Composite Materials Handbook Part 11 ppt

MIL-HDBK-17-4 141 MATERIAL: SCS-6/Ti-15V-3Cr-3Al-3Sn foil/fiber/foil Table 3.8.2.1(k) SiC/Ti Foil/fiber/foil MACHINING: EDM FIBER VOLUME: 35 % SCS-6/Ti-15-3 FIBER SPACING: Tension, x-axis [+/-60] 2s SPECIMEN THICKNESS: 0.08 in. MODULUS Least squares analysis 75, 800 CALCULATION: up to proportional limit Screening TEST METHOD: Sec. 1.4.2.1 PRE-TEST EXPOSURE: Vac. 1292 ° F, 24 hrs. SOURCE: NASA LeRC NORMALIZED BY: Not normalized Temperature (°F) 75 800 Environment Air Air Fiber Volume (%) 35 35 Strain Rate (1/s) 1·10 - 4 1·10 -4 Mean 57 48 Minimum Maximum C.V.(%) B-value F x tu Distribution (ksi) C 1 C 2 No. Specimens 1 1 No. Lots 1 1 Approval Class Screening Screening Mean 17 14 Minimum Maximum E x t C.V.(%) (Msi) No. Specimens 1 1 No. Lots 1 1 Approval Class Screening Screening Mean ν xy t No. Specimens No. Lots Approval Class Mean 1.8 2.95 Minimum Maximum C.V.(%) B-value ε x tu Distribution (%) C 1 C 2 No. Specimens 1 1 No. Lots 1 1 Approval Class Screening Screening MIL-HDBK-17-4 142 MATERIAL: SCS-6/Ti-15V-3Cr-3Al-3Sn foil/fiber/foil Table 3.8.2.1(l) SiC/Ti Foil/fiber/foil MACHINING: EDM FIBER VOLUME: 35 % SCS-6/Ti-15-3 FIBER SPACING: Tension, x-axis [+/-60] 2s SPECIMEN THICKNESS: 0.08 in. MODULUS Least squares analysis 75, 800 CALCULATION: up to proportional limit Screening TEST METHOD: Sec. 1.4.2.1 PRE-TEST EXPOSURE: Vac. 1292 ° F, 24 hrs. SOURCE: NASA LeRC NORMALIZED BY: Not normalized Temperature (°F) 75 800 Environment Air Air Fiber Volume (%) 35 35 Strain Rate (1/s) 1·10 -4 1·10 -4 Mean 36 26 Minimum Maximum C.V.(%) B-value F pl 1 Distribution (ksi) C 1 C 2 No. Specimens 1 1 No. Lots 1 1 Approval Class Screening Screening Mean 41 28 Minimum Maximum C.V.(%) B-value F x ty0 02. Distribution (ksi) C 1 C 2 No. Specimens 1 1 No. Lots 1 1 Approval Class Screening Screening Mean 50 35 Minimum Maximum C.V.(%) B-value F x ty0.2 Distribution (ksi) C 1 C 2 No. Specimens 1 1 No. Lots 1 1 Approval Class Screening Screening MIL-HDBK-17-4 143 MATERIAL: SCS-6/Ti-15V-3Cr-3Al-3Sn foil/fiber/foil Table 3.8.2.1(m) SiC/Ti Foil/fiber/foil MACHINING: EDM FIBER VOLUME: 35 % SCS-6/Ti-15-3 FIBER SPACING: Tension, x-axis [0/90 ] (1) SPECIMEN THICKNESS: 0.08 in. MODULUS Least squares analysis 75 CALCULATION: up to proportional limit Screening TEST METHOD: Sec. 1.4.2.1 PRE-TEST EXPOSURE: Vac. 1292 ° F, 24 hrs. SOURCE: NASA LeRC NORMALIZED BY: Not normalized Temperature (°F) 75 Environment Air Fiber Volume (%) 35 Strain Rate (1/s) 1·10 -4 Mean 148 Minimum 143 Maximum 154 C.V.(%) B-value F x tu Distribution (ksi) C 1 C 2 No. Specimens 4 No. Lots 1 Approval Class Screening Mean 21 Minimum 15 Maximum 25 E x t C.V.(%) (Msi) No. Specimens 4 No. Lots 1 Approval Class Screening Mean 0.18 ν xy t No. Specimens 2 No. Lots 1 Approval Class Screening Mean 1.09 Minimum 1 Maximum 1.21 C.V.(%) B-value ε x tu Distribution (%) C 1 C 2 No. Specimens 4 No. Lots 1 Approval Class Screening (1) Combined data from [0/90] 2s and [90/0] 2s . MIL-HDBK-17-4 144 MATERIAL: SCS-6/Ti-15V-3Cr-3Al-3Sn foil/fiber/foil Table 3.8.2.1(n) SiC/Ti Foil/fiber/foil MACHINING: EDM FIBER VOLUME: 35 % SCS-6/Ti-15-3 FIBER SPACING: Tension, x-axis [0/90 ] (1) SPECIMEN THICKNESS: 0.08 in. MODULUS Least squares analysis 75 CALCULATION: up to proportional limit Screening TEST METHOD: Sec. 1.4.2.1 PRE-TEST EXPOSURE: Vac. 1292 ° F, 24 hrs. SOURCE: NASA LeRC NORMALIZED BY: Not normalized Temperature (°F) 75 Environment Air Fiber Volume (%) 35 Strain Rate (1/s) 1·10 - 4 Mean 33 Minimum 23 Maximum 47 C.V.(%) B-value F pl 1 Distribution (ksi) C 1 C 2 No. Specimens 4 No. Lots 1 Approval Class Screening Mean 58.8 Minimum 37 Maximum 80 C.V.(%) B-value F x ty0 02. Distribution (ksi) C 1 C 2 No. Specimens 4 No. Lots 1 Approval Class Screening Mean 126 Minimum 115 Maximum 136 C.V.(%) B-value F x ty0.2 Distribution (ksi) C 1 C 2 No. Specimens 4 No. Lots 1 Approval Class Screening (1) Combined data from [0/90] 2s and [90/0] 2s . MIL-HDBK-17-4 145 0 50 100 150 200 250 300 10 15 20 25 30 35 40 45 [0], 75 o F [0], 800 o F [90], 75 o F [90], 800 o F F tu (ksi) Fiber Volume Percent FIGURE 3.8.2.1(a) Ultimate tensile strength as a function of fiber volume and temperature. 15 20 25 30 35 10 15 20 25 30 35 40 45 [0], 75 o F [0], 800 o F [90], 7 5 o F [90], 8 00 o F E t (Msi) Fiber Volume Percent FIGURE 3.8.2.1(b) Tensile modulus as a function of fiber volume and temperature. MIL-HDBK-17-4 146 0 20 40 60 80 100 120 140 160 10 15 20 25 30 35 40 45 [0], 75 o F [0], 800 o F [90], 75 o F [90], 800 o F F pl (ksi) Fiber Volume Percent FIGURE 3.8.2.1(c) Proportional limit as a function of fiber volume and temperature. 0 50 100 150 200 250 10 15 20 25 30 35 40 45 [0], 75 o F [0], 800 o F [90], 75 o F [90], 800 o F F ty0.02 (ksi) Fiber Volume Percent FIGURE 3.8.2.1(d) 0.02-offset-strength as a function of fiber volume and temperature. MIL-HDBK-17-4 147 0 50 100 150 200 250 300 0 0.002 0.004 0.006 0.008 0.01 0.012 0.014 Stress (ksi) Strain 41 V f 35 V f 15 V f FIGURE 3.8.2.1(e) Typical tensile behavior of [0] 8 laminae at 75°F (24°C) as a function of fiber volume percent ( V f ) at a strain rate of 1*10 -4 s -1 . 0 50 100 150 200 250 0 0.002 0.004 0.006 0.008 0.01 Stress (ksi) Strain 41 V f 35 V f 25 V f 15 V f FIGURE 3.8.2.1(f) Typical tensile behavior of [0] 8 laminae at 800°F (427°C) as a function of fiber volume percent ( V f ) at a strain rate of 1*10 -3 s -1 . MIL-HDBK-17-4 148 0 50 100 150 200 250 -0.0035 -0.003 -0.0025 -0.002 -0.0015 -0.001 -0.0005 0 Stress (ksi) Transverse Width Strain 42 V f 25 V f 15 V f FIGURE 3.8.2.1(g) Typical tensile behavior of [0] 8 laminae at 800°F (427°C) as a function of fiber volume percent ( V f ) at a strain rate of 1*10 -3 s -1 . 0 5 10 15 20 25 30 [0] [90/0] [0/90] [+/30] [+/-45] [+/-60] [90] 75 o F 800 o F E x t (Msi) Fiber Orientation FIGURE 3.8.2.1(h) Average tensile modulus as a function of fiber orientation and temperature tested at strain rates of 1*10 -3 and 1*10 -4 s -1 . MIL-HDBK-17-4 149 0 50 100 150 200 250 [0] [90/0] [0/90] [+/30] [+/-45] [+/-60] [90] 75 o F 800 o F F x tu (ksi) Fiber Orientation FIGURE 3.8.2.1(i) Average tensile strength as a function of fiber orientation and temperature tested at strain rates of 1*10 -3 and 1*10 -4 s -1 . 0 50 100 150 200 0 0.005 0.01 0.015 0.02 Stress (ksi) Strain [0] 8 [90/0] 2s matrix [+/-45] 2s [90] 8 [+/-60] 2s [+/-30] 2s V f = 35 FIGURE 3.8.2.1(j) Typical tensile behavior of SiC/Ti-15-3 at 75°F (24°C) as a function of fiber orientation (V f = 35) at a strain rate of 1*10 -4 s -1 . MIL-HDBK-17-4 150 3.8.3 ALUMINA/TITANIUM 3.8.4 OTHER/TITANIUM 3.9 OTHER MATRIX COMPOSITES [...]... MIL-HDBK-17-4 APPENDIX A FIGURE A1(a) The effect of specimen thickness on the observed debond strength of SCS-6/Ti24 -11 composite system (Section 1.4.2.13 .11) 153 MIL-HDBK-17-4 APPENDIX A FIGURE A1(b) Pushout test data sheet (Section 1.4.2.13.14) 154 MIL-HDBK-17-4 APPENDIX B RAW DATA TABLES FOR MATRIX MATERIALS PARAGRAPH PAGE B1 ALUMINUMS 156 B2 COPPERS 156 B3 MAGNESIUMS ... TABLE A1(a) Debond load vs specimen thickness for SCS-6/Ti-24 -11 (Section 1.4.2.13.1) Specimen thickness (mm) 149 211 312 322 343 382 414 452 483 534 569 Debond load (N) 4.56 6.06 15.6 14.3 15.8 19.6 18.8 21.8 26.8 31.8 45.3 TABLE A1(b) Typical failure loads for various diameter WC punches (Section 1.4.2.13.1) Punch Dia (mm) 25 50 75 100 115 127 Failure Load (N) 2 5 20 40 50-55 60-70 152 MIL-HDBK-17-4 . 20 100 40 115 50-55 127 60-70 MIL-HDBK-17-4 APPENDIX A 153 FIGURE A1(a) The effect of specimen thickness on the observed debond strength of SCS-6/Ti24 -11 composite system (Section 1.4.2.13 .11) . MIL-HDBK-17-4 APPENDIX. A1(a) Debond load vs. specimen thickness for SCS-6/Ti-24 -11 (Section 1.4.2.13.1). Specimen thickness (mm) Debond load (N) .149 4.56 . 211 6.06 .312 15.6 .322 14.3 .343 15.8 .382 19.6 .414 18.8 .452. 02. Distribution (ksi) C 1 C 2 No. Specimens 4 No. Lots 1 Approval Class Screening Mean 126 Minimum 115 Maximum 136 C.V.(%) B-value F x ty0.2 Distribution (ksi) C 1 C 2 No. Specimens 4 No. Lots 1 Approval