Aeronautical Engineering for National Certificate, Volume 2English Universities Press, 1952 - Aeronautics |
Contents
CHAP PAGE | 2 |
STRUCTURAL DESIGN REQUIREMENTS THE FLIGHT ENVELOPE DETER | 17 |
FUNDAMENTALS OF STRESS AND STRAIN COMPLEMENTARY SHEAR | 25 |
Copyright | |
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Common terms and phrases
aircraft structures angle of twist applied load assumed axial B.M. diagram bending moment diagram buckling calculated centroidal axis compressive stress CONCENTRATED LOAD considered constant cosec critical load cross-sectional area deflection determined direction distance elastic limit element end load end moments equal equilibrium Euler Example fixing flange follows frame given gives Hence indicated in Fig L₁ lateral load longitudinal M/EI M₁ magnitude maximum shear stress method modulus moment of area negative neutral axis normal obtain panel perpendicular plane polar diagram positive principal axes qmax radian radius reactions shear centre shear flow shear force shown in Fig simple bending skin slope stiffener strain energy strut supports tensile tensile stress tension theorem torque torsion tube UNIFORMLY DISTRIBUTED LOAD unit length w₁ wing Young's Modulus zero ΕΙ μα