 0.326 0.027
STZ-7::36 "00.C0 110.0C WEB avg. 0.109 NON --- 1.i15 Dates
WEB !inner. INFC --- 0.lIC PACKED ::-92
REMARKS: FIRED IN A 71C CC BOMB AT C.20 GICC LOADING WEB middle, INFOo-- 0.107 SAMPLED 11--,DENSITY WEB outer INFC ---- ...21 TEST F:N:SHE: "2-;:
L/D INFC --- 0.93: OFFERE: !-;3
D/d INFO --- 30.82 DES:RFOITXN SHEETSFORWARDED
WEB idiff %. INFO --- 6.94
TYPE OF PACKING CONTAINER: OCT 21-C FIBER DRUM
REMARKS: THIS DRUM CONTAINED NET PROPELLANT WEIGHT OF 100 POUNDS
THIS LOT MEETS SPECIFICATION REQUIREMENTS
SIGNATURE OF CONTRACTOR'S REPRESENTATIVE SIGNATURE OF GOVERNMENT QUALITY ASSURANCE REPRESENTATIVE
D. ZZOLI C. N. HALL
72
No.of No.of
2 Adminismror 1 CommanderDefense Technical Info Center U.S. Army Missile CommandATTN: DTIC-DDA ATTN: AMSMI-RD-CS-R (DOC)Cameron Station Redstone Arsenal, AL 35898-5010Alexandria, VA 22304-6145
1 CommanderCommander U.S. Army Tank-Automotive CommandU.S. Army Materiel Command ATTN: AMSTA-JSK (Armor Eng. Br.)ATTIN: AMCAM Warren, MI 48397-50005001 Eisenhower Ave.Alexandria, VA 22333-0001 1 Director
U.S. Army TRADOC Analysis CommandDirector ATIN: ATRC-WSRU.S. Army Research Laboratory White Sands Missile Range, NM 88002-5502ATTN: AMSRL-OP-CI-AD,
Tech Publishing (0- Oy) 1 Commandant2800 Powder Mill Rd. U.S. Army Infantry SchoolAdelphi, MD 20783-1145 ATTN: ATSH-CD (Security Mgr.)
Fort Benning, GA 31905-5660Director
U.S. Army Research Laboratory (Uan, ,,y) 1 CommandantATTN: AMSRL-OP-CI-AD, U.S. Army Infantry School
Records Management ATTN: ATSH-WCB-O2800 Powder Mill Rd. Fort Benning, GA 31905-5000Adelphi, MD 20783-1145
1 WL/MNOI2 Commander Eglin AFB, FL 32542-5000
U.S. Army Armament Research,Development, and Engineering Center Aberdeen Provingt Ground
ATIN: SMCAR-TDCPicatinny Arsenal, NJ 07806-5000 2 Dir, USAMSAA
ATTN: AMXSY-DDirector AMXSY-MP, H. CohenBenet Weapons LaboratoryU.S. Army Armament Research, 1 Cdr, USATECOM
Development, and Engineering Center ATIN: AMSTE-TCATTN: SMCAR-CCB-TLWatervliet, NY 12189-4050 1 Dir, USAERDEC
ATrN: SCBRD-RTDirectorU.S. Army Advanced Systems Res-arch 1 Cdr, USACBDCOM
and Analysis Office (ATCOM) ATTN: AMSCB-CIIATIN: AMSAT-R-NR, M/S 219-1Ames Research Center 1 Dir, USARLMoffett Field, CA 94035-1000 ATTN: AMSRL-SL-I
5 Dir, USARLATIN: AMSRL-OP-AP-L
73
HQDA (SARD-TR/Ms. K. Kominos) 1 CommanderWASH DC 20310-0103 Production Base Modernization Agency
U.S. Army Armament Research,HQDA (SARD-TR/Dr. R.Chait) Development. and Engineering CenterWASH DC 20310-0103 ATTN: AMSMC-PBM-E, L. Laibson
Picatinny Arsenal, NJ 07806-5000ChairmanDOD Explosives Safety Board I PEO-ArmamentsRoom 856-C Project ManagerHoffmnan Bldg. 1 Tank Main Armament System2461 Eisenhower Avenue ATITN: AMCPM-TMAAlexandria, VA 22331-0600 Picatinny Arsenal, NJ 07806-5000
Headqumres I PEO-ArmamentsU.S. Army Materiel Command Project ManagerATTN: AMCDCG-T, M. Fisette Tank Main Armament System5001 Eisenhower Ave. ATrN: AMCPM-TMA-105Alexandria, VA 22333-0001 Picatinny Arsenal, NJ 07806-5000
U.S. Army Ballistic Missile 1 PEO-ArmamentsDefense Systems Command Project Manager
Advanced Technology Center Tank Main Armament SystemP.O. Box 1500 ATTN: AMCPM-TMA-120Huntsville, AL 35807-3801 Picatinny Arsenal, NJ 07806-5000
Department of the Army I PEO-ArmamentsOffice of the Product Manager Project Manager155mm Howitzer, M109A6, Paladin Tank Main Armament SystemATTN: SFAE-AR-HIP-IP, ATTN: AMCPM-TMA-AS, H. Yuen
Mr. R. De Kleine Picatinny Arsenal, NJ 07806-5000Picatinny Arsenal, NJ 07806-5000
3 Commander3 Project Manager U.S. Army Armament Research,
Advanced Field Artillery System Development, and Engineering CenterATTN: SFAE-ASM-AF-E, ATTN: SMCAR-CCH-V,
LTC A. Ellis C. MandalaT. Kuriata E. FennellJ. Shields F. Hildebrant
Picatinny Arsenal, NJ 07801-5000 Picatinny Arsenal, NJ 07806-5000
Pioject Manager I CommanderAdvanced Field Artillery System U.S. Army Armament Research,ATTN: SFAE-ASM-AF-Q, W. Warren Development, and Engineering CenterPicatinny Arsenal, NJ 07801-5000 ATTN: SMCAR-CCH-T, L. Rosendorf
Picatinny Arsenal, NJ 07806-5000CommanderProduction Base Modernization AgencyU.S. Army Armament Research,Development. and Engineering Center
ATTN: AMSMC-PBM, A. SiklosiPicatinny Arsenal, NJ 07806-5000
74
C mm I CmmderU.S. Army Armament Research, U.S. Army Armament Resewch.
Development. and Engineering Center Development and Engineering CenterATTN: SMCAR-CCS ATIN: SMCAR-HFM, E. BarrieresPicatinny Arsenal, NJ 07806-5000 Picazinny Arsenal, NJ 07806-5000
Commander I CommanderU.S. Army Armament Research, U.S. Army Armament Research,
Development, and Engineering Center Development and Engineerng CenterATN: SMCAR-AEE, J. Lannon ATTN: AMSMC-PBE, D. FairPicatinny Arsenal, NJ 07806-5000 Picatinny Arsenal, NJ 07806-5000
13 Commander I CommanderU.S. Army Armament Research, U.S. Army Armament Research.
Development, and Engineering Center Development and Engineerng CenterAT1'N: SMCAR-AEE-B, ATIN: SMCAR-FSA-F, LTC R. Riddle
A. Beardell Picatinny Arsenal, NJ 07806-5000D. DownsS. Einstein I CommanderS. Westley U.S. Army Armament Research,S. Bernstein Development and Engineering CenterJ. Rutkowski ATIN: SMCAR-FSC, G. Ferdinand
B. Brodman Picatinny Arsenal, NJ 07806-5000P. O'ReillyR. Cirincione I CommanderP. Hui U.S. Army Armament Research,J. O'Reilly Development and Engineering CenterB. Strauss ATIN: SMCAR-FS, T. Gora3. Prezelski Picatinny Arsenal, NJ 07806-5000
Picatinny Arsenal, NJ 07806-50001 Commander
5 Commander U.S. Army Armament Research,U.S. Army Armament Research, Development and Engineering Center
Development, and Engineering Center ATIN: SMCAR-FS-DH, J. FeneckATI'N: SMCAR-AEE-WW, Picatinny Arsenal, NJ 07806-5000
M. MezgerJ. Pinto 3 Commander
D. Wiegand U.S. Army Armament Research,P. Lu Development and Engineering CenterC. Hu ATIN: SMCAR-FSS-A,
Picatinny Arsenal, NJ 07806-5000 R. KopmannB. Machek
Commander L. PinderU.S. Army Armament Research, Picatinny Arsenal, NJ 07806-5000
Development, and Engineering CenterATIN: SMCAR-AES, S. Kaplowitz 1 CommanderPicatinny Arsenal, NJ 07806-5000 U.S. Army Armament Research,
Development and Engineering CenterATIN: SMCAR-FSN-N, K. ChungPicatinny Arsenal, NJ 07806-5000
75
3 Director 1 DirectorBenet Weapons Laboratories U.S. Army TRAC-Ft. LeeATTN: SMCAR-CCB-RA, ATTN: ATRC-L, Mr. Cameron
G.P. Ollara Fort Lee, VA 23801-6140G.A. Pflegi
SMCAR-CCB-S, F. Heiser 1 CommandantWatervliet, NY 12189-4050 U.S. Army Command and General
Staff College3 Commander Fort Leavenworth, KS 66027
U.S. Army Research OfficeATTN: Technical Library 1 Commandant
D. Mann U.S. Army Special Warfare SchoolMr. K. Clark ATTN: Rev and Tmg Lit Div
P.O. Box 12211 Fort Bragg, NC 28307Research Triangle Park, NC 27709-2211
1 Commander1 Commander, USACECOM Radford Army Ammunition Plant
R&D Technical Library ATIN: SMCAR-QA/fI LIBATITN: ASQNC-ELC-IS-L-R, Radford, VA 24141-0298
Myer CenterFort Monmouth, NJ 07703-5301 1 Commander
U.S. Army Foreign Science andCommandant Technology CenterU.S. Army Aviation School AYIN: AMXST-MC-3ATTN: Aviation Agency 220 Seventh Street, NEFort Rucker, AL 36360 Charlottesville, VA 22901-5396
Program Manager 2 CommandantU.S. Tank-Automotive Command U.S. Army Field Artillery Center andATTN: AMCPM-ABMS, T. Dean SchoolWarren, MI 48092-2498 ATIN: ATSF-CO-MW, E. Dublisky
ATSF-CN, P. GrossProject Manager Ft. Sill, OK 73503-5600U.S. Tank-Automotive CommandFighting Vehicle Systems 1 CommandantATTN: SFAE-ASM-BV U.S. Army Armor SchoolWarren, MI 48397-5000 ATTN: ATZK-CD-MS, M. Falkovitch
Armor AgencyProject Manager, Abrams Tank System Fort Knox, KY 40121-5215ATrN: SFAE-ASM-ABWarren, MI 48397-5000 2 U.S. Army Research Development and
StandardizationGroup (UK)Director PSC 802 Box 15, Dr. Roy E. RichenbachHQ, TRAC RPD Heinrich EgghartATTN: ATCD-MA FPO AE09499-1500Fort Monroe, VA 23651-5143
2 CommanderCommander Naval Sea Systems CommandU.S. Army Belvoir Research and ATTN: SEA 62R
Development Center SEA 64ATTN: STRBE-WC Washington, DC 20362-5101Fort Belvoir, VA 22060-5006
76
Commander 4 CommandeNaval Air Systems Comnmmd Naval Sufac Warfare CaterATrN: AIR-954-Tech LiAry ATTN: Code G30, Guns & Munitions DivWashington, DC 20360 Code G32, Guns Systems Div
Code G33, T. Doran4 Commander Code E23 Technical Litsary
Naval Research Laboratory Dahlgren, VA 22448-5000ATIN: Technical Library
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Washington, DC 20375-5000 T. BoggsCode 3895,
Office of Naval Research T. ParrATTN: Code 473, R.S. Miller R. Derr800 N. Quincy Street Information Science DivisionArlington, VA 22217-9999 China Lake, CA 93555-6001
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Edwards AFB, CA 93523-50003 Commander
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Code R-13, L. QuinnR. Bernecker, Code R-10 T. Edwards
Silver Spring, MD 20903-5000 5 Pollux DriveEdwards AFB, CA 93524-7048
8 CommanderNaval Surface Warfare Center I WL/MNAAATMN: T.C. Smith ATITN: B. Simpson
K. Rice Eglin AFB, FL 32542-5434S. MitchellS. Peters, Code 6210C I WLIMNMEJ. Consaga Energetic Materials BranchC. Gotzmer 2306 Perimeter Rd.R. Simmons, Code 210Pl STE 9Technical Library Eglin AFB, FL 32542-5910
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2 NASA Langley Research Center 2 Dic=ATTN: M.S. 408, Lawrence Livennore National
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2 CPA -JHU 5 Pensylvana State UniverityATIN: H. J. Hoffma,. Depulmf of Mechanical Eagineerg
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R. Beddini I Washington State University144 MEB; 1206 N. Green SL Department of Mechanical EngineeringUrbana, IL 61801-2978 ATTN: C.T. Crowe
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3 AAI Corporation 1 Hercules Inc.ATTN: J. Hebert ATTN: D. D. Whitney
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1. ARL ReportNumber ARL-TR-465 Date of Report June 1994
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