National Key Laboratory of Science and Technology on Space Intelligent Control

Beijing, China

National Key Laboratory of Science and Technology on Space Intelligent Control

Beijing, China
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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.


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.


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.


Si Z.-H.,Beijing Institute of Control Engineering | Si Z.-H.,National Key Laboratory of Science and Technology on Space Intelligent Control | Liu Y.-W.,Beijing Institute of Control Engineering | Liu Y.-W.,National Key Laboratory of Science and Technology on Space Intelligent Control
Yuhang Xuebao/Journal of Astronautics | Year: 2010

The attitude of satellite is disturbed under the influence of step motor driving during the period of solar array pointing to the sun. Considering the coupling disturbances with satellite attitude caused by driving fluctuation, a compound controller is designed for satellite attitude stabilization and solar array pointing to the sun. For the rigid body attitude stabilization, an Active Disturbance Rejection Controller(ADRC) is proposed to estimate and compensate the disturbances induced by solar array driving and model uncertainties, on the basis of this work, an Adaptive Current Compensator(ACC) is adopted to equalize the friction torque and ripple torque of Solar Array Drive Assembly(SADA). The simulation results demonstrate that the satellite attitude accuracy and stability can both improve greatly and the solar array can track the sun more accurately with this compound control strategy.


Hu J.,Beijing Institute of Control Engineering | Hu J.,National Key Laboratory of Science and Technology on Space Intelligent Control | Zhang H.,Beijing Institute of Control Engineering | Zhang H.,National Key Laboratory of Science and Technology on Space Intelligent Control
Chinese Control Conference, CCC | Year: 2012

In this article, the attitude control problem of a rigid body without angular velocity measurement and subject to actuator saturation is solved in a novel way by the combination of the I&I methodology and the dynamic scaling technique. Different from previous literature that utilized ad hoc methods to solve such kind of problems, we construct the observer for the angular velocity directly, where the gyroscopic term is dominated by the dynamic scaling skill. The controller is a simple PD scheme with a saturate restriction on the angular-velocity part. It's shown that the observer and the controlled attitude dynamics compose a cascaded system. By utilizing the cascade-system stability theory, it is proven that the closed-loop system is globally asymptotically stable. Finally, simulations are conducted to demonstrate the effectiveness of the proposed control scheme. © 2012 Chinese Assoc of Automati.


Wang M.,Beijing Institute of Control Engineering | Wang M.,National Key Laboratory of Science and Technology on Space Intelligent Control | Xie Y.,Beijing Institute of Control Engineering | Xie Y.,National Key Laboratory of Science and Technology on Space Intelligent Control
Science China Technological Sciences | Year: 2010

The set of forces and moments that can be generated by thrusters of a spacecraft is called the "control capability" with respect to the thruster configuration. If the control capability of a thruster configuration is adequate to fulfill a given space mission, we say this configuration is a feasible one with respect to the task. This study proposed a new way to analyze the control capability of the complex thruster configuration. Precise mathematical definitions of feasibility were proposed, based on which a criterion to judge the feasibility of the thruster configuration was presented through calculating the shortest distance to the boundary of the controllable region as a function of the thruster configuration. Finally, control capability analysis for the complex thruster configuration based on its feasibility with respect to the space mission was given followed by a 2-D thruster configuration example to demonstrate its validity. © 2010 Science China Press and Springer-Verlag Berlin Heidelberg.


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.


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.


Zhu Z.-B.,Beijing Institute of Control Engineering | Zhu Z.-B.,National Key Laboratory of Science and Technology on Space Intelligent Control | Li G.,National Key Laboratory of Science and Technology on Space Intelligent Control | He Y.-Z.,Beijing Institute of Control Engineering | And 3 more authors.
Yuhang Xuebao/Journal of Astronautics | Year: 2012

Driven by the close proximity fast fly-around features such as light of sight(LOS) holding requirement and coupled translation and attitude control, a cooperative translation and attitude optimal control method for spacecraft is studied. The coupled nonlinear equation of 6 DOF relative motion is obtained, and eccentric thrust vector is used to provide position control forces as well as attitude control torques. Considering high accuracy dynamic performance demand for close proximity relative motion, a finite horizon optimal control computing method including final state constraints different from the classic infinite horizon Theta-D method is proposed. Differential Ricatti equation and differential Lyapunov equation in process are also prescribed. Constraints of small finite impulse thrusters and finite torque transformation equipments are completely embedded in controller design. Simulation results of close proximity fast fly-around show that the proposed method can get small control output under the condition of guaranteeing stability and performance requirement of relative motion, and have some engineering sense for potential application.


Gu P.,Beijing Institute of Control Engineering | Gu P.,National Key Laboratory of Science and Technology on Space Intelligent Control | Wang D.,Beijing Institute of Control Engineering | Wang D.,National Key Laboratory of Science and Technology on Space Intelligent Control | And 2 more authors.
Zhongguo Kongjian Kexue Jishu/Chinese Space Science and Technology | Year: 2013

The selection of momentum wheel configuration in satellite attitude control system design was investigated. Five different orientations of momentum wheel system were summarized. The design criteria of momentum wheel reconfiguration, the saturation of the momentum wheel under disturbance torque, energy consumption and reliability in different orientations were proposed by comparing the angular momentum envelope. The proposed method could be applied to the design of momentum wheel control system.

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