Integrated Topological Optimization Design Method for Solid Rocket Motor

Individual design of spacecraft and its propulsion system can hardly get an overall trajectory performance optimized result. The spacecraft often cannot get the best trajectory performance even the internal ballistics of its solid rocket motor act the best. To solve this problem, based on genetic algorithm, this paper establishes a set of integrated optimization model, involving the external trajectory of spacecraft, the internal ballistic and structure topological deformation of solid rocket motor. Select the largest final velocity and longest range of a micro rocket as the overall trajectory performance optimizing goal, the structure topological of its motor is optimized. Compared with the original design scheme, different optimal design schemes can achieve 4.38% and 10.80% trajectory performance improvement respectively. The optimization results of the study shows that the SRM optimization model built is reasonable, and the SRM design method based on the integrated simulation of internal and external trajectory is feasible.