National Laboratory of Space Intelligent Control

Beijing, China

National Laboratory of Space Intelligent Control

Beijing, China

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Gong Y.-L.,Beijing Institute of Control Engineering | Gong Y.-L.,National Laboratory of Space Intelligent Control | Wu H.-X.,Beijing Institute of Control Engineering | Wu H.-X.,National Laboratory of Space Intelligent Control
Yuhang Xuebao/Journal of Astronautics | Year: 2010

A characteristic model-based adaptive control method is considered for the attitude control for a hypersonic vehicle. An MIMO characteristic model is established for a 6-DOF X-20 analogous hypersonic vehicle dynamic model during it's unpowered cruising phase. This model is nonlinear, strong couple and with parameters of great uncertainty. The Gold Section adaptive controller based on the characteristic model is designed, and the control algorithm is simplified by forcing one step time-delay of the non-diagonal control inputs. Simulation results for tracking attitude angle commands in wide range of changes of flight height and velocity demonstrate the robustness and adaptability of the controller.


Yan S.,Intelligent Systems Technology, Inc. | Yan S.,Tsinghua National Laboratory for Information Sciences and Technology | Sun Z.,Intelligent Systems Technology, Inc. | Sun Z.,Tsinghua National Laboratory for Information Sciences and Technology | Sun Z.,National Laboratory of Space Intelligent Control
Neurocomputing | Year: 2010

As the important issue in fuzzy control system, some studies on separation principle for total fuzzy system have been done up to now. However, these existing results are far from enough. In order to supplement such theoretical study, this paper proves that separation principle for T-S fuzzy system with switching fuzzy controller and switching fuzzy observer does hold both in the continuous- and discrete-time case, which can guarantee the stability of total fuzzy system when designing corresponding controller and observer independently. At last, a numerical simulation, some conclusions and discussions about the future work are also presented. © 2010 Elsevier B.V.


Li M.,Harbin Institute of Technology | Jing W.,Harbin Institute of Technology | Huang X.,Beijing Institute of Control Engineering | Huang X.,National Laboratory of Space Intelligent Control
Journal of Guidance, Control, and Dynamics | Year: 2012

A study was conducted to consider the systematic error caused by oblateness for a dual cone sensor (DCS) and present the orbit and attitude corrections for the Earth's oblateness. The problem was transferred from the roll and pitch angle errors' correction to nadir vector determination around the oblate Earth. An algorithm determining the nadir vector that accounted for the Earth's oblateness, was derived with the Gauss-Newton method according to the principle of measurement. The nadir vector information, combined with the measurements of other sensors, was used for orbit and attitude determination. The nadir vector determination algorithm was verified and the orbit and attitude corrections for the Earth's oblateness was demonstrated by an integrated algorithm of least-squares orbit determination and two-vector attitude determination based on the orientation information of the sun, Earth, and moon.


Xie Y.-H.,Tsinghua University | Xie Y.-H.,Shenyang Artillery Institute | Sun Z.-Q.,Tsinghua University | Sun Z.-Q.,National Laboratory of Space Intelligent Control
Kongzhi Lilun Yu Yingyong/Control Theory and Applications | Year: 2010

For a class of delayed Chen chaotic systems with unknown parameters, the scheme of its exponential synchronization is discussed. Based on Lyapunov stability theory, an exponential synchronization controller and adaptive laws of parameters are designed. A sufficient condition of exponential synchronization is then given by using the linear matrix inequality technique. The proposed method is also applied to secure communications. The designed controller is easily implemented in practice. An illustrative example is used to demonstrate the effectiveness of the presented method.


Wang X.,Tsinghua University | Guan X.,National Laboratory of Space Intelligent Control | Guan X.,China Academy of Space Technology | Zheng G.,Tsinghua University
Mechanical Systems and Signal Processing | Year: 2015

An inverse solution technique with the ability of obtaining complete steady-state primary harmonic responses of local nonlinear structures in the frequency domain is proposed in the present paper. In this method, the nonlinear dynamic equations of motion is first condensed from many to only one algebraic amplitude-frequency equation of relative motion. Then this equation is transformed into a polynomial form, and with its frequency as the unknown variable, the polynomial equation is solved by tracing all the solutions of frequency with the increase of amplitude. With this solution technique, some complicated dynamic behaviors such as sharp tuning, anomalous jumps, breaks in responses and detached resonance curves could be obtained. The proposed method is demonstrated and validated through a finite element beam under force excitations and a lumped parameter model with a local nonlinear element under base excitations. The phenomenon of detached resonance curves in the frequency response and its coupling effects with multiple linear modes in the latter example are observed. © 2015 Elsevier Ltd.


Cui J.,Tsinghua University | Guan X.,National Laboratory of Space Intelligent Control | Guan X.,China Academy of Space Technology | Zheng G.,Tsinghua University
International Journal for Numerical Methods in Engineering | Year: 2016

A simultaneous iterative procedure for the Kron's component modal synthesis method is developed in this paper for fast calculating the modal parameters of a large-scale and/or complicated structure. To simultaneously improve the precision of all the concerned modal parameters, the modal transformation matrix is chosen as the iterative term. For a faster convergence rate, the reduced system matrices are consistent with the modal transformation matrix. With a mathematically proved consistency and reasonably justified convergence, the proposed method can provide highly accurate results after a few iterations. The implementation details are presented for reference together with some computational considerations. Compared with other methods for obtaining modal parameters, the proposed method has such merits as high computational efficiency and still in a substructuring scheme. Two numerical examples are provided to illustrate and validate the proposed method. © 2016 John Wiley & Sons, Ltd.


Wang J.,National University of Defense Technology | Xiong K.,National Laboratory of Space Intelligent Control | Zhou H.,National University of Defense Technology | Zhou H.,National Laboratory of Space Intelligent Control
Chinese Journal of Aeronautics | Year: 2012

The low-frequency periodic error of star tracker is one of the most critical problems for high-accuracy satellite attitude determination. In this paper an approach is proposed to identify and compensate the low-frequency periodic error for star tracker in attitude measurement. The analytical expression between the estimated gyro drift and the low-frequency periodic error of star tracker is derived firstly. And then the low-frequency periodic error, which can be expressed by Fourier series, is identified by the frequency spectrum of the estimated gyro drift according to the solution of the first step. Furthermore, the compensated model of the low-frequency periodic error is established based on the identified parameters to improve the attitude determination accuracy. Finally, promising simulated experimental results demonstrate the validity and effectiveness of the proposed method. The periodic error for attitude determination is eliminated basically and the estimation precision is improved greatly. © 2012 Chinese Journal of Aeronautics.


Liu H.-B.,National University of Defense Technology | Yang J.-K.,National University of Defense Technology | Yang J.-K.,National Laboratory of Space Intelligent Control | Wang J.-Q.,National University of Defense Technology | And 2 more authors.
Applied Optics | Year: 2011

Star pattern recognition and attitude determination accuracy is highly dependent on star spot location accuracy for the star tracker. A star spot location estimation approach with the Kalman filter for a star tracker has been proposed, which consists of three steps. In the proposed approach, the approximate locations of the star spots in successive frames are predicted first; then the measurement star spot locations are achieved by defining a series of small windows around each predictive star spot location. Finally, the star spot locations are updated by the designed Kalman filter. To confirm the proposed star spot location estimation approach, the simulations based on the orbit data of the CHAMP satellite and the real guide star catalog are performed. The simulation results indicate that the proposed approach can filter out noises from the measurements remarkably if the sampling frequency is sufficient. © 2011 Optical Society of America.


Luo X.,University of Science and Technology Beijing | Luo X.,National Laboratory of Space Intelligent Control | Li J.,University of Science and Technology Beijing
Science China Information Sciences | Year: 2011

The intelligent autonomous control of hypersonic vehicles has aroused great interest from the field of spacecraft. To solve the problem of longitudinal attitude control of hypersonic vehicle in gliding phase, a new intelligent controller is proposed in this paper. This new controller is based on the fuzzy dynamic characteristic modeling method. The fuzzy logic is introduced into the characteristic modeling by dividing the whole restriction range into several subspaces. Simulations show that this modification greatly improves the performance of the original method. With the same whole restriction range the fuzzy dynamic characteristic modeling decreases the time of convergence, and at the same time makes the attitude angle tracing more precise and robust. Since the sub-model is a characteristic model that has stronger adaptiveness than a fixed local model, the number of fuzzy rules is greatly reduced. Our model sharply reduces the complexity in constructing a fuzzy dynamic model. Finally, simulation results are given to show the effectiveness of the proposed approach in dealing with the attitude control problem of hypersonic vehicle in gliding phase. © 2011 Science China Press and Springer-Verlag Berlin Heidelberg.


Liu H.-B.,National University of Defense Technology | Tan J.-C.,National University of Defense Technology | Jia H.,National University of Defense Technology | Li X.-J.,National University of Defense Technology | And 3 more authors.
Optical Engineering | Year: 2011

We have developed a calibration approach for a star tracker camera. A modified version of the least-squares iteration algorithm combining Kalman filter is put forward, which allows for autonomous on-orbit calibration of the star tracker camera even with nonlinear camera distortions. In the calibration approach, the optimal principal point and focal length are achieved at first via the modified algorithm, and then the high-order focal-plane distortions are estimated using the solution of the first step. To validate this proposed calibration approach, the real star catalog and synthetic attitude data are adopted to test its performance. The test results have demonstrated the proposed approach performs well in terms of accuracy, robustness, and performance. It can satisfy the autonomous on-orbit calibration of the star tracker camera. © 2011 Society of Photo-Optical Instrumentation Engineers (SPIE).

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