Composite Materials Handbook Part 12 pps

MIL-HDBK-17-4 APPENDIX B 156 B1.ALUMINUMS B2.COPPERS B3.MAGNESIUMS B4.TITANIUMS MIL-HDBK-17-4 APPENDIX B 157 B4.1 TI 15V 3CR 3AL-3SN (SECTION 3.3.5.1) MATERIAL: Ti-15-3 Table B4.1(a) Ti-15-3 NEAT MATRIX: Ti-15V-3Cr-3Al-3Sn Tension HEAT TREATMENT: 1292°F/24h (vac.) NASA LeRC TEST METHOD: Section 1.9.2.1 Raw Data Specimen No. Lot I.D. (Plate) Test Temp Strain Rate E t (1) F pl F ty0 02. F ty0.2 F tu ε tu RA Product Form Test Environment ν m (°F) (1/s) (Msi) (ksi) (ksi) (ksi) (ksi) (%) (%) T36 B934021 800 1x10-6 10.8 20 29 43 - >3 - HIP Sheet air - T42 B934021 800 1x10-4 11.3 59 73 84 - >3.8 - HIP Sheet air - T33 B934021 800 1x10-8 17 5.2 40 - - >1 - HIP Sheet air - T27 B934021 900 1x10-4 10.9 50 65 75 - >8 - HIP Sheet air - T45 B934021 600 1x10-4 11.4 69 78 87 - >8 - HIP Sheet air - T40 B934021 400 1x10-4 12.6 65 84 96 - >8 - HIP Sheet air - T37 B934021 75 1x10-4 13 94 108 117 - >8 - HIP Sheet air - 7_1 B934027 1000 1x10-4 10.5 23 33 42 43 >8 - HIP Sheet air - 7_22 B934027 900 1x10-4 10.7 57 65 74 75 >8 - HIP Sheet air - 7_15 B934027 1000 1x10-6 5.3 6 6 8 24 >8 - HIP Sheet air - 7_ex B934027 400 1x10-6 12 80 85 96 - >8 - HIP Sheet air - 7_6 B934027 400 1x10-3 12.3 81 87 95 - >8 - HIP Sheet air - 7_18 B934027 1000 1x10-3 11 50 60 67 67 >8 - HIP Sheet air - B8 B934027 800 1x10-5 10.8 56 69 83 - >4 - HIP Sheet air - V700-1 87H? 75 2x10-3 13 111 117 124 127 20.2 - HIP Foil air - 16211_B B934027 75 8.3x10-5 12.4 - - 114 124 20.7 37.8 HIP Sheet 5 ksi Helium - 16210_A B934027 75 8.3x10-5 11.9 - - 110 120 20.3 40.3 HIP Sheet 5 ksi Helium - 16215_F B934027 75 8.3x10-5 12.1 - - 112 122 22.1 39.5 HIP Sheet 5 ksi Helium - 16212_C B934027 75 8.3x10-5 12 - - 116 125 16.8 22 HIP Sheet 5 ksi Hydrogen - 16213_D B934027 75 8.3x10-5 12.5 - - 114 125 17.2 27.1 HIP Sheet 5 ksi Hydrogen - 16214_E B934027 75 8.3x10-5 12.3 - - 114 124 17.5 27.6 HIP Sheet 5 ksi Hydrogen - 1) Modulus was determined by least squares analysis up to the proportional limit MIL-HDBK-17-4 APPENDIX B 158 MATERIAL: Ti-15-3 Table B4.1(a) (cont.) Ti-15-3 NEAT MATRIX: Ti-15V-3Cr-3Al-3Sn Tension HEAT TREATMENT: 1292°F/24h (vac.) NASA LeRC TEST METHOD: Section 1.9.2.1 Raw Data Specimen No. Machining Method Specimen Geometry Specimen Dimensions Surface Condition Test Date Failure Location Failure Mode T36 turned and ground Dogbone .25" dia. x .5" gage as-ground 5/2/96 interrupted - T42 turned and ground Dogbone .25" dia. x .5" gage as-ground 5/3/96 interrupted - T33 turned and ground Dogbone .25" dia. x .5" gage as-ground 5/6/96 interrupted - T27 turned and ground Dogbone .25" dia. x .5" gage as-ground 11/13/96 interrupted - T45 turned and ground Dogbone .25" dia. x .5" gage as-ground 11/14/96 interrupted - T40 turned and ground Dogbone .25" dia. x .5" gage as-ground 11/14/96 interrupted - T37 turned and ground Dogbone .25" dia. x .5" gage as-ground 11/14/96 interrupted - 7_1 turned and ground Dogbone .25" dia. x .5" gage as-ground 2/6/97 interrupted - 7_22 turned and ground Dogbone .25" dia. x .5" gage as-ground 2/6/97 interrupted - 7_15 turned and ground Dogbone .25" dia. x .5" gage as-ground 3/22/97 interrupted - 7_ex turned and ground Dogbone .25" dia. x .5" gage as-ground 3/23/97 interrupted - 7_6 turned and ground Dogbone .25" dia. x .5" gage as-ground 4/11/97 interrupted - 7_18 turned and ground Dogbone .25" dia. x .5" gage as-ground 4/11/97 interrupted - B8 turned and ground Dogbone .25" dia. x .5" gage as-ground 7/31/97 interrupted - V700-1 turned and ground Dogbone .125" dia. x .815" gage as-ground 3/5/88 gage ductile failure 16211_B turned and ground Dogbone .188" dia. x .75" gage as-ground 7/2/97 gage ductile failure 16210_A turned and ground Dogbone .188" dia. x .75" gage as-ground 7/2/97 gage ductile failure 16215_F turned and ground Dogbone .188" dia. x .75" gage as-ground 7/3/97 gage ductile failure 16212_C turned and ground Dogbone .188" dia. x .75" gage as-ground 7/3/97 gage ductile failure 16213_D turned and ground Dogbone .188" dia. x .75" gage as-ground 7/3/97 gage ductile failure 16214_E turned and ground Dogbone .188" dia. x .75" gage as-ground 7/3/97 gage ductile failure MIL-HDBK-17-4 APPENDIX C 159 RAW DATA TABLES FOR TITANIUM MATRIX COMPOSITES PARAGRAPH PA G E C1. SiC/Ti-15-3 (SECTION 3.8.2.1) 160 MIL-HDBK-17-4 APPENDIX C 160 C1. SIC/TI-15-3 (SECTION 3.8.2.1) MATERIAL: SiC/Ti-15-3 Table C 1(a) SiC/Ti-15-3 FIBER: SCS-6 TEST METHOD: Sec. 1.4.2.1 Tension Tension MATRIX: Ti-15V-3Cr-3Al-3Sn PRE-TEST EXPOSURE: 1292°F/24 hrs. (vac.) [0] PRODUCT FORM: Foil/fiber/foil TEST ATMOSPHERE: Air NASA LeRC PRODUCT DIMENSIONS: 10” x 14” Raw Data LAY-UP: Unidirectional PLY COUNT: 8-ply Fiber v/o Specimen No Lot I.D. (Plate) Test Temp. Strain Rate E t 1 F pl 1 F ty 1 002. F ty 1 0.2 F tu 1 ε 1 tu ν νν ν 12 t Comments (°F) (1/s) (Msi) (ksi) (ksi) (ksi) (ksi) (%) 15 L1_15 F914005 75 1x10-4 20 123 141 172 185 1.21 - Mo-weave 15 15_1 F914007 800 1x10-3 19 - 116 - 138 0.86 0.39 Mo-weave 15 15-2 F914007 800 1x10-3 19 - 115 - 136 0.75 0.37 Mo-weave 25 25-1 B934026 800 1x10-3 24 - 164 - 197 0.88 0.32 Ti-Nb weave 25 25-2 B934026 800 1x10-3 24 - 151 - 192 0.91 0.31 Ti-Nb weave 35 29 87H153 800 1x10-4 32 17 42 - 200 0.77 - Ti-weave 35 30 87H153 800 1x10-3 26 31 147 - 201 0.89 - Ti-weave 35 4 87H153 75 1x10-4 25 121 160 - 196 0.84 - Ti-weave (1) 35 2 87H153 75 1x10-4 26 133 168 - 168 0.66 - Ti-weave (1) 35 5 87H153 75 1x10-4 37 142 140 - 194 0.67 - Ti-weave 35 6 87H153 75 1x10-4 28 33 82 - 194 0.85 - Ti-weave 35 7 87H153 75 1x10-4 26 83 83 - 206 1 - Ti-weave 35 8 87H153 75 1x10-4 26 127 157 - 204 0.89 - Ti-weave 35 9 87H153 75 1x10-4 28 112 160 - 217 0.88 - Ti-weave 35 33 87H153 800 1x10-5 29 24 90 - 198 0.82 - Ti-weave 35 27 87H153 75 1x10-4 25 141 169 - 208 0.96 0.28 Ti-weave 35 53 D890054 75 1x10-4 29 150 186 - 211 0.77 - Mo-weave 35 5_36 J890505 800 1x10-3 27 151 185 - 209 0.84 - Mo-weave (2) 35 35-8 B934025 800 1x10-3 29 - 187 - 252 1 - Ti-Nb weave 35 35-10 B934025 800 1x10-3 26 - 182 - 243 1.06 - Ti-Nb weave 41 L1-45 D910518 75 1x10-4 31 151 160 - 201 0.73 - Mo-weave 41 L4 D910518 75 1x10-4 31 128 192 - 252 0.9 - Mo-weave 41 42-1 D910519 800 1x10-3 30 - 212 - 245 0.84 0.31 Mo-weave 41 42-2 D910519 800 1x10-3 32 - 187 - 251 0.83 0.28 Mo-weave (1) Straight sided specimen (2) 32 ply material MIL-HDBK-17-4 APPENDIX C 161 MATERIAL: SiC/Ti-15-3 Table C1(a) (cont.) SiC/Ti-15-3 FIBER: SCS-6 TEST METHOD: Sec. 1.4.2.1 Tension Tension MATRIX: Ti-15V-3Cr-3Al-3Sn PRE-TEST EXPOSURE: 1292°F/24 hrs. (vac.) [0] PRODUCT FORM: Foil/fiber/foil TEST ATMOSPHERE: Air NASA LeRC PRODUCT DIMENSIONS: 10” x 14” Raw Data LAY-UP: Unidirectional PLY COUNT: 8-ply Specimen No. Machining Method Specimen Geometry Specimen Dimensions Surface Condition Te s t Date Failure Location Failure Mode L1_15 EDM Dogbone 0.5x6.0x0.12" as-machined 9/25/92 Radius - 15_1 Water Jet + Diamond Grind Dogbone 0.5x6.0x0.12" as-machined 10/2/96 Outside gage - 15-2 Water Jet + Diamond Grind Dogbone 0.5x6.0x0.10" as-machined 10/2/96 mid-gage - 25-1 Water Jet + Diamond Grind Dogbone 0.5x6.0x0.10" as-machined 10/2/96 mid-gage - 25-2 Water Jet + Diamond Grind Dogbone 0.5x6.0x0.10" as-machined 8/21/89 gage - 29 EDM Dogbone 0.5x5.5x0.08" as-machined 8/21/89 gage - 30 EDM Dogbone 0.5x5.5x0.08" as-machined 8/9/88 mid-gage - 4 EDM Rectangular 0.5x4.0x0.08" as-machined 6/29/88 mid-gage - 2 EDM Rectangular 0.5x4.0x0.08" as-machined 6/29/88 grips - 5 EDM Dogbone 0.5x4.0x0.08" as-machined 11/16/88 radius - 6 EDM Dogbone 0.5x4.0x0.08" as-machined 7/8/88 radius - 7 EDM Dogbone 0.5x4.0x0.08" as-machined 8/22/88 radius - 8 EDM Dogbone 0.5x4.0x0.08" as-machined 6/30/88 gage - 9 EDM Dogbone 0.5x4.0x0.08" as-machined 7/7/88 mid-gage - 33 EDM Dogbone 0.5x5.5x0.08" as-machined 8/21/89 gage - 27 EDM Dogbone 0.5x5.5x0.08" as-machined 10/17/89 gage - 53 EDM Dogbone 0.5x5.5x0.07" as-machined 9/10/90 radius - 5_36 EDM + Diamond Grind Dogbone 0.5x6.0x0.3" as-machined 5/23/95 radius - 35-8 Water Jet + Diamond Grind Dogbone 0.5x6.0x0.07" as-machined 5/21/96 radius - 35-10 Water Jet + Diamond Grind Dogbone 0.5x6.0x0.07" as-machined 7/2/96 radius - L1-45 EDM Dogbone 0.5x6.0x0.06" as-machined 9/25/92 outside gage - L4 EDM Dogbone 0.5x6.0x0.06" as-machined 10/14/92 mid-gage - 42-1 Water Jet + Diamond Grind Dogbone 0.5x6.0x0.06" as-machined 10/2/96 radius - 42-2 Water Jet + Diamond Grind Dogbone 0.5x6.0x0.06" as-machined 10/2/96 gage - MIL-HDBK-17-4 APPENDIX C 162 MATERIAL: SiC/Ti-15-3 Table C 1(b) SiC/Ti-15-3 FIBER: SCS-6 TEST METHOD: Sec. 1.4.2.1 Tension Tension MATRIX: Ti-15V-3Cr-3Al-3Sn PRE-TEST EXPOSURE: 1292°F/24 hrs. (vac.) [90] PRODUCT FORM: Foil/fiber/foil TEST ATMOSPHERE: Air NASA LeRC PRODUCT DIMENSIONS: 10” x 14” Raw Data LAY-UP: Unidirectional PLY COUNT: 8-ply Fiber v/o Specimen No Lot I.D. (Plate) Test Temp. Strain Rate E t 2 F pl 2 F ty 2 002. F ty 2 0.2 F tu 2 ε 2 tu ν νν ν 21 t Comments (°F) (1/s) (Msi) (ksi) (ksi) (ksi) (ksi) (%) 15 T2_15 F914005 75 1x10-4 17 42 44 75 96 1.91 - Mo-weave 35 41 87H153 75 1x10-4 19 17 38 49 59 1.43 0.17 Ti-weave 35 42 87H153 75 1x10-4 17 15 40 50 62 1.38 0.18 Ti-weave 35 43 87H153 800 1x10-4 17 16 25 34 42 0.71 - Ti-weave 35 44 87H153 800 1x10-5 17 15 22 30 41 0.99 - Ti-weave 41 T1_45 D910518 75 1x10-4 18 - - - 23 0.12 - Mo-weave (1) 41 T2_45 D910518 75 1x10-4 18 - - - 33 0.19 - Mo-weave (1) Broke in elastic regime MIL-HDBK-17-4 APPENDIX C 163 MATERIAL: SiC/Ti-15-3 Table C1(b) (cont.) SiC/Ti-15-3 FIBER: SCS-6 TEST METHOD: Sec. 1.4.2.1 Tension Tension MATRIX: Ti-15V-3Cr-3Al-3Sn PRE-TEST EXPOSURE: 1292°F/24 hrs. (vac.) [90] PRODUCT FORM: Foil/fiber/foil TEST ATMOSPHERE: Air NASA LeRC PRODUCT DIMENSIONS: 10” x 14” Raw Data LAY-UP: Unidirectional PLY COUNT: 8-ply Specimen No. Machining Method Specimen Geometry Specimen Dimensions Surface Condition Te s t Date Failure Location Failure Mode T2_15 EDM Dogbone 0.5x6.0x0.12" as-machined 9/25/92 outside gage - 41 EDM Dogbone 0.5x5.5x0.08" as-machined 10/19/89 gage - 42 EDM Dogbone 0.5x5.5x0.08" as-machined 10/27/89 gage - 43 EDM Dogbone 0.5x5.5x0.08" as-machined 8/22/89 gage - 44 EDM Dogbone 0.5x5.5x0.08" as-machined 8/23/89 gage - T1_45 EDM Dogbone 0.5x5.5x0.06" as-machined 9/25/92 gage - T2_45 EDM Dogbone 0.5x5.5x0.06" as-machined 9/25/92 radius - MIL-HDBK-17-4 APPENDIX C 164 MATERIAL: SiC/Ti-15-3 Table C 1(c) SiC/Ti-15-3 FIBER: SCS-6 TEST METHOD: Sec. 1.4.2.1 Tension Tension MATRIX: Ti-15V-3Cr-3Al-3Sn PRE-TEST EXPOSURE: 1292°F/24 hrs. (vac.) Laminates PRODUCT FORM: Foil/fiber/foil TEST ATMOSPHERE: Air NASA LeRC PRODUCT DIMENSIONS: 10” x 14” Raw Data LAY-UP: Cross-ply laminates PLY COUNT: 8-ply FIBER VOLUME PERCENT: 35 Fiber v/o Specimen No Lot I.D. (Plate) Test Temp. Strain Rate E x t F x pl F x ty0 02. F x ty0.2 F x tu ε x tu ν νν ν xy t Comments (°F) (1/s) (Msi) (ksi) (ksi) (ksi) (ksi) (%) +/- 30 H3 D890053 75 1x10-4 23 44 60 105 - - - Mo-weave (1) +/- 30 H16 D890053 75 1x10-4 23 48 60 108 179 1.66 - Mo-weave +/- 30 26 87H149 75 1x10-4 24 58 74 114 148 1.14 - Ti-weave +/- 30 25 87H149 75 1x10-4 21 62 73 114 145 1.11 - Ti-weave +/- 30 24 87H149 75 1x10-4 22 67 75 112 144 >1.5 - Ti-weave (2) +/- 30 23 87H149 75 1x10-4 24 48 71 115 145 0.99 - Ti-weave +/- 30 22 87H149 75 1x10-4 20 65 97 146 147 1.04 - Ti-weave +/- 30 19 87H149 75 1x10-4 22 61 79 121 153 1.2 - Ti-weave +/- 30 18 87H149 75 1x10-4 21 33 26 95 133 1.44 - Ti-weave (3) +/- 30 12 87H149 75 1x10-4 22 59 64 91 146 1.32 - Ti-weave +/- 30 11 87H149 75 1x10-4 22 63 81 113 140 1.26 - Ti-weave +/- 30 9_23 J890509 800 1x10-3 20 40 50 86 134 1.52 - Mo-weave (4) +/- 45 A11 87H148 75 1x10-4 17 30 40 52 77 >4.0 - Ti-weave (2) +/- 45 A6 87H148 800 1x10-4 13 21 35 47 68 7.29 - Ti-weave +/- 45 A13 87H148 800 1x10-5 17 28 30 29 64 >4.6 - Ti-weave (2) +/- 60 F1 87H149 75 1x10-4 17 36 41 50 57 1.8 - Ti-weave +/- 60 F4 87H149 800 1x10-4 14 26 28 35 48 2.95 - Ti-weave 0/90 B2 87H150 75 1x10-4 21 23 37 115 143 1 - Ti-weave 0/90 B4 87H150 75 1x10-4 23 47 72 136 149 1.08 - Ti-weave 90/0 C5 87H150 75 1x10-4 15 40 80 135 145 1.21 0.15 Ti-weave 90/0 C4 87H150 75 1x10-4 25 23 46 118 154 1.07 0.21 Ti-weave (1) Slipped in grips (3) Stress discontinuity at yield point (2) Test interrupted (4) 32 ply material MIL-HDBK-17-4 APPENDIX C 165 MATERIAL: SiC/Ti-15-3 Table C1(c) (cont.) SiC/Ti-15-3 FIBER: SCS-6 TEST METHOD: Sec. 1.4.2.1 Tension Tension MATRIX: Ti-15V-3Cr-3Al-3Sn PRE-TEST EXPOSURE: 1292°F/24 hrs. (vac.) Laminates PRODUCT FORM: Foil/fiber/foil TEST ATMOSPHERE: Air NASA LeRC PRODUCT DIMENSIONS: 10” x 14” Raw Data LAY-UP: Cross-ply laminates PLY COUNT: 8-ply FIBER VOLUME PERCENT: 35 Specimen No. Machining Method Specimen Geometry Specimen Dimensions Surface Condition Tes t Date Failure Location Failure Mode H3 EDM Dogbone 0.5x6.0x0.07" as-machined 9/6/90 - H16 EDM Dogbone 0.5x6.0x0.07" as-machined 9/7/90 gage 26 EDM Rectangular 0.75x6.0x0.08" as-machined 6/13/89 gage 25 EDM Rectangular 0.75x6.0x0.08" as-machined 6/13/89 gage 24 EDM Rectangular 1.0x6.0x0.08" as-machined 6/13/89 mid-gage 23 EDM Rectangular 1.0x6.0x0.08" as-machined 6/13/89 gage 22 EDM Dogbone 0.5x6.0x0.08" as-machined 12/1/88 gage 19 EDM Dogbone 0.5x6.0x0.08" as-machined 12/1/88 radius 18 EDM Dogbone 0.5x4.0x0.08" as-machined 7/13/88 radius 12 EDM Dogbone 0.5x4.0x0.08" as-machined 8/9/88 grips 11 EDM Dogbone 0.5x4.0x0.08" as-machined 11/15/88 gage 9_23 EDM + Diamond Grind Dogbone 0.5x6.0x0.3" as-machined 11/24/92 mid-gage A11 EDM Dogbone 0.5x6.0x0.08" as-machined 1/24/90 - A6 EDM Dogbone 0.5x6.0x0.08" as-machined 3/3/89 radius A13 EDM Dogbone 0.5x6.0x0.08" as-machined 2/1/90 - F1 EDM Dogbone 0.5x6.0x0.08" as-machined 1/24/90 gage F4 EDM Dogbone 0.5x6.0x0.08" as-machined 2/1/90 radius B2 EDM Dogbone 0.5x6.0x0.08" as-machined 6/7/89 gage B4 EDM Dogbone 0.5x6.0x0.08" as-machined 4/4/89 gage C5 EDM Dogbone 0.5x6.0x0.08" as-machined 10/27/89 gage C4 EDM Dogbone 0.5x6.0x0.08" as-machined 10/19/89 gage [...]... chemicals Pedigree Physical property test methods Fiber Lamina/laminate (continuous fiber) Matrix Power blending and consolidation Rapid infrared joining Reactive processing (in-situ composites) References (use of) Reinforcement materials Coatings Role of Types of Residual strength and stiffness Resistance spot welding Safety Secondary manufacturing processes Joining Secretariat Shear (in-plane) Lamina/laminate... hazards Inertia friction welding Joining Potential issues Qualitative assessment Types of Laser beam welding Manufacturing processes Assembly and consolidation Material system codes (matrix/fiber Matrix materials Forms of Mechanical property test methods Microstructcural analysis Physical property test methods Role of Test plans Types of Mechanical fastening Microhardness Microstructural analysis techniques . 75 8.3x10-5 12. 1 - - 112 122 22.1 39.5 HIP Sheet 5 ksi Helium - 16 212_ C B934027 75 8.3x10-5 12 - - 116 125 16.8 22 HIP Sheet 5 ksi Hydrogen - 16213_D B934027 75 8.3x10-5 12. 5 - - 114 125 17.2 27.1. 75 2x10-3 13 111 117 124 127 20.2 - HIP Foil air - 16211_B B934027 75 8.3x10-5 12. 4 - - 114 124 20.7 37.8 HIP Sheet 5 ksi Helium - 16210_A B934027 75 8.3x10-5 11.9 - - 110 120 20.3 40.3 HIP Sheet. 0.5x6.0x0.08" as-machined 12/ 1/88 gage 19 EDM Dogbone 0.5x6.0x0.08" as-machined 12/ 1/88 radius 18 EDM Dogbone 0.5x4.0x0.08" as-machined 7/13/88 radius 12 EDM Dogbone 0.5x4.0x0.08"