Attitude stabilization of flexible spacecraft under limited communication with reinforced robustness

Amrr, Syed Muhammad; Nabi, M.

doi:10.1177/0142331219860651

Cited by 24 publications

(16 citation statements)

References 38 publications

(66 reference statements)

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“…where η max(c 2 ξ 2 |x 2 | ξ 2 −1 ) ≥ 0, which is a lumped value. Now, using completing the square technique (Amrr and Nabi, 2019) by introducing a constant κ such that 0 < κ < α 1 . Further, adding and subtracting a term (η T) 2 4κ in (89) as…”

Section: Controller Design and Stability Analysismentioning

confidence: 99%

Speed control of a wind turbine–driven doubly fed induction generator using sliding mode technique with practical finite‐time stability

2022

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This work investigates the application of sliding mode control (SMC) on a doubly fed induction generator (DFIG). In conventional control schemes like PI controllers, the responses are relatively slow, and the transient state is often subjected to sustained oscillation. Further, the PI control achieves lesser invariance behavior against system uncertainties, and the selection of its gain parameters is a skillful task. In contrast, the SMC is well-known for its faster convergence, robustness, and better transient and steady-state behavior. In this study, the nonsingular fast terminal sliding mode control (NSFTSMC) is applied in the speed loop of the rotor side vector control of DFIG. The proposed NSFTSMC scheme results in less speed fluctuation with a change in wind speed, which is maintained by controlling the torque component of the current (iq*). This paper also presents detailed modeling of the DFIG, power converters, and the related control schemes. Moreover, stability analysis of the proposed methodology ensures the practical finite time stability of the overall system. The comparative controller performance and validation are carried out in Matlab/Simulink environment. The proposed control strategy presents much better results than conventional PI-based control.

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Section: Controller Design and Stability Analysismentioning

confidence: 99%

Speed control of a wind turbine–driven doubly fed induction generator using sliding mode technique with practical finite‐time stability

2022

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“…Consequently, the controller consumes more time and energy for regulating the spacecraft to the farthest equilibrium point. This is called the unwinding phenomenon, where the spacecraft selects a longer maneuvering path 5,38 …”

Section: Mathematical Modelmentioning

confidence: 99%

Fault‐tolerant finite‐time adaptive higher order sliding mode control with optimized parameters for attitude stabilization of spacecraft

Amrr

Sarkar

Banerjee

et al. 2021

Intl J Robust & Nonlinear

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This article considers the problem of attitude regulation of rigid spacecraft under the effect of inertial ambiguity, exogenous disturbances, input saturation, and actuator uncertainties. In this regard, an adaptive second‐order sliding mode control (ASOSMC) is designed to provide robustness against the lumped disturbances (the combination of uncertainties and faults). The ASOSMC presents a two‐fold advantage over conventional SMC. The use of adaptive law eliminates the assumption of a priori knowledge on the upper bounds of the disturbances. Further, the SOSMC methodology alleviates the high‐frequency chattering in the input without compromising robustness. The theoretical analysis under the proposed strategy guarantees the convergence of sliding surface and system states to the origin in a finite‐time. Besides, this work also resolves the inbuilt problem of unwinding in the quaternion‐based attitude representation. Further, the nominal parameters of the proposed control law are optimized offline using an ant lion optimization method. The numerical simulation validates the effectiveness of the proposed controller by comparing its performance with the other existing controllers.

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“…Thus, the spacecraft will save time and energy by choosing the shorter maneuvering path. 29 The attitude tracking dynamics is defined as 27…”

Section: Kinematics and Dynamics Of Attitude Trackingmentioning

confidence: 99%

A fault-tolerant attitude tracking control of spacecraft using an anti-unwinding robust nonlinear disturbance observer

Amrr

Nabi

Tiwari

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper investigates the application of an integral sliding mode control with a robust nonlinear disturbance observer to obtain an anti-unwinding spacecraft attitude tracking response with robustness against external disturbances, inertia matrix uncertainties, and actuator faults. In the controller design, external disturbances, uncertainties, and actuator faults are lumped together and estimated by the robust nonlinear disturbance observer. The proposed robust nonlinear disturbance observer guarantees the convergence of estimated lumped disturbance error to origin in finite time. The estimated disturbance is then used in the controller as a feed-forward compensator. Further, an adaptive law is also incorporated in the proposed controller to ensure additional robustness. The stability of the overall system and anti-unwinding characteristic are proved using the Lyapunov stability theory. Finally, numerical simulation analysis is performed in the presence of all the sources of lumped disturbances. It is observed that the proposed control strategy is ensuring higher accuracy, good steady-state precision, and eliminates the unwinding phenomenon.

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Attitude stabilization of flexible spacecraft under limited communication with reinforced robustness

Cited by 24 publications

References 38 publications

Speed control of a wind turbine–driven doubly fed induction generator using sliding mode technique with practical finite‐time stability

Speed control of a wind turbine–driven doubly fed induction generator using sliding mode technique with practical finite‐time stability

Fault‐tolerant finite‐time adaptive higher order sliding mode control with optimized parameters for attitude stabilization of spacecraft

A fault-tolerant attitude tracking control of spacecraft using an anti-unwinding robust nonlinear disturbance observer

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