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		题名	作者	年代	出处	被引量
	1	Analytic Initial Relative Orbit Solution for Angles-Only Space Rendezvous Using Hybrid Dynamics Method显示文摘A closed-form solution to the angles-only initial relative orbit determination(IROD)problem for space rendezvous with non-cooperated target is developed,where a method of hybrid dynamics with the concept of virtual formation is introduced to analytically solve the problem.Emphasis is placed on developing the solution based on hybrid dynamics(i.e.,Clohessy-Wiltshire equations and two-body dynamics),obtaining formation geometries that produce relative orbit state observability,and deriving the approximate analytic error covariance for the IROD solution.A standard Monte Carlo simulation system based on two-body dynamics is used to verify the feasibility and evaluate the performance proposed algorithms.The sensitivity of the solution accuracy to the formation geometry,observation numbers is presented and discussed.	Baichun Gong Shuang Li Lili Zheng Jinglang Feng	2020	Computer Modeling in Engineering & Sciences2020，，1：	2
	2	Hybrid method for accurate multi-gravity-assist trajectory design using pseudostate theory and deep neural networks显示文摘This paper presents a novel hybrid method to design the continuous and accurate multi-gravity-assist trajectory for a high-fidelity dynamics.The gravitational perturbation of the primary body is considered during the gravity assistance.The pseudostate technique is applied to approximate the gravity-assisted trajectory,where the optimal sweepback duration is solved using a trained deep neural network.The major factors that affect the optimal sweepback duration of the approach and departure segments are investigated.The results show that the optimal sweepback duration of the approach segment only relies on the shape of the approach trajectory and is independent of the flight time.Then,a gravity-assisted trajectory patched strategy and a hybrid algorithm combining the particle swarm optimization and the sequential quadratic programming are developed to optimize the multi-gravity-assist trajectory.The proposed hybrid method is applied to the Europa orbiter mission.In comparison with the traditional patched conic method,this method demonstrates outstanding performance on accuracy and significantly reduces the computational time and complexity of the trajectory correction with the high-fidelity dynamics.	YANG Bin FENG JingLang HUANG XuXing LI Shuang	2022	Science China(Technological Sciences)2022，65，3：	1

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