空间飞行器有限推力轨道转移优化设计  

Optimal orbital transfer design of space vehicle by finite thrust

作　　者：顾大可[1] 

机构地区：[1]东北电力大学自动化工程学院,吉林吉林132012

出　　处：《电机与控制学报》2011年第8期88-92,共5页Electric Machines and Control

基　　金：国家自然科学基金(60710002)

摘　　要：为了解决空间飞行器有限推力轨道转移最优轨迹的设计问题,利用参数化控制思想和强化控制技术给出了最优轨道转移轨迹求解方法。给出了空间飞行器轨道转移最优控制问题的基本描述,通过参数化控制及强化技术将有限推力轨道转移最优控制问题转化为静态参数优化问题,即用若干段个分段的常数去逼近最优解。应用经典的数学规划方法即可求得最优控制律的一个近似解,通过增加参数个数,重复优化得到逼近连续最优解的参数化解。仿真结果表明,所提出的方法对于空间飞行器转移轨道初始参数取值不敏感,具有一定的鲁棒性,并且最优解的精确度较高,设计方法简单、有效。In order to solve the optimal design of orbital transfer with finite thrust,a computational method,based on the control parametrization in conjunction with enhancing control technique was developed.Firstly,problem formation of space vehicle orbital transfer optimization control was given.By applying control parametrization and enhancing technique,the optimal control problem of orbital transfer with finite thrust was transformed into parameters selection problems which can be solved by the classical mathematical programming method.By means of increasing the number of parameters and the iteration of optimization,the parametric solution which approaches the continuous optimal solution was derived.The simulation results demonstrate that the proposed method is not sensitive to orbital transfer initial conditions and good in robustness,and high precision of solution,also simple and effective.

关 键 词：参数化控制 强化技术 有限推力 最优轨道转移 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]