Robust Saturated Finite-Time Attitude Control for Spacecraft Using Integral Sliding Mode

Guo, Yong; Huang, Bing; Song, Shenmin; Li, Aijun; Wang, Changqing

doi:10.2514/1.g003520

Cited by 64 publications

(35 citation statements)

References 25 publications

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“…In this section, simulations results are presented to verify the effectiveness of the proposed controllers FxFSMC (38) and FxISMC (48) in various scenarios. The recent proposed finite-time integrate sliding mode controller (denoted by FnISMC) in [34] is used here for comparison purpose.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…The parameters of FxFSMC and FxISMC are chosen via our recommended processes in Remark 2, 3, and 6, which are given as c 1 = 0.81, c 2 = 1.45, λ 1 = 0.14, λ 2 = 0.15, λ 3 = 1.0, p = 0.8, q = 1.2 (µ 1 = µ 2 = 0.2), k 1 = 1.5, k 2 = 2, k 3 = 1, k 4 = k 5 = 2, ρ = 1, . The parameters of FnISMC in [34] are determined by trial and error until a good tracking performance is achieved, and are given as k 1 = 1, k 2 = 1, k 3 = 1.5, α 1 = 0.9. Note that the discontinuous sign function in FxFSMC [34] is approximated by the saturation function s i /(|s i | + Φ) with Φ = 0.001 to reduce inevitable chattering induced by noises.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…The parameters of FnISMC in [34] are determined by trial and error until a good tracking performance is achieved, and are given as k 1 = 1, k 2 = 1, k 3 = 1.5, α 1 = 0.9. Note that the discontinuous sign function in FxFSMC [34] is approximated by the saturation function s i /(|s i | + Φ) with Φ = 0.001 to reduce inevitable chattering induced by noises. The discontinuous terms • 0 in FxFSMC and FxISMC are directly utilized in simulation without any approximation.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…Remark 5: It is worthy mention thatṡ I = 0 is necessary in the proof, but most existing FxISMC results [27], [34] can only achieve first-order sliding mode s I = 0, andṡ I is regarded as 0. However,ṡ I = 0 can not necessarily be implied by s I = 0 directly, sinceṡ is discontinuous or nonexistent [39].…”

Section: Volume 4 2016mentioning

confidence: 99%

“…Moreover, the proposed FxISMC can realize second-order sliding modeṡ = s = 0 and provide rigorous proof of fixed-time convergence for the attitude and angular velocity tracking error. While most existing integral sliding mode controllers, such as [27], [34], can only achieve first-order sliding mode s = 0.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Continuous Fixed-Time Sliding Mode Attitude Controller Design for Rigid-Body Spacecraft

Wang

Song

2020

IEEE Access

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Fast and high-precision attitude control for the rigid spacecraft is important for its broad applications in astronautics. In this paper, we address this problem via continuous nonsingular fixed-time sliding mode control approach. At first, by improving the adding power integral technique, a nonsingular nominal attitude controller is presented to achieve fixed-time convergence of the unperturbed attitude system, which underpins the basics for design of the sliding mode motion and surfaces for the subsequent proposed main results. Then, a fixed-time full-order sliding mode controller with an explicit bound of settling time is proposed to track the desire attitude even in the presence of external disturbances. However, this controller requires the angular acceleration signals which is usually unmeasurable. To this end, an integral sliding mode controller is further presented to achieve fixed-time attitude tracking without using any acceleration information. This proposed integral sliding mode controller can realize second-order sliding mode with rigorous proof of fixed-time convergence. Both the proposed fixed time full-order and integral sliding mode controller are inherent nonsingular and chattering-free. Numerical examples are illustrated to demonstrate the effectiveness of the results given herein in practical scenarios. INDEX TERMS Attitude control, sliding mode control, fixed-time convergence.

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Section: Simulation Resultsmentioning

confidence: 99%

Section: Simulation Resultsmentioning

confidence: 99%

Section: Simulation Resultsmentioning

confidence: 99%

Section: Volume 4 2016mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Continuous Fixed-Time Sliding Mode Attitude Controller Design for Rigid-Body Spacecraft

Wang

Song

2020

IEEE Access

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Global finite‐time cooperative control for multiple manipulators using integral sliding mode control

Van

Ceglarek

2022

Asian Journal of Control

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In this paper, a global finite-time cooperative control is first time proposed for cooperative multiple manipulators. The proposed control scheme is developed based on an integration between a finite-time disturbance observer (FTDO) and a finite-time integral sliding mode controller (FTISMC) to get a high robustness against the effects of the model uncertainties and disturbances in the system.The switching term of the integral sliding mode controller is reconstructed such that the desired sliding manifold can be convergent in a finite time. The nominal controller of the integral sliding mode control is developed based on an advanced backstepping control, namely, finite-time backstepping control, which also provides a finite time convergence. The integration of the finite-time disturbance observer, finite-time switching term, and the finite-time backstepping controller forms a new global finite-time integral sliding mode control. The effectiveness of the proposed approach is demonstrated based on a cooperative control of a dual two-link manipulators.

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Predefined‐time control for Euler–Lagrange systems with model uncertainties and actuator faults

Wang

Hou

Feng

et al. 2022

Asian Journal of Control

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A novel adaptive predefined-time tracking control algorithm is proposed for the Euler-Lagrange systems (ELSs) with model uncertainties and actuator faults. Compared with traditional finite-time and fixed-time studies, the system output tracking error under the proposed predefined-time controller converges to a small neighborhood of zero in finite time, whose upper bound is exactly a design parameter in the control algorithm. For the uncertain model, radial-based function neural network (RBFNN) is utilized to approximate the continuous uncertain dynamics. To deal with the actuator faults, an adaptive control law is involved in the fault-tolerant controller. In order to achieve the predefined-time bounded, a novel predefined-time sliding mode surface is designed. It is proved that the tracking error vector trajectory of closed-loop system is semi-globally uniformly ultimately predefined-time bounded, and the upper bounds of both the system settling time and the corresponding output tracking error can be adjusted with a simple parameter. Simulation examples finally demonstrate the effectiveness of the proposed control algorithm.

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Robust Saturated Finite-Time Attitude Control for Spacecraft Using Integral Sliding Mode

Cited by 64 publications

References 25 publications

Continuous Fixed-Time Sliding Mode Attitude Controller Design for Rigid-Body Spacecraft

Continuous Fixed-Time Sliding Mode Attitude Controller Design for Rigid-Body Spacecraft

Global finite‐time cooperative control for multiple manipulators using integral sliding mode control

Predefined‐time control for Euler–Lagrange systems with model uncertainties and actuator faults

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