高升阻比滑翔飞行器异面最优变轨迹策略设计与分析  

Design and Analysis of Optimal Trajectory Change Strategy for Different Planes of High Lift-to-drag Glider

作　　者：樊晨霄 董超[1] 蔡辉 贾平会 王永海[1] Fan Chenxiao;Dong Chao;Cai Hui;JiaPinghui;Wang Yonghai(Beijing Institute of Space Long March Vehicle,Beijing 100076,China;Unit 96901 of PLA,Beijing 100094,China)

机构地区：[1]北京航天长征飞行器研究所,北京100076 [2]中国人民解放军96901部队,北京100094

出　　处：《战术导弹技术》2021年第6期121-129,共9页Tactical Missile Technology

摘　　要：针对高升阻比飞行器在倾侧转弯飞行过程中能量保持的需求,提出一种能量最优的气动力辅助异面倾侧转弯机动(BTT)飞行策略。通过建立轨道动力学及大气层内飞行器横纵向运动方程及动力学模型,分析高升阻比飞行器倾侧转弯的弹道特性,推导并证明终端速度与倾侧转弯幅度相关的解析形式公式,实现弹道参数间的解耦和简化;通过数值优化方法进一步验证飞行策略的能量优化性能,通过龙格库塔法进行数值积分求解,获得能量最优的飞行轨迹。仿真结果表明,该飞行策略与数值优化方法获得的结果高度一致,证明了该解析方法在大幅提升求解效率的同时,具有较高可靠性,可有效指导制导策略总体设计工作,具有工程应用意义。Aiming at the demand of energy maintenance of high lift-to-drag aircraft during tilting and turning flight, an aerodynamic assisted maneuvering flight strategy of different plane tilting and turning with optimal energy is proposed. By establishing the orbital dynamics and the horizontal and longitudinal motion equations and dynamic models of the aircraft in the atmosphere, the trajectory characteristics of the aircraft with high lift-to-drag ratio are analyzed, and the analytic formulas related to the terminal speed and the amplitude of the tilt are derived and proved to realize the decoupling and simplification of the trajectory parameters. The energy optimization performance of the flight strategy is further proved by the numerical optimization method, and the numerical integration solution is performed by the Runge-Kutta method to obtain the energy-optimized flight trajectory. The simulation results show that the flight strategy is highly consistent with the results obtained by the numerical optimization method, which proves that the analytical method has high reliability while greatly improving the solution efficiency. This method can effectively guide the overall design of the guidance strategy, and has engineering application significance.

关 键 词：高升阻比飞行器 能量优化 倾侧转弯 最优控制 异面变轨迹策略 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]