针对RLV发动机推力下降故障的弹道与制导律优化  

Ballistic and Guidance Law Optimization for RLV Engine Thrust Loss Fault

作　　者：李远东 邵小东 胡庆雷[1] 胡海峰[3] 潘豪[3] Li Yuandong;Shao Xiaodong;Hu Qinglei;Hu Haifeng;Pan Hao(School of Automation Science and Electrical Engineering,Beihang University,Beijing 100191,China;School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China;Beijing Aerospace Automatic Control Institute,Beijing 100854,China)

机构地区：[1]北京航空航天大学自动化科学与电气工程学院,北京100191 [2]北京航空航天大学航空科学与工程学院,北京100191 [3]北京航天自动控制研究所,北京100854

出　　处：《航天控制》2022年第2期3-8,共6页Aerospace Control

基　　金：国防基础科研项目(JCKY2018203B022);国家自然科学基金重点国际(地区)合作项目(61960206011)。

摘　　要：针对RLV(可重复利用运载火箭)发动机推力下降后助推段与返回段的协调弹道优化问题,提出了弹道评估与决策方案及新型优化制导律。首先基于弹道数值积分与入轨机械能设计了针对RLV助推段推力下降故障的运载与返回能力评估与决策方案,得到效益最优的弹道决策区间。进而设计利用PSO(粒子群优化算法)优化ZEM/ZEV(零控脱靶量)制导律的弹道优化方案。在助推段发动机推力下降后优化关机与落地时间使入轨与返回能力综合最优;在助推级分离后优化二次点火高度与制导律参数使其满足最大热流约束;在降落段推力进一步下降后,精细优化落地时间与制导参数以实现精确软着陆。仿真结果表明,本文提出的方案提高了RLV在发动机推力下降情况下的入轨与着陆能力,且算法计算量小,结构简单。Aiming at the problem of coordinated trajectory optimization between the boost and return sections of the RLV,a trajectory evaluation and decision-making program and a new optimized guidance law are proposed.Firstly,based on the numerical integration of ballistics and the mechanical energy,the carrying and return capability evaluation and decision-making plan for the thrust loss fault of the RLV booster stage are designed,and the trajectory decision interval with the best benefit is obtained.Then,PSO is used to optimize the ZEM/ZEV guidance law.After the thrust of the booster phase is reduced,the shutdown and landing time are optimized to promote the orbiting and return capabilities.After the payload and booster phases are separated,the secondary ignition height and the guidance law parameters are optimized to meet the maximum heat flow constraint.After the thrust is further reduced,the landing time and guidance parameters are finely optimized to achieve a precise soft landing.The simulation results show that the scheme proposed in this paper improves the RLV’s orbiting and landing ability under the condition of engine thrust loss and the algorithm has benefits for simple structure and low burden computation.

关 键 词：可重复利用运载火箭 发动机故障 弹道优化 ZEM/ZEV制导律 粒子群优化算法 

分 类 号：V448[航空宇航科学与技术—飞行器设计]