Integrated Optimization Design of Solid Rocket Trajectory / Overall Parameters

Abstract

This paper studies the integrated optimization design of trajectory / overall parameters of multistage solid launch vehicle. The mathematical models related to the overall design of solid launch vehicle are established, mainly including flight program control model, ballistic model, mass model, engine performance calculation model and so on. An optimization model for integrated trajectory / overall parameter optimization design of solid launch vehicle is proposed. The optimization model takes the maximum effective load as the objective function and clarifies the path constraints and terminal constraints that should be met during the flight of the launch vehicle. The particle swarm optimization algorithm is used as the optimization algorithm to improve the values of inertia weight and learning factor in the particle swarm optimization algorithm, so that the algorithm has better search accuracy and exploration ability. The integrated optimization design of solid rocket trajectory and overall parameters is realized in this paper. The simulation results show that the rocket carrying capacity of the optimization scheme is improved by 13.1 %, and the terminal constraints and process constraints are well satisfied. The thrust scheme can provide theoretical reference for the detailed design of solid rocket motors at all levels.