Spacecraft attitude fault-tolerant control based on iterative learning observer and control allocation

Hu, Qinglei; Niu, Guanglin; Wang, Chenliang

doi:10.1016/j.ast.2017.12.031

Cited by 92 publications

(43 citation statements)

References 20 publications

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“…The reliability of a spacecraft system mainly depends on its fault tolerability. Among existing fault‐tolerant schemes, actuator failures are particularly emphasized (see References , , , , to name a few) and various techniques are developed to design the fault‐tolerant controllers for spacecraft systems such that the degradation caused by actuator failures can be compensated. In this work, the attitude‐tracking control of spacecraft with actuator fault is further studied.…”

Section: Resultsmentioning

confidence: 99%

“…Remark 2. The sliding surface (13) avoids singularity compared with those in References 25 and 26, offers faster convergence rate compared with Reference 27, and is not constrained by error variables compared with Reference 28. Considering the spacecraft system (9), (10), the time derivative of FNTSM surface (13) can be obtained…”

Section: Construction Of Fntsm Surfacementioning

confidence: 99%

“…(30). Consider the spacecraft system (9) and (10) with the sliding surface (13), if the condition S = S = 0 is met, then {e v (t) ≡ 0, e 4 (t) ≡ 1, Ω e (t) ≡ 0} can be reached in finite time.…”

Section: Lemma 4 (34) Lagrange Mean Value Lemma: Suppose  Is a Funmentioning

confidence: 99%

“…A review on recent development of FTC schemes for spacecraft attitude tracking was provided in Reference , in which most of the active and passive fault‐tolerant techniques have been covered. In addition, some other advanced approaches for tackling actuator failures of spacecraft are developed, such as multiple‐model adaptive control against sign errors of actuator response, iterative learning observer‐based control allocation, uncertainty decomposition‐based FTC, to name a few. However, most of the attitude controllers mentioned above are asymptotically convergent, which means that the fastest convergence rate is in exponential form with infinite settling time, that is, the attitude and angular velocity of rigid spacecraft cannot be guaranteed to converge into equilibrium in finite time.…”

Section: Introductionmentioning

confidence: 99%

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Finite‐time attitude‐tracking control for rigid spacecraft with actuator failures and saturation constraints

Gao

Jing

et al. 2019

Intl J Robust & Nonlinear

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Summary In this article, the problem of finite‐time attitude‐tracking control for rigid spacecraft is addressed. Uncertainties caused by external disturbances, unknown inertial matrix, actuator failures, and saturation constraints are tackled simultaneously. First, a smooth function that is more qualified to approximate the standard saturation characteristics is presented to deal with the actuator saturation constraints. Second, a fast nonsingular terminal sliding mode (FNTSM) manifold is constructed as a foundation of controllers design. By incorporating the fuzzy logic system into FNTSM technique, a less demanding solution of coping with model uncertainties is provided because the requirement of a prior knowledge of unknown inertial parameters and external disturbances in many existing achievements is removed. To reduce the number of parameters to be estimated, the norm approximation approach is exploited. Subsequently, an antichattering attitude controller is presented such that all the tracking errors converge into arbitrary small domains around the origin in finite time. The result is further extended to obtain a fault‐tolerant controller against completely failed actuators. Finally, numerical simulation is conducted to verify the effectiveness of the proposed control scheme and comparison with relevant literature demonstrates its high performance. Furthermore, an experiment for the large satellite Hubble Space Telescope is carried out to validate the practical feasibility.

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Section: Resultsmentioning

confidence: 99%

Section: Construction Of Fntsm Surfacementioning

confidence: 99%

Section: Lemma 4 (34) Lagrange Mean Value Lemma: Suppose  Is a Funmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Finite‐time attitude‐tracking control for rigid spacecraft with actuator failures and saturation constraints

Gao

Jing

et al. 2019

Intl J Robust & Nonlinear

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“…Therefore, the actuators were switched in the order of RCS only, RCS and AS controlled together, and AS only [2]. In order to maintain the stable and accurate attitude control, the control allocation algorithm of RCS and AS should be studied [3,4].…”

Section: Introductionmentioning

confidence: 99%

RCS and Aero Surfaces Control Allocation Research on RLV’s Re-Entry Phase

Zhang

Ping

et al. 2019

Applied Sciences

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Based on the characteristics of aero surfaces and reaction control system (RCS), a control allocation scheme is needed to specify aero surface deflections and RCS thruster’s firing commands, during the re-entry phase of reusable launch vehicle (RLV). To analyze the control performance differences introduced by different allocation algorithms, this paper presents a proportional allocation scheme based on dynamic pressure, a daisy-chaining allocation scheme based on the control error, and a multi-object-based optimal allocation scheme, to deal with the allocation problem of RCS and aero surfaces. The first allocation scheme is the simplest, and the second one is more complicated, when considering the actuators’ physical constraints in the allocation problem. The third scheme not only takes the physical constraints into account, but also the rate constraints, and other constraints of RCS and aero surfaces, while for the objective optimization function, not like the single-object function of the other two schemes, it combines the allocation error minimization, fuel consumption minimization, and other functions, with the adaptive weight values. After the stability analysis, the feasibility of the aforementioned allocation schemes are verified by the simulation, and the contrastive analysis of their control performances are followed.

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Fault diagnosis for semilinear distributed parameter systems with actuator/sensor based on iterative learning control

Zhang

Cui

Dai

2020

Asian Journal of Control

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This paper focuses on the fault diagnosis problem for a class of semilinear distributed parameter systems with actuator and sensor. To diagnose the actual fault, a fault estimator is designed by using an introduced virtual fault for this system. Based on the semigroup theory and λ-norm, the residual signal is used in the PD-type iterative learning control scheme to regulate the introduced virtual fault, making the virtual fault track the practical fault. Then, the goal of fault diagnosis is obtained. Finally, the effectiveness of the proposed method is tested on a Fisher equation and applied to a class of typical chemical industry processes.

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Spacecraft attitude fault-tolerant control based on iterative learning observer and control allocation

Cited by 92 publications

References 20 publications

Finite‐time attitude‐tracking control for rigid spacecraft with actuator failures and saturation constraints

Finite‐time attitude‐tracking control for rigid spacecraft with actuator failures and saturation constraints

RCS and Aero Surfaces Control Allocation Research on RLV’s Re-Entry Phase

Fault diagnosis for semilinear distributed parameter systems with actuator/sensor based on iterative learning control

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