MIL-HDBK-17-3F Volume 3,Chapter 10 Thick-Section Composites F =Stress (psi) Y,&=Strain (in./in.) E=Extensional modulus(psi) G=Shear modulus (psi) 9"o0 V=Poisson's ratio Az zy FYG FIGURE 10.2.3.1(g)Oriented laminate thickness direction design properties. 10-11
MIL-HDBK-17-3F Volume 3, Chapter 10 Thick-Section Composites 10-11 FIGURE 10.2.3.1(g) Oriented laminate thickness direction design properties
MIL-HDBK-17-3F Volume 3,Chapter 10 Thick-Section Composites TABLE 10.2.3.1(b)Test methods available for determining 3-D lamina properties. Loading Inplane Out-of-Plane Test Method Loading Test Method Property Property x-Ten Flu ASTM D3039? z-Ten x elu SACMA SRM-4? id To Be Developed 小少 u 《+ ASTM D3410? z-Comp eCU SACMA SRM-1? Fa ALLIANT ToBe TECHSYSTEMS Developed 唱 DTRC 吸 ARL dU ASTM D3039? xz-Shear F ASTM D2344? SACMA SRM-1? SACMA SRM-8? 红 IOSIPESCU ASTM D3410? yz-Shear eQ SACMA SRM-1? ALLIANT z IOSIPESCU TECHSYSTEMS 8 DTRC ARL Fsu ASTM D4255? Noles: IOSIPESCU ?.Applicability depends on laminate layup configuration. 10-12
MIL-HDBK-17-3F Volume 3, Chapter 10 Thick-Section Composites 10-12 TABLE 10.2.3.1(b) Test methods available for determining 3-D lamina properties