Variable-structure control of spacecraft attitude maneuvers

Dwyer, Thomas A.; Sira‐Ramírez, Hebertt

doi:10.2514/3.20303

Cited by 175 publications

(34 citation statements)

References 9 publications

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“…Sliding mode control is deployed in this section for attitude synchronization and tracking in the presence of model uncertainties and external disturbances. However, in conventional sliding mode control laws , an important assumption is that inertia uncertainties and external disturbances are bounded and that their bounds are available to the designer. These bounds provide important information to guarantee the stability of the closed‐loop system.…”

Section: Decentralized Adaptive Sliding‐mode Control Designmentioning

confidence: 99%

“…This paper presents a decentralized control law for satellite attitude synchronization and tracking in the presence of model uncertainties and external disturbances. Sliding mode control is an efficient approach to control spacecraft attitude when there are model uncertainties and external disturbances . Here, a novel decentralized adaptive sliding mode control law is proposed and analyzed based on algebraic graph theory for attitude synchronization and tracking in spacecraft formation with undirected interspacecraft communication links.…”

Section: Introductionmentioning

confidence: 99%

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Decentralized sliding‐mode control for attitude synchronization in spacecraft formation

Wang

Poh

2012

Intl J Robust & Nonlinear

113

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This paper addresses attitude synchronization and tracking problems in spacecraft formation in the presence of model uncertainties and external disturbances. A decentralized adaptive sliding mode control law is proposed using undirected interspacecraft communication topology and analyzed based on algebraic graph theory. A multispacecraft sliding manifold is derived, on which each spacecraft approaches desired timevarying attitude and angular velocity while maintaining attitude synchronization with the other spacecraft in the formation. A control law is then developed to ensure convergence to the sliding manifold. The stability of the resulting closed-loop system is proved by application of Barbalat's Lemma. Simulation results demonstrate the effectiveness of the proposed attitude synchronization and tracking methodology. Copyright

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Section: Decentralized Adaptive Sliding‐mode Control Designmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Decentralized sliding‐mode control for attitude synchronization in spacecraft formation

Wang

Poh

2012

Intl J Robust & Nonlinear

113

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“…The sliding mode control law is chosen as (24). Then the system trajectories globally exponentially converge to the sliding mode (6).…”

Section: Exponential Stabilitymentioning

confidence: 99%

“…Over the last few years, VSC has been applied to the design of attitude control system for spacecraft as discussed in Refs. [3,6,13,20]. However, the conventional VSC is always limited to the systems with full-state feedback.…”

Section: Introductionmentioning

confidence: 99%

Adaptive Variable Structure Maneuvering Control and Vibration Reduction of Three-axis Stabilized Flexible Spacecraft

2006

European Journal of Control

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“…Hence, applying SMC to design attitude control for satellite has been intensively carried out [22]. The first attempt using SMC to achieve large angle attitude maneuver for spacecraft was made in [23] and further pursued in [24]. A higher-order SMC control scheme was presented in [25].…”

Section: Introductionmentioning

confidence: 99%

Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite

Huo

Karimi

et al. 2014

Abstract and Applied Analysis

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The problem of finite-time control for attitude tracking maneuver of a rigid spacecraft is investigated. External disturbance, unknown inertia parameters are addressed. As stepping stone, a sliding mode controller is designed. It requires the upper bound of the lumped uncertainty including disturbance and inertia matrix. However, this upper bound may not be easily obtained. Therefore, an adaptive sliding mode control law is then proposed to release that drawback. Adaptive technique is applied to estimate that bound. It is proved that the closed-loop attitude tracking system is finite-time stable. The tracking errors of the attitude and the angular velocity are asymptotically stabilized. Moreover, the upper bound on the lumped uncertainty can be exactly estimated in finite time. The attitude tracking performance with application of the control scheme is evaluated through a numerical example.

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Variable-structure control of spacecraft attitude maneuvers

Cited by 175 publications

References 9 publications

Decentralized sliding‐mode control for attitude synchronization in spacecraft formation

Decentralized sliding‐mode control for attitude synchronization in spacecraft formation

Adaptive Variable Structure Maneuvering Control and Vibration Reduction of Three-axis Stabilized Flexible Spacecraft

Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite

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