基于Gauss伪谱法的航天器气动力辅助平面变轨问题研究  

Study of Spacecraft Aeroassisted Coplanar Orbital Transfer Based on Gauss Pseudospectral Method

作　　者：符俊[1] 蔡洪[1] 李安梁[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2011年第6期95-99,110,共6页Journal of National University of Defense Technology

基　　金：国家"863"高技术计划基金资助项目

摘　　要：气动力辅助变轨技术可以有效地节约燃料,是未来航天器新型变轨技术的发展方向之一。该文采用Gauss伪谱法对航天器从高轨道向低轨道共面轨道转移问题进行了研究。在考虑热流限制、控制约束的条件下,得到了航天器大气飞行段的次优轨迹,并对轨迹特性进行了分析,证明优化结果满足一阶最优性必要条件。同时采用间接法处理该问题,对两种方法的计算结果进行了比较。仿真分析表明:Gauss伪谱法处理约束方法简单,解的精度高,且克服了间接法对初值敏感、鲁棒性差的缺点,适合应用于航天器大气内轨迹优化问题。It is well known that the use of aeroassisted orbital transfer can save fuel efficiently,thus representing one of development trends of new orbital transfer technology.This paper is concerned with the problem of coplanar orbital transfer of spacecraft from high earth orbit to low earth orbit based on Gauss pseudospectral method（GPM）.With the consideration of heating rate limit and control constraints,sub-optimal trajectory of spacecraft＇s flight in atmosphere was obtained.On the analysis of trajectory characteristic the first-order necessary optimality conditions of optimized results was demonstrated.Indirect method was also adopted to solve the problem,then the calculation results of the two methods were compared.Simulation results show that it is a simple way to handle constraints with GPM,and it has high precision solutions and can overcome the disadvantages of the indirect method,such as initial value sensitivity and poor robustness.Therefore,GPM is suitable to be applied in the problem of atmospheric spacecraft trajectory optimization.

关 键 词：轨迹优化 升力系数 GAUSS伪谱法 打靶法 轨道转移 

分 类 号：V448[航空宇航科学与技术—飞行器设计]