摘要
通过求解零初始速度下的无控相对运动距离最小值,分析了圆参考轨道下航天器近距离相对悬停的被动安全特性。航天器相对悬停的被动安全特性可描述为处于受控悬停状态的航天器在控制力消失后的相对运动轨迹与目标禁飞区之间的空交集状态,该问题可转换为求解零初始速度下的相对运动距离最小值。由于初始位置的不同,相对距离最小值点可能位于整数倍周期极小值或非整数倍周期极小值点,通过分析两种类型极小值点的存在条件以及极小值点为最小值点的分界条件得到临界被动安全悬停区域的计算方法。针对典型的相对悬停场景,仿真分析了平面圆和三维球形禁飞区约束下临界安全悬停区域,评估了模型误差和J2摄动对悬停被动安全特性的影响。该分析方法可为具有被动安全特性的近距离悬停任务设计提供指导。
The passive safety features for spacecraft in close relative hovering with respect to circular reference orbit were analyzed by solving the minimum relative distance during the free motion with zero initial velocity. The passive safety features of spacecraft relative hovering can be described as the state of empty intersection between the relative motion trajectory and the target′s no-fly zone after the disappearance of the control force. This problem can be by transformed into the problem of minimum relative distance with zero initial velocity. The minimum relative distance varies with the initial position, and may be located in the integer period minimum value or the non-integer period minimum value point. The existence conditions of two kinds of minimum value points were analyzed. Then the calculation method of critical passive safe hovering area was obtained by solving the boundary condition in two cases. For the typical relative hovering scenario, the critical safe hovering area under the constraint of plane circle and three-dimensional spherical no-fly zone was simulated and analyzed. The effects of model error and J2 perturbation on hovering passive safety features were evaluated. This analysis method can provide consultation for hovering mission design with passive safety features.
作者
李彬
张洪波
郑伟
LI Bin;ZHANG Hongbo;ZHENG Wei(College of Aeronautics and Astronautics,National University of Defense Technology,Changsha 410073,China)
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2019年第6期1-11,共11页
Journal of National University of Defense Technology
基金
国家自然科学基金委重大项目资助项目(61690210,61690213)
关键词
航天器
悬停
被动安全特性
禁飞区
spacecraft
hovering
passive safety features
no-fly zone
