Structural Design Optimization of an Aircraft Wing Stiffened Panel with Hat and I Section Stringer
Cheluve Gowda D1, Nagarajappa N2, Kiran K Shetty3
1Cheluve Gowda D, PG Student, Department of Civil Engineering, Manipal Institute of Technology, Manipal Academy of Higher Education, Manipal, Udupi, India.
2Nagarajappa N, Principal Scientist, Structural Technologies Division, CSIR-National Aerospace Laboratories, Bangalore, India.
3Dr. Kiran K Shetty, Professor, Department of Civil Engineering, Manipal Institute of Technology, Manipal Academy of Higher Education, Manipal, Udupi, India.
Manuscript received on 01 April 2019 | Revised Manuscript received on 09 May 2019 | Manuscript published on 30 May 2019 | PP: 2764-2768 | Volume-8 Issue-1, May 2019 | Retrieval Number: A1422058119/19©BEIESP
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Abstract: Stiffened panel of aircraft consists of stringers which must be placed in proper spacing because increase in spacing decreases buckling strength and decrease in spacing increases weight. In order to find the proper optimum spacing structural optimization of aircraft wing stiffened panel is done to find the minimum weight satisfying all the design constraints and structural integrity to perform under operational loads. Aluminum / Composite materials are widely used in airframe structures because of its strength to weight ratio and stiffness to weight ratio when compared to conventional materials. Structural design optimization is carried out for stiffened panels of wing with HAT section stringer and I section stringer for different spacings from 75mm to 250mm for both metal and composite materials. A comparative study of design optimization is carried for both metal and composite stiffened plates. Thickness of skin is considered as design variables for all different sets of stringer spacings. Tsai-Wu failure criterion is used for satisfying strength and Eigen value approach is used for satisfying buckling criteria during optimization. The spacing at which the minimum weight is obtained satisfying all the structural design constraints is considered as optimum stringer spacing. Optimization deck for the above-mentioned strength and buckling criteria constraints is developed using design response level 1 cards (DRESP1) and solution-200 (SOL 200) for MSC Nastran solver to carry out the optimization.
Key words: Composites; Optimization; Stiffened; Stringers.
Scope of the Article: Cross Layer Design and Optimization