Aerospace Vehicle Structures-II B.Tech Question Paper : vardhaman.org
College : Vardhaman College Of Engineering
Degree : B.Tech
Department : Aeronautical Engineering
Semester : V
Subject : Aerospace Vehicle Structures-II
Document type : Question Paper
Website : vardhaman.org
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June – 2014 :https://www.pdfquestion.in/uploads/vardhaman.org/6380-BT5S%20JUNE14.pdf
December – 2013 : https://www.pdfquestion.in/uploads/vardhaman.org/6380-B.%20Tech%20V%20Semester%20Regular%20Examinations%20December%20-%202013.pdf
Aerospace Vehicle Structures-II Question Paper :
Four Year B. Tech V Semester Supplementary Examinations June – 2014
(Regulations: VCE-R11)
(Aeronautical Engineering)
Date: 19 June, 2014 FN
Time: 3 hours
Max Marks: 75
Answer ONE question from each Unit
All Questions Carry Equal Marks
Related : Vardhaman College Of Engineering Antennas & Wave Propagation B.Tech Question Paper : www.pdfquestion.in/6379.html
All parts of the question must be answered in one place only :
Unit – I :
1. a) What is meant by complete tension field beam? 7M
b) Explain semi-monocoque and monocoque structures? 8M
2. What is the function of ribs, stringers and spar webs on the function of aircrafts? 15M
Unit – II :
3. a) Derive an equation for direct stress distribution due to bending of an unsymmetrical beam? 8M
b) A beam having the cross section as shown in Fig.1 is subjected to a bending moment of 1500 N m in a vertical plane. Calculate the maximum direct stress due to bending stating the point at which it acts? Fig.1 7M
4. a) Derive an equation for Bending moment in a symmetrical section beam. 7M
b) The cross section of a beam has the dimensional as shown in Fig.2 if the beam is subjected to a negative bending moment of 100 KNm applied in a virtual plane, determine the distribution of direct stress through the depth of the section. 8M
Unit – III :
5. a) Explain the concept of stability of stiffened Panels? 7M
b) Explain the terms shear flow, shear center and elastic axis?
6. a) Determine the shear flow distribution in the thin walled Z section queen in the as shown in Fig.3 due to shear load sy applied through the shear inter of the section Fig.3 8M
b) Explain the phenomenon of local instability? 7M
Unit – IV :
7. a) Derive the generative torsion bending equation for an open section subjected to torsion and wheel is axially constrained? 8M
b) Discuss in brief the concept of warping of beams? 7M
8. a) Obtain an expression for torsion – bending constant? 8M
b) Explain the phenomenon of Torsion and bending? 7M
Unit – V :
9. a) Derive:
i. Equation of equilibrium
ii. Compatibility Equations 10M
b) Differentiate between Plane Stress and Plane Strain problems. 5M
10. A three-flange wing section is stiffened by the wing rib shown in Fig. 4. If the rib flanges and stiffeners carry all the direct loads, while the rib panels are effective only in shear, calculate the shear flows in the panels and the direct loads in the rib flanges and stiffeners. 15M
B. Tech V Semester Regular Examinations, December – 2013 :
(Regulations: VCE-R11) :
Aerospace Vehicle Structures-II :
(Aeronautical Engineering)
Date : 12 December, 2013
Time : 3 Hours
Max. Marks : 75
Answer ONE question from each Unit
All Questions Carry Equal Marks
All parts of the question must be answered in one place only
Unit – 1 :
1. a) Explain briefly about complete and incomplete diagonal tension beams. 8M
b) Explain the importance of Wagner’s theory of beams? 7M
2. a) Explain the following:
i. Stability of stiffened Panel
ii. Monocoque and semi monocoque 8M
b) Derive the equation for shear force at any section of an incomplete tension field beam? 7M
Unit – 2 :
3. The doubly symmetrical fuselage section shown in fig.1 has been idealized into an arrangement of direct stress carrying booms and shear stress carrying skin panels; the boom areas are all 150 mm2. Calculate the direct stresses in the booms and the shear flows in the panels when the section is subjected to a shear load of 50 kN and a bending moment of 100 kN m.
4. Figure .2 shows the cross section of a two-cell torque box. If the shear stress in any wall must not exceed 140N/mm2, find the maximum torque which can be applied to the box. If this torque were applied at one end and resisted at the other end of such a box of span 2500mm, find the twist in degrees of one end relative to the other and the torsional rigidity of the box. The shear modulus G=26600N/mm2 for all walls. Data are as follows: Shaded areas: A34 = 6450mm2, A16 = 7750mm2 Wall lengths: S34 = 250mm, S16 = 300mm Wall thickness: t12 = 1.63mm, t34 = 0.56mm, t23 = t45 = t56 = 0.92mm, t61 = 2.03mm, t25 = 2.54mm. 15M
Unit – 3 :
5. a) Explain effective skin width concept in skin stringer construction. 7M
b) Briefly discuss about stability of stiffened Panel. 8M
6. a) Derive an expression for share flow in open section? 8M
b) Give a brief note about unsymmetrical beams and mention its assumptions. 7M
Unit – 4 :
7. Derive the expression for primary wrapping of thin walled open section beam. 1 5M
8. The cold-formed section shown in fig.3 is subjected to a torque of 50Nm. Calculate the maximum shear stress in the section and its rate of twist. G= 25000N/mm2. fig.3 15M