Army Research Laboratory 

Aberdeen Proving Ground, MD 21005-5069 

ARL-TR-2463 April 2001 

High-Rate Mechanical Response and 

SEM Morphology of EX99 Gun 

Propellants 

Michael G. Leadore and Robert J. Lieb 

Weapons and Materials Research Directorate, ARL 

Approved for public release; distribution is unlimited. 
Abstract 

Two lots of EX99 gun propellants from the Naval Surface Warfare Center (NSWC) 

were tested in uniaxial compression to an end strain of -60%. The materials were 

preconditioned at test temperatures of 21°, 50”, and -20 “C while at ambient pressure. 

The stress at faih+re, strain at failure, compressive modulus, failure modulus, 

incremental energy density (IED), and the fracture assessment values (FAV) were 

recorded for each test. These materials were also evaluated for microstructure using a 

scanning electron m+croscope (SEM). 

ii 
Contents 

List of Figures 

List of Tables 

1. Introduction 

2. Background 

3. Approach and Results 

4. Conclusions 

5. References 

Appendix. Thermoplastic Elastomer Response 

Distribution List 

Report Documentation Page 

V 

vii 

1 

1 

2 

2 

7 

9 

13 

31 

. . . 

ill 
iv 

INTENTIONALLYLEFTBLANK. 
List of Figures 

Figure 1. Ml Abrams tank with 120-mm gun. ............................................................ 1 

Figure 2. Prepared test specimens.. ............................................................................... 2 

Figure 3. Energetic material prepared for testing on the MTS load frame .............. 3 

Figure 4. Tested specimens at 50”, 21”, and -20 “C. ................................................... 5 

Figure 5. Stress vs. strain plot at 21”, 50”, and -20 “C. ............................................... 5 

Figure A-l. Stress vs. strain plot for TGD-019 lot M5U-001 

next-generation high-energy gun propellant.: .................................................... .lO 

Figure A-2. Photograph of tested material from lot TGD-019. ............................... 10 

Figure A-3. SEM micrographs of the EX99 propellants showing the 

difference in binder filler interaction. ................................................................... 11 
INTENTIONALLY LEFT BLANK. 

vi 
List of Tables 

Table 1. Mechanical properties of EX99 gun propellants at 21°, 50”, and 

-20 “C . . . . ..~...~....~~...........~_......._.........................~.................._____._.................~... . . . ..*.....*. 3 

Table A-l. Mechanical properties of BAMO/GAP/RDX (TGD-019 lot 

M56-4-001) next-generation high-energy gun propellant (solid stick). . . . . . . . . . . ...9 

Vii 
INTENTIONALLY LEFT BLANK. 

..* 

Vlll 



At 21 “C, the ~mechanical properties of the EX99 propellants were very poor. 

Note the comRressive and failure modulus values, which indicate the material 

provided brittle response and was unable to sustaining loads past about 10% 

strain. When ~comparmg these values with the propellant lot contained in the 

Appendix, it becomes clearer the large difference in compressive and failure 

modulus. Also, the tested specimens at 21 “C (Figure 2) showed severe axial 

fracture. 

At 50 “C, agam the stress at failure, compressive, and failure modulus values 

indicate how brittle the material was. Axial fracture at 50 “C usually does not 

occur and is a 

ity 

pica1 in most gun propellants, i.e., JA2, M30, Appendix lot, etc. 

The tested specimens at 50 “C again showed moderate-to-severe fracturing of the 

materials. I 

At -20 “C, theitested specimens (Figure 4) from both lots of EX99 suffered severe 

axial and shear fracture damage that would have likely caused significant 

increases in the surface area of this material. The &ess/strain plots (Figure 5) 

for the materials also correlate with the physical damage observed. Note the 

sharp stress vs. strain pulse for the lot that indicates the material had likely glass 

transitioned as a result of the -20 “C exposure. The highly negative failure 

modulus valuks also indicated the material’s inability to sustain load at -20 “C 

beyond about p % strain. 

Overall, the Ex99 7-perforated gun propellants showed very poor mechanical 

properties at 21°, 50”, and -20 “C when compared with the Appendix lot. The 

EX99 test results indicated both lots were sensitive to the uniaxial compressive 

testing, becoming “brittle” at 21” and -20 “C, and suffering prolific fracture. It 

should also be noted that the grains received by ARL from lot FBOl contained 

-25% specimens with irregular perforation patterns while none of these flawed 

specimens were tested for mechanical response. Also, the scanning electron 

micrographs shown in Figure A-3 clearly show a lower level of binder-filler 

interaction ins lot FBOl as compared to lot 0088. The fracture in the 0088 lot 

proceeds only through the binder, whereas the fracture in the FBOl lot takes 

advantage of ~the lower binder-filler interaction and proceeds by jumping from 

ai-l 

k 

particle to p, 

exposed and 

FBOZ at 21” ; 

the fracture 

was residual 

across the cf 

residual stre 

nonuniform 

had sign& 

demonstrate 

or 

icle. In this process, the cyclotrimethylenetriamine (RDX) is 

‘actured. This may explain the lower stress levels achieved for lot 

l-20 “C (Figure 5) as compared to lot FBOl. (Note: The nature of 

the specimen during specimen preparation indicated that there 

tresses in both propellant lots. The fracture, which was initiated 

er of the grain ran quickly to the outside edge. This is caused by 

2s within the grain directing the crack to the outside because of a 

ternal stress field.) When comparing the two lots tested, lot 0088 

tly better properties at lower temperature. However, both lots 

very brittle responses. 

-1 

m 

4 

INTENTIONALLY LEFT BLANK. 

6 

L 
5. References 

1. Gazonas, G. A. “The Mechanical Response of M30, XM39, and JA2 

Propellants at Strain Rates From 10-2 to 250 Set-1.” BRL-TR-3181, U.S. Army 

Ballistic Research Laboratory, Aberdeen Proving Ground, MD, January 1991. 

2. Lieb, R. J- “Impact-Generated Surface Area in Gun Propellant.” 

BRL-TR-2946, U.S. Army Ballistic Research Laboratory, Aberdeen Proving 

Ground, MD, November 1988. 

3. Lieb, R. J., and J. J. Rocchio. “High Strain Rate Mechanical Properties Testing 

on Lots of Solid Gun Propellant With Deviant Interior Ballistic Performance.” 

1982 JANNAF Structures and Mechanical Behavior Subcommittee Meeting, CPIA 

Publication 368, pp. 23-38, October 1982. 

4. Leadore, M. G. “MTS Servo-Hydraulic Tester (SHT) Mechanical Properties 

Evaluation of M43 Propellants.” ARL-TN-5, U.S. Army Research Laboratory, 

Aberdeen Proving Ground, MD, March 1993. 

5. Leadore, M. G., and C. J. Gillich. “Material Testing System (MTS) ServoHydraulic Tester (SHT) Mechanical Response of Energetic Thermal Plastic 

Elastomer (ETPE) RDX Based Propellants.” ARL-TN-28, U.S. Army Research 

Laboratory, Aberdeen Proving Ground, MD, April 1994. 

6. Leadore, M. G. “Mechanical Response of Energetic Thermoplastic Elastomer 

Low-Vulnerability Ammunition (ETPE-LOVA) RDX-Based, TNAZ-Based, 

and CL-20-Based Gun Propellants.” ARL-TN&, U.S. Army Research 

Laboratory, Aberdeen Proving Ground, MD, March 1996. 

7. Lieb, R. J. Personal communication. “TGD-019 Lot M56-4-001 Customer 

Technology Transfer Report,” October 2000. 

7 
8 

INTENT~oNAILY LEFT BLANK. 
Appendix. Thermoplastic Elastomer Response 

Table A-l. Mechanical properties of BAMO/GAP/RDX (TGD-019 lot M564-001) nextgeneration high-energy gun propellant (solid stick). 

Lot 

M56-4-001 

Stress at Strain at Failure 

Failure Failure Modulus Modulus ED FAV 

WJW (%) (@a) FW ww 

at 21 “C 

1 31.1 1 9.40 1 0.460 1 0.013 1 15.16 1 1B 

MS-4-001 

M56-4-00 1 

at -20 “C 

1 97.09 1 4.82 1 2.59 1 0.71 1 11.12 1 7AS 

at 50 “C 

1 16.5 1 8.82 1 0.27 1 0.009 1 6.11 1 1B 

aThe failure modulus (slope of the curve after failure) has been added. Generally, the lower the 

value, the worse the material (i.e., negative value indicates the material is unable to sustain load). 

A positive value indicates a positive faihtre slope (i.e., the material is better able to support load 

after failure). 

bThe IED (incremental energy density) value reported is the amount of energy per unit volume 

absorbed at 25% strain, this includes a portion of the area located beneath the stress/strain curve. 

CThe tested specimens were assigned a fracture assessment value (FAV). The values range from 0 

(no observed fracturing) through 9 (severe fracturing observed). The type of fracture was also 

characterized using the following methodology: A = axial fracture, S = shear fracture, 

B = barreling/deformation, I3 = radial splitting (i.e., 9A indicates the tested specimens showed a 

severe amount of axial fracture). 


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30 
al Response and SEM Morphology of EX99 Gun Propellants lL161102AH43 

. Leadore and Robert J. Lieb 

: AMSRL-WM-MB 

Aberdeen Proving Ground, MD 2 1005-5069 

12a. DlSTRlBUTlONlAVAllABlLliY STATEMENT 12b. DISTRIBUTION CODE 

4pproved for public release; distribution is unlimited. 

13. ABSTRACT(Maximum 200 words) 

Two lots of EX99 gun propellants from the Naval Surface Warfare Center (NSWC) were tested in uniaxi; 

compression to an end strain of -60%. The materials were preconditioned at test temperatures of 21°, 50”, and -20 “C 

while at ambient pressure. The stress at .failure, strain at failure, compressive modulus, failure modulus, increment 

energy density (IED), and the fracture assessment values (FAV) were recorded for each test. These materials were ah 

evaluated for microstructure using a scanning electton microscope @EM). 

14. SUBJECT TERMS 15. NUMBER OF PAGES 

high rate, high energy, deformation stress, strain, mechanical properties, gun propellant, 32 

uniaxial compression, fracture, modulus, mechanical response, material testing system M.PRICE CODE 

scannim electron microscope, high-strain rate 

17. SECURITY CLASSIFICATION 18. SECURlfY CLASSIFICATION 19. SECURITY CLASSIFICATloN 

OF REPORT 

20. LIMITATION OF ABSTRACl 

OF THIS PAGE OF ABSTRACT 

UNCLASSIFIED UNCLASSIFIED UNCLASSIFIED UL 

NSN 7%O-fJl-280-5500 

31 Standard Fwm 298 (Rev. 2-89) 

Presctibed byANSl Std. 239-18 29.3-l 02 
IP~TE~I~NALLY mT BLANK. 

32 
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