Aircraft Structures

aircraft airplane analysis applied assumed axes axial loads beam shown bending moment bending moments bending stresses bolt box beam buckling stress C₁ calculated center of gravity centroid components compression load compressive stress considered constant coordinates crippling stress cross section cutout deflection deformation displacements edges elastic limit element equal equation equilibrium Figure Find the shear fitting factor flange flange loads fuselage horizontal in² kips lb/in² length load factor margin of safety material maximum method moment of inertia neutral axis obtained from Eq plane plate product of inertia q₁ ratio rectangular resist resultant rivet rotation semimonocoque shear center shear flows shearing stresses sheet shown in Fig simply supported skin SOLUTION spar statically statically indeterminate stiffener stress distribution stress-strain curve stringers structure shown summation symmetrical tensile stress tension field thermal stress torque torsional truss tube values vertical webs weld wing zero