Integral-Type Sliding Mode Fault-Tolerant Control for Attitude Stabilization of Spacecraft

Shen, Qiang; Wang, Danwei; Zhu, Senqiang; Poh, Eng Kee

doi:10.1109/tcst.2014.2354260

Cited by 210 publications

(161 citation statements)

References 38 publications

Supporting

Mentioning

160

Contrasting

Order By: Relevance

“…LEMMA 5 [48]. Given the parameter adaptive law in (34a)-(34c), the parameters γ i , as well as their estimateŝ γ i , have upper bounds; i.e., there always exist positive scalarsγ i such thatγ i ≤γ i and γ i ≤γ i for all t > 0, respectively.…”

Section: B Adaptive Finite-time Fault-tolerant Controller Designmentioning

confidence: 99%

Finite-time fault-tolerant attitude stabilization for spacecraft with actuator saturation

Shen

Wang

Zhu

et al. 2015

IEEE Trans. Aerosp. Electron. Syst.

Self Cite

174

View full text Add to dashboard Cite

This paper addresses the finite-time fault-tolerant attitude stabilization control problem for a rigid spacecraft in the presence of actuator faults or failures, external disturbances, and modeling uncertainties. First, a basic fault-tolerant controller is proposed to accommodate actuator faults or failures and guarantee local finite-time stability. When there is no a priori knowledge of actuator faults, disturbances, and inertia uncertainties, an online adaptive law is proposed to estimate the bounds of these uncertainties, and local finite-time convergence is achieved by an adaptive fault-tolerant controller. In addition, another adaptive fault-tolerant control scheme is derived that explicitly takes into account the actuator saturation. The proposed attitude controller provides fault-tolerant capability despite control input saturation and ensures that attitude and angular velocity converge to a neighborhood of the origin in finite time. Finally, simulation studies are presented to demonstrate the effectiveness of the proposed method.

show abstract

Section: B Adaptive Finite-time Fault-tolerant Controller Designmentioning

confidence: 99%

Finite-time fault-tolerant attitude stabilization for spacecraft with actuator saturation

Shen

Wang

Zhu

et al. 2015

IEEE Trans. Aerosp. Electron. Syst.

Self Cite

174

View full text Add to dashboard Cite

show abstract

“…In the representation of (26), g(σ ) is a similar scalar defined by (19) by replacing ρ with σ . This completes the proof.…”

Section: Stability Analysismentioning

confidence: 99%

Unified saturated proportional derivative control framework for asymptotic stabilisation of spacecraft

Chen

2016

IET Control Theory & Applications

View full text Add to dashboard Cite

In this study, the authors propose a unified approach to saturated proportional derivative (SPD) controller design for asymptotic attitude stabilisation of spacecraft subject to actuator constraints. It is shown that a class of simple and high computation efficient SPD controller can ensure asymptotic stabilisation of spacecraft with actuator constraints. The proposed SPD controller utilises the general saturation function, and thus provides a unified framework for asymptotic stable control design of spacecraft subject to actuator constraints. Advantages of the proposed design framework include the intuitive structure, high computation efficiency, easy implementation and asymptotic stabilisation with the ability to ensure that actuator constraints are not violated. This is accomplished by selecting control gains a priori. Two examples are presented to demonstrate the effectiveness and the improved performance of the proposed approach. IntroductionStabilisation of spacecraft is quickly developing in the last few decades and much progress has been achieved. Several control schemes that stabilise the attitude of spacecraft can be found in the literature. Specifically, in [1], passivity between the angular velocity vector and the Euler parameter vector of a spacecraft is established and an adaptive control is proposed. Some interesting passivity velocity-free controllers are developed in [2]. Tsiotras [3] extend this passivity result. For progress on attitude stabilisation of spacecraft by using the unit-quaternion and angular velocity in the feedback control law, see [4][5][6][7] and the references within. In [8][9][10][11], various optimal attitude stabilisation control schemes have been proposed. The effort that stabilises the spacecraft with disturbance can be found in [12][13][14], and the references within. Recently, some interesting finite-time stable controllers for attitude stabilisation of spacecraft have been proposed [15][16][17]. Fault-tolerant stabilisation result of spacecraft can be found in [18,19]. A minor drawback that remains for these controls is the spacecraft actuators are assumed to be able to provide any requested torque. This assumption can lead to difficulties in practice since the torque amplitude is limited in actual spacecraft. It is known that control system design approaches that do not incorporate input constraints directly into the design may result in degraded or unpredictable motion and thermal or mechanical failure, if the controller commands more torque than the actuators can supply from the control [20][21][22].Taking into account actuator constraints, several effective schemes have been proposed for attitude stabilisation of spacecraft. In particular, Tsiotras and Luo [23] construct a saturation control law for an underactuated spacecraft, by using a non-standard attitude representation and decomposing the general motion into two rotations. Boskovic et al. [24] develop two robust saturated sliding mode controllers for asymptotic stabilisation of uncertain spacecraft. Wallsgrove...

show abstract

“…Sliding mode control has attracted extensive attention owing to its robustness with respect to external disturbances and model uncertainties. This control method has been applied to attitude stabilization of spacecraft in [9,10].…”

Section: Introductionmentioning

confidence: 99%

Output Feedback Control for Asymptotic Stabilization of Spacecraft with Input Saturation

Pukdeboon

2017

Journal of Control Science and Engineering

View full text Add to dashboard Cite

This paper investigates the attitude stabilization problem of rigid spacecraft subject to actuator constraints, external disturbances, and attitude measurements only. An output feedback control framework with input saturation is proposed to solve this problem. The general saturation function is utilized in the proposed controller design and a unified control method is developed for the asymptotic stabilization of rigid spacecraft without velocity measurements. Asymptotic stability is proven by Lyapunov stability theory. Moreover, a new nonlinear disturbance observer is designed to compensate for external disturbances. Then, a composite controller is presented by combining a unified saturated output feedback control with a nonlinear disturbance observer. Desirable features of the proposed control scheme include the intuitive structure, robustness against external disturbances, avoidance of model information and velocity measurements, and ability to ensure that the actuator constraints are not violated. Finally, numerical simulations have been carried out to verify the effectiveness of the proposed control method.

show abstract

Integral-Type Sliding Mode Fault-Tolerant Control for Attitude Stabilization of Spacecraft

Cited by 210 publications

References 38 publications

Finite-time fault-tolerant attitude stabilization for spacecraft with actuator saturation

Finite-time fault-tolerant attitude stabilization for spacecraft with actuator saturation

Unified saturated proportional derivative control framework for asymptotic stabilisation of spacecraft

Output Feedback Control for Asymptotic Stabilization of Spacecraft with Input Saturation

Contact Info

Product

Resources

About