By David J. Peery
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 go sections. extra subject matters comprise spanwise air-load distribution, exterior rather a lot at the plane, joints and fittings, deflections of buildings, and specified tools of research. issues regarding a data of aerodynamics look in ultimate chapters, permitting scholars to review the prerequisite aerodynamics themes in concurrent courses.
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Additional info for Aircraft Structures (Dover Books on Aeronautical Engineering)
16. no. 17. Sd& The aide trueses are first d y a e d 89 coplanar trusses CSrrJring loads of 500 Ib. The forces obtained are shown in Fig. 17. Thew! 3 Member ER BE' BB' BC' CC' I Forcea resulting from Mlolbperade Forces resulting from 10,ooO in-lb, torsion Total forcerr -632 +a8 +266 -286 +319 0 0 0 Co' +638 Do' -532 0 Eo' -319 0 +3€9 -286 +319 0 -319 d +319 -266 +a7 -m -819 This structure is in reality statically indeterminate, and the t o r s i o d analysis gives only approximate values of the forces in the members.
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. 5. REFBRENCES FOR CHAPTER 2 R. : primary Strem Determination in Space Frames, Enqi1. Sowrmm~~, neering, Feb. 6,1920. 2. : The Analysis of Aircraft Structures as Space Frameworks, NACA TM 522,1929.
65)* X 500 X = 219 Ib This force is much smaller than other forces acting on the turret, and is usually neglected. In part (c) of this problem, certain simplifyingassumptions were made which do not quite cornpond with actual landing ~nditions. Aerodynamic forces were neglected, and the ground reactions on the landing gear were assumed constant while the landing gear was being compressed. The actual compregsion of the landing gear is a combination of the tire deflection, in which the load is approximately proportional to the deformation, and the oleo-strut deflection, in which the load is almost constant during the entire deformation, as assumed in the problem.