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EQUIlIBRIUM OF FORCES
INERTIA FORCES AND lOAD FACTORS
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aerodynamic airplane alloy analysis angle of attack approximately assumed axial loads beam shown bending moments bending stresses bending-moment diagram bolt buckling stress calculated center of gravity centroid coefficient components compression load compressive stress conjugate beam considered constant cross section deflection deformations distance elastic limit equal equilibrium Example Find the shear fixed-end flange flange areas flange loads following equation fuselage heat-treated horizontal in-lb inertia forces joint lb/in length lift coefficient load factor material maximum method modulus neutral axis obtained from Eq plane plate produce product of inertia ratio reactions redundant represents resist resultant rivets rotation semimonocoque shear center shear flows shear stress shearing force sheet shown in Fig skin Solution span spanwise spar statically indeterminate stiffener stress distribution stress-strain curve stringers Substituting summation Table tensile stress tension field tion torsional truss tube values vertical webs welding wing yield zero