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Technical Brief

Vibration Induced Fatigue Analysis of [0n/90n]s Simply Supported Composite Plate Under Central Patch Impulse Loading

[+] Author and Article Information
K. Jayaprakash

Aerospace Engineering Department,
Indian Institute of Technology Bombay,
Powai, Mumbai 400076, India
e-mail: prakasjp@gmail.com

M. Muthukumar

Aerospace Engineering Department,
Indian Institute of Technology Bombay,
Powai, Mumbai 400076, India
e-mail: muthukumarmathivanan@gmail.com

Y. M. Desai

Civil Engineering Department,
Indian Institute of Technology Bombay,
Powai, Mumbai 400076, India
e-mail: desai@civil.iitb.ac.in

N. K. Naik

Aerospace Engineering Department,
Indian Institute of Technology Bombay,
Powai, Mumbai 400076, India
e-mail: nknaik@aero.iitb.ac.in

1Corresponding author.

Contributed by the Materials Division of ASME for publication in the JOURNAL OF ENGINEERING MATERIALS AND TECHNOLOGY. Manuscript received April 19, 2014; final manuscript received March 27, 2015; published online June 15, 2015. Assoc. Editor: Tetsuya Ohashi.

J. Eng. Mater. Technol 137(4), 044501 (Oct 01, 2015) (7 pages) Paper No: MATS-14-1084; doi: 10.1115/1.4030338 History: Received April 19, 2014; Revised March 27, 2015; Online June 15, 2015

Fatigue analysis of a simply supported composite plate with laminate configuration of [0n/90n]s under central patch impulse loading is presented using an analytical method. The method mainly consists of two steps, one, evaluation of vibration induced stresses for the given central patch impulse loading using modal analysis, and two, fatigue analysis using S–N curve approach, residual strength approach as well as failure function approach. The stress state in the plate was evaluated using viscous damping model as a function of time. The stress-time history was converted into block loading consisting of many sub-blocks. In the present study, the block loading consisted of four sub-blocks and a total of 175 numbers of cycles. The block loading was repeated after every 5 s. Next, fatigue analysis was carried out based on the block loading condition evaluated. Number of loading blocks for fatigue failure initiation and the location of failure were obtained. Studies were also carried out using two-dimensional (2D) finite element analysis (FEA). Number of loading blocks required to cause fatigue failure initiation under central patch impulse loading was found to be 3120 and 3170 using the analytical method and 2D FEA, respectively.

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Figures

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Fig. 1

Boundary condition representation for [0n/90n]s composite plate, simply supported, and under central patch impulse loading

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Fig. 2

Simply supported plate under central patch impulse loading, m = 50 kg, V = 32 m/s, ti = 0.001 s, midpoint peak deflection versus time, and before failure initiation: (a) analytical and (b) 2D FEA

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Fig. 3

Simply supported plate under central patch impulse loading, m = 50 kg, V = 32 m/s, ti = 0.001 s, analytical: (a) peak bending stress at midtop surface (location 2) versus time along y, before failure initiation and (b) peak bending stress at midtop surface (location 2) versus time along x, after second mode of failure

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Fig. 4

Simply supported plate under central patch impulse loading, m = 50 kg, V = 32 m/s, ti = 0.001 s, 2D FEA: (a) peak bending stress at midtop surface (location 2) versus time along y, before failure initiation and (b) peak bending stress at midtop surface (location 2) versus time along x, after second mode of failure

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Fig. 5

Number of loading blocks versus residual strength at location 2 of top layer under central patch impulse loading, simply supported plate, m = 50 kg, V = 32 m/s, ti = 0.001 s: (a) analytical and (b) 2D FEA

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