Available at: https://digitalcommons.calpoly.edu/theses/2968
Date of Award
6-2023
Degree Name
MS in Aerospace Engineering
Department/Program
Aerospace Engineering
College
College of Engineering
Advisor
Faysal Kolkailah
Advisor Department
Aerospace Engineering
Advisor College
College of Engineering
Abstract
This study utilizes MATLAB genetic algorithm (GA) to perform optimization on a solid rocket motor (SRM) chamber structure. The (SRM) structure is modelled as a cylindrical composite laminate where unidirectional fiber orientations are the primary design variable in the optimization problem formulation. Additional design variables such as chamber length, diameter, and internal pressure are altered along with the ply angles to minimize the safety margin towards a near-zero value and encourage efficient layup design. Classical lamination theory with Tsai-Wu failure criterion are used to calculate ply-level safety margins. A thickness minimization scheme is employed to reduce the ply count from a conservative predetermined value to assist in limiting the structural mass of the system. The optimized layup configurations produced by the MATLAB GA implementation are compared to a previous optimization study from literature for mass, dimensions, and propulsion capabilities. Finite element analysis is used as a validation tool to confirm the safety of the proposed design. Finally, the capabilities of the GA are evaluated against a commercially available structural optimization software package on the same SRM chamber model.
