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aeroplane aircraft structures angle of twist applied load assumed axial bending moment diagram buckling calculated centroidal axis component compressive stress CONCENTRATED LOAD considered constant continuous beams cosec cospla critical load cross-sectional area curved beam deflection determined diagonal direction distance elastic limit element end load end moments equal equilibrium Euler Example fixed flange follows frame given gives Hence joints lateral load M/EI magnitude maximum shear stress method modulus moment of area neutral axis normal obtained panel perpendicular plane polar diagram positive principal axes radian radius reactions resultant shear shear centre shear flow shear force shear stress shown in Fig simple bending skin slope ſº space frame spar stiffener strain energy strut supports tensile stress tension field theorem Thin-walled torque torsion tube UNIFORMLY DISTRIBUTED LOAD unit length vertical wing zero