Fault-Tolerant Tracking Control of Spacecraft with Attitude-Only Measurement Under Actuator Failures

Two finite-time control algorithms are developed for distributed cooperative attitude synchronisation of multiple spacecraft with a dynamic virtual leader. Each spacecraft is modelled as a rigid body incorporating with model uncertainty and unknown external disturbance. The virtual leader gives commands to some of the follower spacecraft, and the communication network between followers can be an undirected or a directed graph. By using two neighbourhood synchronisation error signals, a finite-time control algorithm is designed associated with adaptive mechanism such that all follower spacecraft synchronise to the virtual leader in finite time. Then a novel estimator-based finite-time distributed cooperative control algorithm is developed by using the followers' estimates of the virtual leader, and the convergence of the attitude and angular velocity errors can be guaranteed in finite time. Moreover, both of the control strategies are chattering-free for their continuous design. Simulation examples are illustrated to demonstrate the validity of the two algorithms. IntroductionResearch on attitude control of spacecraft, especially attitude synchronisation among multiple spacecraft, has long been of interest in recent years because of the theoretical significance and broad applications [1][2][3][4][5][6][7][8][9][10][11][12]. For instance, in deep space exploration, a coordinated cluster of micro-satellites can replace the traditional large and expensive spacecraft to complete a common task, and such schemes can offer the superiorities of low cost, high flexibility, high impact and so on. Besides that, the requirement of keeping the precise relative attitude is essential in inter-spacecraft laser communication operation. This study can also be applied to formation manoeuvres in interferometry application, stereo imaging, passive radiometry, terrain mapping and so on [8,13]. Some solutions about attitude control problem for multiple spacecraft can be found in [7,[14][15][16][17][18]. However, they did not consider the model uncertainties or unknown disturbances. A virtual systems-based control algorithm was proposed for the attitude synchronisation problem in [7] without using the angular velocity measurements, it provided a new approach to address the timevarying communication delays and angular velocity unavailable together. A formation flying control problem of multiple spacecraft was studied in [16] by using a novel fast terminal sliding manifold (FTSM) and adaptive control, and a distributed attitude coordination control scheme was developed with a constraint about the initial condition to achieve finite time convergence. Similar to [16,17] also relied on a constraint about the initial condition and proposed a distributed output feedback attitude coordination control algorithm for spacecraft formation flying without using the angular velocities. A leader-following consensus problem was investigated in [18] for multiple rigid spacecraft, by applying a non-linear distributed observer, a distributed control scheme ...

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“…The following fundamental properties [9,[25][26][27][28] and assumptions regarding system (3) are summarised for the further analysis.…”

Section: Attitude Kinematics and Dynamics Of Rigid Spacecraftmentioning

confidence: 99%

Distributed cooperative control design for finite‐time attitude synchronisation of rigid spacecraft

Zhou

Xia

et al. 2015

IET Control Theory & Applications

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“…The fuzzy adaptive observer (19) is introduced for the unmeasured states estimation but not the fault information estimation, which is more similar to the results in [40]. In another research front, the fault estimation methods have also been investigated (see [41]).…”

Section: A Fuzzy State Observer Designmentioning

confidence: 99%

“…The attitude control laws were shown in [1], [32], and [42] for relevant spacecrafts with input constraints. In [40], the attitude-tracking control scheme was proposed for the rigid body, and this scheme considered actuator faults and actuator saturation simultaneously. In [43], an adaptive dynamic surface control in the presence of input nonlinearity was proposed.…”

mentioning

confidence: 99%

Fuzzy Adaptive Fault-Tolerant Output Feedback Attitude-Tracking Control of Rigid Spacecraft

Huo

Xia

Yin

et al. 2017

IEEE Trans. Syst. Man Cybern, Syst.

102

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This paper proposes a stable adaptive fuzzy faulttolerant attitude-tracking controller for a rigid spacecraft in the presence of unavailable velocities, external disturbance, actuator faults, and actuator saturation. Fuzzy logic systems are applied to approximate the unknown nonlinear function vector, and a fuzzy adaptive observer is designed to estimate the unmeasured velocity of the rigid body. By using the backstepping technique, a novel adaptive fuzzy attitude-tracking fault-tolerant control scheme is developed. It has been testified that this control approach guarantees that all signals of the rigid spacecraft are bounded and the tracking error between the system output and the reference signal converges to a small neighborhood of zero. Simulation examples with constant faults and time-variant faults are provided to show the fault-tolerant effectiveness of the control method.Index Terms-Actuator faults, actuator saturation, adaptive fuzzy control, attitude tracking, fault-tolerant control (FTC).

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“…Various nonlinear control algorithms have been purposed to improve the closed-loop system performance in these unwanted situations (see, for instance [8,9,11,14,[17][18][19]30,[46][47][48]). Time delay is one of the other salient features whose frequently encountered co-presences in many practical systems can lead to severe performance limitations, or even causes the instability of closed-loop systems.…”

Section: Introductionmentioning

confidence: 99%

Global attitude stabilization of rigid spacecraft with unknown input delay

et al. 2015

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Global attitude stabilization of a rigid spacecraft with unknown actuator delay time is an important problem that has rarely been studied. In this paper, first we investigate a Lyapunov-based controller for attitude regulation of a rigid spacecraft with delayed inputs. Simple conditions for global asymptotical stability are obtained by assuming that the true delay value is unknown, but approximation of its upper bound is available. It is also shown that a proper design of the controller prevents the unwinding phenomenon. Then, we extend the results for the system while taking disturbance effects into account. Based on LyapunovKrasovskii methodology, it is proven that the proposed controller can drive the closed-loop trajectories to a small region in the neighborhood of the origin in the presence of external disturbances and model uncertainties. Various numerical simulations are carried out to illustrate the effectiveness of the proposed control system.

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Fault-Tolerant Tracking Control of Spacecraft with Attitude-Only Measurement Under Actuator Failures

Cited by 134 publications

References 50 publications

Distributed cooperative control design for finite‐time attitude synchronisation of rigid spacecraft

Distributed cooperative control design for finite‐time attitude synchronisation of rigid spacecraft

Fuzzy Adaptive Fault-Tolerant Output Feedback Attitude-Tracking Control of Rigid Spacecraft

Global attitude stabilization of rigid spacecraft with unknown input delay

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