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Hybrid EDA-based optimal attitude control for a spacecraft in a class of control task
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ACM/SIGEVO Summit on Genetic and Evolutionary Computation archive
Proceedings of the first ACM/SIGEVO Summit on Genetic and Evolutionary Computation table of contents
Shanghai, China
POSTER SESSION: Poster sessions table of contents
Pages 903-906  
Year of Publication: 2009
ISBN:978-1-60558-326-6
Authors
Xiong Luo  School of Information Engineering, University of Science and Technology Beijing, Beijing 100083, Beijing, China
Zengqi Sun  Tsinghua University, Beijing 100084, Beijing, China
Xiang Zhang  Yangtze University, Jingzhou 434023, Jingzhou, China
Laihong Hu  Tsinghua University, Beijing 100084, Beijing, China
Chao Wang  School of Information Engineering, University of Science and Technology Beijing, Beijing 100083, Beijing, China
Sponsors
SIGEVO: ACM Special Interest Group on Genetic and Evolutionary Computation
ACM: Association for Computing Machinery
Publisher
ACM  New York, NY, USA
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ABSTRACT

In the practical situation, if failure of one of the actuators occurs, there exists the attitude control task of a rigid spacecraft using only two control torques supplied by momentum wheel actuators. Here, this class of control task for a rigid spacecraft is discussed. This nonlinear control problem can be converted to the nonholonomic motion planning optimization problem of a drift-free system. In order to improve the search efficiency of current optimization algorithms, the hybrid estimation of distribution algorithm (EDA) is presented by combing the idea of differential evolution strategy (DES). Then, the optimal attitude control task for the spacecraft using two momentum wheel actuators is achieved. By comparing the proposed algorithm with existing genetic algorithm and evolutionary programming, the simulation results show the accuracy and efficiency of hybrid EDA.


REFERENCES

Note: OCR errors may be found in this Reference List extracted from the full text article. ACM has opted to expose the complete List rather than only correct and linked references.

 
1
Crouch, P. E. 1984. Spacecraft attitude control and stabilization: application of geometric control theory to rigid body models. IEEE Transactions on Automatic Control, 29, 4(Aug. 1984), 87--95.
 
2
Krishnan, H., McClamroch, N. H., and Reyhanoglu, M. 1995. Attitude stabilization of a rigid spacecraft using two momentum wheel actuators. Journal of Guidance, Control and Dynamics, 18, 2(Apr. 1995), 256--263.
 
3
Ge, X. S., Chen, L. Q., and Liu, Y. A. 2004. Nonholonomic motion planning for the attitude of rigid spacecraft with two momentum wheel actuators. Control Theory and Applications, 21, 5(Oct. 2004), 781--784.
 
4
Ge, X. S. and Chen, L. Q. 2004. Attitude control of a rigid spacecraft with two momentum wheel actuators using genetic algorithm. Acta Astronautica, 55, 1(Jan. 2004), 3--8.
 
5
Luo, X. and Sun, Z. Q. 2006. Optimal attitude control for a spacecraft using two momentum wheel actuators based on intensified evolutionary programming. Dynamics of Continuous, Discrete and Impulsive Systems, Series A: Mathematical Analysis, 13, Suppl. S(Dec. 2006), 733--737.
 
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8
Cho, D. Y. and Zhang, B. T. 2004. Evolutionary continuous optimization by distribution estimation with variational Bayesian independent component analyzers mixture model. Lecture Notes in Computer Science, 3242(Apr. 2004), 212--221.

Collaborative Colleagues:
Xiong Luo: colleagues
Zengqi Sun: colleagues
Xiang Zhang: colleagues
Laihong Hu: colleagues
Chao Wang: colleagues