Appointed-time fault-tolerant attitude tracking control of spacecraft with double-level guaranteed performance bounds

Liu, Mingmin; Shao, Xiaodong; Ma, Guangfu

doi:10.1016/j.ast.2019.06.017

Cited by 67 publications

(29 citation statements)

References 30 publications

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“…Remark 1: The meanings and the effects of the parameters in the appointed-time decaying function ρ y (t) are discussed here [48]- [58]. First, the parameters t 0 is the activation time of the constraint (6), meaning that from the time t 0 , the variable y(t) should meet the constraint (6) (that is, y(t 0 ) < ρ y (t 0 )).…”

Section: Appointed-time Performance Function and Error Transformationmentioning

confidence: 99%

“…Recently, the prescribed performance control method [48]- [50] has been proposed, where the prescribed performance control problem of the original control system is converted into the stabilization problem of an unconstrained nonlinear control system. Then several quaternion-based and MRPs-based prescribed performance attitude control schemes are designed [51]- [58]. In [59], a velocity-free prescribed-time attitude synchronization control scheme is derived on SO(3).…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Constrained Attitude Control of Uncertain Spacecraft With Appointed-Time Control Performance

Jia

et al. 2023

IEEE Trans. Syst. Man Cybern, Syst.

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Section: Appointed-time Performance Function and Error Transformationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Constrained Attitude Control of Uncertain Spacecraft With Appointed-Time Control Performance

Jia

et al. 2023

IEEE Trans. Syst. Man Cybern, Syst.

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“… T 1 is the upper bound of convergence time. Based on equation (4), one can obtain lim t → T 1 ϱ 3 ( t ) = ϱ 3 ∞ with the detailed proof given in Wei et al 74 To achieve finite-time convergence, as an alternative, Liu et al 75 constructed a novel appointed-time convergence performance function via using a quartic polynomial, which is omitted for brevity. Thus, compared with the foregoing exponential and hyperbolic cotangent performance functions, the convergence rate of ϱ 3 ( t ) is much faster.…”

Section: Ppcmentioning

confidence: 99%

An overview of prescribed performance control and its application to spacecraft attitude system

Wei

Chen

Liu

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part I:

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High-quality control method is of great importance for the attitude determination and maneuvering of spacecraft in the on-orbit servicing technology. Prescribed performance control methodology, as a potential way, has gained considerable attention due to its quantitative description for the transient and steady-state control performance in recent years. Thus, this article constructs a survey for the prescribed performance control methodology along with the detailed analysis of the attitude control methods in the existing reported works. Then, the basic structure of prescribed performance control methodology is discussed in theory, and application to the attitude control of postcapture spacecraft works as an example to further explain the procedure of prescribed performance control methodology. Finally, with consideration of some vital aerospace applications, potential open issues of the prescribed performance control methodology are analyzed.

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“…Actuator faults also occur frequently during the space operations due to the harsh working environment and may result in a series of hazardous results. This problem motivates fault-tolerant control design for spacecraft attitude maneuvers (Li et al , 2019; Liu et al , 2019), which usually requires reliability and guaranteed performance (Fan et al , 2017; Zhang et al , 2020; Sun et al , 2020). Furthermore, actuator saturation is another practically key issue (2018; Jia et al , 2019), which may degrade the closed-loop performance or even give rise to instability and has attracted enormous research effort (Shen et al , 2015a, 2015b; Lu et al , 2016; Lian et al , 2018).…”

Section: Introductionmentioning

confidence: 99%

Robust fault-tolerant attitude control of spacecraft using hybrid actuators

2021

AEAT

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Purpose This paper aims to address the spacecraft attitude control problem using hybrid actuators in the presence of actuator saturation, uncertainties and faults, inertia uncertainties and external disturbances. Design/methodology/approach A hybrid actuator configuration is used where thrusters are engaged for rapid attitude maneuvers, while reaction wheels (RWs) are used for fine pointing. Findings The key advantages are two-fold: a finite-time high-level controller is designed to produce the three-axis virtual control torques; an online robust control allocation (RobCA) scheme is proposed to redistribute virtual control signals to the actuators with taking into account the actuator saturation, uncertainties and faults; and the RobCA scheme allows a smooth switch between thrusters and RWs, which handles the inaccuracy problem of thrusters and saturation problem of RWs. Practical implications An online RobCA algorithm is designed that maps the total control demands onto individual actuator settings and allows a smooth switch between thrusters and RWs. Simulation results show the effectiveness of the proposed control strategy. Originality/value This work may be used on modern space missions, which impose higher requirements on smooth switching of spacecraft thrusters and RWs.

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Appointed-time fault-tolerant attitude tracking control of spacecraft with double-level guaranteed performance bounds

Cited by 67 publications

References 30 publications

Constrained Attitude Control of Uncertain Spacecraft With Appointed-Time Control Performance

Constrained Attitude Control of Uncertain Spacecraft With Appointed-Time Control Performance

An overview of prescribed performance control and its application to spacecraft attitude system

Robust fault-tolerant attitude control of spacecraft using hybrid actuators

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