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Guan X.,Tsinghua University | Wang Q.-W.,Beijing Institute of Control Engineering | Wang Q.-W.,National Key Laboratory of Science and Technology on Space Intelligent Control | Zheng G.-T.,Tsinghua University
Yuhang Xuebao/Journal of Astronautics | Year: 2010

High precision payloads of a modern spacecraft require an ultra-quiet operating environment. As one of the major disturbance sources, the vibration of the reaction wheels greatly affects the performance of payloads. Besides improving the manufacturing accuracy, it is a good choice to add vibration isolators to the reaction wheels. The existing research work and solutions on flywheel vibration isolation are summarized in this paper and the characteristics of both passive and active isolation are discussed. An equivalent passive element technique is used to analyze the nature of active isolation and a pseudo-active isolation method is proposed, in which passive elements are used to implement the active control law. Simulation results indicate that the pseudo-active isolation method can improve the performance of the passive isolators by restraining the resonance peak while maintaining the high frequency performance. Source


Li G.-M.,Beijing Institute of Control Engineering | Li G.-M.,National Key Laboratory of Science and Technology on Space Intelligent Control | Liu L.-D.,Beijing Institute of Control Engineering
Yuhang Xuebao/Journal of Astronautics | Year: 2011

We address multiple rigid spacecraft attitude coordinated and tracking control under a general undirected interaction topology. Distributed attitude coordinated controllers are considered for multiple spacecraft without model parameter or disturbance uncertainties, and with unknown model parameter and constant external disturbances. For the first case, the controller designed based on the sliding mode guarantees that all group spacecraft can achieve synchronized attitude maneuver, i. e., tracking a time-varying desired attitude while synchronizing their attitudes. For the second case, we design an adaptive coordinated attitude controller, to obtain synchronized attitude maneuver. Based on Lyapunov-Krasovskii method, our proposed controllers are robust to the constant communication delays existing in information exchange channels. Numerical simulations have demonstrated the effectiveness of our proposed approach. Source


Wang Y.,Beijing Institute of Control Engineering | Wang Y.,National Key Laboratory of Science and Technology on Space Intelligent Control
Advances in the Astronautical Sciences | Year: 2013

In this paper, a stability analysis framework of adaptive control based on characteristic model for the SISO minimum-phase system is generalized to the MIMO minimum-phase system, which parameterizes the high-order, minimum-phase system to the lower-order linear model via a special decoupling method, and analyzes the stability of the complex sampled-data adaptive system via the stability analysis method of sampled-data system based on the approximated discrete-time model. Moreover, based on the idea, a decentralized modeling method helpful to design the decentralized controller, is proposed and applied in the attitude controller design of a kind of hypersonic vehicle. Simulation results show that the proposed methodology achieves excellent tracking performance. Source


Wang Y.,Beijing Institute of Control Engineering | Wang Y.,National Key Laboratory of Science and Technology on Space Intelligent Control
Procedia Engineering | Year: 2012

Through treating the high-order subsystem as a nonlinear uncertainty, this paper converts a high-order hybrid adaptive system to a lower-order, sampled-data, indirect adaptive control problem through a special transformation, and analyzes its stability via the framework for stabilization of sampled-data systems based on its approximate discrete-time models. Therefore, a stability analysis framework for the adaptive control based on the characteristic model is proposed, and it is helpful to analyze the stability of system which applies the lower-order adaptive robust controller to control the high-order system. © 2011 Published by Elsevier Ltd. Source


Liu W.-J.,Beijing Institute of Control Engineering | Liu W.-J.,National Key Laboratory of Science and Technology on Space Intelligent Control | Wang N.-H.,Beijing Institute of Control Engineering | Wang N.-H.,National Key Laboratory of Science and Technology on Space Intelligent Control
Yuhang Xuebao/Journal of Astronautics | Year: 2011

Considering the spacecraft control system's features such as closed-loop, limited resource and computational capacity constraint of the on-board computer, a fault detection scheme based on the coprime factorization and Youla parameterzation is proposed. Based on the kinematics and dynamics equations, a linearized model for the spacecraft attitude control system as well as its state space expression is obtained; in terms of the state observer, the coprime factorization and Youla parameterzation are used to analyze the relationships between the control signal and the control error and residual separately, then the residual only related to the control signal and the control error is obtained; The proposed method is validated and the simulation results show that without running the state observer in parallel, the residual equivalent to the one obtained by the sate observer expends much less time. Source

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