By T.H.G. Megson
Aircraft constructions for Engineering scholars is the top self contained plane buildings path textual content. It covers all primary matters, together with elasticity, structural research, airworthiness and aeroelasticity. Now in its fifth version, the writer has revised and up to date the textual content all through and further new examples and routines utilizing Matlab(c). extra labored examples make the textual content much more obtainable through displaying program of ideas to airframe buildings. contains a ideas guide on hand to all adopting teachers.
* New labored examples through the textual content reduction realizing and relate thoughts to genuine global purposes * Matlab examples and workouts further all through to aid use of computational instruments in research and design
* an intensive plane layout undertaking case research exhibits the appliance of the foremost suggestions within the ebook * extra finish of bankruptcy workouts, with an accompanying Solutions handbook (for teachers simply) at http://textbooks.elsevier.com
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Additional info for Aircraft Structures for Engineering Students
Reference  Timoshenko S, Goodier JN. Theory of elasticity. 2nd ed. New York: McGraw-Hill; 1951. 1 A metal plate has rectangular axes Ox, Oy marked on its surface. The point O and the direction of Ox are fixed in space and the plate is subjected to the following uniform stresses: Compressive, 3p, parallel to Ox, Tensile, 2p, parallel to Oy, Shearing, 4p, in planes parallel to Ox and Oy, in a sense tending to decrease the angle xOy. Determine the direction in which a certain point on the plate is displaced; the coordinates of the point are (2, 3) before straining.
1. 12) eqI ¼ vpa(-sig_I þ (sig_xþsig_y)/2 þ sqrt((sig_x-sig_y)^2 þ 4*tau_xy^2)/2); eqII ¼ vpa(-sig_II þ (sig_xþsig_y)/2 - sqrt((sig_x-sig_y)^2 þ 4*tau_xy^2)/2); % Add eqI and eqII and solve for the value of sig_x sig_x_val ¼ vpa(solve(eqIþeqII,sig_x)); % Calculate the axial load (P in kN) P ¼ vpa(sig_x_val*A/1000); P ¼ round(double(P)*10)/10; % Substitute sig_x back into eqI and solve for tau_xy tau_xy_val ¼ sym(max(double(solve(subs(eqI,sig_x,sig_x_val),tau_xy)))); % Calculate the applied torsion (T in kN-m) using Eq.
Vi), B þ 15Dh2 ¼ 0 (ix) so that, subtracting Eq. (viii) from Eq. 3 Inverse and semi-inverse methods 55 and f¼ Ã q Â À10h3 x2 þ 15h2 x2 y À 2h2 y3 À ð5x2 y3 À y5 Þ 3 40h The obvious disadvantage of the inverse method is that we are determining problems to fit assumed solutions, whereas in structural analysis the reverse is the case. However, in some problems, the shape of the body and the applied loading allow simplifying assumptions to be made, thereby enabling a solution to be obtained. St. Venant suggested a semi-inverse method for the solution of this type of problem, in which assumptions are made as to stress or displacement components.