JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD B.Tech III AIRCRAFT STRUCTURAL ANALYSIS Previous Question Paper (May/June - 2019 - R16)

A thin rectangular plate a × b is simply supported along its edges and carries a uniformly distributed load of intensity q0. Determine the deflected form of the plate and distribution of bending moment.

The beam shown in Figure 1 is assumed to have a complete tension field web. If the cross-sectional areas of the flanges and stiffeners are, respectively, 350 mm2 and 300 mm2 and the elastic section modulus of each flange is 750 mm3, determine the maximum stress in a flange and also whether or not the stiffeners will buckle. The thickness of the web is 2 mm and the second moment of area of a stiffener about an axis in the plane of the web is 2000 mm4; E = 70,000 N/mm2.

A beam having the cross-section shown in figure 2 is subjected to a bending moment of 1,500 Nm in a vertical plane. Calculate the maximum direct stress due to bending stating the point at which it acts.

Derive the Bredt-Batho formula related to torsion. What are the assumptions made?

Calculate the shear flow distribution in the channel section shown in figure 3 produced by a vertical shear load of 4.8 kN acting through its shear center. Assume that the walls of the section are effective in resisting only shear stresses, while the booms, each of area 300 mm2, carry all the direct stresses.

Idealize the box section shown in figure 4 into an arrangement of direct stress carrying booms positioned at the four corners and panels that are assumed to carry only shear stresses. Hence, determine the distance of the shear center from the left-hand web.

Derive the expression of the torsion bending constant for an open section beam fully built-in at one end.

A thin-walled two-cell beam with the singly symmetrical cross-section shown in Figure 5 is built-in at one end where the torque is 11000 Nm. Assuming the cross-section remains undistorted by the loading; determine the distribution of shear flow for side 12. The shear modulus G is the same for all walls.

Determine the shear flow distribution in the web of the tapered beam shown in Figure 6, at a section midway along its length. The web of the beam has a thickness of 2 mm and is fully effective in resisting direct stress. The beam tapers symmetrically about its horizontal centroidal axis and the cross-sectional area of each flange is 400 mm2.

The wing section shown in figure 7 has been idealized such that the booms carry all the direct stresses. If the wing section is subjected to a bending moment of 300 kNm applied in a vertical plane, calculate the direct stresses in the booms: Boom areas: B1=B6 =2580 mm2; B2 =B5 =3880 mm2; B3 = B4 =3230 mm2.