Exam Details
| Subject | Aircraft Structures | |
| Paper | ||
| Exam / Course | B.Tech in Aerospace Engineering (BTAE) | |
| Department | School of Engineering & Technology (SOET) | |
| Organization | indira gandhi national open university | |
| Position | ||
| Exam Date | December, 2016 | |
| City, State | new delhi, |
Question Paper
No. of Printed Pages: 3 IBAS-0141
B.Tech. AEROSPACE ENGINEEWNG
(BTAE)
Term-End Examination
December, 2016
00073
BAS-014 AIRCRAFT STRUCTURES
Time hours Maximum Marks: 70
Note: Answer any seven questions. All questions carry equal marks. Use of non-programmable calculator is permitted.
1. What are the various types of stresses developed in thin cylinders? 4
A cylindrical air receiver for a compressor is 2 m in internal diameter and made of plates 15 mm thick. If the hoop stress is not to exceed 90 N/mm2 and the axial stress is not to exceed 60 N/mm2 find the maximum safe air pressure. 6
2. What are the assumptions made in the theory of Pure Torsion? 3
A solid circular shaft transmits 75 kW at 200 rpm. Calculate the shaft diameter, if the twist in the shaft is not to exceed 1 degree in 2 metres of shaft and the shearing stress is limited to 50 N/mm2•
Take C 1 x 10^5 N/mm2 7
3. A cantilever of length 2 metres carries a uniformly distributed load of 2500 N per metre for a length of 1.25 metres from the fixed end and a point load of 1000 N at the free end. If the section is rectangular, 120 mm side and 240 mm deep, find the deflection at the free end.
Take E 10000 N/mm2 . 10
4. Explain, in brief, the following: 10
Monocoque Fuselage
Semi-monocoque Fuselage
Truss Type Fuselage
Composite Materials
Linearly Varying Distributed Load
5. A shell, 3.5 metres long, 1 metre in diameter, is subjected to an internal pressure of 1 N/mm2 . If the thickness of the shell is 10 mm, find the circumferential and longitudinal stresses. Also find the maximum shear stress and the changes in the dimensions of the shell.
Take E 2 x 10^5 N/mm2 and 1/m 0.3. 10
6. A shaft has to transmit 105 kW at 160 rpm. If the shear stress is not to exceed 65 N/mm2 and the twist in length of 3.5 m must not exceed 1 degree, find a suitable diameter.
Take C 8 x 10^4 N/mm2 . 10
7. Calculate the safe compressive load on a hollow cast iron column (one end rigidly fixed and the other hinged) of 150 mm external diameter and 100 mm internal diameter and 10 metres in length. Use Euler's formula with a factor of safety of 5 and E=95 kN/mm2. 10.
8. Explain the following briefly: 5x2=10
Modulus of Elasticity
Modulus of Rigidity
Hoop Stress
Shear Force Diagram
Bending Moment Diagram
9. What is the difference between a column and abeam? 2
Define the effective length of a column. 2
Find the shortest length L for a pin ended column having a cross-section of 60 mm x 100 mm for which Euler's formula applies. Take E 2x 10^5 N/mm2 and critical proportional limit is 250 N/mm2. 6
10. With the help of V-n diagram explain the flight envelope in reference to positive and negative load factors. 10
B.Tech. AEROSPACE ENGINEEWNG
(BTAE)
Term-End Examination
December, 2016
00073
BAS-014 AIRCRAFT STRUCTURES
Time hours Maximum Marks: 70
Note: Answer any seven questions. All questions carry equal marks. Use of non-programmable calculator is permitted.
1. What are the various types of stresses developed in thin cylinders? 4
A cylindrical air receiver for a compressor is 2 m in internal diameter and made of plates 15 mm thick. If the hoop stress is not to exceed 90 N/mm2 and the axial stress is not to exceed 60 N/mm2 find the maximum safe air pressure. 6
2. What are the assumptions made in the theory of Pure Torsion? 3
A solid circular shaft transmits 75 kW at 200 rpm. Calculate the shaft diameter, if the twist in the shaft is not to exceed 1 degree in 2 metres of shaft and the shearing stress is limited to 50 N/mm2•
Take C 1 x 10^5 N/mm2 7
3. A cantilever of length 2 metres carries a uniformly distributed load of 2500 N per metre for a length of 1.25 metres from the fixed end and a point load of 1000 N at the free end. If the section is rectangular, 120 mm side and 240 mm deep, find the deflection at the free end.
Take E 10000 N/mm2 . 10
4. Explain, in brief, the following: 10
Monocoque Fuselage
Semi-monocoque Fuselage
Truss Type Fuselage
Composite Materials
Linearly Varying Distributed Load
5. A shell, 3.5 metres long, 1 metre in diameter, is subjected to an internal pressure of 1 N/mm2 . If the thickness of the shell is 10 mm, find the circumferential and longitudinal stresses. Also find the maximum shear stress and the changes in the dimensions of the shell.
Take E 2 x 10^5 N/mm2 and 1/m 0.3. 10
6. A shaft has to transmit 105 kW at 160 rpm. If the shear stress is not to exceed 65 N/mm2 and the twist in length of 3.5 m must not exceed 1 degree, find a suitable diameter.
Take C 8 x 10^4 N/mm2 . 10
7. Calculate the safe compressive load on a hollow cast iron column (one end rigidly fixed and the other hinged) of 150 mm external diameter and 100 mm internal diameter and 10 metres in length. Use Euler's formula with a factor of safety of 5 and E=95 kN/mm2. 10.
8. Explain the following briefly: 5x2=10
Modulus of Elasticity
Modulus of Rigidity
Hoop Stress
Shear Force Diagram
Bending Moment Diagram
9. What is the difference between a column and abeam? 2
Define the effective length of a column. 2
Find the shortest length L for a pin ended column having a cross-section of 60 mm x 100 mm for which Euler's formula applies. Take E 2x 10^5 N/mm2 and critical proportional limit is 250 N/mm2. 6
10. With the help of V-n diagram explain the flight envelope in reference to positive and negative load factors. 10
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Subjects
- Aerodynamics- I
- Aerodynamics- II
- Aircraft Design/Launch Vehicle/ Rocket Design
- Aircraft Instruments
- Aircraft Safety and Maintenance Engineering
- Aircraft Structures
- Aircraft Systems And Airworthiness Requirements
- Applied Chemistry
- Applied Physics
- Basic Control Theory
- CNS-ATM system
- Composite Materials
- Computer Fundamentals
- Engineering Drawing
- Environmental Science
- Flight Mechanics
- High Speed Aerodynamics
- Instruction To Computer Play Device
- Introduction to Aeronautics
- Introduction To Rocket And Missiles
- Mechanics Design
- Propulsion- I
- Propulsion- II
- Rocket Propulsion
- Space Dynamics
- Strength of Materials
- Technical Writing and Communication Skills
- Workshop Technology