Aircraft Structures by David J. Peery

By David J. Peery

Still correct a long time after its 1950 e-book, this mythical reference textual content on plane rigidity research is taken into account the simplest e-book at the topic. It emphasizes uncomplicated structural conception, which continues to be unchanged with the advance of recent fabrics and development tools, and the appliance of the simple ideas of mechanics to the research of plane structures.
Suitable for undergraduate scholars, this quantity covers equilibrium of forces, house buildings, inertia forces and cargo components, shear and bending stresses, and beams with unsymmetrical move sections. extra themes comprise spanwise air-load distribution, exterior rather a lot at the aircraft, joints and fittings, deflections of buildings, and particular equipment of research. themes regarding a data of aerodynamics seem in ultimate chapters, permitting scholars to check the prerequisite aerodynamics themes in concurrent courses.

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This can be done in a fabric-covered wing by providing drag t r u m at both the upper and lower surfaces of the wing, as shown in Fig. 19,rather than the single drag truss shown in Figs. 20. Fm. 19. It is desirable to have the area of the wing cross section enclosed by the spars and the drag trusses as large as possible, since this is the area A to be used in Eq. 7 for a torsional analysis. High-performance airplanes have much higher wing loadings than light private airplanes. The wing weight per square foot must be much greater in order to provide adequate strength.

S i n c e the area of the triangle OBC' shown in Figs. 14(c) or (d)is rd/2, the moment of the force in member BC' about the axis through 0 may be written as follows. AT = 2p X (mOBC') The momenta of the forces in all the envelope members may be obtained in a similar manner. The sum of all the triangular areas will be equal to the shaded area shown in Fig. 14(c), and the sum of all the torsional incremenb will be equal to the external torque, T. T = 2p X (s~~~EE'BC'CD') This area, which is always equal to the area e n c l d by the projection of the envelope members on the plane of a bulkhead, will be designated as A.

24 is mmilar to that used for some full-cantilever fabrimvered wings. One main spar, member Add3& carries all the-wing bending moment. The s t ~ c t u r eaft of this spar carries wing torsion and is somewhat similar to landing-gear torque links. The structure aft of the spar also serves as a truss to resist drag loads on the wing. Unlike the twospar wing, the structure is statically determinab, since a section through the wing would cut only six membem, which could be analyzed by the equations of static8.

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