Download GTU BE/B.Tech 2019 Winter 5th Sem New 2150103 Aircraft Structures Ii Question Paper

Download GTU (Gujarat Technological University) BE/BTech (Bachelor of Engineering / Bachelor of Technology) 2019 Winter 5th Sem New 2150103 Aircraft Structures Ii Previous Question Paper

1
Seat No.: ________ Enrolment No.___________

GUJARAT TECHNOLOGICAL UNIVERSITY

BE - SEMESTER ? V (New) EXAMINATION ? WINTER 2019
Subject Code: 2150103 Date: 04/12/2019

Subject Name: Aircraft Structures II
Time: 10:30 AM TO 01:00 PM Total Marks: 70

Instructions:
1. Attempt all questions.
2. Make suitable assumptions wherever necessary.
3. Figures to the right indicate full marks.

MARKS

Q.1 (a) Clearly explain the loads acting on an aircraft for different flight conditions with
neat sketches.
03
(b) Discuss about the failures occur in structural components of aircraft for different
flight conditions.
04
(c) Briefly explain about the load bearing members of wing, fuselage and empennage
section with neat sketches
07

Q.2 (a) Define Shear Centre and Shear Flow. 03
(b) What do you understand by the term buckling of a structure? Give an example of
an aircraft structural component prone to buckling.
04
(c) How the structure of civil aircraft is different from fighter aircraft? Discuss using
critical points.
07
OR
(c) A simply supported beam has a central point load of W. Determine the deflection
curve and the maximum deflection if the beam is doubly symmetric.
07
Q.3 (a) Define Stiffness and state the characteristics of Stiffness Matrix. 03
(b) Explain with neat sketch the state of stress at a point in three dimensions 04
(c) Derive the equation of torque for a bar from Prandtl stress function 07
OR
Q.3 (a) Enlist the different ways of making the section free from torsion. 03
(b) Describe the difference between Symmetrical Bending and Unsymmetrical
Bending?
04
(c) What is the need of V-n diagram? Explain using neat sketch. 07
Q.4 (a) Define Principal Centroidal Axis. 03
(b) What are the different cross sections that can be used in spar of a wing? Which one
is most preferable and why?
04
(c) Explain torsion of multi cell open section beams. 07
OR
Q.4 (a) Define neutral axis. 03
(b) Enlist the basic equations of equilibrium, compatibility and stress strain relations
for plane stress condition in polar coordinate system.
04
(c) Explain torsion of multi cell closed section beams. 07
Q.5 (a) Explain St Venant?s principle. 03
(b) Describe principle moment of inertia. 04
(c) Derive the equations for direct bending stress distribution. Also sketch the direct
bending stress distribution of an I-section.
07
OR

Q.5 (a) What do you mean by in plane stress and out of plane stress? 03
(b) Prove that ?Stiffness matrix and Flexibility matrix are inverse to one another?. 04
(c) What is redundancy? Explain its significance with suitable example of aircraft
structure.
07
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