scholarly journals Optimal Sliding Mode Controllers for Attitude Stabilization of Flexible Spacecraft

2011 ◽  
Vol 2011 ◽  
pp. 1-20 ◽  
Author(s):  
Chutiphon Pukdeboon
Keyword(s):  
Optimal Control ◽  
Control System ◽  
Sliding Mode Control ◽  
Control Problem ◽  
Attitude Control ◽  
Sliding Mode ◽  
Flexible Spacecraft ◽  
Attitude Control System ◽  
Control Laws ◽  
Mode Control

The robust optimal attitude control problem for a flexible spacecraft is considered. Two optimal sliding mode control laws that ensure the exponential convergence of the attitude control system are developed. Integral sliding mode control (ISMC) is applied to combine the first-order sliding mode with optimal control and is used to control quaternion-based spacecraft attitude manoeuvres with external disturbances and an uncertainty inertia matrix. For the optimal control part the state-dependent Riccati equation (SDRE) and optimal Lyapunov techniques are employed to solve the infinite-time nonlinear optimal control problem. The second method of Lyapunov is used to guarantee the stability of the attitude control system under the action of the proposed control laws. An example of multiaxial attitude manoeuvres is presented and simulation results are included to verify the usefulness of the developed controllers.

Sliding Mode Predictive Control Method for Attitude Control of Networked Launch Vehicle

2011 ◽  
Vol 467-469 ◽  
pp. 962-967
Author(s):  
Yu Chen ◽  
Guang Li ◽  
Chao Yang Dong ◽  
Qing Wang
Keyword(s):  
Control System ◽  
Sliding Mode Control ◽  
Predictive Control ◽  
Attitude Control ◽  
Control Method ◽  
Sliding Mode ◽  
Launch Vehicle ◽  
Uncertain Parameters ◽  
Attitude Control System ◽  
Mode Control

A novel adaptive fuzzy sliding mode predictive control (AFSMPC) method for solving the networked launch vehicle attitude control system with network-induced delay, uncertain parameters and outer disturbances is proposed in this paper for the attitude stabilization of the networked launch vehicle control system. The proposed sliding mode surface includes a predictor to compensate for the network-induced delay of the NCS. Then, for the networked Launch vehicle attitude control system with uncertain parameters and outer disturbances, a total sliding-mode control system is proposed, which is designed without the reaching phase of a conventional sliding-mode control. In order to attenuate the chattering phenomena brought by the proposed control, a fuzzy logic system is designed to mimic the good behavior of a total sliding-mode predictive control system. Finally, Simulation results show that the proposed control scheme is effective.

scholarly journals Nonsingular Integral Sliding Mode Attitude Control for Rigid-Flexible Coupled Spacecraft with High-Inertia Rotating Appendages

Complexity ◽  
2021 ◽  
Vol 2021 ◽  
pp. 1-17
Author(s):  
Gaowang Zhang ◽  
Xueqin Chen ◽  
Ruichen Xi ◽  
Huayi Li
Keyword(s):  
Sliding Mode Control ◽  
Control Problem ◽  
Attitude Control ◽  
Sliding Mode ◽  
Control Law ◽  
Solar Panels ◽  
Integral Sliding Mode ◽  
Complex Control ◽  
Mode Control ◽  
Attitude Tracking

This study addresses the challenge of attitude tracking control for a rigid-flexible spacecraft with high-inertia rotating appendages. The Lagrange method was used to establish the kinematic and dynamic models of the spacecraft. The translation and rotation of the spacecraft, vibrations of solar panels, and imbalance caused by the rotating appendages, which cause a complex control problem, were considered. To address the complex control problem, a novel, fast nonsingular integral sliding mode control method is proposed to perform the attitude tracking function of spacecraft. A sliding mode control law was established for the high-inertia appendages to maintain an appropriate angular velocity during rotation. Finally, the effectiveness of the proposed attitude control law was verified by numerical simulations for a spacecraft with high-inertia rotating appendages and symmetrical flexible solar panels.

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