Integrated Finite-Time Disturbance Observer and Controller Design for Reusable Launch Vehicle in Reentry Phase
Publication: Journal of Aerospace Engineering
Volume 30, Issue 1
Abstract
An integrated finite-time disturbance observer (FDO) and attitude controller is designed for a reusable launch vehicle (RLV) in this paper. In accordance with the multiple-timescale features, RLV attitude dynamics are divided into an outer-loop subsystem and an inner-loop subsystem. Based on the recently developed sliding mode control (SMC), a novel multivariable supertwisting sliding mode controller driven by a FDO is designed to achieve a fast and accurate reentry attitude tracking. This integrated design can generate a continuous control law which has excellent robustness to uncertainty and disturbances with known bounds while achieving an arbitrarily fast convergence. The finite-time stability of the overall system is proved by using the Lyapunov function technique and the multiple-timescale separation principle. In addition, an optimal control allocation for allocating torque commands into aerodynamic surface deflection commands with constraints is also proposed. Finally, the effectiveness and the robustness of the integrated control scheme are verified by the simulation results of a six-degree-of-freedom (6-DOF) RLV.
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Acknowledgments
The project was supported by the National Natural Science Foundation of China (Grants No. 61273092 and No. 61503323) and a Key Project of the Chinese Ministry of Education (Funding No. 311012).
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Published In
Journal of Aerospace Engineering
Volume 30 • Issue 1 • January 2017
Copyright
© 2016 American Society of Civil Engineers.
History
Received: Dec 21, 2015
Accepted: May 19, 2016
Published online: Jul 29, 2016
Discussion open until: Dec 29, 2016
Published in print: Jan 1, 2017
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