Design And Overall Optimization For Solid Pulse Rocket Motor

Solid pulse motors are the executive mechanisms of guided ammunition's thrust vector control system, having many characters such as miniaturization, low mass, rapid response, short pulse, multi-tubes and modularization. Therefore, with pulse motors for trajectory correction or attitude control, executive mechanisms have many advantages in technique foundation, economy and flexibility. In this thesis, taking the demand of smart vehicle (mini-missile, micro-KKV, cargo warhead etc.) for high performance attitude and trajectory control motors as application requirement, design and optimization is primarily investigated for solid pulse motors.After consulting and analyzing great deal of foreign and domestic information, a specific motor structure with side nozzle is proposed according to the overall target, and the arranging of solid pulse motors is also designed. Then, the grains, nozzle and igniter are investigated in detail including grain type choose, motor parameter, nozzle performance analysis and igniter design.The motor's operation experiments are accomplished, and the grain type is chosen across the rsults. For optimization, based on the deficiency of the simple genetic algorithm (SGA), an improved method (multimode FGA) is introduced, which can be used to combine with Back-Propagation Network to optimize motors' overall parameters. The simulation results show that solid pulse motor's performance has been improved to a great extent. Finally, the performance distribution of solid pulse motors is analyzed with Monte-Carlo method, and the sensitivity study based on orthogonal design implys that propellant is the main factor which cause the random distribution of the total impulse.The design idea and optimization methods accomplished in this thesis could supply valuable reference to the engineering development of solid pulse motors.