Control of orientation for spacecraft formations in the vicinity of the Sun-Earth L2 libration point

Qi, Rui; Xu, Shijie; Chen, Tong

doi:10.1007/s11433-014-5398-0

Cited by 4 publications

(4 citation statements)

References 11 publications

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“…The motion of the controlled follower spacecraft can be described by the nonlinear equations shown in (1-3) obviously. However, it is noted that the scale of Halo orbits is 10 5 km [7,[18][19][20]26] while the mutual distance of the leader spacecraft and follower spacecraft may be chosen on the order of several kilometers [26]. As a result, the scale of mutual distance between the leader and follower spacecrafts is much smaller than the scale of the Halo orbit, and then, the linearization techniques can be implemented.…”

Section: Dynamical Model Of Spacecraftmentioning

confidence: 99%

“…On the other hand, we are mainly interested in the relative positions of follower spacecrafts with respect to the leader spacecraft. Thus, for the sake of the simplicity of derivation and saving computational consumption, linearized equations of relative motion between the leader and follower spacecraft adopted by many studies [19,20,26] will also be utilized in this paper.…”

Section: Dynamical Model Of Spacecraftmentioning

confidence: 99%

“…Libration points, which represent a series of five points where the gravitational and centrifugal forces are in balance in the circular restricted three-body problem (CR3BP), are ideal choice for settling space stations, a set of interferometer space telescopes and midway refueling space stations for large missions [8,9]. Thus, potential applications involved formation flights near the vicinity of the libration points have attracted great interest in formation control strategies in a multibody regime [10][11][12][13][14][15][16][17][18][19][20][21].…”

Section: Introductionmentioning

confidence: 99%

“…An impulsive controller was developed to keep the chief on the desired Halo orbit while a nonlinear adaptive control scheme based on nonzero set-point LQR and neural network was applied to the deputy to form a desired relative position. Recently, Qi et al [19,20] studied the use of impulsive control to maintain formation flight in the circular restricted three-body problem. Héritier and Howell [21] explored the natural dynamics in a multibody regime for formation flying applications.…”

Section: Introductionmentioning

confidence: 99%

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Optimal control of loose spacecraft formations near libration points with collision avoidance

Peng

Zhong

2015

Nonlinear Dyn

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This paper investigates the optimal control of loose leader-following spacecraft formations near libration points. The formation reconfigurations and keepings can be applied at the same time for the loose formations. A loose sphere leader-following formation, i.e., the leader spacecraft moves along the reference Halo orbits while the motions of all follower spacecrafts are restricted to a sphere formation with its center located at the leader, is explored in this study carefully. Collision avoidances among follower spacecrafts are taken into consideration since there are no constraints between followers and then the formation for all followers is loose. A symplectic penalty iteration algorithm is proposed to obtain the optimal solutions with minimization of energy cost. An effective penalty function to avoid collision is developed, and a high efficiency and structure-preserving symplectic method is introduced in the iteration algorithm. Several optimal control problems including formation reconfigurations and formation keepings are solved to show the effectiveness of the proposed algorithm. Numerical results show that errors of formations can be reduced to millimeters or smaller only by few control input and the collision can be avoided successfully by the developed penalty function.

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