Characterization of Candidate Materials for 

Composite Cartridge Case 

by Aristedes Yiournas, Brian M. Powers, 

Travis A. Bogetti, and William H. Drysdale 

ARL-TR-3341 September 2004 

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Army Research Laboratory 

Aberdeen Proving Ground, MD 21005-5069 

ARL-TR-3341 September 2004 

Characterization of Candidate Materials for 

Composite Cartridge Case 

Aristedes Yiournas, Brian M. Powers, 

Travis A. Bogetti, and William H. Drysdale 

Weapons and Materials Research Directorate, ARL 

Approved for public release; distribution is unlimited. 
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Characterization of Candidate Materials for Composite Cartridge Case 

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Aristedes Yiournas, Brian M. Powers, Travis A. Bogetti, and William H. Drysdale 

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13. SUPPLEMENTARY NOTES 

14. ABSTRACT 

Cased telescoped ammunition designs were developed for the Multi-Role Armament and Ammunition System that employed a 

composite cartridge case. Three candidate composite material systems are being considered for the application—50% chopped 

fiberglass/Nylon 12, 30% chopped fiberglass/ULTEM (a registered trademark of GE Plastics Corp.), and a continuous 

fiberglass/urethane. Each of these material systems was subjected to preliminary mechanical testing in order to characterize 

their basic material properties and to support finite-element modeling of the cartridge case/gun chamber during the firing cycle. 

Basic mechanical properties such as stress-strain curves, Poisson’s ratio, and residual plastic deformation after unloading were 

obtained and are presented in this report. 

15. SUBJECT TERMS

composite materials, cartridge case, characterization 

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Aristedes Yiournas 

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iii

Contents 

List of Figures iv

List of Tables iv

Acknowledgments v

1. Introduction 1

2. Sample Materials and Test Preparation 2

3. Test Results 3

3.1 The 50% Fiberglass/Nylon..............................................................................................3 

3.2 The 30% Fiberglass/ULTEM ..........................................................................................7 

3.2.1 Extruded Fiberglass/ULTEM ..............................................................................8 

3.2.2 Injection-Molded Fiberglass/ULTEM.................................................................8 

3.3 Fiberglass/Urethane.......................................................................................................10 

3.3.1 [0°]5 Fiberglass/Urethane ..................................................................................10 

3.3.2 [90°]10 Fiberglass/Urethane...............................................................................10 

3.3.3 [±45°]5 Fiberglass/Urethane..............................................................................12 

3.3.4 [0°/90°]5 Fiberglass/Urethane ...........................................................................14 

4. Conclusions 16

Distribution List 17 
iv

List of Figures 

Figure 1. Illustration of tensile specimen sectioning from sample tubes and radial coordinate 

system with respect to tube arc. .................................................................................................2 

Figure 2. Illustration of tensile specimen sectioning from sample tubes and radial coordinate 

system with respect to tube arc. .................................................................................................5 

Figure 3. Examples of Poisson’s ratio behavior of Nylon 12 material...........................................6 

Figure 4. Example of load/unload of Nylon 12 material for residual strain characteristics. ..........6 

Figure 5. Micrograph of Nylon 12 material where alignment can be seen near tube inner wall 

in longitudinal direction. View is looking into the “theta” direction........................................7 

Figure 6. Representative example of extruded/machined ULTEM series results. .........................8 

Figure 7. Summary of injection molded ULTEM series results.....................................................9 

Figure 8. Summary of Poisson’s ratio behavior of both ULTEM series. .......................................9 

Figure 9. Summary of [0°]5 urethane response obtained prior to end tab debond........................10 

Figure 10. Poisson’s ratio behavior of [0°]5 urethane series specimens.......................................11 

Figure 11. Initial portion of [90°]10 urethane response. Strains exceeded gage capabilities, 

while loads remained low until failure.....................................................................................11 

Figure 12. Example of Poisson’s ratio behavior of a [90°]10 urethane specimen. Strain gage 

measured lateral contraction on outer ply face, which was resisted by the alignment of the 

fibers in this direction. Through-thickness behavior is not represented and may differ 

significantly..............................................................................................................................12 

Figure 13. Tensile response of a [±45°]10 coupon. .......................................................................13 

Figure 14. Reduction of [±45°]10 tensile data into shear coordinate system. ...............................13 

Figure 15. Apparent Poisson’s ratio behavior on outer ply face of a [±45°]10 specimen. ............14 

Figure 16. Stress-strain data reduced from [0°/90°]10 tests. Odd failure region results from 

strain gage being mounted on outer 0° ply, which failed prior to catastrophic specimen 

failure. This ply partially relaxed before specimens went on to a slightly higher load. .........15 

Figure 17. Observed Poisson’s ratio behavior on outer 0° ply of [0°/90°]10 samples. .................15 

List of Tables 

Table 1. Summary of tensile test configurations. ...........................................................................4 

Table 2. Summary of tensile test results. ........................................................................................4 

Table 3. Summary of residual strain after loading/elastic recovery. ..............................................5 
v

Acknowledgments 

This research was supported in part by an appointment to the Research Participation Program at 

the U.S. Army Research Laboratory (ARL) administered by the Oak Ridge Institute for Science 

and Education through an interagency agreement between the U.S. Department of Energy and 

ARL. 
vi

INTENTIONALLY LEFT BLANK. 
1

1. Introduction 

A cartridge case contains the propellant and ignition system necessary to launch a projectile from 

a gun and provides alignment to allow the projectile to enter the gun tube smoothly. After the 

firing cycle is complete, the case must be extracted from the gun chamber to allow the next 

round to be loaded. 

Conventional breech loaded cartridge cases have traditionally been made of brass or steel. The 

case is inserted into the chamber of a gun, and the propellant is ignited. Relatively low pressure 

is needed to expand the case until it contacts the gun chamber wall, taking up the clearance 

designed between the case and chamber wall. From this point in the loading until peak pressure, 

the gun chamber provides the major part of the resistance to gun pressure. 

The deformation of the gun chamber by the propellant pressure is completely elastic due to the 

residual stresses created in the gun tube by the autofrettage process. In contrast, the deformation 

in the case commonly contains a significant plastic component. 

As the propellant pressure decreases in the chamber, both the case and chamber shrink 

elastically. The goal of the case design and material selection is to ensure that the plastic 

deformation is not allowed to develop to such a level that there is no clearance between the case 

and the chamber wall after all pressure has been exhausted.1

Further aid in the extraction of a conventional case is obtained by including a slight taper in the 

case and chamber wall. Then, any rearward movement of the case due to engagement of the 

extractor pins at breech opening further increases the clearance and assists smooth extraction. 

Cased telescoped ammunition (CTA) was developed for use in the Multi-Role Armament and 

Ammunition System (MRAAS) swing chamber gun. This concept places additional design 

burdens on the cartridge case. 

For the swing chamber gun, the round is loaded into the chamber in its rotated position. The 

chamber is then turned 90° so that it is aligned with the gun tube, and the round is fired. The 

chamber is then rotated back into the open position, and the spent cartridge is extracted by being 

pushed through the chamber by the loading of the next round.2

The cartridge must now seal both ends of the chamber, not just the breach end, as with 

conventional guns. This push-through feature for removing spent rounds means that the chamber 

 1

U.S. Army Materiel Command. Engineering Design Handbook: Ammunition Series, Section 4, Design Projection; AMCP 

706-247, July 1964. 

2

FC Munition Design Team Review. Picatinny Arsenal, NJ, 11 July 2000. 
2

and case cannot be tapered to aid in extraction. Thus, the responsibility for ease of case 

extraction falls solely on case design (clearances, etc.) and material selection. 

The material must deform without failing under firing pressures and elastically recover enough 

deformation so that the spent case can be removed by the force of loading. Since the gun 

chamber absorbs the majority of the propellant pressure, ductility and elastic recovery, rather 

than strength, are the important properties of the sought material. 

2. Sample Materials and Test Preparation 

Three composite material systems were evaluated for use in the CTA. They are fiberglass/Nylon 

12, fiberglass/ULTEM,* and fiberglass/urethane. The Nylon 12 and ULTEM matrix composites 

used chopped fiberglass, while the urethane composites used continuous fiberglass laminates. 

The fiberglass/Nylon 12 was supplied as a hollow tube of ~6° inches in length and 5.5 inches in 

diameter, made by injection molding. The wall thickness was 0.375 in. The fiber reinforcement 

consisted of chopped fiberglass of 50% weight. Narrow arcs were cut out and machined into 

rectangular blocks from which tensile test coupons were sectioned with a precision slot-grinder 

machine fitted with a diamond cut-off saw. This process and the tube coordinate system are 

illustrated in figure 1. 

Figure 1. Illustration of tensile specimen sectioning from sample tubes and 

radial coordinate system with respect to tube arc.

 

*ULTEM is a registered trademark of GE Plastics Corp.
3

The 30% weight fiberglass/ULTEM was also supplied in two hollow tubes, with the effects of 

two manufacturing processes investigated. Both tubes had a diameter of 5.5 in and a length of 

6 in. The first tube was made by machining an extruded fiberglass/ULTEM cylinder. After 

extrusion, the cylinder was machined to a 0.25-in wall thickness, and end-seal chevrons were 

placed on each end of the tube. The second tube was manufactured by injection molding and had 

a wall thickness of 0.375 in. This tube was supplied with no further processing after being 

injection molded. Samples from both the ULTEM matrix tubes were prepared by the same 

process outlined for the Nylon 12 matrix tube. 

The fiberglass/urethane samples were manufactured by the hand lay-up of unidirectional 

fiberglass plies into flat panels with various laminates from which tensile coupons were 

sectioned directly. The manufacturing process took place at the U.S. Army Research Laboratory 

facility located in Aberdeen, MD. The four lay-ups manufactured were [0°]5, [90°]10, [±45°]5, 

and [0°/90°]5. Test samples were cut from the flat panels using a slot-grinder fitted with a 

diamond cut-off wheel. 

As was practical, all materials were tensile tested in the best accordance with ASTM D 3039.3

 

This standard specifies whether bonded end tabs or friction tabs, such as emory cloth, are 

appropriate for random, discontinuous fiber composites. Where applicable, end-tab material was 

a fiberglass composite. Except for where specifically noted, Hysol* structural adhesive was used 

to bond the end tabs to the samples. An Instron† 4484 multipurpose test machine was used to 

perform tensile tests on all the samples, and cross-head displacement rates varied from 0.05 to 

0.5 in/min, depending on lay-up as defined in the ASTM D 3039 standard. Table 1 summarizes 

the test configurations and loading rates for all test samples. Except where noted, all specimens 

were instrumented with strain gages to measure both longitudinal and transverse strain. Young’s 

modulus and Poisson’s ratio were determined from this data. 

3. Test Results 

Data from the Instron’s load cell and a strain gage acquisition computer was reduced to stress vs. 

strain curves. It was found that all materials except for [0°]5 and [0°/90°]10 fiberglass/urethane 

exhibited a nonlinear softening curve. Tables 2 and 3 summarize all of the test results. Sections 

3.1–3.3 discuss individual materials. 

3.1 The 50% Fiberglass/Nylon 

The first series of tests on the 50% fiberglass/Nylon 12 was not fitted with strain gages. Because 

calculation of strain from crosshead displacement was inaccurate, stress-strain curves could not 

be constructed for series 1. Tensile strength was determined and found to be ~7–8 ksi.

 3

ASTM D 3039. Standard Test Method for Tensile Properties of Fiber-Resin Composites, Annu. Book ASTM Stand. 2002. 

*

Hysol is a registered trademark of the Dexter Corp. 

†

Instron is a registered trademark of the Instron Corp. 
4

Table 1. Summary of tensile test configurations. 

Material Original Section Dimensions 

(in) 

End Tabs/ 

Adhesive/No. Loading Rate

(in/min) 

Nylon series 1 3/8-in wall tube 

injection mold 

4 × 0.31 × 0.13 2 tabbed 

(quick epoxy) 

2 untabbed 

0.05 

Nylon series 2 3/8-in wall tube 

injection mold 

4 × 0.29 × 0.09 3 tabbed 

(quick epoxy) 

2 untabbed 

0.025 

Nylon series 3 3/8-in wall tube 

injection mold 

4 × 0.33 × 0.09 6 tabbed 

(Hysol 9309) 

0.025 

ULTEM extruded 1/4-in wall tube 

machined 

4.38 × 0.39 × 0.1 4 untabbed 

emory cloth 

0.025 

ULTEM injection 

molded 

3/8-in wall tube 

injection mold 

6 × 0.31 × 0.1 4 untabbed 

emory cloth 

0.025 

Urethane [0°]10 ~1/10-in sheet 

5 plies 

10 × 0.5 × 0.09 4 tabbed 

(Hysol 1C) 

0.05 

Urethane [90°]10 ~1/4-in sheet 

10 plies 

10 × 1 × 0.24 5 tabbed 

(Hysol 9309) 

3 untabbed 

0.5 

Urethane [±45°]5 ~1/4-in sheet 

10 plies 

10 × 1 × 0.22 5 tabbed 

(Hysol 9309) 

0.25 

Urethane [0°/90°]5 ~1/4-in sheet 

10 plies 

10 × 1 × 0.24 5 untabbed 0.05 

Table 2. Summary of tensile test results. 

Material System 

Average σf 

Standard Deviation 

(psi) 

Average Eo

(psi) 

Average εf

(in/in) 

Average Poisson’s 

Ratio 

Nylon series 1 7160 533 NA NA NA 

Nylon series 2 7484 449 890,000 0.013 0.4 

Nylon series 3 8220 882 812,000 0.018 0.45 

ULTEM extruded 21525 1550 1,000,000 0.031 0.3 

ULTEM injection 

molded 

17340 869 1,048,000 0.024 0.35 

Urethane [0°]10 51870a

 5106 6,100,000 End tab failure 

occurs before 0.01 

0.4 

(parallel to lamina) 

Urethane [90°]10 811 130 39,900 0.45 0.05 

(parallel to lamina) 

Urethane [±45°]5 8727a

 488 60,600 0.42 1.0 

(parallel to lamina) 

Urethane [0°/90°]5 15822a

 968 1,754,000 End failure occurs 

before 0.01 

0.25 

(parallel to lamina) a

Value is not the true failure stress. 

Note: NA = not available.
5

Table 3. Summary of residual strain after loading/elastic recovery. 

Material Nylon/Glass ULTEM/Glass Urethane [90°] 

(%) 

Urethane [45°] 

(%) 

Residual 

plastic strain 

0.3% 0.2% 1.6 1.0 

Unloaded 

form 

90% fail load/ 

1.4% strain 

90% fail load/ 

2% strain 

4.6 4.5 

Series 2 was fitted with strain gages, and stress-strain results are shown in figure 2. The samples 

had 0.75-in fiberglass/epoxy end tabs bonded with a common quick-set epoxy. Specimens 1 and 

2 in figure 2 show drops in stress that correspond to the end tabs pulling away from the samples. 

The samples did not have transverse strain gages, so Poisson’s effect was not measured. 

0

1000

2000

3000

4000

5000

6000

7000

8000

0 0.005 0.01 0.015 0.02 0.025 0.03

Specimen 4 (untabbed)

Specimen 3 (untabbed)

Specimen 2 (tabbed)

Specimen 1 (tabbed)

Stress (psi)

Strain

Figure 2. Illustration of tensile specimen sectioning from sample tubes and radial coordinate 

system with respect to tube arc. 

To prevent the end tabs from pulling away, Hysol structural adhesive was used in series 3 tests. 

Despite this, the material did not strain greater than 2%. Biaxial strain gages accurate up to 5% 

were mounted on specimens, allowing the Poisson’s ratio results in figure 3. The samples were 

also loaded and unloaded incrementally to measure residual plastic strain after loading, as shown 

in figure 4. 

Some fiberglass/Nylon 12 specimens were tested using emory cloth, as recommended by the 

American Society for Testing and Materials. Failure loads from these tests compared favorably 

to tests performed using end tabs. Also, the end-tabbed samples did not show a preference for 
6

0

0.2

0.4

0.6

0.8

1

0 0.002 0.004 0.006 0.008 0.01 0.012 0.014 0.016

Poisson's ratio

Strain

Figure 3. Examples of Poisson’s ratio behavior of Nylon 12 material. 

0

1000

2000

3000

4000

5000

6000

7000

8000

0 0.005 0.01 0.015 0.02

Series 3 Specimen 4

Stress (psi)

Strain

Figure 4. Example of load/unload of Nylon 12 material for residual strain characteristics. 
7

where failure occurred, with samples failing both in the gage section and at the end tabs. This 

trend was also observed in the tests using the emory cloth. 

Commercial data sheets on similar materials report strengths of ~20 ksi. The discrepancy 

between current tests and published data may be due to manufacturing differences. It has been 

suggested that preferential fiber alignments, which can occur easily in thin-walled injection 

molded parts, do not occur throughout a thicker part, such as the 0.375-in thick tube supplied for 

this study. Microscopy performed on the fiberglass/Nylon 12 material shows varied fiber 

alignment, as seen in figure 5. Some alignment occurs in the injection direction (longitudinal 

tube directions) near the walls of the mold. The alignment of fibers found near the inner wall 

can be seen to diminish to near random closer to the center of the thickness. In an effort to 

preserve fiber alignment, the series 3 tests employed specimens that were carefully sectioned 

directly from an arc section of tube. The results of this last series showed negligible benefit as a 

result of this method. In general, the occasional irregularities between similar specimens may be 

due to irregularities in the dispersion and orientation of fibers that can occur during mixing and 

injection. 

Figure 5. Micrograph of Nylon 12 material where alignment can be seen near tube 

inner wall in longitudinal direction. View is looking into the “theta” 

direction. 

3.2 The 30% Fiberglass/ULTEM 

Two tubes of the 30% chopped fiberglass/ULTEM were tested in this study. The first tube was 

machined from an extruded section. The second tube was injection molded to shape, with no 
8

post-molding machining. This allowed for the effects of processing to be evaluated in regards to 

material properties. 

3.2.1 Extruded Fiberglass/ULTEM 

The extruded 30% chopped fiberglass/ULTEM was supplied as a 6-in long tube of 5.5-in 

diameter, with a 0.25-in wall thickness with end-seal chevrons. The samples were prepared 

using the previously outlined method, except the chevrons on the end were removed. The 

ultimate strength of this material is 21.5 ksi, with an initial modulus of 1 to 1.1 Msi, making it 

slightly stiffer but over twice as strong as the fiberglass/Nylon 12 samples. The strain capability 

of this system is also significantly better with a 3.1% strain to failure. The stress-strain response 

is similar to the fiberglass/Nylon 12, exhibiting nonlinear softening to a clean break, as shown in 

figure 6. 

0

5000

1 104

1.5 104

2 104

2.5 104

0 0.005 0.01 0.015 0.02 0.025 0.03 0.035

Series 1 Specimen 1

Stress (psi)

Strain

Figure 6. Representative example of extruded/machined ULTEM series results. 

3.2.2 Injection-Molded Fiberglass/ULTEM 

The injection-molded tube had a 6-in diameter and a 0.375-in wall thickness. Samples were 

prepared and tested with the method outlined for the fiberglass/Nylon 12 tube. The stress-strain 

results from the tension tests are shown in figure 7. The plastic strain is measured from a load/ 

unload test. The stress-strain behavior is similar to the extruded material, but the failure 

properties differ. The ultimate stress is 18 ksi, and strain-to-failure is 2.4%. Both properties 

are lower than for the extruded version of the ULTEM material. The Poisson’s ratio graph in 

figure 8 shows the slight difference in transverse behavior between the two types of ULTEM 

samples. 
9

0

5000

1 104

1.5 104

2 104

0 0.005 0.01 0.015 0.02 0.025 0.03

spec. 4 (Load/Unload)

specimen 3

specimen 2

specimen 1

Stress (psi)

Strain

Figure 7. Summary of injection molded ULTEM series results. 

0

0.2

0.4

0.6

0.8

1

0 0.005 0.01 0.015 0.02 0.025 0.03 0.035

series 2 specimen 1

series 2 specimen 3

series 1 specimen 1

series 1 specimen 3

series 1 specimen 2

Poisson's ratio

Strain

Injection Molded

Extruded

Figure 8. Summary of Poisson’s ratio behavior of both ULTEM series.

Series 2 Specimen 1 

Series 2 Specimen 3 

Series 1 Specimen 

Series 1 Specimen 3 

Series 1 Specimen 2

Specimen 4 (load/unload) 

Specimen 3 

Specimen 2 

Specimen 1 
10

3.3 Fiberglass/Urethane 

A continuous fiberglass/urethane composite was also examined as a candidate cartridge case 

material. Four different lay-ups were tested—[0°]5, [90°]10, [±45°]5, and [0°/90°]5. These layups allowed the characterization of the longitudinal, transverse, and shear properties. 

3.3.1 [0°]5 Fiberglass/Urethane 

The stress-strain results from tension tests on the [0°]5 samples are shown in figure 9. Since the 

behavior of the samples is governed by the glass fibers, the stress-strain relation is basically 

linear, with a modulus of 6.1 Msi. The average ultimate stress is 51.8 ksi, but it should be noted 

that all of the samples failed at the ends with the same characteristic pattern. The self-tightening 

action of the Instron grips squeezed out the material between the end tabs. The end tabs pulled 

off, tearing out a section of the sample. A different end-tabbing scheme is required to measure 

actual ultimate strength. The transverse behavior is mainly due to the properties of the rubber, as 

evident in figure 10 where Poisson’s ratio approaches 0.5. 

0

1 104

2 104

3 104

4 104

5 104

6 104

0 0.002 0.004 0.006 0.008 0.01

Specimen 3

Specimen 4

Specimen 1

Specimen 2

Stress (psi)

Strain

Figure 9. Summary of [0°]5 urethane response obtained prior to end tab debond. 

3.3.2 [90°]10 Fiberglass/Urethane 

The properties of the [90°]10 samples are now primarily due to the rubber, with no reinforcement 

in the test direction. The stress-strain results are shown in figure 11, indicating a high degree of 

nonlinear flattening of the curve. The plot is not indicative of the failure strains, which 
11

0

0.2

0.4

0.6

0.8

1

0 0.002 0.004 0.006 0.008 0.01

Specimen 1

Specimen 2

Specimen 3

Specimen 4

Poisson's ratio

Strain

Figure 10. Poisson’s ratio behavior of [0°]5 urethane series specimens. 

0

100

200

300

400

500

600

700

0 0.005 0.01 0.015 0.02 0.025 0.03 0.035

Specimen 3

Specimen 2

Specimen 1

Stress (psi)

Strain

Figure 11. Initial portion of [90°]10 urethane response. Strains exceeded gage 

capabilities, while loads remained low until failure.
12

approached 50%, because the strain gages used have a maximum strain capacity of 5%. The 

stress never became greater than 1 ksi. At higher strains, striations between fiber bundles 

became apparent on the outer surfaces until the specimens failed. Because of the transverse 

fibers, lateral contraction was limited, as evident in figure 12, which shows the transverse 

Poisson’s ratio behavior of the [90°]10. 

0

0.1

0.2

0.3

0.4

0.5

0 0.005 0.01 0.015 0.02 0.025 0.03 0.035 0.04

Series 1 Specimen 3

Poisson's ratio

Strain

Figure 12. Example of Poisson’s ratio behavior of a [90°]10 urethane specimen. 

Strain gage measured lateral contraction on outer ply face, which was 

resisted by the alignment of the fibers in this direction. Throughthickness behavior is not represented and may differ significantly. 

3.3.3 [±45°]5 Fiberglass/Urethane 

The next lay-up tested with the fiberglass/urethane materials was a [±45°]5. Figure 13 shows the 

tensile response of a test sample. This specific lay-up allows the shear properties (G12, τult) to be 

measured through tension. To determine the shear stress-shear strain curves, the tensile response 

is transformed to the shear response using the relations 2

x

shear

σ

τ = and shear x y γ = ε + ε . 

Figure 14 shows the data from a test converted to shear components. This particular 

configuration exhibits a “scissoring” dominated mode of contraction, tending to rotate fibers into 

the test direction. A directional Poisson’s ratio this large would suggest a negative ration in the 

through-thickness direction, correlating with the observed behavior of the cross section of the 

samples. Expansion in the thickness direction and high Poisson in the lateral direction produced 

a rounded cross section from a rectangular one.
13

0

200

400

600

800

1000

1200

0 0.01 0.02 0.03 0.04 0.05 0.06

Series 2 Specimen 2

Stress (psi)

Strain

Figure 13. Tensile response of a [±45°]10 coupon. 

0

100

200

300

400

500

600

0 0.02 0.04 0.06 0.08 0.1

Shear Stress (psi)

Shear Strain

Figure 14. Reduction of [±45°]10 tensile data into shear coordinate system.
14

The initial shear modulus is ~15 ksi. The maximum loads achieved are not representative of 

the ultimate because of the type of failure observed. At the end tabs, a ply-by-ply failure was 

observed as outer plies appeared to tear off. This suggests that even higher loads are possible 

if end effects are effectively neutralized. A Poisson’s ratio near 1, evident in figure 15, 

demonstrates the high transverse contraction of this lay-up, which is due to the “scissoring” 

action of the fibers as they rotate into the test direction. 

0

0.5

1

1.5

0 0.005 0.01 0.015 0.02 0.025 0.03 0.035

Poission's ratio

Strain

Figure 15. Apparent Poisson’s ratio behavior on outer ply face of a [±45°]10 specimen. 

3.3.4 [0°/90°]5 Fiberglass/Urethane 

The final fiberglass/urethane combination tested was a [0°/90°]5 lay-up. These specimens were 

placed directly into the grips of the testing machine, with no end tabs. The stress-strain results 

are shown in figure 16, and the Poisson’s ratio results are shown in figure 17. 

Until failure, the samples displayed approximate linear behavior, with a modulus of ~1.8 Msi. 

Ply-level failure of the outer [0°] ply occurred at ~12 ksi. This is most likely from the stress 

concentration at the grips, causing the fibers in the outer ply to fail. Instead of the opposite 

[90°] face, the strain gage was mounted on this same [0°] face because of a better bonding 

surface. When the [0°] outer ply failed, it became partially unloaded, causing the strain to 

decrease (represented by the erratic behavior of the stress-strain curve above 12 ksi). The 

remainder of the laminate stayed intact and carried a higher load. To obtain the true ultimate 

characteristics of this lay-up, an effective end-tabbing scheme is again required.
15

0

2000

4000

6000

8000

1 104

1.2 104

1.4 104

1.6 104

0 0.001 0.002 0.003 0.004 0.005 0.006 0.007 0.008

specimen 2

specimen 3

spec. 4 Load/Unload

specimen 1

Stress (psi)

Strain

Figure 16. Stress-strain data reduced from [0°/90°]10 tests. Odd failure region results 

from strain gage being mounted on outer 0° ply, which failed prior to 

catastrophic specimen failure. This ply partially relaxed before specimens 

went on to a slightly higher load. 

0

0.2

0.4

0.6

0.8

1

0 0.001 0.002 0.003 0.004 0.005 0.006 0.007

specimen 1

specimen 2

specimen 3

Poisson's ratio

Strain

Figure 17. Observed Poisson’s ratio behavior on outer 0° ply of [0°/90°]10 samples.

Specimen 2 

Specimen 3 

Spec. load/unload 

Specimen 1 

Specimen 1 

Specimen 2 

Specimen 3 
16

It should be noted that after the initial outer [0°] ply failure and marginally increased load, all 

[0°] plies failed completely, as could be expected in comparison to the compliant [90°] plies. 

The interesting characteristic of this particular lay-up is that even after complete failure of the 

[0°] plies, the [90°] plies kept the coupon in one piece. 

4. Conclusions 

Three composite material systems, 50% chopped fiberglass/Nylon 12, 30% chopped 

fiberglass/ULTEM, and continuous fiberglass/urethane, were tested in order to determine basic 

material properties and suitability as candidates for use in the cartridge case for the CTA of the 

MRAAS 105-mm gun. The shape of the stress-strain curve, moduli, Poisson’s ratio, failure 

stress and strain, and residual plastic deformation after unloading were determined. The results 

are presented graphically and in tabular form. These material properties are required to 

understand the mechanical response of the case to the loading cycle and to support the 

finite-element modeling of the case/chamber. 

Finite-element analysis of the cartridge case in the chamber of the MRAAS swing chamber gun 

during a firing cycle will be presented in a separate report.4 These analyses confirm the intuitive 

feeling that strength and stiffness in this case are superfluous; the gun chamber supports the load 

created by the high-propellant gas pressure. The most important characteristics for the case 

material are its ability to go to high levels of failure strain (especially in the vicinity of the 

discontinuation near the end seals) and to suffer minimal residual plastic strain after a firing 

cycle. 

 4

Powers, B.; Bogetti, T.; Drysdale, W. Finite Element Analysis of a Composite Cartridge Case in the Multi-Role Armament 

and Ammunition System Gun. U.S. Army Research Laboratory: Aberdeen Proving Ground, MD, to be published. 
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 R S ENGEL 

 245 HAMMOND BLDG 

 UNIVERSITY PARK PA 16801 

 2 PENN STATE UNIV 

 R MCNITT 

 C BAKIS 

 212 EARTH ENGR 

 SCIENCES BLDG 

 UNIVERSITY PARK PA 16802 

 1 PURDUE UNIV 

 SCHOOL OF AERO & ASTRO 

 C T SUN 

 W LAFAYETTE IN 47907-1282 

 1 STANFORD UNIV 

 DEPT OF AERONAUTICS 

 & AEROBALLISTICS 

 S TSAI 

 DURANT BLDG 

 STANFORD CA 94305 

 1 UNIV OF MAINE 

 ADV STR & COMP LAB 

 R LOPEZ ANIDO 

 5793 AEWC BLDG 

 ORONO ME 04469-5793 

 1 JOHNS HOPKINS UNIV 

 APPLIED PHYSICS LAB 

 P WIENHOLD 

 11100 JOHNS HOPKINS RD 

 LAUREL MD 20723-6099 

 1 UNIV OF DAYTON 

 J M WHITNEY 

 COLLEGE PARK AVE 

 DAYTON OH 45469-0240 

 1 NORTH CAROLINA ST UNIV 

 CIVIL ENGINEERING DEPT 

 W RASDORF 

 PO BOX 7908 

 RALEIGH NC 27696-7908 

 5 UNIV OF DELAWARE 

 CTR FOR COMPOSITE MTRLS 

 J GILLESPIE 

 M SANTARE 

 S YARLAGADDA 

 S ADVANI 

 D HEIDER 

 201 SPENCER LAB 

 NEWARK DE 19716 
NO. OF NO. OF 

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 1 DEPT OF MTRLS 

 SCIENCE & ENGRG 

 UNIV OF ILLINOIS 

 AT URBANA CHAMPAIGN 

 J ECONOMY 

 1304 WEST GREEN ST 115B 

 URBANA IL 61801 

 1 UNIV OF MARYLAND 

 DEPT OF AEROSPACE ENGRG 

 A J VIZZINI 

 COLLEGE PARK MD 20742 

 1 DREXEL UNIV 

 A S D WANG 

 3141 CHESTNUT ST 

 PHILADELPHIA PA 19104 

 3 UNIV OF TEXAS AT AUSTIN 

 CTR FOR ELECTROMECHANICS 

 J PRICE 

 A WALLS 

 J KITZMILLER 

 10100 BURNET RD 

 AUSTIN TX 78758-4497 

 3 VA POLYTECHNICAL 

 INST & STATE UNIV 

 DEPT OF ESM 

 M W HYER 

 K REIFSNIDER 

 R JONES 

 BLACKSBURG VA 24061-0219 

 1 SOUTHWEST RESEARCH INST 

 ENGR & MATL SCIENCES DIV 

 J RIEGEL 

 6220 CULEBRA RD 

 PO DRAWER 28510 

 SAN ANTONIO TX 78228-0510 

 1 BATELLE NATICK OPERS 

 B HALPIN 

 313 SPEEN ST 

 NATICK MA 01760 

 3 DIRECTOR 

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 A FRYDMAN 

 2800 POWDER MILL RD 

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ABERDEEN PROVING GROUND

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 W C FRAZER 

 400 COLLERAN RD 

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 91 DIR USARL 

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 AMSRD ARL SL BB 

 D BELY 

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 J SMITH 

 H WALLACE 

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 A HORST 

 T KOGLER 

 AMSRD ARL WM BA 

 D LYON 

 AMSRD ARL WM BC 

 J NEWILL 

 P PLOSTINS 

 A ZIELINSKI 

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 B FORCH 

 M LEADORE 

 C LEVERITT 

 R LIEB 

 R PESCE RODRIGUEZ 

 B RICE 

 AMSRD ARL WM BF 

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 AMSRD ARL WM M 

 B FINK 

 J MCCAULEY 

 AMSRD ARL WM MA 

 L GHIORSE 

 S MCKNIGHT 

 E WETZEL 

 AMSRD ARL WM MB 

 J BENDER 

 T BOGETTI 

 L BURTON 

 R CARTER 

 K CHO 

 W DE ROSSET 

 G DEWING 

 R DOWDING 

 W DRYSDALE 
NO. OF NO. OF 

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 R EMERSON 

 D HENRY 

 D HOPKINS 

 R KASTE 

 L KECSKES 

 M MINNICINO 

 B POWERS 

 D SNOHA 

 J SOUTH 

 M STAKER 

 J SWAB 

 J TZENG 

 AMSRD ARL WM MC 

 J BEATTY 

 R BOSSOLI 

 E CHIN 

 S CORNELISON 

 D GRANVILLE 

 B HART 

 J LASALVIA 

 J MONTGOMERY 

 F PIERCE 

 E RIGAS 

 W SPURGEON 

 AMSRD ARL WM MD 

 B CHEESEMAN 

 P DEHMER 

 R DOOLEY 

 G GAZONAS 

 S GHIORSE 

 C HOPPEL 

 M KLUSEWITZ 

 W ROY 

 J SANDS 

 D SPAGNUOLO 

 S WALSH 

 S WOLF 

 AMSRD ARL WM RP 

 J BORNSTEIN 

 C SHOEMAKER 

 AMSRD ARL WM T 

 B BURNS 

 AMSRD ARL WM TA 

 W BRUCHEY 

 M BURKINS 

 W GILLICH 

 B GOOCH 

 T HAVEL 

 E HORWATH 

 M NORMANDIA 

 J RUNYEON 

 M ZOLTOSKI 

 AMSRD ARL WM TB 

 P BAKER 

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 R COATES 

 AMSRD ARL WM TD 

 D DANDEKAR 

 T HADUCH 

 T MOYNIHAN 

 M RAFTENBERG 

 S SCHOENFELD 

 T WEERASOORIYA 

 AMSRD ARL WM TE 

 A NIILER 

 J POWELL 
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 1 LTD 

 R MARTIN 

 MERL 

 TAMWORTH RD 

 HERTFORD SG13 7DG 

 UK 

 1 SMC SCOTLAND 

 P W LAY 

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 ROSYTH ROYAL DOCKYARD 

 DUNFERMLINE FIFE KY 11 2XR 

 UK 

 1 CIVIL AVIATION 

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 PO BOX 8 

 BEN GURION INTRNL AIRPORT 

 LOD 70150 

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 1 AEROSPATIALE 

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 A BTE CC RTE MD132 

 316 ROUTE DE BAYONNE 

 TOULOUSE 31060 

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 SEVEN OAKS KENT TN 147BP 

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 2600 JA DELFT 

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 2 DEFENSE TECH & PROC 

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32

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