Army Research Laboratory 

Aberdeen Proving Ground, MD 21005-5066 

ARL-TR-2452 April 2001 

Mechanical and Ballistic Data for 

Al25 19 Plate, Forgings, and Weldments 

Scott M. Grendahl, Richard J. Squillacioti, 

Daniel J. Snoha, and Christopher E. Miller 

Weapons and Materials Research Directorate, ARL 

Approved for public release; distribution is unlimited. 
Abstract 

The development and potential use of aluminum-armor alloys in the design and 

construction of combat vehicles has been repeatedly scrutinized as the military 

continually pushes toward lightweight, mobile, and more deployable forces. In doing so, 

it is necessary to fully characterize and understand the engineering material properties and 

the ballistic resistance of any prospective material. Aluminum 2519 (Al25 19) was 

developed nearly 20 years ago as a high-strength, heat-treatable alloy with excellent 

ballistic performance. This alloy was not utilized extensively beyond the experimental 

phase and as such has not been continually produced by the aluminum industry. 

Therefore, when the utilization of this alloy recently became expected, questions arose 

about the ability of the suppliers to reproduce the same product that had been developed 

in the past. As part of the ensuing analysis, the engineering properties and the chemical 

and ballistic resistance of the alloy required validation. Additionally, work needed to be 

performed to verify that the alloy and its various heat treatments were feasible for joining 

in the construction of armored vehicles. Several common heat treatments were 

characterized, in addition to the most common weld joints presently designed by Team 

Crusader. 

ii 
Acknowledgments 

The authors would like to thank Brian Pothier and Marc Pepi of the Processing and 

Properties Branch, and Dr. Martin Wells, John Chinella, and Chris Miller of the Metals and 

Ceramics Research Branch for their support in preparing the U.S. Army Research Laboratory 

(ARL) program for Team Crusader. Multiple changes to the original program were made 

throughout this effort, and their assistance was invaluable. The authors would also like to thank 

Dr. Bill Herman from General Dynamics Land Systems (GDLS), Rick Brynsvold from United 

Defense Limited Partnership (UDLP), and Dale Roark from the U.S. Army 

Tank-automotive and Armaments Command (TACOM) for their assistance in obtaining funding 

and material for testing, as well as for many rewarding discussions. Richard Squillacioti would 

like to acknowledge the support of the U.S. Aberdeen Test Center (ATC), especially Gary Rowe 

and Barbara Kaschenbach, for all the required ballistic testing and evaluations. 

. . . 

111 
iv 
Table of Contents 

Acknowledgments *‘* . . . . . . . ..~....f..._............f.._..._....................f...._.......f.............~.......f..... 111 

List of Figures . . . . ..~.............._............................_.........__..f........ . . . .._f_.._...__............. vii 

List of Tables . . . .._____.fff......f......~....__.________._....ff..f.............._____________..................f..._._

ix 

1. Introduction . . . . . . . . . . . . .._....................._.._..._......_.__._f....f.............f....._..__...................._... 1 

1.1 Materials Characterization ................................................................................... 

1.2 Ballistic Characterization ..................................................................................... 

1.2.1 Part A ............................................................................................................. 

1.2.2 Part B ............................................................................................................. 

1.3 Program Objectives .............................................................................................. 

1 

1 

1 

2 

2 

2. Procedures .f..._._,__.__f.........f.........______f__._..................f..._._______.____.f_f. + ................f.._._.__ 2 

2.1 

2.1.1 

2.1.2 

2.1.3 

2.1.4 

2.1s 

2.2 

Mechanical Property and Chemical Resistance Characterization 

of A12519.. ........................................................................................................... 

Tensile Testing ............................................................................................... 

Fatigue Testing .............................................................................................. 

General Corrosion ......................................................................................... 

Pitting Corrosion ........................................................................................... 

Stress Corrosion Cracking ............................................................................. 

Ballistic Characterization of A125 19 Plate and Welds ........................................ 

2 

S 

6 

7 

7 

10 

10 

3. Testing and Results . . . ..f.__.__._........................ + _f_.____.__.__.f....f...............,..._....____________ + 14 

3.1 

3.1.1 

3.1.2 

3.1.3 

3.1.4 

3.1-s 

3.2 

Mechanical Properly and Chemical Resistance Characterization 

of A12519 ............................................................................................................. 14 

Tensile Testing ............................................................................................... 14 

Fatigue Testing ............................................................................................... 14 

General Corrosion ......................................................................................... 14 

Pitting Corrosion ........................................................................................... 26 

Stress Corrosion Cracking . . . ....................... . .................................................. 28 

Ballistic Characterization of A125 19 Plate and Welds ........................................ 32 

4. Summary and Conclusion ...._._._______..f.... e .. . . . . . . . . . . ..______...~......................___.~.....~...~... 39 

4.1 Part 1: Mechanical Property and Chemical Resistance Characterization . . . .._...__ 39 

4.2 Part 2: Ballistic Characterization .___._____..__.f_............._______..____.__.ff..f......f.f..__._____

44 

V 
5. References ................................................................................................................. 45 

Appendix A: Amendment 1 to MIL-DTL-46192 C (MR) ................................... 47 

Appendix B: Individual‘Test Shots for Developing the VSO Acceptance 

Tables . . . . . .._...._............_..............................._..._.......__._....................... 53 

Distribution List . . . . . . . . . . . . . . . . . . . . . . . . . . . ..__...___._______._................................_.f...._________...f.... 75 

Report Documentation Page . . . . . . . . . . . . . . . . . . . . . . .._._...._........._...............................f._..._... 77 

vi 
List of Figures 

Figure 

1. 

T 2. 

3. ? 

4. 

5. 

6. 

7. 

8. 

9. 

10. 

11. 

12. 

13. 

14. 

15. 

16. 

17. 

18. 

Single-V Joint Schematic With Longitudinal Specimen Orientation .f.....f..._..._._.. _.. 

Double-V Joint Schematic With Transverse Specimen Orientation ..____._..f............... 

Tensile Specimen Schematic ___. .*. . . . . . . . . . . ___ __ ______.... . . . . . . . . . . . . . __. f._...f.._......_.__f.f....f........ 

Rotating-Beam (R. R. Moore) Specimen Schematic . . . . ..______..._....... ....___.._...........ff... 

Axial Fatigue Specimen for Unwelded Base Material . . . . . . . . . .._. .__...f...f...._........f......... 

Axial Fatigue Specimen for Welded Material . ..____..................._..................._.f.......... 

Welded-Plate Axial Fatigue Specimen Orientation . . ..___....................._. + ... . ...f........... 

SCC C-Ring Specimen Schematic . ..f............_...____...............____....................._............ 

SCC Sandwich Specimen Schematic .*.............__..*.....*...........~.....................*............. 

Disassembled 75-mm Aluminum Projectile. . . ..___..___.............._...._.. ._*.........._........_.... 

Assembled 75-mm Aluminum Projectile .______._____ff.f....ff.____._____..........__.__.____....f........ 

Rotating Beam and Axial Fatigue Data for the T87-T87 Weldment, R-Ratio = - 1, 

Kt = 1 .._... ..*.......f..._.______...f........f..._...__.__f......................f....*...........__.f..*................f... 

Rotating Beam and Axial Fatigue Data for the T87 Base Plate, R-Ratio = - 1, 

Ia = 1 . . . . . . . . . . .f.......f..._......_.f_.........f.......__..f.f........._........._.f*....................*................... 

Rotating Beam and Axial Fatigue Data for the T6 Surrogate, R-Ratio = - 1, 

Kt = 1 _.._................._._ *.* .. . . . . . . . . . . . . . .._........ *...* . . . . . . . . . . . . . . . . . . . . .._........................................ 

T87-T87 1 00-Hr Salt-Fog-Exposed R. R. Moore Specimen __,, + f....._f____.___._.........._._.. 

T87 Base Alloy lOO-Hr Salt-Fog-Exposed R. R. Moore Specimen .......................... 

T6 Surrogate lOO-Hr Salt-Fog-Exposed R. R. Moore Specimen .............................. 

Surface Detail of T87-T87 lOO-Hr Salt-Fog-Exposed R. R. Moore Specimen ......... 

& 

5 

5 

6 

8 

8 

9 

9 

10 

11 

12 

12 

22 

22 

23 

23 

24 

24 

25 

vii 
Fipure 

19. 

20. 

21. 

22. 

23. 

24. 

25. 

26. 

27. 

28. 

29. 

30. 

31. 

32. 

33. 

34. 

35. 

Surface Detail of T87 Base Alloy lOO-Hr Salt-Fog-Exposed R. R. Moore 

Specimen ................................................................................................................. 

Surface Detail of T6 Surrogate lOO-Hr Salt-Fog-Exposed R. R. Moore 

Specimen ................................................................................................................. 

T87-TX7 With 23 19 Filler Metal Corrosion Specimen After Chemical Cleaning .... 

T6 Corrosion Specimen After Chemical Cleaning.. ................................................. 

T87-T87 With 23 19 Filler Metal Corrosion Specimen After Chemical Cleaning .... 

C-Rings and Sandwich Specimens After One Day of Salt-Fog Exposure.. .............. 

C-Rings and Sandwich Specimens After 10 Dgys of Salt-Fog Exposure ................. 

Cleaned C-Ring Specimens After 10 Days of Salt-Fog Exposure.. .......................... 

Cleaned Sandwich Specimens After 10 Days of Salt-Fog Exposure.. ...................... 

Details of Cleaned C-Ring Specimens After 10 Days of Salt-Fog Exposure ........... 

Details of Cleaned Sandwich Specimen After 10 Days of Salt-Fog Exposure.. ....... 

75-mm Projectile Test Firing 30-l-l.. ............................................................... . ...... 

75-mm Projectile Test Firing 30-2-l.. ...................................................................... 

75mm Projectile Test Firing 35-5 After Both Shots (Front). .................................. 

75-mm Projectile Test Firing 35-5 After Both Shots (Back) ................................... 

75-mm Projectile Test Firing 50-2 After Both Shots (Front) ................................... 

75-mm Projectile Test Firing 50-2 After Both Shots (Back) ................................... 

Page 

25 

26 

26 

27 

28 

29 

29 

30 

30 

31 

31 

35 

35 

36 

36 

37 

37 

. . . 

Vlll 
Table 

List of Tables 

1. 

2. 

3. 

4. 

5. 

6. 

7. 

8. 

9. 

10. 

11. 

12. 

13. 

14. 

15. 

7 

B-l f 

Material Characterization Test Matrix for Al25 19 Forgings, Plate, and 

Weldments ................................................................................................................. 

Ballistic Curve Development Table ........................................................................... 

Tensile and Elongation Data for the T87-TS7 Weldments ........................................ 

Tensile and Elongation Data for the T87-T6 Weldments .......................................... 

Tensile and Elongation Data for the T6 Alloy.. ......................................................... 

R, R. Moore Rotating-Beam Fatigue Data for the T87-T87 Weldments.. ................. 

Axial Fatigue Data for the T87-T87 Weldments ....................................................... 

R. R. Moore Rotating-Beam Fatigue Data for the TX7 Alloy .................................... 

Axial Fatigue Data for the T87 Alloy ........................................................................ 

R. R. Moore Rotating-Beam Fatigue Data for the T6 Alloy ...................................... 

Striking Velocity Data ............................................................................................... 

Minimum Required Striking Velocity Ballistic Limits .............................................. 

VsO Velocity Data ....................................................................................................... 

Minimum Required Ballistic Limits 0.50-Cal. AP M2 Projectiles vs. Al25 19 Plate 

at 0” Obliquity ............................................................................................................ 

Minimum Required Ballistic Limits 14.5-mm BS 41 Projectiles vs. A12519 Plate 

at 0” Obliquity ............................................................................................................ 

Individual Test Shots for Developing the VSO Acceptance Tables ............................ 

4 

13 

15 

15 

16 

17 

18 

19 

19 

20 

33 

34 

38 

40 

42 

55 

ix 

1. Introduction 

1.1 Materials Characterization. The FY99 program objectives were accomplished by 

substantiating the values of the material properties of the Al25 19 base metal, heat treatments, and 

weldment mechanical properties, and by specifically addressing weldment toughness and stress 

corrosion cracking (SCC) in the weldment and heat-affected zones (HA%). A good deal of 

mechanical property data was previously published for this material. This work made an attempt 

to validate the existing data and fill in some of the pertinent data voids. Several proposals were 

provided to the U.S. Army Tank-automotive and Armaments Command (TACOM) by the 

U.S. Army Research Laboratory (ARL) to address these issues. TACOM, United Defense 

Limited Partnership (UDLP), and General Dynamics Land Systems (GDLS) agreed on a subset 

of those proposals. This involved limited tensile and corrosion testing and somewhat more 

extensive fatigue testing. An evaluation of the corrosion resistance was critical, including SCC 

of both the T6 forging base plate and the weld/HA2 of the various heat treatment/alloy 

combinations to be utilized. 

1.2 Ballistic Characterization. To deliver the best products to the soldier, requirements are 

specified and quality assurance provisions (or verification or certification) are developed that 

provide the accept/reject criteria for determining whether the US. Government will use an item. 

The two ballistic standardization documents, MIL-STD-1946 [l] and MIL-A-46192 [2], had 

voids that needed to be addressed. The ballistic characterization effort was divided into two 

parts: 

l Part A: develop acceptance criteria (striking velocities) for weldments, and 

l Part B: develop two ballistic acceptance tables for MIL-A-46192 [2] and incorporate them 

into the specification via an amendment, and retitling the specification MIL-DTL-46192. 

1.2.1 Pati A. The Part A effort concentrated on updating MIL-STD-1946 [l] (a canceled 

document) by adding striking velocities for 15-, 20-, 25-, 30-, 35-, and 50-mm-thick A12519 base 

plate. The 57-mm Ml001 A plate-proofing projectile was proposed for thicknesses between 

1 
15 and 25 mm. The 7%mm Ml002A plate-proofmg projectile was proposed for thicknesses 

between 30 and 50 mm. Both projectiles are made of aluminum. The Al25 19 material utilized 

was supplied by the Office of the Program Manager (OPM). 

1.2.2 Part B. The Part B effort also utilized a canceled document, MLA-46192 [2]; 

however, the standardization group that governs the upkeep of documents was persuaded to 

reinstate the specification after much discussion. The reinstated document was designated 

MLA-46192 [2]. The two required tables that needed to be generated were specified by the 

OPM so that material could be bought and accepted up to 4.000 in. These included both the 

ballistic limit of Al25 19 vs. the 0.50-cal. projectile for 1.5-3.0-in thickness, and the ballistic limit 

of A12519 vs. the 14.5-mm BS41 projectile for 3&4.0-in thickness. 

1.3 Program Objectives. This work encompassed the agreed-upon revisions to the 

previous package submitted to OPM Crusader on 30 June 1998. Changes were incorporated to 

more effectively address the Crusader requirements. The objective of this effort was to provide 

mechanical, chemical resistance, and ballistic data on the high-strength A12519 base plate and 

weldments of some heat treatments of the alloy. .The mechanical property and chemical 

resistance data were suitable for the material certification and structural design of the vehicle’s 

chassis. The ballistic information will fill the voids in the ballistic shock database, which is 

required to address the welding procedure qualification requirements and weldment ballistic 

shock loading requirements. Additionally, ballistic acceptance criteria were developed for plate 

thicknesses over 1.5 in, The data acquired will be used for determining the quality and 

consistency of the weld procedure. 

2. Procedures 

2.1 Mechanical Property and Chemical Resistance Characterization of A12519. The 

mechanical characterization was performed .on the base alloy in different heat-treated conditions, 

as well as on weldments of the alloy to itself and to other aluminum alloys. Previous studies of 

this material have produced a limited database of material and weldment properties. This 

2 
program attempted to validate some of the previous data, as well as expand the information to 

include forgings and various weldments. The test matrix in Table 1 includes the following types 

of testing: (1) tensile tests at room temperature and 300 OF, (2) rotating beam (R. R. Moore) and 

dog bone fatigue tests, and (3) general corrosion, pitting corrosion, and stress corrosion cracking 

characterization. The various heat treatments and weldments of the material investigated 

included A12519-T6 plate as a surrogate for T6 forgings, A12519-T87 wrought base plate, weld 

joints for A12519-T87 to itself using Al2319 filler wire, and weld joints for A12519-T87 to 

A12519-T6 forging using Al2219 filler wire. Not all tests were performed for each material 

configuration. Again, the goal was not to redevelop an Al25 19 database, but only to fill the 

voids in the data and to verify the suppliers’ ability to manufacture products similar to those in 

the past. Table 1 lists the quantities and orientations of the specimens evaluated as part of the 

mechanical and chemical resistance characterization. 

The material configurations were representative of planned sections for the A12519 hull 

structure in the Crusader self-propelled howitzer (SPH) and resupply vehicle (RSV). The weld 

joints were representative of those planned for the fabrication of this vehicle system. More 

detailed descriptions of each test are listed in the following sections. The mechanical and 

corrosion resistance portion of the program centered on evaluating four combinations of alloys 

and weldments. The mechanical testing was limited to both tensile and fatigue testing due to 

cost restrictions. 

Multiple-pass automated gas metal arc welding (GMAW) was utilized in joining the 

weldments. These weldments were tested in two orientations. Longitudinal specimens were 

machined from a single-v joint weldment with the specimen axis parallel to the weld fusion line. 

This resulted in a specimen consisting primarily of weld metal, although the appearance of HAZ 

material might be possible, depending on the weldment and the machining. A schematic of the 

cross section of the single-V joint weldment is shown in Figure 1. Transverse tensile specimens 

were machined from an offset double-v joint across the weld, with the gauge section of the 

specimen containing base metal, HAZ, and weld metal. A schematic of the cross section of the 

double-V joint weldment is shown in Figure 2. Weldments were measured for yield strength 

3 
Table 1. Material Characterization Test Matrix for A12519 Forgings, Plate, and Weldrnents 

P 

II Test Test Details [ T6 Forging 2519-T87 Base T87 to T87 25 19-T87 to I Test Standard 

ASTM-G-47 [ 101 

,.-, , 
Figure 1. Single-V Joint Schematic With Longitudinal Specimen Orientation (Not to 

Scale). 

Figure 2. Double-V Joint Schematic With Transverse Specimen Orientation (Not to 

Scale). 

(YS), ultimate tensile strength (UTS), percent elongation, and reduction in area 

(RA) in both directions. Longitudinal tensile elongation was recorded, although this is not a true 

measure of weldment ductility due to the nonhomogeneity of the specimen in that orientation. 

The critical measure of weldment ductility was evaluated under the ballistic shock’portion of this 

work. Six room-temperature specimens from each orientation were tested for the Al25 19-TX7 

weldment to itself, along with two elevated temperature tests. Two room-temperature tests were 

performed for the Al25 19-T87 welded to the Al25 19-T6 forging in the longitudinal direction, 

which isolated any ductility loss in the weld. 

2.1.1 Tensile Testing. Tensile tests were performed according to established standards, such 

as ASTM-E-8 [3] and AWS-B-4.0 [4], for the A12519-T6 forgings and weldments, respectively. 

Six specimens were tested for the forgings in each orientation, four at room temperature and two 

at 300 “F. Two samples were reserved as spares for each orientation. The tensile specimens 

were tested with full stress-strain to failure. The data acquired included YS, UTS, percent 

elongation and RA in the longitudinal and transverse orientations. Figure 3 shows a schematic of 

the tensile specimen utilized. 

5 
4.75 f l/32 

Notes: (1) Dimensions in inches. 

(2) Tolerances, unless noted. 

Squareness I Perpendicular f 0.001 TIR 

( 1 Parallel f 0.001 TIR 

(3) Diameters Q Concentric To m f 0.001 TIR 

(4) Fractions f l/64 

(5) Decimal XXX + 0.005 

x.xxx f 0.001 

x.xXxX f 0.0005 

Figure 3. Tensile Specimen Schematic. 

2.1.2 Fatigue Testing. Rotating beam fatigue tests (R. R. Moore type) were performed for 

several variants of A12519 in both the longitudinal and transverse direction Continuous-radius 

round-bar specimens were tested at an applied load ratio of - 1 .O to a run-out limit of 10’ cycles. 

The samples reaching the run-out limit were discontinued. The testing was carried out at room 

. 

temperature on Satec R. R. Moore machines operating at a rate of 9,000 r-pm. Stress levels were 

chosen to produce cycle lives between lo5 and 10’ cycles. Material configurations included 

Al25 19-T6 forging surrogate, Al25 19-T87 plate, and weldments between A12519-TX7 plates. 

The forging surrogate and weldment testing consisted of four specimens at six different stress 

levels. Stress vs. number of cycles (S-N) curves were derived from the acquired data. An 

6 
appropriate mathematical model was used to develop regression curves for the data. The 

equations derived to best fit the data are depicted on the individual plots. The base material data 

was verified and contrasted with the previously accepted values at two different stress levels. 

Bending fatigue data were also generated for these three materials after the specimens were 

exposed to a salt fog environment for 100 hr. This testing was performed in accordance with 

ASTM-B-l 17 [S], and it provided a measure for the effect of pitting on the fatigue life for these 

material configurations. A schematic of the rotating beam specimen utilized is depicted in 

Figure 4. 

Axial fatigue values were generated using a rectangular dog-bone specimen for A12519-T87 

and weldments. The goal for this testing was to evaluate the entire throat of the welded 

structure, including both the cap and root passes. This type of testing provided information 

relative to the weld fatigue life that a machined round-bar specimen masks. The base material 

was tested to provide baseline values for this geometry. Four specimens were tested at two stress 

levels. S-N curves were derived from the acquired data. An appropriate mathematical model 

was used to develop regression curves for the data. The equations derived to best fit the data are 

depicted on the individual plots. Schematics of the axial tensile specimen utilized are shown in 

Figures 5 and 6 for the unwelded and welded specimens, respectively. Specimens were obtained 

from the welded plates, as depicted in Figure 7. 

2.1.3 General Corrosion. Three coupons of A12519-T87 welded to itself were immersed in 

a solution of 4.0-M NaCl, 0.5-M KCI, and 0.1-M nitric acid for 96 hr as per ASTM-G-34 [6]. 

Samples were examined after 4, 24, 48, 72, and 96 hr of exposure. Several panels of base 

material were evaluated through leveraged efforts of other ARL programs. 

2.1.4 Pitting Corrosion. Coupons of Al2519-T6 forging surrogate and Al25 19 T&7-T87 

weldments were exposed to a 5% NaCl solution for 1,000 hr per ASTM-B-l 17 [8]. Coupons 

were examined following 1, 10, 100, 400, and 1,000 hr of exposure for pitting. FoIlowing 

exposure, coupons were cleaned and re-examined. 

7 
Fillet \ 

Notes: (1) 

(2) 

(3) 

(4) 

(5) 

(6) 

Relief \ Centers 

Note 3. 

\ 

#6 drill & Tap 

l/4- 20, 0.5 

Dimensions in inches. 

Radius may be changed depending on gage length 

Taper 0.625 f 0.005Kt on diameter. 

Centers for tumiug, use 60’ included angle center with 

maximum diameter of center, 0.344 f 0.005 diameter. 

l/4 - 20 tapped holes must be concentric to outside 

diameter within 0.002 TIR. 

All outside diameters. Must be concentric to center line 

and to each other within 0.0005 TIR. 

Figure 4. Rotating-Beam (R. R. Moore) Specimen Schematic. 

- 15-0 b 

3.60 0.50 

2.90 2.00 i--t/-T, 1 

v 

0.25 

R = 6.00 

Notes: (1) Dimensions in inches. 

(2) Tolerances, unless noted. 

Squareness I Perpendicular + 0.001 TIR 

1 1 Parallel + 0.001 TIR 

(3) Factions -t l/64 

(4) Decimal X.Xx -t- 0.005 

x.xXx 1- 0.001 

x.xXxX _+ 0.0005 

I .oo 

1-i 

pzq 

Figure 5. Axial Fatigue Specimen for Unwelded Base Material. 

8 
Notes: (1) Dimensions in inches. 

(2) Tolerances, unless noted. 

Squareness I Perpendicular + 0.001 TIR 

1 1 Parallel f 0.001 TIR 

(3) Fractions + l/64 

(4) Decimal XXX f 0.005 

x.xxx f 0.001 

x.xxxx + 0.0005 

Figure 6. Axial Fatigue Specimen for Welded Material. 

Figure 7. Welded-Plate Welded-Plate Axial Fatigue Fatigue Specimen Specimen Orientation. Orientation. 

9 
2.1.5 Stress Corrosion Cracking. Twelve samples from A12519-T6 forgings were evaluated 

for SCC susceptibility. C-ring specimens were produced according to ASTM-G-38 [9] and 

alternately immersed in 3.5% sodium chloride solution, as specified in ASTM-G-47 [lo]. A 

schematic of the C-ring specimen is shown in Figure 8. Both weldment configurations (T&7-T87 

and T87-T6) were evaluated for SCC behavior in accordance with ASTM-G-44 [ 1 l] using a 

sandwich weldment specimen. This specimen geometry simulates a rigid structure; when it is 

subjected to a corrosive environment, it provides. a screening test for SCC. GDLS performed all 

welding. A schematic of the sandwich weldments is depicted in Figure 9. 

kO.748 + 0.748 - 

\ No. lo-32 

Typical 

Notes: (1) Dimensions in inches. 

(2) Tolerances, unless noted. 

Squareness I Perpendicular f 0.001 TIR 

1 ( Parallel 4 0.001 TIR 

(3) Fractions f l/64 

(4) Decimal XXX f 0.005 

x.xxx f 0.001 

x.xxxx f 0.0005 

Figure 8. SCC C-Ring Specimen Schematic. 

2.2 Ballistic Characterization of A12519 Plate and Welds. The objectives for this portion 

of the work package were threefold. 

(1) Standardize the base plate dimensions for the ballistic shock test used for determining 

the critical velocity, that is to be subsequently used to calculate striking velocities for the 

10 


(3) Expand the ballistic limit acceptance data for thicker sections of A12519. Thicknesses 

were tested against 0.50-Cal. armor-piercing (AP) M2 and 14.5-mm armor-piercing 

incendiary (API) BS41 threats. Plate thicknesses were 1.50, 2.25, 3.00, 3.50, and 

4.00 in. The data developed by these tests were used to expand the ballistic acceptance 

tables of MIL-DTL-46192 [2]. 

Ideally, the development of the specification curves for Al25 19 requires three different 

manufacturers, each providing three lots of material in three different thicknesses within the two 

thickness ranges previously discussed. This is the minimum sample size to address lot-to-lot and 

manufacturer-to-manufacturer variances. This amounts to 54 ballistic-limit data points. The test 

matrix is shown in Table 2. 

Table 2. Ballistic Curve Development Table 

No. of Plates Required 

Supplier A Supplier B Supplier C 

3 3 3 

3 3 3 

3 3 3 

3 3 3 

3 3 3 

3 3 3 

Plate Threat 

Thickness Obliquity 

(in) (“> 

Projectile 

1.50 0 0.50-Cal. AP M2 

2.25 0 0.50-cal. AP M2 

3.00 0 OSO-Cal. AP M2 

3.00 0 14.5-m BS 41 

3.50 0 14.5~mm BS 41 

4.00 0 14.S-mm BS 41 

The ballistic limit for each of the data points needs to be determined by the method of 

maximum likelihood from 12 test rounds fired in accordance with the Langlie method. An 

appropriate mathematical model was used to develop a regression curve, where the values of the 

constants in the curve were determined using the method of least squares. The curve was then 

utilized to generate the tables in Appendix A. The minimum acceptable ballistic limit 

requirements were the;i set to reject 5% of the plates submitted for “first time” lot-acceptance 

testing. 

13 
3. Testing and Results 

3.1 Mechanical Property and Chemical Resistance Characterization of A12519. 

3.1.1 Tensile Testing. The tensile strength and elongation data for the T87-T87 and T87-T6 

weldments and the T6 alloy are presented in Tables 3-5, respectively. The specimen number 

indicates an “L” for those specimens machined in the longitudinal direction, and a “T” for those 

machined in the transverse direction. 

3.1.2 Fatigue Testing. The R. R. Moore rotating bear-n and axial fatigue test data for the 

T87-T87 weldment and the T87 and T6 alloy base plate are presented in Tables 6-10, 

respectively. The corresponding graphs are presented in Figures 12-14, respectively. The 

100-hr salt-fog-exposed specimens for the T87-T87 weldment, the T87 base alloy, and the T6 

surrogate are depicted in Figures 15-17, respectively. The surface details of these respective 

figures are presented in Figures 18-20. 

3.1.3 General Corrosion. After 5 hr of exposure to the sodium chloride, potassium chloride, 

and nitric acid solution, all three T87-T87 coupons had small bubbles effervescing from the 

surface and had caused the solution to cloud. There was less activity at the weld. Upon closer 

inspection, the ends of the coupon had darkened, while the weld and heat-affected zone remained 

bright. The welding material was Al23 19 for these weld configurations. 

The reaction slowed significantly, and a reddish-brown scale formed on the nonweld portions 

of the coupon after 24 hr. The scale appeared to be loosely adherent. Although bubbles formed 

on the welded portions of the coupons, these areas remained bright. 

After 48 hr, the weld began to tarnish, while a reddish product formed in the heat-affiited zone. 

The reddish-brown exfoliant continued to form on the rest of the coupon. The panels’ appearance 

changed only slightly after 72 hr. There was more of the reddish product on the weld and in the 

heat-affected zones, and more of the reddish-brown exfoliant than previously observed. 

14 
Table 3. Tensile and Elongation Data for the T87-TS7 Weldments 

4D/5D 

hmple No. Temperature UTS 0.2% YS Elongation RA Ult. Load 0.2% Load Orig. Gauge Final Gauge Orig. Area 

(“F) (ksi) (ksi) (%) (%) (lb) (lb) ( in) (in1 ‘-I I (in21 \-- , 

8.5’17.2 1 1 8,523 1 3,960 1 

-.- - 212.5 1 - -- Ll R.T. 42.4 19.7 1 26.8 2.3712.93 1 0.433 

L2 R.T. 42.7 19.9 20.5116.4 33.7 8,590 3,999 2i2.5 2.4112.91 0.412 

L3 RT. 42.1 19.7 15.5113.6 18.1 8,405 3,930 212.5 2.3 l/2.84 0.456 

Tl R.T. ) 43.5 1 26.0 [ 6.014.8 8,754 I T2 1 R.T. I 44.1 I 27.1 I 5.0/4.4 I 21.6 1 8,862 I 5,453 2i2.5 2.1012.61 0.448 

T3 R.T. 1 43.0 1 26.8 ) 4.Ot3.2 ) 15.9 1 8,644 1 J,JU” <1QL , 1L ?/2.5 2.08/2.58 0.464 I T4 1 R.T. 1 43.9 1 26.8 I 5.014.0 I 23.4 I 8,821 I 5,387 2i2.5 2.10/2.6 0.443 

& I R.T. I\. I. 1 , -r-r.* 43.8 , 1 28.7 *,.v , 1 J.YI7,” 5.014.4 , 1 25.8 I, .1 1 8,816 “,Y”Y , 1 5,765 5,837 212.5 2i2.5 2.10/2.62 2.1012.61 

0.432 

0.436 

T7 T 300 1 35.6 1 25.4 1 6.515.2 1 33.7 1 7,168 1 5,lO: T 2/2.5 2.13/2.63 0.412 

T8 \ 300 1 36.0 1 26.0 1 7.015.6 1 33.4 1 7.216 1 5,198 1 212.5 1 2.14/2.64 1 0.412 

Table 4. Tensile and Elongation Data for the T87-T6 Weldments 

4D 

Sample No. Temperature UTS 0.2% YS Elongation RA Ult. Load 0.2% L,oad Orig. Gauge Final Gauge Orig. +rea 

I &sil I Ckksi) I (%) (%I W (lb) (3 (in) (in’) 

L1 R.T. ) 42.1 ) 19.8 1 15 18.1 8,424 3,968 2.0 2.30 ] 0.200 

II T .3 RT I 47.1 I 2n.2 I 18 30.2 8.437 4.046 2.0 2.36 I 0.200 
Table 5. Tensile and Elongation Data for the T6 AIIoy 

4D 

SampIe No. Temperature UTS 0.2% YS Elongation RA 

C%) (%I 

Ult. Load 0.2% Load Orig. Gauge Final Gauge Orig. Area 

Ilb‘l llhl iin‘l tin> (in2) 

18.6 

t- 24.7 

12,520 

““jI 12.440 9,402 1 

L5 R.T. 63.5 48.8 11.5 19.4 12,470 9,589 2.0 2.23 0.196 

L6 R.T. 63.5 48.7 11.5 20.1 12,500 9,566 2.0 2.23 0.196 

L7 300 52.5 44.6 13.0 44.3 10,280 8,752 2.0 2.26 0.196 

L8 300 52.0 44.4 14.0 38.8 10,170 8,709 2.0 2.22 0.196 

Tl R.T. 65.0 51.0 10.0 24.3 12,740 10,040 2.0 2.20 0.196 

T2 R.T. 64.5 48.2 10.5 23.6 12,650 9,469 2.0 2.21 0.196 

T3 R.T. 64.5 48.2 10.0 21.5 12,650 9,466 2.0 2.20 0.196 

T4 R.T. 64.5 48.3 10.0 16.1 12,690 9,493 2.0 2.20 0.196 

T5 R.T. 64.5 49.2 10.5 22.6 12,690 9,664 2.0 2.21 0.196 

T6 R.T. 65.0 49.7 11.0 24.7 12,750 9,761 2.0 2.22 0.196 

T7 300 52.0 46.1 13.5 49.0 10,210 9,058 2.0 2.27 0.196 

T8 300 52.0 47.5 14.0 48.4 10,220 9,32 1 2.0 2.28 0.196 
Table 6. R. R. Moore Rotating-Beam Fatigue Data for the TS7-T87 Weldments 

Machining 

Direction 

RRMT5 

(in) (ksi) 

0.2508 18 

(lb) 

13.9 2,936,929 gauge transverse 

RRMT7 0.2512 18 14.0 969,744 gauge 

RRMT15 0.25 14 18 14.0 7,148,OOO mw 

RRMT16 0.2515 18 14.1 7,304,500 gauge 

RRMT2 0.2515 20 15.6 8,418,OOO &awe 

RRMT13 0.2513 20 15.6 1,269,811 e-w 

RRMT19 0.2515 20 15.6 573,321 P-w transverse I 

transverse I 

transverse I 

transverse I 

transverse I 

transverse 

transverse 4 transverse 

transverse 

RRMT18 0.2517 24 18.8 371,001 gauge 

RRMTl 0.2515 28 21.9 50,000 gauge 

transverse I 

transverse I 

FxMT8 0.2513 28 21.8 108,388 P-w 

RRMT9 0.2515 28 21.9 122,291 w-w 

FXMT21 0.2515 28 21.9 106,980 gauge 

FSMT20 0.2514 32 25.0 0 gauge 

RRMT6 0.2145 16 12.5 1 O,OOO,OOO discontinued 

FCRMT23 0.2507 16 12.4 10.000.000 discontinued 

omitted for fit 

omitted for fit 

omitted for fit 

lowitudinal 

lontitudinal I 

longitudinal 1 

loneitudinal I 

lon&udinal I 

longitudinal I 

lon&udinal I 

longitudinal I 

RF&IT24 0.2510 16 12.4 10,000,000 discontinued 

RF&IL22 0.2515 18 14.1 1,873,OOO gauge 

RRTvIL23 0.2515 18 14.1 7,X87,000 gauge 

RRML8 0.2522 20 15.7 1,996,OOO gauge 

FNML9 0.2512 20 15.6 6,801,OOO gauge 

FSML19 0.2519 20 15.7 2,728,OOO gauge 

FXML24 0.2513 20 15.6 1,311,ooo gauge 

RRML2 0.2516 22 17.2 1.403.000 radius 

RRMLS 0.2514 I 22 17.2 361,394 radius 

RJxMLl3 0.2513 22. 17.1 727,000 w-w 

FSML17 0.2513 22 17.1 402,804 gauge 

FCRMLl 0.2511 24 18.7 520,000 gauge 

longitudinal I 

longitudinal 1 

lomzitudinal 1 

RRMLlO 0.2521 24 18.9 324,850 P-w 

FSML14 0.252 1 24 18.9 453.490 nawe 

17 
Table 6. R. R. Moore Rotating-Beam Fatigue Data for the T87-TS7 Weldments 

(Continued) 

I I \R31, I I I I ‘I 

RR ML11 1 0.2513 1 28 1 21.8 124,858 ) gauge 

RRMLl5 1 0.2519 1 28 1 

1 longitudinal ]I 

22.0 148,651 1 longitudinal 11 

RRML4 

14.1 

0.2513 18 14.0 

RRMLS 

14.0 

0.2516 18 14.1 

SF8 

17.1 

0.2511 10 7.8 

SF1 

17.1 

0.25 14. 14 10.9 

SF4 

7.8 

0.2515 14 10.9 

SF3 0.25 17 18 

SF7 0.2514 18 

SF2 0.2512 22 

SF5 0.2513 22 

SF6 0.2513 10 

715,000 gauge salt fog 

1 O,OOO,OOO 

614,563 

discontinued 

radius 

omitted for 

salt fog 

fit 

127,000 gauge salt fog 

1 

118,000 

O,OOO,OOO 

gauge 

discontinued 

salt fog -, 

omitted for 

10,000,000 

fit 

discontinued omitted for fit 

1,664,OOO radius salt fog 

1,787,000 gauge salt fog 

2.884.156 radius salt foe 

Table 7. Axial Fatigue Data for the TS7-T87 Weldments 

Sample Alternating Alternating Cycles to Failure Machining 

No. Area Stress Load Failure Location Direction 

(in”) (ksi) (lb) 

7 0.380135 8 3,062 396,875 HIA2 axial transverse 

I 6 80.380058 0.380135 I ) 8 I 3,041.0 

12.5 -4,769 

I 12.5 4.740 

t 507,906 1 HAZ 

1 123,254 

I axial transverse II 

axial 

-t- axial 

axial 

-t- axial 

axial k axial 

18 
Table 8. R. R. Moore Rotating-Beam Fatigue Data for the TS7 Alloy 

Sample Measured Maximum Maximum Cycles 

No. Diameter Stress Load to Failure 

Failure 

Location 

Machining 

Direction 

(in (ksi) (lb) 

RRML2 0.2511 24 18.7 7,294,789 radius transverse 

RJXML8 0.2517 25 19.6 10,269,OOO gauge transverse 

RRMT u---4 0.25 16 26 20.3 4,240,530 gauge transverse 

RRMLl 0.2513 30 23.4 3,645,OOO gauge transverse 

RRMT ,&UU.IY 7 I n7517 V.C.3 A . 17 7.5 s21 .x73 Pawe transverse 

ii 56.7 

---I-‘- a-- --a 

FWvlL5 0.2521 272,99 1 gauge transverse 

RRML3 0.252 23 18.1 1 o,ooo,ooo discontinued omitted for fit 

RRML6 0.2511 28 21.x 1 o,ooo,ooo discontinued omitted for fit 

- 

RRTbfl 

, -y---7--- 

RRML16 0.2526 12.7 416,195 gauge salt fog 

RRMLlO 0.2517 18 14.1 429,93 8 gauge salt fog 

RRML9 0.2516 22 17.2 235,876 gauge salt fog 

EUXML12 -0.2518 10 7.8 10,000,000 discontinued omitted for fit 

RRML141 I__-_ -- , - - ~7516 I 1 --I---’ I r IO I 7.8 1 10.000.000 1 discontinued 1 omitted for fit 

Table 9. Axial Fatigue Data for the T87 Alloy 

19 
Table 10. R. R. Moore Rotating-Beam Fatigue Data for the T6 Alloy 

Sample Measured Maximum Maximum Cycles to Failure 

No. Diameter 

Machining 

Stress Load Failure Location Direction 

~ RRMT13 I 0.2502 I 20 I 15.4 I 8,700,000 

6,873,OOO 

X.521,207 

radius 

gauge 

gauge 

transverse 

transverse 

transverse 

gauge 1 transverse 71 

864,000 1 gauge transverse II 

1 O,OOO,OOO discontinued 1 omitted for fit 11 

1 O,OOO,OOO 1 discontinued 1 omitted for fit 11 

1 o-oofi 000 I discontinued Iomitted for fit II 

lXRML6 

RRML15 

RRMLl 

RRML4 

RRML13 

RRMLS 

RRML9 

RRML18 

RRML22 RRML23 

0.2513 

0.2515 

0.25 14 

22 

22 

24 

17.1 

17.2 

18.7 

9,987,OOO 

11,178,OOO 

3,X77,955 

5,855,614 

gauge 

radius 

gauge 

gauge 

longitudinal 

longitudinal 

longitudinal 

longitudinal 

0.2517 24 18.8 2,3 12,000 1 gauge 1 longitudinal 11 * 

0.2517 24 18.8 4,64?,175 1 gauge ) longitudinal 11 

0.2517 , 28 21.9 954,126 1 gauge 

0.2511 28 21.8 

1 longitudinal II 

1,X32,000 w-w longitudinal 

0.2514 28 21.8 1,326,OOO gauge longitudinal 

0.2518 28 21.9 670,606 gauge longitudinal 0.2519 32 25.1 -. 

459.000 1 Eawe I lonfhAina1 II 

20 












Table 11. Striking Velocity Data 

Plate Thickness Projectile Shot No. Velocity Result Remarks 

(m@ b-J@ 

generate the tables in Appendix A. The values of the constants in the regression curve were 

determined using the method of least squares. ! 

The minimum acceptable ballistic limit requirements were then set to reject 5% of the plates 

submitted for first time lot-acceptance testing. The resulting ballistic data tables are identified as 

Tables 14-15. As mentioned previously, these tables should be incorporated into 

33 
Table 12. Minimum Required Striking Velocity Ballistic Limits 

[ IThick.nesk( Required IThicknessl Required (Thickness ( Required lThicknessl Required 11 

(in) j(BL(P),FPS) (in) (BL(P),FPS) (in) (BL(P),FPS)j (in) IWW+‘S) 

0.975 1 541 1.130 745 1.285 908 1.440 1049 

0.980 549 1.135 751 1.290 913 1.445 1053 

0.985 556 1.140 756 1.295 918 1.450 1057 

0.990 563 1.145 762 1.300 923 1.455 1061 

1.040 634 969 1.505 1103 

1.045 640 1.200 823 1.355 974 1.510 1106 

1.050 647 1.205 827 1.360 978 1.515 1111 

1.055 653 1.210 833 1.365 983 1.520 1114 

1.060 660 1.215 838 1.370 987 1.525 1119 

1.065 666 1.220 843 1.375 992 1.530 1122 

1.070 672 1.225 849 1.380 996 1.535 1127 

1.075 679 1.230 853 1.385 1001 1.540 1130 

I: 1.080.085 685 691 1.23540 85964 1.3905 1010005 1.545.50 11359 I 

1.090 698 1.245 869 1.400 1014 1.555 1142 

1.095 704 1.250 874 1.405 1019 1.560 1147 

1.100 709 1.255 878 1.410 1022 1.565 1150 

1.105 716 1.260 884 1.415 1027 1.570 1154 

1.110 722 1.265 888 1.420 1031 1.575 1158 

I 1.12015 72734 1.2750 89894 1.430.425 1036040 1.580.585 1162166 I 

1.125 739 1.280 904 1.435 1044 1.590 117b 

- 

- - - - - 11595 1174 

- - ! - - - 1.600 1177 

Note: Minimum Required Ballistic Limits-75 mm, M1002a Aluminum Plate Proofing Projectile vs. 2519 

Aluminum Welds at 0” Obliquity: Based on 90% of Base Armor Standard. 

34 




Table 13. VSO Velocity Data (Continued) 

Projectile 

Sample Average Rounds v50 

No. Thickness Considered Velocity ZMR GAP Spread 

w> I ; 

145-mm API BS41 3.1-2 3.186 10 2,949 6 0 161 

145-mm API BS41 3.1-3 3.176 10 2,927 7 0 73 

145-mm API BS41 3.1-4 3.174 10 2,905 2 0 84 

145-mm API BS41 3.1-5 3.166 10 2,931 26 0 46 

145~mm API BS41 3.1-6 3.173 1 10 2,915 1 17 ( 0 1 58 

145-mm API BS41 3.1-7 3‘177 I 10 2.944 1 30 1 0 1 64 

145-mm API BS41 3.1-8 3.183 10 2,924 0 4 54 

145~mm API BS41 3.1-9 3.191 10 2,933 14 0 44 

145-mm API BS41 4.1-l 3.963 10 3.314 16 0 54 

145-mmAPIBS41 1 4.1-2 3.988 10 3300 7 0 95 

145-mm APZ 4.1- ,3 4.033 10 3.317 55 0 81 

145-mm API BS41 I 4.1-4 4.028 10 3,329 8 0 76 

145-mm API BS41 ] 4.1- ,5 4.030 10 3.332 27 0 88 

145-mm API BS41 4.1-6 4.025 10 3,357 48 0 57 

145-mm API BS41 4.1-7 3.988 10 3.292 40 0 70 

145mmAPIBS41 1 4.1-8 1 4.035 1 10 3,050 ] 7 1 0 1 50 

MIL-DTL-46 192 [2]. An amendment was prepared by the authors for inclusion into 

MIL-DTL-461.92 [2]. A copy of this amendment was sent to the Standardization Group on 

18 January 2000 and is presented in Appendix A. 

4. Summary and Conclusion 

4.1 Part 1: Mechanical Property and Chemical Resistance Characterization. The 

mechanical property characterization was completed. The results compared favorably with 

previously published data for the material. The UTS and the YS for the T87 weldments were 

only slightly lower than values previously presented by Chase et al. [14] (45.9 and 30.4 vs. 43.8 

and 27.4, respectively). Correspondingly, percent elongation was slightly higher, 4.2 vs. 5.0. 

The fatigue data generated fell within expectations. The T87-T87 weldment data showed a 

l&20% decrease in the fatigue strength, as compared with base material when tested by the 

39 
Table 14. Minimum Required Ballistic Limits 0.50~cal. AP M2 Projectiles vs. A12519 Plate at 0” Obliquity 
Table 14. Minimum Required Bailistic Limits OSO-cal. AP M2 Projectiles vs. A12519 Plate at 0” Obliquity (Continued) 

Thickness I Required 1 Thickness 1 Required 1 Thickness 1 Required Thickness Required 

W-WW (in> @WW’S) 

11660 I , I\ 2,204 \I I 1 2.060 . , 

., 

I 2,501 1 2.460 1 2,766 

(in‘) 1 CBL(bFPSj 1 (in) 1 (BUhQ'S) 1 (in) 

2.860 3,008 

1.670 2,212 2.070 2,507 2,470 2,772 2.870 3,014 

1.680 2,220 2.080 2,514 2.48 0 I- 2,778 1 -.-- 2.880 - 3.020 

2,785 

I 

2.228 I 2.090 I 2.521 2.890 1 3,025 -I-- 
R 

Table 15. Minimum Required Ballistic Limits 14.5mm BS 41 Projectiles vs. A12519 Plate at O” Obliquity 

II 

i mumess 

lKequirea 1 nmmess I mumess 1 nrckness 

(in) (BL(P)FPS) (BL(P)FFS) (in) ( 

LYUU 2;/43 3.200 3.200 I L,YUJ 3.3uw 3,056 3.800 

2.920 2,754 3.220 3.220 1 2,914 I 

3,201 

3.520 3,066 3.820 3,211 

2.930 2,75 9 3.230 2,919 3.530- 3,071 3.830 I 3 ,215 

2.940 2,765 3.240 2,924 3.540 : 5,076 3.840 3,220 

2.950 2,77 0 3.250 2,929 3.550 3,081 3.850 3 8,225 

-._._ 2.9tM -__ 2 776 

2:;s:;s i 

I I _,I.,” _,I.,” ? 3m I I 2.935 

21940 

L L 3.560 - .- -_ - .- -_ I ? -,-v.,,-v., nxc I 2 I.““”““” xfm I 2329 a,*--,*- 

2.970.970 3.270 3,570 3,090,090 3.870 3,234 

2.980 2,78 6 3.280 2,945 3.580 3,095 3.880 3 ,239 

2.990 2,792 ’ ’ 3 39n W.-/v _.__V , 2.950 

, r 3.590 I 3,100 3.890 3,243 

3.000 2,79 3,248 

I mumess 

_(BL(P)FPS) (in) 

L,YUJ 3.3uw 

2,914 I 3.520 

Kequirea 1 nrckness 

(BL(P)FPS) (in) 

3,056 3.800 

3,066 3.820 

5,076 3.840 

Kequmu 

(BL(P)FPS) 

3,201 

3,211 

,215 

3,220 

8,225 

7 3.300 2,955 3.600 3,105 3.900 

11 3.010 -1 2,803 3.310 2,960 3.610 3,110 3.910 I 3,253 

3.020 2,808 3.320 2,965 I 3.620 3,115 3.920 3,257 

3.030 2,81, ,262 

3.040 2,81, 1,124 3.940 I 3,267 

1.271 

4 3.330 2,970 3.630 3,120 3.930 I 3 

9 3.340 2,976 3.640 2 

2,824 3,350 2,981 3.650 3,129 3.950 I 7 I 

3.660 3,134 I 3.960 I 31276 

1,281 

11 3.080 1 2,84; 

3.370 2,991 3.670 3,139 3.970 3 

3.380 2,996 3.680 3,144 3.980 3,285 1 3.990 I 3,290 ,6 3.390 3,001 3.690 3,149 

1 3.400 3,006 3.700 3,153 4.000 3,294 

74in 3.011 3.710 3.158 I I L’--- 4.010 31299 

I J.I.5” I J,lUJ I 4.u.Lu I 3,304 

4”II I -I-Id” -1 21”” I Lt.V-lY I 33b” 

2 3.440 3026 3.740 3173 4.040 3313 

3.150 2877 3.450 3031 3.750 3177 4.050 3317 

3.160 

II 

2883 3.460 3036 3.760 3182 4.060 ‘: E-(1 
Table 15. Minimum Required Ballistic Limits 14.5mm BS 41 Projectiles vs. Al2519 Plate at 0’ Obliquity (Continued) 

Thickness Required Thickness 

(in) (BL(P)FPS) (in} 

3.170 2888 3.470 

3.180 2893 3.480 

3.190 2898 3.490 

- - 

Required Thickness 

(BL(P)FPS) (in) 

3041 3.770 

3046 3.780 

3051 3.790 

- - 

Required 

(BL(P)FPS) 

3187 

3192 

3196 

- 

Thickness Required 

( in) W4PP’S) 

4.070 3326 

4.080 3331 

4.090 3336 

4.100 3340 
rotating beam. The axial data showed almost a 50% decrease for the same groups. These results 

cannot be compared with the Chase et al. [ 143 data due to the variation in weldment design and 

specimen type. In general, the salt-fog-exposed samples demonstrated a 10% drop in fatigue 

strength when compared to baseline fatigue properties. These results compared well with the 

exposure data for this material. The chemical resistance of untreated Al25 19 is poor and proved 

to be so within the scope of this study. 

i 

4.2 Part 2: Ballistic Characterization. As a result of this effort, the only ballistic data that 

can be used for military acceptance is found in Appendix A, Amendment 1 to 

MIL-DTL-46192 C (MR) [2], Tables A-V and A-VI. 

L 

44 
5. References 

1. 

2. 

3. 

4. 

5. 

6. 

7. 

8. 

9. 

U.S. Department of the Navy, U.S. Army Research Laboratory. “MIL-STD-1946 Welding 

of Aluminum Alloy Armor.” Canceled, December 1995. 

U.S. Department of the Navy, U.S. Army Research Laboratory. “MIL-DTL-46 192 

Aluminum Alloy Armor Rolled Plate (l/2 to 4 Inches Thick), Weldable (Alloy 2519)” 

Formerly MIL-A-46 192, July 1991. 

American Society for Testing and Materials. “ASTM-E-8 Standard Test Methods for 

Tension Testing of Metallic Materials.” West Conshohocken, PA, 1998. 

American National Standards Institute/American Welding Society (ANSJIAWS). Methods 

for Mechanical Testing of WeZds. B-4.0, AWS Structural Welding Committee, Miami, FL, 

1998. 

American ‘Society for Testing and Materials. “‘ASTM-E-466 Standard Practice for 

Conducting Force Controlled Constant Amplitude Axial Fatigue Tests of Metallic 

Materials.” West Conshohocken, PA, 1996. 

American Society for Testing and Materials. “ASTM-G-34 Standard Test Method for 

Exfoliation Corrosion Susceptibility in 2XXX and 7XXX Series Aluminum Alloys.” West 

Conshohocken, PA, 1996. 

American Society for Testing and Materials. “ASTM-G-l 12 Standard Guide for 

Conducting Exfoliation Corrosion Tests in Aluminum Alloys.” West Conshohocken, PA, 

1997. 

American Society for Testing and Materials. “ASTM-B-1 17 Standard Practice for 

Operating Salt Spray (Fog) Apparatus.” West Conshohocken, PA, 1997. 

American Society for Testing and Materials “ASTM-G-38 Standard Practice for Making 

and Using C-Ring Stress Corrosion Test Specimens.” West Conshohocken, PA, 1995. 

10. American Society for Testing and Materials. “ASTM-G-47 Standard Test Method for 

Determining Susceptibility to Stress Corrosion Cracking of 2XXX and 7XXX Aluminum 

Alloy Products.” West Conshohocken, PA, 1998. 

11. American Society for Testing and Materials. “ASTM-G-44 Standard Practice for Exposure 

of Metals and Alloys by Alternate Immersion in Neutral 3.5% Sodium Chloride Solutions.” 

West Conshohocken, PA, 1995. 

45 
12. U.S. Department of the Navy, U.S. Army Research Laboratory. “MIL-DTL-46027 Armor 

Plate, Aluminum Alloy, Weldable 5083 and 5456.” September 1998. 

13. United Defense Limited Partnership. “GSD-99.055/GAM Hull Material Change.” 

Memorandum from Armament Systems Division, Minneapolis, MN, to Ground Systems 

Division, Santa Clara, CA, June 1999. 

14. Chase, M., N. Kackley, and W. Bethoney. “Engineering and Ballistic Properties of a Newly 

Developed 2XXX Series Aluminum Alloy Armor.” Ninth International Symposium on 

Ballistics, vol. 2, pp. 51 l-521, American Defense Preparedness Association, Shrivenham, 

England, 1986. 

46 
Appendix A: 

Amendment 1 to MIL-DTL-46192 C (MR) 

Note: This appendix appears in its original form, without editorial change. 

I 47 
48 
INCH-POUND 

MIL-DTL-46 192C(MR) 

AMENDMENT 1 

SUPERSEDING 

MIL-DTL-46192C(MR) 

28 August 1998 

DETAILED SPECIFICATION 

ALUMINUM ALLOY ARMOR ROLLED PLATE (l/2 TO 4 INCHES THICK), 

WELDABLE (ALLOY 25 19) 

This amendment forms a part of MIL-A-46192C(MR), dated 28 August 1998, and is approved for use by all 

Departments and Agencies of the Department of Defense. 

PAGE 9 

Table V.: Delete the footnote (a). 

APPENDIX A 

Add the attached Table A-V. at the end of the specification. 

Add the attached Table A-VI. after Table A-V. 

Custodian: Preparing activity: 

Army - MR Army - MR 

Review activities: 

Army - AT, AR, TE 

DLA - IS 

AMSC N/A 

Project 9535-xXxX 

FSC 9535 

49 
DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited. 

MIL-DTL-46192C(MR) 

APPENDIX A 

TABLE A-V. MINIMUM REQUIRED BALLISTIC LIMITS - CALIBER .50 AP M2 PROJECTILES 

VERSUS 2519 ALUMINUM PIATE AT O0 OBLIQUITY 

THICKNESS, 

REQUIRED THICKNESS, : REQUIRED THICKNESS, REQUIRED THICKNESS, REQUIRED 

INCHES BL(P),FPS INCHES BL(P),FPS INCHES BL(PI,FPS 

1.400 1988 1.800 2312 2.200 2596 

1.410 1997 1.810 2320 2.210 2603 

1.420 2005 1.820 2327 2.220 2610 

1.430 2014 1.830 2335 2.230 2617 

1.440 2023 1.840 2342 2.240 2623 

1.450 2031 1.850 2349 2.250 2630 

1.460 2040 1.860 2357 2.260 2636 

1.470 2048 1.870 2364 2.270 2643 

1.480 2057 1.880 2372 2.280 2650 

1.490 2065 1.890 2379 2.290 2656 

*1.500 2074 1.900 2386 2.300 2663 

1.510 2082 1.910 2394 2.310 2669 

1.520 2090 1.920 2401 2.320 2676 

1.530 2099 1.930 2408 2.330 2662 

1.540 2107 1.940 2415 2.340 2683 

1.550 2115 1.950 2423 2.350 2635 

1.560 2123 1.960 2430 2.360 2702 

1.570 2132 1.970 2437 2.370 2708 

1.580 2140 1.980 2444 2.380 2115 

1.590 2148 1.990 2451 2.390 2721 

1.600 2156 2.000 2458 2.400 2728 

1.610 2164 2.010 2465 2.410 2734 

1.620 2172 2.020 2472 2.420 2740 

1.630 2180 2.030 2479 2.430 2141 

1.640 2188 2.040 2487 2.440 2753 

1.650 2196 2.050 2494 2.450 2759 

1.660 2204 2.060 2501 2.460 2766 

1.670 2212 2.070 2507 2.470 2772 

1.680 2220 2.080 2514 2.480 2778 

1.690 2228 2.090 2521 2.490 2785 

1.700 2235 2.100 2528 2.500 2791 

1.710 2243 2.110 2535 2.510 2791 

1.720 2251 2.120 2542 2.520 2803 

1.730 2259 2.130 2549 2.530 2810 

1.740 2266 2.140 2556 2.540 2816 

1.750 2274 2.150 2563 2.550 2822 

1.760 2282 2.160 2569 2.560 2828 

1.770 2289 2.170 2576 2.570 2834 

1.780 2237 2.180 2583 2.580 2841 

1.790 2304 2.190 2590 2.590 2847 

INCHES BL,(P),FPS 

2.600 2853 

2.610 2859 

2.620 2865 

2.630 2871 

2.640 2877 

2.650 2883 

2.660 2689 

2.670 2895 

2.680 2902 

2.690 2908 

2.700 2914 

2.710 2920 

2.720 2926 

2.730 2931 

2.740 2937 

2.750 2943 

2.760 .2949 

2.770 2955 

2.780 2961 

2.790 2967 

2.800 2973 

2.810 2979 

2.820 2985 

2.830 2991 

2.840 2996 

2.850 3002 

2.860 3008 

2.870 3014 

2.880 3020 

2.890 3025 

2.900 3031 

2.910 3037 

2.920 3043 

2.930 3048 

2.940 3054 

2.950 3060 

2.960 3066 

2.970 3071 

2.980 3077 

2.990 3083 

t*3.000 3088 

* Specification requirements begin for ordered thickness 1.500 inch. 

** Specification requirements end for ordered thickness 3.000 inch. 

i 

50 
MIL-DTL-46192CtMR 

APPENDIX A (Cont. 

1 

TABLE VI. MINIMUM REQUIRED BALLISTIC LIMITS - 14.5MM BS41 PROJECTILES 

VERSUS 2519 ALUMINUM PLATE AT O0 OBLIQUITY 

THICKNESS, REQUIRED THICKNESS, REQUIRED 

INCHES BL<P),FPS 

THICRNESS, REQUIRED THICKNESS, REQUIRXD 

INCHES BL(P),FPS INCHLS BL.(P),FPS INCHES BL(P),tPPS 

2.900 2743 3.200 2903 3.500 3056 3.800 3201 

2.910 2748 3.210 2909 3.510 3061 3.810 3206 

2.920 2754 3.220 2914 3.520 3066 3.820 3211 

2.930 2759 3.230 2919 3.530 3071 3.830 3215 

2.940 2765 3.240 2924 3.540 3076 3.840 3220 

2.950 2770 3.250 2929 3.550 3081 3.850 3225 

2.960 2776 3.260 293s 3.560 3085 3.860 3229 

2.970 2781 3.270 2940 3.570 3090 3.870 3234 

2.980 2766 3.280 2945 3.580 3095 3.880 3239 

2.990 2792 3.290 2950 3.590 3100 3.890 3243 

*3.000 2737 3.300 2955 3.600 3105 3.900 3248 

3.010 2803 3.310 2960 3.610 3110 3.910 3253 

3.020 2808 3.320 2965 3.620 3115 3.920 3257 

3.030 2814 3.330 2970 3.630 3120 3.930 3262 

3.040 2819 3.340 2916 3.640 3124 3.940 3267' 

3.050 2824 3.350 2381 3.650 3129 3.950 3271 

3.060 2830 3.360 2986 3.660 3134 3.960 3276 

3.070 2835 3.370 2991 3.670 3139 3.970 3281 

3.080 2840 3.380 2996 3.680 3144 3.980 3285 

3.090 2846 3.330 3001 3.690 3149 3.990 3290 

3.100 2851 3.400 3006 3.700 3153 * *4.000 3294 

3.110 2856 3.410 3011 3.710 3158 4.010 3293 

3.120 2862 3.420 3016 3.720 3163 4.020 3304 

3.130 2067 3.430 3021 3.730 3168 4.030 3308 

3.140 2872 3.440 3026 3.740 3173 4.040 3313 

3.150 2077 3.450 3031 3.750 3177 4.050 3317 

3.160 2883 3.460 3036 3.760 3182 4.060 3322 

3.170 2688 3.470 3041 3.770 3187 4.070 3326 

3.180 2893 3.480 3046 3.780 3192 4.080 3331 

3.190 2898 3.490 3051 3.790 3196 4.090 3336 

* Specification requirements begin for ordered thickness 3.000 inch. 

** Specification requirements end for ordered thickness 4.000 inch. 
52 
Appendix B: 

Individual Test Shots for Developing the 

VsO Acceptance Tables 
54 
Table B-l, Individual Test Shots for Developing the VSIJ Acceptance Tables 

t 

c 

1.4-l 0.50~cal. AP M2 199904369 2,041 C 

1.4-1 0.50~Cal. AP M2 199904363 2,047 C 

I 1.4-l OSO-cal. AF’ M2 199904360 2,057 C 

1.4-1 OSO-Cal. Ap M2 199904366 2,059 C 

1.4-1 0.50~cal. AP M2 199904364 2,071 C 

1.4-l 0.50-cal. AP M2 199904365 2,082 C 

1.4-l 0.50-cal. AP M2 199904354 2.096 C 

1 1.4-2 0.50~cal. AP M2 199904371 1,997 P 

1.4-2 0.50-Cal. AP M2 199906008 2,001 P 

1.4-2 OSO-cal. AP M2 199906011 2,011 P 

1.4-2 0.50-cal. Al? M2 199906010 2,015 P 

1.4-2 0.50-Cal. AP M2 199904373 2,020 P 

1.4-2 1 0.50~Cal. AP M2 ,199904374 2,024 P 

1.4-2 1 0.50-cal. AP M2 199904381 2.024 P 

’ D is disallowed. 

55 
Table B-l. Individual Test Shots for Developing the VSO Acceptance Tables (Continued) 

SampleNo.) Projectile I Round 1 Strik I ~~ :ing Velocity ( Penetration 

1.4-2 OSO-cal. AP M2 199904376 2,082 C 

1.4-2 OSO-cal. AP M2 199904377 2,082 C 

1.4-2 OSO-Cal. AP M2 199906004 2,086 c 

l-4-3 0.50-cal. AP M2 199904383 2,014 P 

1.4-3 2.020 P 

1.4-3 

1.4-3 

1.4-3 

0.50-Cal. 

0.50-cal. 4= 0.50-Cal. 

0.50-Cal. 

APM2 199904384 I--- 

APM2 199904390 2,039 P 

APM2 199904385 2,041 P 

APM2 199904391 2,042 P 

1.4-3 I 0.50-cal. AP M2 I 199904382 1 I 2,061 C 

1.4-3 1 0.50-cal. AP M2 1 199904389 1 2,063 C I 

1.4-3 1 0.50-cal. AP M2 I 199904388 I 2,064 C 

1.4-3 0.50-cal. AP M2 199904386 2,077 C 

1.4-3 0.50-cal. AP M2 199904387 2,078 C _ . . 

1.4-6 1 0.50-cal. AP M2 1 199904421 2,033 P I 1.4-6 1 0.50-Cal. AP M2 I 199904416 1 2,038 P 

1 is disallowed. 

f 

56 
Table B-l. Individual Test Shots for Developing the V& Acceptance Tables (Continued) 

f 

c 

5 

IISamp1eNo.l Projectile Round 1 Striking Velocity 1 Penetration 11 

1 I 1.4-6 0.50-cal. AP M2 199904415 199904414 2,047 2,039 C PI 

I- 1.4-6 0.50~cal. 0.50~Cal. AP M2 199904417 199904413 2,049.55 C c I 

1.4-6 0.50-Cal. AP M2 199904412 2,063 c 

1.4-6 0.50-cal. AP M2 199904422 2,074 C 

1.4-7 0.50-cal. AP M2 199904440 2,034 P 

I 1.4-7 0.50-Cal. 0.50-cal. AP M2 199904439 199904438 2,040.1 P I 

1.4-7 0.50-Cal. AP M2 199904434 2,057 P 

1.4-7 0.50-cal. AP M2 199904441 2,057 P 

1.4-7 0.50~Cal. AP M2 199904436 2,059 C 

11 1.4-7 1 0.50-Cal. AP M2 1 199904437 1 2.066 I D II 

114-7 0.50-cal. AP M2 i 99904433 2,071 C 

1.4-7 0.50-cal. AP M2 199904442 2,072 C 

1.4-7 0.50~cal. AP M2 199904435 2,074 C 

I 1.4-87 0.50~cal. 0.50-cal. AP M2 199904443 199904453 2,080.3 C PI 

I- 1.4-8 0.50~cal. 0.50-Cal. AP M2 199904448 199904455 2,032 2,03 1 P I 

1.4-8 0.50-cal. AP M2 199904452 2,034 P 

1.4-8 0.50-Cal. AP M2 199904454 2,046 c 

1.4-8 0.50-cal. AP M2 199904450 2.054 c 

I l-.4-8 0.50~cal. AP M2 199904446 2,063 C 1.4-8 0.50-cal. AP M2 199904447 2.066 P I 

1.4-8 0.50-Cal. AP M2 199904444 2,07 1 C 

1.4-a 0.50~cal. AP M2 199904451 2.075 C 

1.4-8 0.50~Cal. AP M2 

1.4-x 0.50~cal. AP M2 

199904449 2,087 C 

199904445 2.088 C I 

1.4-9 O.jO-cal. 0.50-cal. AP M2 M2 199904465 199904456 2,037.9 P P I 

II 1.4-9 1 0.50-cal. AP M2 1 199904463 2,043 c II 

II 1.4-g I O-50-cal. AP M2 I 199904464 I P II 

114-9 0.50~cal. AP M2 199904462 21058 P 

1.4-9 0.50~cal. AP M2 199904457 2,060 P 

1.4-9 0.50-cal. AP M2 199904461 2,068 C 

11 1.4-9 1 0.50-Cal. AP M2 1 199904460 1 2,077 C II 

a D is disallowed. 

57 
Table B-l. Individual Test Shots for Developing the VSO Acceptance Tables (Continued) 

Sample No. Projectile Round Striking Velocity Penetration 

1.4-9 OSO-cal. AP M2 199904458 2,084 C 

1.4-9 OSO-cal. AP M2 199904459 2.r)wl l-! 

2.6-l 1 0.50-cal. AP M2 1 199904467 1 2,034 P 

2.6-l 0.50-cal. AP M2 199904466 2,038 P 

2.6-l 0.50-cal. AP M2 199904468 2,094 P 

2.6-l 0.50-Cal. AP M2 199904469 2,124 P 

2.6-l o-50- cal. AP M2 199904470 2,196 P 

2.6-l O-50-cal. AP M2 19990447 1 2,294 P 

2.6-l O.SO-cal. AP M2 199904472 2,501 P 

2.6-l 0.50-cal. AP M2 199904473 2,701 P 

2.6-l 0.50~cal. AP M2 199904479 2.871 P 

-I--- I 

2.6-l 1 0.50~cal. AP M2 1 1999044747 

2.6-1 

G-t 

2,879 C 

0.50-cal. AP M2 199904475 2,882 P 

O.SO-cal. AP M2 199904484 2,884 P 

0.50-Cal. AP M2 199904485 2,884 P 

2.6-l 1 0.50- cal. AP M2 I 199904481 1 

2.6-l 0.50-cal. AP M2 

2.6-l 0.50-cal. AP M2 

2.6-l O-SO-cal. AP M2 

2.6-l 0.50-cal. AP M2 

-7--. 

199904483 2,898 

199904476 2,902 C 

199904482 2,903 C 

19990447R 2.904 P 

2.6-l 

2.6-l 

2.6-2 

0.50~cal. AP M2 

O-50-cal. AP M2 

0.50-cal. AP M 

-,- - . 

Ii9904480 2,908 c 

199904477 2,932 C 

12 199904492 2,837 P 

2.6-2 0.50~cal. AP M2 199904502 2,845 P 

2.6-2 0.50-cal. AP M2 199904499 2.x55 r: -I-- - I 

2.6-2 O-50-cal. AP M2 199904495 2.875 P 

2.6-2 O-50-cal. AP M2 199904491 21882 i 

2.6-2 O-50-cal. AP M2 199904500 2,886 C 

2.6-2 0.50-cal. AP M2 199904501 2,890 C 

2.6-2 O.SO-cal. AP M2 199904487 2,894 C 

2.6-2 0.50-cal. AP M2 199904493 2,896 C 

2.6-2 OSO-cal. AP M2 199904490 2,897 D 

2.6-2 0.50-cal. AP M2 199904498 2.900 t-7 

-3s - - 

2.6-2 0.50-Cal. AP M2 199904497 2,902 C 

2.6-2 OSO-cal. AP M2 199904496 2,904 C 

2.6-2 0.50-cal. AP M2 199904494 2,907 C 

2.6-2 1 0.50-cal. AP M2 1 199904489 2,917 P 

1 is disallowed. 

58 
Table B-l. Individual Test Shots for Developing the VSO Acceptance Tables (Continued) 

sample No. Projectile Round Striking Velocity Penetration 

2.6-2 0.50-cal. AP M2 199904486 2,919 P 

2.6-2 0.50-cal. AP M2 199904488 2,925 C 

2.6-3 0.50-Cal. AP M2 199904534 2,864 P 

Y 2.6-3 0.50-Cal. AP M2 199904533 2,872 P 

2.6-3 0.50-d AP M2 199904539 2,876 P 

2.6-3 0.50-cal. AP M2 199904541 2.882 P 

2.6-3 0.50-cal. AP M2 199904536 2,890 C 

2.6-3 0.50-cal. AP M2 199904540 2,893 C 

2.6-3 0.50-cal. AP M2 199904537 2,896 C 

2.6-3 0.50-Cal. AP M2 199904538 2,898 P 

2.6-3 0.50-Cal. AP M2 199904535 2,903 C 

2.6-3 0.50-cal. AP M2 199904542 2,903 C 

2.6-4 0.50-Cal. AP M2 199904543 2,879 P 

2.6-4 OSO-cal. AP M2 199904544 2,879 P 

2.6-4 OSO-cal. AP M2 199904549 2.882 P 

2.6-4 0.50-cal. AP M2 199904552 2,883 P 

2.6-4 0.50-Cal. AP M2 199904548 2,886 C 

2.6-4 OSO-cal. AP M2 199904546 2,888 P 

2.6-4 0.50-cal. AP M2 199904551 2,892 C 

2.6-4 OSO-Cal. AP M2 199904545 2.895 P 

2.6-4 O-50-cal. AP M2 199904550 2,898 c 

2.6-4 OSO-Cal. AP M2 199904547 2,899 C 

2.6-4 0.50-cal. AP M2 199904553 2,907 C 

2.6-5 OSO-Cal. AP M2 199904558 2,892 C 

2.6-5 OSO-cal. AP M2 199904561 2,894 P 

2.6-5 OSO-cal. Ap M2 199904564 2,895 C 

2.6-5 0.50-Cal. AP M2 199904560 2,898 P 

2.6-5 0.50-cal. AP M2 199904556 2,903 P 

2.6-5 0.50-cal. AP M2 199904562 2.904 P 

2.6-5 0.50-cal. AP M2 199904555 2,908 P 

2.6-5 0.50-cal. AP M2 199904557 2,911 P 

2.6-5 0.50-cal. AP M2 199904559 2,913 C 

2.6-5 0.50-Cal. AP M2 199904554 2.914 C 

2.6-5 0.50-cal. AP M2 199904563 2,933 C 

2.6-6 0.50-Cal. AP M2 199904574 2.865 D 

2.6-6 0.50-cal. AP M2 199904575 2,871 P 

2.6-6 0.50-cal. AP M2 199904572 2,884 P 

3 is disallowed. 

59 
Table B-l. Individual Test Shots for Developing the Vso Acceptance Tables (Continued) 

L- 

? 

Striking Velocity 

2,901 

3 an2 

netratio] C 

P 

A,/ “J P 

199904565 2,904 C 

199904571 2,905 C 

199904573 2,922 P 

19aandw7 2,924 C 

2,925 C 

1 aaanLt5&c I///“-rJV” 2,935 C 

199904576 2,879 P 

2,880 P 4 

Ll 

ZI 

2.6-7 0.50-Cal. AP M2 

2.6-7 0.50-cal. AP M2 

2.6-7 0.50-Cal. AP M2 

2.6-7 0.50~cal. AP M2 

2.6-8 0.50-cal. AP M2 

2.6-8 0.50-cal. AP M2 

2.6-8 0.50-cal. AP M2 

2.6-8 0.50~cal. AP M2 

2.6-8 0.50~cal. AP M2 

2.6-8 0.50~cal. AP M2 

2.6-8 0.50-cal. AP M2 

199904581 

199904583 

199904580 

199904585 

199904600 i 

199904603 

199904601 

199904599 

1 aaand5aQ 

1/,/“7d,V 

2.6-8 0.50-cal. AP M2 

2.6-8 0.50-cal. AP M2 

2.6-8 

2.6-X 

2.6-8 

2.6-8 

2.6-8 

2.6-8 

0.50-cal. AP M2 

0.50-cal. AP M2 

0.50-cal. AP M2 

0.50-Cal. AP M2 

0.50-cal. AP M2 

0.50-cal. AP M2 

199904587 

199904597 

199904591 

199904590 

i A,,,vTJ,T aaan4544 

199904592 

199904595 

199904593 

i aaandl;ac; 

0.50-cal. 

1u 

AP 

Z 

2,920 C 

2,920 C 

2,926 P 

hI-I>“T-I,” 2,937 C 

199904589 2,943 C 

I 199904588 2,955 C 

1 199904604 2-876 P 

- 

II 2.6-8 1 0.50-cal. AF’ M2( 3 t;-R n mrai AP ~3 

i 

t 

an1 

60 
Table B-l. Individual Test Shots for Developing the V50 Acceptance Tables (Continued) 

1 is disallowed. 

61 
Table B-l. Individual Test Shots for Developing the Vs,-, Acceptance Tables (Continued) 

Sample No. Projectile Round Striking Velocity Penetration 

2.9-1 145-mm API BS41 199904868 3,045 C 

2.9-l 145-mm API BS41 19991)4854 ? n47 I r 

2.9-l 145-mm API BS4 1 1995 

2.9-l 

JO4864 3,103 C 

199904852 3,119 C 

2.9-l APIBS41 ! 

199904855 3,130 C 

199904853 3.209 C 

2.9-l 1 0.50-Cal. Ap M2 

I 199904840 2,890 P 

2.9-l 1 0.50-cal. AP M2 199904839 2,906 P 

2.9-l OSO-cal. AP M2 199904841 2,947 P 

2.9-l 0.50-cal. AP M2 199904842 2,995 P 

2.9-l 0.50-cal. AP M2 199904843 3,063 P 

2.9-l 0.50-cal. AP M2 199904850 3,132 C 

2.9-l 0.50~cal. Al? M2 199904844 3,162 P 

2.9-l 0.50-cal. AP M2 199904849 3,163 C 

2.9-l 0.50-cal. AP M2 199904848 3,165 C 

2.9-l 0.50-Cal. AP M2 199904847 3-l x4 l-Y 

-,-- 

2.9-l 0.50~cal. AP M2 199904846 3,229 c 

2.9-l 0.50-cal. AP M2 199904845 3,240 C 

2.9-2 145~mm API BS41 199904870 2-614 P -,-- 

2.9-2 145~mm API BS41 199904878 2,645 6 

2.9-2 145~mm API BS41 199904869 2hS9 P 

I I I 

2.9-2 1 145~mm API BS41 1 19GO4874 1 

-,--c 

I ,* 

2,678 P 

2.9-2 t 145~mmAPIBS41 

145-mm API BS41 

145-mm API BS41 

z--t 

145-mm API BS41 

145-mm API BS41 

145-mm API BS41 s--t 145-mm API BS41 

145-mm API BS41 

145-mm API BS41 

199906020 2,714 P 

19990602 1 2,720 P 

199904872 2,734 D 

199906022 2,755 P 

199906024 2,758 P 

199906023 2,775 C 

199904873 2,787 P 

199906019 2.819 c 

I 

I 

199904875 2I855 r 

I I 

2.9-2 1 145-mm APIBS41 1 1999 06018 2,873 C 

2.9-2 145-mm API BS41 199904sso 2,881 C 

2.9-2 145~mm APT BS41 199904882 2,910 C 

2.9-2 145-mm API BS41 199904876 2,920 C 

2.9-2 145-mm API BS41 199904871 2-968 c I I 

2.9-2 ( 145~mmAPIBS41 ) 

I 

199906017 1 2:&o I c 

is disallowed. 

. 

62 
Table B-l. Individual Test Shots for Developing the V50 Acceptance Tables (Continued) 

i 

Projectile Round I sample No. 1 ) Striking Velocity ( Penetration 

2.9-2 145”mm API BS41 199904879 3,043 C 

2.9-2 145-mm API BS41 199906016 3,110 C 

2.9-2 145~mm API BS41 199904881 3,117 C 

2.9-2 145-mm API BS41 199904877 3,163 C ~ ~ 

2.9-2 0.50-cal. AP M2 1 199904890 1 

2.9-2 0.50-cal. AP M2 199906015 31052 C 

2.9-2 0.50-cal. AP M2 199904891 3,055 P 

2.9-2 O-50-Cal. AP M2 199904892 3,055 P 

2.9-2 0.50~cal. AP M2 199904888 3,057 P 

2.9-2 0.50~cai. AP M2 199904886 3,077 P 

2.9-2 0.50-Cal. AP M2 199904887 3.089 C 

2.9-2 0.50-cal. AP M2 199904889 3,090 C 

2.9-2 0.50-Cal. AP M2 199904885 3,099 c 

2.9-2 0.50”cal. AP M2 199906014 3,104 C 

2.9-2 0.50-cal. AP M2 199904884 3,128 C 

2.9-2 0.50-cal. AP M2 199906013 3.128 C 

2.9-2 0.50-cal. AP M2 199904883 3,138 C 

2.9-3 145-mm API BS41 199904915 988 D 

2.9-3 145-mm API BS41 199904912 2,630 P 

2.9-3 145-mm API BS41 199904914 2,665 P 

2.9-3 145~mm API BS41 199904909 2,701 P 

2.9-3 145-mm API BS41 19990492 1 2,743 P 

2.9-3 145-mm API BS41 199904922 2,744 P 

is disallowed. 

63 
Table B-l. Individual Test Shots for Developing the VSO Acceptance Tables (Continued) 

samde No. 1 Proiectile Round LStrikin~ Velncilv I Penetrntinn 

14*-LAPI 

- ---^_-__ ----__ * -------..a-** 

2.9-3 BS41 199904907 2,931 C 

2.9-3 145-m API BS41 199904919 3 931 I r 

2.9-3 145-mm API BS41 19990, 

2.9-3 1,45-mm 

145-mm 

API 

API 

BS41 

BS41 

4918 2,998 C 

199904906 3.034 C 

2.9-3 145mm API BS41 

199904913 3,051 C 

199904903 3.061 C 

2.9-3 145~mm API BS41 199904917 3,070 C 

2.9-3 145~mm API BS41 199904916 3,110 D 

2.9-3 145~mm API BS41 199904905 3,179 C 

2.9-3 145-mm API BS41 199904904 3,210 C 

2.9-3 OSO-cal. AP M2 199904894 3,065 P 

2.9-3 OSO-cal. AP M2 199904893 3.078 P 

-I-- 

2.9-3 0.50-cal. AP M2 199904895 3,090 i 

2.9-3 0.50~cal. AP M2 199904897 3.104 P 

I ->--- l 

2.879 C 

I 

2.9-4 O-50-cal. Ap M2 199904942 3,079 c 

2.9-4 0.50-cal. AP M2 199904940 3,082 P 

2.9-4 0.50~cal. AP M2 199904941 3,084 P 

2.9-4 0.50-cal. Ap M2 199904937 3,087 P 

2.9-4 0.50~Cal. AP M2 199904938 3,105 C 

2.9-4 0.50-cal. AP M2 199904945 3.108 c 

i 

c 

is disallowed. 

64 
Table B-l. Individual Test Shots for Developing the VSO Acceptance Tables (Continued) 

hrmle No. 

2.9-4 

2.9-4 

2.9-5 

2.9-5 

2.9-5 

2.9-5 

2.9-S 

2.9-5 

2.9-5 

2.9-5 

2.9-5 

2.9-5 

2.9-5 

2.9-5 OSO-Cal, AP M2 199904946 3jO84 P 

2.9-5 0.50~cal. AP M2 199994948 3,102 P 

2.9-5 

2.9-5 

2.9-5 

2.9-5 

2.9-5 

2.9-5 

2.9-5 

2.9-5 

2.9-6 

2.9-6 

2.9-6 

2.9-6 

2.9-6 

2.9-6 

2.9-6 

2.9-6 

2.9-6 

2.9-6 

2.9-6 

2.9-6 

2.9-6 

2.9-6 

1 is disallowel 

0.50-d. AP M2 199904947 3,104 P 

0.50-Cal. AP M2 19990495 1 3,105 P 

0.50-cal. AP M2 199904949 3,119 C 

0.50-Cal. AP M2 199904950 3,119 P 

OSO-Cal. AP M2 199904952 3.127 C 

65 
Table B-l. Individual Test Shots for Developing the VSO Acceptance Tables (Continued) 

a D is disallowed. 
Table B-l. Individual Test Shots for Developing the Vso Acceptance Tables (Continued) 

iample No. Projectile Round Striking Velocity Penetration 

2.9-8 145-mm API BS41 199904970 2,816 C 

2.9-8 145-mm API BS41 199904975 2,816 C 

2.9-8 145-mm API BS41 199904966 2,823 C 

2.9-8 145-mm API BS41 199904967 2,835 C 

2.9-8 0.50-cal. AP M2 199904987 3 -060 P 

2.9-8 0.50-Cal. AP M2 199904993 3,072 P 

2.9-8 0.50~cal. AP M2 199904983 3,074 P 

2.9-8 O-50-cal. AP M2 199904985 3,078 P 

2.9-8 0.50-cal. AP M2 199904982 3,098 C 

2.9-8 0.50-cal. AP M2 199904976 3,111 P 

2.9-8 0.50-cal. Ap M2 199904994 3,112 C 

2.9-8 0.50~cal. AP M2 199904981 3.187 C 

2.9-9 0.50-cal. AP M2 199905051 3,094 P 

2.9-9 0.50-cal. AP M2 199905052 3.106 P 

2.9-9 0.50-cal. AP M2 199905053 3,121 P 

2.9-9 0.50~cal. A.P M2 199905050 3.125 P 

2.9-9 O-50-cal. AP M2 199905047 3,128 C 

2.9-9 O-50-cal. AP M2 199905055 3.180 C 

2.9-9 0.50-cal. AP M2 199905057 3,185 C 

2.9-9 0.50~cal. AP M2 199905054 3.187 c 

2.9-9 O-50-cal. AP M2 199905056 3,197 C 

3.1-1 145-mm API BS41 199905068 2,825 P 

3.1-l 145~x1 API BS41 199905070 2,886 P 

3.1-1 1 145-mmAPIBS41 1 199905071 2,889 P 

is disallowed. 

67 
Table B-l. Individual Test Shots for Developing the VSO Acceptance Tables (Continued) 

Sample No. Projectile Round Striking Velocity Penetration 

3.1-1 145mm API BS41 199905077 2,904 P 

3.1-1 145-mm API BS41 199905076 2.919 C 

3.1-1 145~mm API BS41 199905072 2,936 P 

3.1-1 14hnm API BS41 199905075 2,939 C 

3.1-1 14%mm AF’I BS41 199905073 2.945 C 

3.1-1 145~mm API BS41 199905069 2,968 c 

3.1-1 145~mm API BS41 199905074 2.982 C 

I 3.1-2 145-mm API BS41 199905332 199905334 2.914,892 P 

I 3.1-2 145-mm API BS41 199905329 199905333 2,917.23 P 

3.1-2 145-mm API BS41 199905331 2,934 C 

3.1-2 145-mm API BS41 199905336 2,940 P 

3.1-2 145-mm API BS41 199905330 2.947 C 

I 3.1-2 145mm API BS41 199905335 199905328 2,954 3.018C 

I 3.1-23 145-mm API BS41 199905327 199905337 3,053 2.890C P

3.1-3 145~mm API BS41 199905340 2,914 P 

3.1-3 145~mm API BS41 199905343 2.914 P 

3.1-3 145-mm API BS41 199905344 2,921 P 

3.1-3 145-mm API BS41 199905342 2,925 C 

3.1-3 145-mm API BS41 199905339 2.927 C I 3.1-3 145-mm~mm API BS41 199905345 199905346 2,932.3 C P

I 3.1-3 145-mm API BS41 199905338 199905341 2,953.6 C 

I 3.1-4 145-mm~mm API BS41 199905355 199905358 2,843.50 P I 3.1-4 145-mm API BS41 199905351 199905347 2,891.919 P 

I- 3.1-4 145~mm-mm API BS41 199905357 199905352 2,920.2 C P I 3.1-4 145-mm API BS41 199905349 199905356 2.925,4 C 

3.1-4 145-mm API BS41 199905354 2,926 C 

3.1-4 145-mm API BS41 199905350 2,927 C 

’ D is disallowed. 

i 

68 
Table B-l. Individual Test Shots for Developing the V50 Acceptance Tables (Continued) 

f 

iample No. Projectile Round Striking Velocity Penetration 

3.1-4 145mm API BS41 199905353 2,928 C 

3.1-4 145~mm API BS41 199905348 2,962 C 

3.1-5 145~mm API BS41 199905367 2,905 P 

3.1-5 145-mm API BS41 199905362 2,909 P 

3.1-5 145~mm API BS41 199905359 2,914 P 

3.1-5 145-mm API BS41 199905364 2,915 P 

3.1-5 145~mm API BS41 199905368 2,920 P 

3.1-5 145~mm API BS41 199905369 2,928 C 

3.1-5 145~mm API BS41 199905361 2,930 C 

3.1-5 145~mm API BS41 199905366 2,941 C 

3.1-5 145-mm API BS41 199905365 2,945 C 

3.1-5 145~mm API BS41 199905363 2,954 P 

3.1-5 145~mm API BS41 199905360 2,955 C 

3.1-6 145-mm API BS41 199905377 2.887 P 

1 is disallowed. 

69 
Table B-l. Individual Test Shots for Developing the VSO Acceptance Tables (Continued) 

I zmlp1c IYO. rroj ectile Kound I Srrxmg Velocity ) Yenetratlon 

3.1-8 145~mm API BS41 A///v.,J/ A , -,s I” I 

31-X I 1 d<-mm APT RCdl 1 199905395 2,924 I P 

1 cm4ncta3 I 3 939 

199905394 I 2,940 I f199905390 1 2,956 C 

145-mm APT RCA1 1 1 aaancnna I 3 913 I D 

31-9 I Ids-mm APT RCA1 I 1 aoonznnr, I 3 93n I r 

3.1-9 , * .I *lull Lxx AYVTA 1 /,/“J-r”~ 1 

3.1-9 1 145-mmAPIBS41 I~~~vJ7vJ , 1:::: 

1 I 

1 QQQfKAn? I 3 915 I -- I P I 

-*- _ L .d *I-II 1 u I YV-rI I ,,/“J-F”L I 1 

::::: 

I ld 

3.1-9 145~mm API BS41 1QQQfKAfS x///vsx-vv , I 3 93x I I P I 

J.l-, l-f>-11~111 ILIT1 Da-1 lYYYUJ4U4 I L,YJV I L 

3.1-9 145-n-m API BS41 c///vd-,.v> , -,--- I 1. 

1’.1’7 1’+3-111111 PuTI Da41 lYYYU34UU L,Y34 

3.1-9 145~mm API BS41 199905407 2,948 E 

3.1-9 145~mm API B342 lYYYU34Ul L,YJJ 

3.1-9 145~mm API BS41 199905408 2,956 c” 

II 4-l 1 145-mm APT Rm 

- .- --^_----*-- ,* 199905706 3,152 P 

4-l 145~mm API BS41 199905707 3,237 P 

4-1 145~mm API BS41 199905713 3,293 P 

4-l 145-mm API BS41 199905712 3,299 P 

4-1 145~mrn API BS41 1999OS7 1 I) 3.303 P 

II 

I 

4-2 1 145~mm APIBS41 1 17-?Yl,J ILL I 1 nnnnr?.-b-l I - 2 3QQ I -r--.-- 

4-2 145-mm API BS41 ii9905729 3,292 6 

4-2 145~mm API BS41 199905727 3,295 P 

4-2 145~mm API BS41 199905721 3,315 C 

a D is disallowed. 

70 
Table B-l. Individual Test Shots for Developing the VSO Acceptance Tables (Continued) 
Table B-l. Individual Test Shots for Developing the VSO Acceptance Tables (Continued) 

I~Sarnple No.1 Projectile Round 1 Striking Velocity 1 Penetration 

II 4-5 145-mm API BS41 199905756 3,383 C 

145~mm API BS41 199905771 3.324 P 

145~mm API BS41 199906064 ( 3,332 I p 

II 4-6 1 145-mm APIBS41 1 15 19905770 3,336 C 

4-6 145~mm API BS41 199906065 3,337 P 

4-6 145~mm API BS41 199905765 3,338 P 

II 4-6 145-mm API BS41 , 199906066 3,353 C 

145~mm API BS41 199905769 3,380 C 

145~mm API BS41 199905767 3,383 C 

11 4-6 

I 4-6 

4-6 145-mm API BS41 1 199905766 3,384 P 

II 4-6 1 145-mm APIBS41 10 1s 19905768 3.404 C c --145-mm API BS41 199906057 2,761 D 

145~mm API BS41 199906061 3.255 P 

145-n-m API BS41 

145~mm API BS41 

145-mm API BS41 

199906063 3,267 P 

199906060 3.285 C 

199905775 3,288 P 

145-mm API BS41 199906062 3.294 C 

145-mm API BS41 199905774 1 3,295 P 

145~mm API BS41 199906059 ) 

145-m API BS41 IS 

3,295 I c 

II 4-7 I 

4-7 1 145~mm API BS41 

4-7 145~mm API BS41 

4-7 145~mm API BS41 

j9906056 3,304 C 

199906058 3,313 C 

199905776 3.325 P 

199905777 3,327 C 

4-7 145~mm API BS41 199906054 3.329 C 

4-7 145~mm API BS41 199906052 3,334 C 

4-7 145-mm API BS41 199906053 3.336 C 

4-7 145-mm API BS41 199906055 3,339 C 

4-7 II- 4-7 

145-mm API BS41 199905773 3,353 C 

145-mm API BS41 199905772 3,354 C 

145~mm API BS41 19990605 1 3,356 C 

145-mm API BS41 199906047 3,265 P 

145-mm API BS41 199905784 3,315 P 

145-mm API BS41 199905783 3,350 C 

II 4-7 

II 4-8 

11 4-8 

145~mm API BS41 199906049 1 

145-mm API BS41 15 

3,355 I p 

-- 

29905778 3,356 P 

I 4-8 P-8 145-mm~mm API BS41 199905780 199905782 3,3576 C P

a D is disallowed. 

72 
Table B-l. Individual Test Shots for Developing the Vso Acceptance Tables (Continued) 

4-8 145~mm API BS41 199906050 3,370 C 

4-8 145-mm API BS41 199905781 3,373 C 

4-8 145~mm API BS41 199905779 3,388 C 

4-8 145-mm API BS41 199906048 3.416 c 

a D is disallowed. 

5 

73 
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REPORT DOCUMENTATION PAGE I Form Approved 

OMB No. O7WO1i38 

April 2001 1 Final, October 199X-June 1999 

4. TITLE AND SUBTITLE 5. FUNDING NUMBERS 

Mechanical and Ballistic Data for A125 19 Plate, Forgings, and Weldments TU9A9FlllANU 

6. AUTHOR(S) 

Scott M. Grendahl, Richard J. Squillacioti, Daniel J. Snoha, 

and Christopher E. Miller 

7. PERFORMING ORGANIZATION NAME(S) AND ADDR&S(ES) 

U.S. Army Research Laboratory 

AT-I-N: AMSRL-WM-MD 

Aberdeen Proving Ground, MD 2 1005-5066 

8. PERFORMING ORGANlZATlON 

REPORT NUMBER 

ARL-TR-2452 

9. SPONSORlNGlMONlTORlNG AGENCY NAMES(S) AND ADDRESS lO.SPONSORING/MONITORlNG 

AGENCY REPORT NUMBER 

U.S. Army Tank-automotive and Armaments Command 

Heavy Combat Commodity Business Unit, ATIN: AMSTA-LC-CA 

Warren, MI 48397-5000 

11. SUPPLEMENTARY NOTES 

12a. DlSTRlBUTlONlAVAllABILlN STATEMENT 

Approved for public release; distribution is unlimited. 

12b. DISTRIBUTION CODE 

, 

--- 1 

The development and potential use of aluminum-armor alloys in the design and construction of combat vehicles has 

been repeatedly scrutinized as the military continually pushes toward lightweight, mobile, and more deployable forces. 

In doing so, it is necessary to fully characterize and understand the engineering material properties and the ballistic 

resistance of any prospective material. Aluminum 2519 (A12519) was developed nearly 20 years ago as a high-strength, 

heat-treatable alloy with excellent ballistic performance. This alloy was not utilized extensively beyond the 

experimental phase and as such has not been continually produced by the alutninum industry. Therefore, when the 

utilization of this alloy recently became expected, questions arose about the ability of the suppliers to reproduce the 

same product that had been developed in the past. As part of the ensuing analysis, the engineering properties and the 

chemical and ballistic resistance of the alloy required validation. Additionally, work needed to be performed to verify 

that the alloy and its various heat treatments were feasible for joining in the construction of armored vehicles. Several 

common heat treatments were characterized, in addition to the most common weld joints presently designed by Team 

Crusader. 

14. SUBJECT TERMS 115. NUMBER OF PAGES 

alumina 25 19, fatigue, weldments 82 

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