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aerodynamic loads aeroelastic loads airplane allowable stress Anisotropic bending Buckling Analysis buckling constraints buckling critical panels chart in figure composite airframe structures composite material composite panels computer programs computer resources Computer-Aided Design core cover panels fiber orientations figure 6(a finite-element flow chart FREE DESIGN Fundamental frequency fuselage grouping high Young's modulus HM/H HM/P hybrid construction integrated computer itera Jaroslaw Langley Research Center LM/H configuration LM/P load path loop low Young's modulus maneuver mass reduction mass savings membrane forces minimum gage NASA nonoptimum mass number of design objective function optimization procedure orientation angles orthotropy panels in figure percent ply thicknesses pure composite construction reoptimization Rib and spar sandwich cover sandwich depth tc sandwich panel SCAR Conference shear shear stress shown in figure struc structural mass Structural Optimization tion titanium baseline titanium caps tural U.S. Customary Units wing cover wing tip deflection