AE1402 CT I
Transcript of AE1402 CT I
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M ount Z ion Co l lege o f Eng ineer ing & Techno logyTo Mak e Man Who le ! ! A n I S O 9 0 0 1 : 2 0 0 8 C e r t i f i e d I n s t i t u t i o n
CYCLE TEST I –August 2012
SPR No.: Year/Dept: IV/AERO Date: Wednesday, 01 August 2012
Pilivalam P.O, Pudukkottai Dt., Tamil Nadu. Pin - 622 507, Fax: 04333 – 277125, Ph: 04322 - 320801, 320802, Website: www.mzcet.in, Email: [email protected]
Page 1 of 1 - Rec/Cor/01 Rev 05
AE1402 COMPOSITE MATERIALS AND STRUCTURES
Time: 09:10 a.m.–
12:10 p.m.100
Marks
(Answer All the Questions)
PART A - 2 Mark Qs (10x2=20)
1. What is mean by composites?
2
2. Explain difference between fibers and whiskers.
3. What is mean by Anisotropic material constants?
4. Name any four aircraft using composites and parts in which used.
5. Explain the function and desirable properties of resins used in FRP.
6. What the assumptions made in the strength of materials approach model?
7. What about the Transverse Stiffness?
8. What is a Laminate?
9. What is the Off-Axis Stiffness of a Ply?
10. What is the Toughness (Fracture Energy) of a Composite?
PART B - 16 Mark Qs (5x16=80)
11. a Determine E1 & E2 for lamina using macro - mechanics where 1 and 2 are arbitrary axis. 16
(OR)
11. b What happens with Short Fibres? 16
12. a Using machines of material approach obtain expressions for E1, E2, G12 , ?12 and show their
relations with Vf. 16
(OR)
12. b Discuss the production of glass fibers in detail using a neat sketch.Give the composition of E glass and
S glass.
16
13. a Derive the governing differential equation for an unidirectional anistropic plate and reduce if to
orthotropic plates and isotropic plates.
16
(OR)
13. b What are the Stresses within a Crossply Laminate? 16
14. a In a built up aluminium alloy I-section shown in fig.1. One flange was removed and replaced by steel
angle of same dimensions. Calculate the change in rivet shear for a shear load of 10000N. The rivets
have 4mm diameter and 20mm spacing. EAl = 70 Gpa.
16
(OR)
14. b
Compare the properties of metals, ceramics and polymers as matrix materials. 16
15. a For the following laminate configuration compute the stiffness matrices. No of layers 4, Each layer is
1mm thickness 0? / - 45 / 45? / 90?.E1 = 40 Gpa, E2 = 8 Gpa G12 > 4 Gpa. ?12 = 0.25 (16).
16
(OR)
15. b List down the boundary conditions used for the analysis of laminated plate (both simply supported
and fixed edges) obtain the expression for the maximum deflection of a simply supported orthotropic
plate subjected to uniformly distributed load of intensity qo.
16