Finite time coordinated formation control for spacecraft formation flying under directed communication topology

In this paper, finite-time attitude coordinated control for spacecraft formation flying (SFF) subjected to input saturation is investigated. More specifically, a bounded finite-time state feedback control law is first developed with the assumption that both attitude and angular velocity signals can be measured and transmitted between formation members. Then, a bounded finite-time output feedback controller is designed with the addition of a filter, which removes the requirement of the angular velocity measurements. In both cases, actuator saturation is explicitly taken into account, and the homogeneous system method is employed to demonstrate the finite-time stability of the closed-loop system. Numerical simulation results are presented to illustrate the efficiency of the proposed control schemes.

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Finite-Time Control for 6DOF Spacecraft Formation Flying Systems

Journal of Aerospace Engineering ◽

10.1061/(asce)as.1943-5525.0000476 ◽

2015 ◽

Vol 28 (5) ◽

pp. 04014137 ◽

Cited By ~ 8

Author(s):

Qixun Lan ◽

Jun Yang ◽

Shihua Li ◽

Haibin Sun

Keyword(s):

Finite Time ◽

Formation Flying ◽

Spacecraft Formation ◽

Spacecraft Formation Flying ◽

Time Control

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Distributed Attitude Consensus Control of Multiple Homogeneous Spacecrafts While Preserving Connectivity

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.157-158.1356 ◽

2012 ◽

Vol 157-158 ◽

pp. 1356-1360

Author(s):

Ying Chun Zhang ◽

Fan Zhang ◽

Shi Jie Zhang ◽

Wei Chao Zhong

Keyword(s):

Formation Flying ◽

Field Of View ◽

Future Research ◽

Control Law ◽

Consensus Control ◽

Spacecraft Formation ◽

Spacecraft Formation Flying ◽

Communication Topology ◽

Engineering Problems ◽

Simulation Results

In this paper, a distributed attitude consensus control law has been proposed in the context of multiple homogeneous spacecraft formation flying only through local interactions while the GPS and antenna are denied. One of the engineering problems of implementing the aforementioned spacecraft formation is that some relative measurement sensors, e.g. the camera, have limited field-of-view (FOV). It raises that the maximum relative attitude of any two neighbor spacecrafts in the formation should not be greater than the constant attitude deviation determined by the FOV of these immobile sensors during formation maneuvers and keeping. Our approach to this problem is based on the state-weight strategy for network consensus problems, which has been a little investigated in the literature. We present a leaderless distributed attitude consensus control law such that all the attitudes of the formation flying spacecrafts can globally reach consensus, and the connectivity of the interconnected commination topology is strictly preserved. Throughout this paper, the interconnected communication topology is assumed to be undirected. Simulation results demonstrate the effectiveness of the control law. The future research has been discussed in the end.

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