Guided rocket projectile inner and outer trajectory joint design method adopting coupling iterative optimization

The invention discloses a guided rocket projectile inner and outer trajectory joint design method adopting coupling iterative optimization, and the method comprises the steps: building a solid rocket engine inner trajectory performance and guided rocket projectile flight trajectory coupling solution equation set, and comprehensively considering the engine inner trajectory design constraint and flight outer trajectory design constraint; selecting an expected optimization control variable and a target function, establishing an inner and outer trajectory joint optimization mathematical model, and solving the model through a particle swarm optimization algorithm, so as to realize the coupling design of the inner trajectory design parameters and the flight outer trajectory design parameters of the guided rocket projectile engine. The method is simple and effective, the architecture is universal, and engineering practice is easy. 本发明公开了一种采用耦合迭代优化的制导火箭弹内外弹道联合设计方法，通过建立固体火箭发动机内弹道性能与制导火箭弹飞行弹道耦合解算方程组，综合考虑发动机内弹道设计约束与飞行外弹