基于逆多项式轨迹成形法的小推力轨道设计  

Inverse Polynomial Shape-based Method for Low-thrust Trajectory Design

作　　者：程兴[1] 史晓宁[1] 崔乃刚[1] 

机构地区：[1]哈尔滨工业大学,哈尔滨150001

出　　处：《中国空间科学技术》2011年第6期1-7,共7页Chinese Space Science and Technology

基　　金：国家自然科学基金(61005060);微小型航天器技术国防重点学科实验室开放基金(HIT.KLOF.2009090)资助项目

摘　　要：轨迹成形法是一种基于反向设计思想的轨道设计方法,它假设待研究的轨道呈现某一形状,利用数学曲线进行逼近从而得到设计结果。逆多项式轨迹成形法为小推力地球转移轨道设计和数值求解最优轨迹过程中初值的选取提供了新的研究思路。首先结合轨道动力学方程和逆多项式曲线模型给出了轨迹成形法的设计过程,并在考虑时间约束的情况下对小推力转移轨道进行设计。仿真结果表明逆多项式轨迹成形法适宜于小推力转移轨道设计,并且其设计结果是一组近优解,可以作为求取精确最优轨迹的初值猜测。Shape-based approach is a reverse design method by assuming a certain shape of the trajectory to find the parameters which fulfill the boundary conditions. The inverse polynomial function provided a new shape-based method for the low-thrust trajectory design and initial value selection for direct optimization solver. Coupled with the astrodynamics functions, the inverse polynomial shape-based method was derived and used to solve the low-thrust transfer problem in a fixed time. The results demonstrate that the method presented is reasonable for the low-trust trajectory design. Furthermore, the solutions tend to be near-optimal and are able to provide initial guess for direct optimizer.

关 键 词：逆多项式 转移轨道 最优轨迹 轨道设计 航天器 

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]