Name of the College : Sphoorthy Engineering College
University : JNTUH
Department : AERONAUTICAL ENGINEERING
Subject Code/Name : 09A52103 /AEROSPACE VEHICLE STRUCTURES – II
Year : December 2011
Degree : B.Tech
Year/Sem : III/I
Website : sphoorthyengg.com
Document Type : Model Question Paper
Download Model/Sample Question Paper : https://www.pdfquestion.in/uploads/sphoorthyengg.com/4800-09A52103%20-%20AEROSPACE%20VEHICLE%20STRUCTURES-II.pdf
Aerospace Vehicle Structures-II :
B. Tech III Year I Semester Examinations, December-2011
(AERONAUTICAL ENGINEERING)
Time: 3 hours
Related : Sphoorthy Engineering College 09A52101 Flight Mechanics-II B.Tech Question Paper : www.pdfquestion.in/4802.html
Max. Marks: 75
Answer any five questions :
All questions carry equal marks :
1.a) What is the difference between monocoque and semi monoque structure.
b) A beam having the cross-section is shown in the figure below subjected to a bending moment of 1500nm in a vertical plane. Calculate the maximum direct stress due to bending stating the point at which it acts. [7+8]
2. Illustrative give the examples of Aircraft sheet stringer elements through free-Body diagram. [15]
3. A thin walled pin ended column is 2m long and has the cross – section shown in figure below if the ends of the column are free to wrap determine the lowest value of axial load which will cause buckling and specify the buckling mode. [15] Take E = 75000 N/mm² and G = 21000 N/mm²
4. Determine the direct stress distribution in the thin–walled Z–section figure. Below produced by a positive bending moment Mx. [15]
5. The beam shown in figure below is simply supported at each end and carriers a load of 6000N. If all the direct stresses are resisted by the flanges and stiffeners and the web panels are effective only in shear, calculate the distribution of a axial load in the flange ABC and the stiffener BE and the shear flows in the panels. [15]
6.a) Discuss about torsion of an arbitrary section beam.
b) Explain brief on I – section beam subjected to torsion with neat sketch. [7+8]
7.a) Explain the principles of stiffener/web construction?
b) Write a short note on:
i) Fuselage frames ii) Wing ribs. [9+6]
8.a) Explain the following terms:
i) Ductility ii) Brittleness iii) Orthotropic materials IV) Plasticity
b) Discuss about the torsion of a narrow Rectangular strip. [8+7]
R09Code No: 09A52103
SET-2
1.a) Explain about the tension field webs and give some examples with neat sketch?
b) What is the difference between Semi tension and complete tension field beams? [7+8]
2. Write about the failure stress in plates and stiffened panels? With neat sketch. [15]
3. The skin of the upper side of an airplane wing made of 2024 –T6 Alclad. The Stringer spacing is 5”, and the rib spacing is 20” .Assuming the edges to be simply supported, find the compression buckling stress for skin gages of:
a) 0.040” b) 0.084” [15]
4. The cantilever beam is uniformly tapered along its length in both X and Y directions and carriers a load of 100kn at its free end. Calculate the forces in the booms and the shear flow distribution in the walls at a section 2m from the built-in end if the boom resists all the direct stresses while the walls are effective only in shear.
Each corner boom as a cross- sectional area of 900mm². While both central booms have cross- sectional areas of 1200mm². [15]
5.a) Explain briefly about types of wings and Fuselages with a neat sketch.
b) Calculate the shear stress distribution in the walls of the three – cell wing section shown below .when it is subjected to an anti-clock wise torque of 11.3KNM. [7+8]
6. Explain the condition for zero warping at a section, and derive the warping of the cross – section. [15]
7. Find the angle twist per unit length in the wing whose cross –section is shown figure below. When it is subjected to a torque of 10KNM. Find also the maximum shear stress in the section. G = 25000 N/mm²; wall12 (outer) =900m. Nose cell area = 20,000mm². [15]
8. Explain the following terms.
a) Parallel axis theorem.
b) Theorem of perpendicular axes.
c) Three boom shell.
d) Fuselage frames. [15]