航天器轨迹优化的通用数值方法  

A Common Numerical Calculation Method ofOptimizing the Trajectories of Space Vehicles

作　　者：南英[1] 陈士橹[2] 严辉[2] 

机构地区：[1]北京航空航天大学,北京100083 [2]西北工业大学,西安710072

出　　处：《飞行力学》1996年第3期20-26,共7页Flight Dynamics

摘　　要：给出了航天器轨迹优化的一种通用数值仿真方法,该方法是由静态参数优化和动态参数优化构成。其中,静态参数优化采用可变误差多面体算法,动态参数优化采用基于最优控制理论的共轭梯度方法。简述了该动态、静态参数优化的算法,给出了仿真框图。该方法已成功地用于求解航天器的各类轨迹优化及总体设计等问题,如各类航天运载器上升轨迹及分离马赫数的选择、(气动力辅助)空间变轨、返回与再入轨迹、飞行轨迹/飞行器总体参数一体化设计和导弹程序段弹道设计等。Abstract A common numerical calculation method is studied for optimizing the trajectories of space vehicles. The method is composed of static parameter optimization and dynamic parameter optimization, where the static optimization is chosen as static varied tolerance polyhedrons algorithm and dynamic optimization is chosen as conjugate gradient numerical calculation method based on optimal control theory. The static and dynamic optimization algorithms are given. The common numerical method is successfully applied to optimize the following projects; return and reentry trajectories of space shuttle and manned space vehicles, space trajectory transfers, aeroassisted trajectory transfers, ascent trajectories of space plane (with two stages ) and space vehicles (with two stages), integrative design for trajectories/the global parameters of the vehicle, the program controlled trajectory of a land to air missile or an air - to - land missile. The large amount numerical results shown that the common numerical calculation method can widely apply to optimize the trajectories of space vehicles, and to space vehicle design.

关 键 词：飞行轨迹 总体设计 最优控制 数值仿真 航天器 

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]