椭圆形悬挂轨道控制策略研究  

Study on Control Strategy of an Elliptical Orbit Hovering

作　　者：李雪华[1] 徐卫昌 田园 和兴锁[3] 

机构地区：[1]西安工业大学建筑工程学院,西安710021 [2]第二炮兵工程大学士官职业技术教育学院,青州262500 [3]西北工业大学力学与土木建筑学院,西安710129

出　　处：《西安工业大学学报》2014年第10期800-804,共5页Journal of Xi’an Technological University

基　　金：西安工业大学校长基金项目(XAGDXJJ1221)

摘　　要：为了实现椭圆形悬挂轨道,文中以航天器相对运动动力学模型为基础,对椭圆形悬挂轨道的控制策略进行了分析研究.根据悬挂轨道的定义,通过理论分析和推导,得到了悬挂星在椭圆悬挂轨道上运行时所需要的控制加速度,并对其进行了数值仿真.仿真结果表明:控制加速度曲线平滑,易于实现和控制,且仿真结果与泛开普勒轨道所需的控制加速度一致,椭圆形悬挂轨道实现方法正确可行.Based upon analyzing the relative motion dynamics model of spacecraft,an elliptical orbit hovering method was presented.According to the definition of hovering orbit,theoretical dynamic analysis of the hovering orbit was conducted,the acceleration requirements during the hovering process were deduced,and the corresponding simulations were conducted.The simulation results show that control acceleration curves are smooth enough to realize orbit control,and the results and their analysis show preliminarily that the method is in agreement with the method in Ref.9,and thus is plausibly correct and feasible.

关 键 词：相对运动动力学 椭圆轨道 悬挂轨道 控制加速度 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]