中型固体运载火箭内外弹道联合优化设计方法研究

Propulsion and Trajectory United Optimization Design Method Research of Middle Scale Solid Launch Vehicle

为了兼顾中型固体运载火箭二级起控环境和运载能力,研究内外弹道联合优化设计方法。研究结果表明:相比于单推力的内弹道形式,Ⅰ级发动机采用“前高后低”双推力的内弹道形式在改善二级起控环境的同时减少运载能力的损失;采用序列二次规划(Sequential Quadratic Programming, SQP)算法可以实现多过程约束多终端约束下的内外弹道联合优化设计。研究成果可为中型固体运载火箭的总体方案论证提供借鉴。

In order to balance the capacity of second stage attitude control and payload of middle scale solid launch vehicle,this paper researches a propulsion and trajectory united optimization design method.The research result shows that:compared to single thrust propulsion,first stage engine adopting″first-high-second-low″thrust propulsion can reduce the loss of payload capacity and improve second stage attitude control condition.The sequential quadratic programming(SQP)method realizes the proposed optimization on condition of multy process and terminal constraints.The research results can provide reference for the overall scheme argumentation of medium-sized solid launch vehicles.