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	Optimal trajectory generation for spacecraft formation flying reconfiguration
	Chenguang Zhang ; Bin Li ; Darong Chen
	2010-05-10 ; 2010-05-10
会议名称	Proceedings of the SPIE - The International Society for Optical Engineering ; International Conference on Space Information Technology ; Wuhan, China ; INSPEC
关键词	Practical Theoretical or Mathematical/ aerospace control collision avoidance fuel optimal control Hermitian matrices interpolation nonlinear programming quadratic programming space vehicles/ fuel optimal trajectory spacecraft formation flying reconfiguration finite thrust relative dynamics model Clohessy-Wiltshire equation optimal control trajectory optimization nonlinear programming Hermite interpolation state transition matrix collision avoidance sequential quadratic programming method/ B7610 General aspects of aircraft, space vehicles and satellites B0260 Optimisation techniques B0290F Interpolation and function approximation (numerical analysis) B0290H Linear algebra (numerical analysis) C3360L Aerospace control C4140 Linear algebra (numerical analysis) C4130 Interpolation and function approximation (numerical analysis) C1180 Optimisation techniques C1330 Optimal control C3120C Spatial variables control
中文摘要	Multiple spacecraft formation flying has been identified as an enabling technology for many future space missions. In this paper, the generation of fuel optimal trajectories for spacecraft formation reconfiguration with finite thrust was investigated. The relative dynamics model of spacecraft in the formation was developed by employing the famous Clohessy-Wiltshire equations. Based on these equations, the generation of transferring trajectory for spacecraft was modeled as an optimal control problem with defined transferring time and known initial and terminal relative states. A direct method was applied to convert the trajectory optimization problem to a nonlinear programming problem. By this approach, the whole transferring trajectory was separated into several finite thrust arcs and non-thrust arcs. Then a collocation method based on Hermite interpolation was used to produce the constraints of thrust arcs, and the state transition matrix based on Clohessy-Wiltshire equations was applied to produce the constraints of non-thrust arcs. Meanwhile, to avoid collisions among spacecrafts during formation reconfiguration, an imaginary 3-dimensional sphere surrounding each spacecraft was introduced as a constraint of collision avoidance. The nonlinear programming problem was solved by sequential quadratic programming method. A numerical simulation of a formation reconfiguration with three spacecrafts was performed. The results showed that the present nonlinear programming method can be used to generate optimal trajectories for spacecrafts in the formation and the total fuel consumption of the whole formation is guaranteed.
会议录出版者	SPIE - The International Society for Optical Engineering ; USA
语种	英语 ; 英语
内容类型	会议论文
源URL	[http://hdl.handle.net/123456789/19267]
专题	清华大学
推荐引用方式 GB/T 7714	Chenguang Zhang,Bin Li,Darong Chen. Optimal trajectory generation for spacecraft formation flying reconfiguration[C]. 见:Proceedings of the SPIE - The International Society for Optical Engineering, International Conference on Space Information Technology, Wuhan, China, INSPEC.

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