Analysis and Design of Flight Vehicle Structures

aircraft airplane aluminum alloy angle applied assumed axes axial loads beam section bending moment bending stress bolt buckling stress calculated cell centroid Chapter coefficient column compressive stress core crippling stress cross-section curve cylinder deflection determined diagram edge end moments equal equation equilibrium Example Problem external loads factor failure fatigue flange forces frame fuselage given hence in.lb inch inertia joint longeron material matrix maximum method modulus moment of inertia neutral axis obtained plane plate reactions redundant rivet Room Temperature shear center shear flow shear load shear strength shear stress sheet panels shown in Fig shows simply supported skin solution static statically determinate steel stiffener stiffness strain energy strength stress-strain stress-strain curve stringer structure Table take moments tensile tensile stress thickness torsional truss tube values vertical wing yield strength zero ΕΙ