Aircraft Structures by David J. Peery

By David J. Peery

Still suitable a long time after its 1950 booklet, this mythical reference textual content on airplane rigidity research is taken into account the simplest publication at the topic. It emphasizes simple structural idea, which is still unchanged with the advance of recent fabrics and building equipment, and the appliance of the trouble-free ideas of mechanics to the research of plane structures.
Suitable for undergraduate scholars, this quantity covers equilibrium of forces, area constructions, inertia forces and cargo elements, shear and bending stresses, and beams with unsymmetrical go sections. extra issues contain spanwise air-load distribution, exterior a lot at the aircraft, joints and fittings, deflections of constructions, and unique tools of study. issues concerning a data of aerodynamics look in ultimate chapters, permitting scholars to review the prerequisite aerodynamics themes in concurrent courses.

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Sample text

About a vertical axia and T, about a side axis. 6T In the f mbod y diagram for the entire structure, shown in Fig. 10(b), there are six unknown forcea The forces at B and C act along the member; therefore there is only one unknown at each point. The force at A is unknown in dimtion and must be considered as three unknown force components, or 88 an unknown force and two unknown direction angles. Usually it is more convenient to find the componenta, after which the resultant force may be obtained from Eq.

3 U ~ ~ J O ; t . 3 ~ ; t . 3 0 . ~ ~ ~ ~ 3 ~ ~ T- 9 c LA C PBOB. 11. 6) (-@f w i n d the loads in the fuselage truss structure shown by analyzing the '\ e i i w as coplanar structurea each carrying half the vertical load and by /b) h O B . 12. k) euperimpo&ngthe forces resulting from torsion about the oenter line. 5. U. Find the torsional form in the 8tructw-e of Example 3, Art. 5, by the method used for landing-gear torque links in m p l e 4, Art. 3. After findingthe forces on the aft structure, apply these forcee to the spar, and analyze the spar as a coplanar truss.

The bending moment m the front spar at the cut cross section is M = 2,400 X 50 = 120,000 in-lb The bending moment in the rear spar is M = 1,600 X 50 80,000 in-lb These forces are shown in Fig. 22(a). Example 3. The wing structure shown in Fig. 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.

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