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定制化保持环约束下控制量优化算法设计
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作者 王露莎 杨国昌 +1 位作者 曾光 薛永泰 《航天控制》 CSCD 2024年第5期62-68,共7页
针对大数量卫星轨迹保持控制策略自动快速计算的需求,开展了定制化保持环指标下卫星轨道控制量计算优化设计研究。在分析回归轨道特性基础上,优化了轨迹网预报参考基准计算方法,以历史精密星历构造伪观测数据,计算平均大气阻尼系数,将... 针对大数量卫星轨迹保持控制策略自动快速计算的需求,开展了定制化保持环指标下卫星轨道控制量计算优化设计研究。在分析回归轨道特性基础上,优化了轨迹网预报参考基准计算方法,以历史精密星历构造伪观测数据,计算平均大气阻尼系数,将其作为轨迹网精密预报模型的输入,设计基于迭代修正的轨道控制量自动计算方法,通过合理选择初值、调控控制量粗筛区间,设置迭代终止门限,加快搜索速度。仿真结果表明,该方法能够快速完成卫星轨迹环到达指定西边界的控制量自动计算,为后续大数量卫星例行轨控策略高效自动计算提供理论支撑。 展开更多
关键词 定制化 保持环 轨道控制量
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On Applications of Selenodesy to Lunar Detection 被引量:1
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作者 WEI Erhu LIU Jingnan 《Geo-Spatial Information Science》 2006年第3期162-170,共9页
According to the history of lunar detection, the relationship between selenodesy and lunar detection is reviewed , and the focus of the lunar detection and the lunar detection plan of China are summarized. The key tec... According to the history of lunar detection, the relationship between selenodesy and lunar detection is reviewed , and the focus of the lunar detection and the lunar detection plan of China are summarized. The key techniques of selenodesy are presented, and the applications of selenodesy to the lunar detection are discussed. 展开更多
关键词 selenodesy lunar detection lunar orbit lunar gravity field lunar reference frame lunar control network lunar topography
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On all-propulsion design of integrated orbit and attitude control for inner-formation gravity field measurement satellite 被引量:2
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作者 JI Li LIU Kun XIANG JunHua 《Science China(Technological Sciences)》 SCIE EI CAS 2011年第12期3233-3242,共10页
The inner-formation gravity field measurement satellite (IFS) is a novel pure gravitational orbiter. It aims to measure the Earth's gravity field with unprecedented accuracy and spatial resolution by means of preci... The inner-formation gravity field measurement satellite (IFS) is a novel pure gravitational orbiter. It aims to measure the Earth's gravity field with unprecedented accuracy and spatial resolution by means of precise orbit determination (POD) and relative state measurement. One of the key factors determining the measurement level is the outer-satellite control used for keeping the inner-satellite flying in a pure gravitational orbit stably. In this paper the integrated orbit and attitude control of IFS during steady-state phase was investigated using only thrusters. A six degree-of-freedom translational and rotational dynamics model was constructed considering nonlinearity resulted from quaternion expression and coupling induced by community thrusters. A feasible quadratic optimization model was established for the integrated orbit and attitude control using con- strained nonlinear model predictive control (CNMPC) techniques. Simulation experiment demonstrated that the presented CNMPC aigorithm can achieve rapid calculation and overcome the non-convexity of partial constraints. The thruster layout is rational with low thrust consumption, and the mission requirements of IFS are fully satisfied. 展开更多
关键词 gravity field measurement satellite inner-formation integrated orbit and attitude control model predictive techniques
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