基于弹道制导联合仿真的新一代中型运载火箭安全余量分析

Propellant Safety Margin Analysis of New Medium Launch Vehicle Based on Joint Simulation of Trajectory and Guidance

为获取运载火箭各级最优安全余量配置,分析了影响火箭运载能力的偏差种类及其数学模型,建立了涵盖各种偏差条件和制导诸元的运载火箭弹道制导联合仿真模型。采用基于蒙特卡洛仿真的火箭安全余量评估方法,对新一代中型运载火箭各级安全余量最优分配方案进行了仿真分析。根据助推器和芯级安全余量的范围,设计了25个典型仿真工况,通过对各工况进行仿真分析和结果统计,研究了各级安全余量、耗尽概率对实现运载能力的影响规律,获得了新一代中型火箭最优安全余量配置方案,进一步优化了火箭运载能力。

To obtain the optimum distribution scheme of launch vehicle(LV),various deviations affecting launch capacity were analyzed,and the simulation model of LV by considering various deviations and guidance data was built.The method to evaluate trajectory propellant safety margin(PSM)based on Monte Carlo simulation was applied,and the optimum distribution scheme of PSM for new-generation LV was simulated.According to the range of PSM,25 working conditions for simulation were designed.The PSM of every stage was analyzed,and the influence of PSM and exhaustion probability on payload capacity was also studied.The optimum distribution scheme of PSM for new-generation LV was obtained,and the payload capacity was optimized.