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Previous Year Exam Questions of Composite Materials of bput - CM by Verified Writer

  • Composite Materials - CM
  • 2017
  • PYQ
  • Biju Patnaik University of Technology Rourkela Odisha - BPUT
  • Civil Engineering
  • B.Tech
  • 586 Views
  • 12 Offline Downloads
  • Uploaded 1 year ago
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Registration No: Total Number of Pages: 01 B.Tech PECI5404 7th Semester Regular/Back Examination 2017-18 Composite Materials & Structures BRANCH : CIVIL Time: 3 Hours Max Marks: 70 Q.CODE: B341 Answer Question No.1 which is compulsory and any five from the rest. The figures in the right hand margin indicate marks. Q1 a) b) c) d) e) f) g) h) i) j) Q2 a) Answer the following questions : State the difference between isotropic material and composite material. What are the various constituents of a composite? State different types of fibres used in preparation of composites. Distinguish between E 11 and E 22 . State the various strain components developed in a composite laminate subjected to external loading. State an example of a symmetric laminate. What do you mean by stacking sequence? Differentiate between cross-ply and angle ply laminate. State the various independent elastic constants by which an unidirectional lamina is characterized. State the characteristics of B matrix in a composite laminate. (2 x 10) Explain the difference between principal material axis system and reference axis system with neat sketches for each one. Why is it necessary for transformation of stresses and strains from one axis system to another? Develop the transformation matrix, T wrt stress when transformed from principal material axis, 1-2 to the reference axis, x-y. (4) Distinguish between micromechanics and macromechanics Develop the constitutive relationship for a specially orthotropic material. (4) (6) Q4 For a composite of unidirectional lamina with fibre orientation of 30 degree, calculate the compliance matrix , stiffness matrix and transformed reduced stiffness matrix if E11= 130 GPa, E22 = 9 GPa, G12 = 7 GPa, and  12 = 0.32. (10) Q5 Calculate the A and B matrix for a three layered [90/0/90] laminate if E1 = 125 GPa, E2 = 10 GPa, E6 = 6 GPa,  12 = 0.30 and total thickness of the laminate is 1.5 mm. (10) Q6 Derive the Navier’s solution for finding deflection at the centre of a rectangular orthotropic laminate with all edges simply supported. (10) Q7 For a 30/90/30 three layered laminate subjected to Nx = 120 MPa-mm thrust, find the resultant stresses along the reference axis for each lamina. E11 = 120 GPa, E2 = 10 GPa, thickness of each layer is 0.1 mm,  12 = 0.3. (10) b) Q3 a) b) Q8 a) b) c) d) Write short notes on (any TWO) : Uses and applications of composites Lamina and laminate Transformation matrix for strain anti symmetric angle ply laminate (6) (5 x 2)

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