混合推力作用下基于傅里叶级数展开的轨道设计方法  

A Shape-Based Method Using Fourier Series with a Hybrid Low-Thrust Propulsion System

作　　者：方群[1,2] 王雪峰 孙冲[1,2] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]航天飞行动力学技术国家重点实验室,陕西西安710072

出　　处：《西北工业大学学报》2017年第5期761-766,共6页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(11272255)资助

摘　　要：针对航天器机动轨道设计问题,引入太阳帆/电推进混合推力模式(太阳帆产生径向推力,用于改变引力场的引力大小;而与此同时电推进产生切向推力),研究了混合推力作用下的基于傅里叶级数展开的轨道设计方法。首先,根据太阳帆/电推进混合推力模型,建立航天器在极坐标系下的运动模型;然后,依据傅里叶级数展开式,将轨道设计问题转化为关于傅里叶系数的非线性规划问题。另外,文中改进原有的形状轨道设计方法,研究了航天器轨道转移的时间最优问题。最后,在考虑航天器任务约束的情况下,基于该方法设计了混合推力作用下的"地球-火星"转移轨道。仿真分析了太阳光压对形状轨道设计方法产生的影响,验证了应用混合推力设计形状轨道的可行性,并且在一定范围内可以得到燃料消耗更优的航天器连续推力转移轨道,为轨道优化提供了参考依据。In order to design spacecraft maneuver orbit, we investigate a shape-based method using Fourier series with a hybrid low-thrust propulsion （HLTP） system, which is constituted by a low-thrust thruster coupled with a so- lar sail, in this paper. In such way, a solar sail can provide a radial force, so the spacecraft is virtually subjected to a reduced solar gravity; meanwhile, the electric thruster provides a tangential force. Firstly, with the HLTP system, a new spacecraft dynamics model under the polar coordinate is given. Secondly, according to the Fourier series ex- pansion, the differential equation is converted to an algebraic equation and the trajectory design problem is conver- ted to a nonlinear programing problem about Fourier series coefficients. And an optimal time problem is discussed in this paper. With thrust constraint, a simple Earth-Mars rendezvous is used to depict the proposed method＇s feasibili- ty in interplanetary low-thrust orbit design with HLTP system. Results show that the auxiliary solar sail can decrease the fuel consumption under certain conditions.

关 键 词：连续推力 混合推力 轨道设计 傅里叶级数 形状方法 

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]