A new tool for designing a solid propellant rocket motor casing made of composite materials is obtained by merging the genetic algorithm optimization method with the finite element method. The genetic algorithm optimization method is used to determine the best design parameters of the laminate to minimize the weight of the rocket motor casing. The ANSYS finite element code is used to analyze the overstressing strength of the rocket motor casing. Tsai-Wu failure criterion is used to assess the first ply failure and an overstressing load level factor is introduced to describe the failure strength. Practical design examples, of composite rocket motor casings, are investigated using the present design tool.
N., E., N., Z., & M., E. (2011). DESIGN OPTIMIZATION OF COMPOSITE ROCKET MOTOR CASES USING GENETIC ALGORITHMS. International Conference on Aerospace Sciences and Aviation Technology, 11(ASAT Conference, 17-19 May 2005), 251-267. doi: 10.21608/asat.2011.27151
MLA
EI-Geuchy M. N.; Zayed A. N.; El-Maddah M. M.. "DESIGN OPTIMIZATION OF COMPOSITE ROCKET MOTOR CASES USING GENETIC ALGORITHMS", International Conference on Aerospace Sciences and Aviation Technology, 11, ASAT Conference, 17-19 May 2005, 2011, 251-267. doi: 10.21608/asat.2011.27151
HARVARD
N., E., N., Z., M., E. (2011). 'DESIGN OPTIMIZATION OF COMPOSITE ROCKET MOTOR CASES USING GENETIC ALGORITHMS', International Conference on Aerospace Sciences and Aviation Technology, 11(ASAT Conference, 17-19 May 2005), pp. 251-267. doi: 10.21608/asat.2011.27151
VANCOUVER
N., E., N., Z., M., E. DESIGN OPTIMIZATION OF COMPOSITE ROCKET MOTOR CASES USING GENETIC ALGORITHMS. International Conference on Aerospace Sciences and Aviation Technology, 2011; 11(ASAT Conference, 17-19 May 2005): 251-267. doi: 10.21608/asat.2011.27151
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