Journal of Astronautics ›› 2015, Vol. 36 ›› Issue (2): 186-195.doi: 10.3873/j.issn.1000-1328.2015.02.009

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Disturbance Attenuation Control for Flight Vehicle Switched Polytopic System

WANG Qing, HOU De long, CHEN Bin, DONG Chao yang   

  1. 1. Science and Technology on Aircraft Control Laboratory,Beihang University,Beijing 100191,China;
    2. Beijing Astronautics Systems Engineering Institute,Beijing 100080,China;
    3. School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China
  • Received:2013-12-18 Revised:2014-03-31 Online:2015-02-15 Published:2015-02-25


Aiming at the flight vehicle switched polytopic system in the present of parameters uncertainties and external disturbances, a disturbance attenuation control scheme is proposed in this paper. Both parameter uncertainties and external disturbances are considered as equivalent disturbances to the system. A kind of improved differentiator is put forwarded to estimate the equivalent disturbances, and the disturbances are compensated in the controller. Compared with the traditional robust control method such as H∞, the method proposed in this paper avoids the convex hypothesis of system uncertainties, and the closed loop system represents good performance both in nominal and uncertain condition. The stability of the closed loop system is proved by the method combining differential inequality with average dwell time. The proposed method is applied to the trajectory tracking control of hypersonic flight vehicle, which validates the advantage of the proposed method.

Key words: Uncertainty, Disturbance attenuation, Switched polytopic system, Robust tracking, Hypersonic flight vehicle

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