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Volume 40 Issue 3
Mar.  2014
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Journal of Beijing University of Aeronautics and Astronautics  > 2014  >  40(3): 401-406.
Zhang Lei, Fang Yangwang, Diao Xinghua, et al. Design of nonlinear optimal controller for multi-missile formation[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(3): 401-406. doi: 10.13700/j.bh.1001-5965.2013.0268(in Chinese)
Citation: Zhang Lei, Fang Yangwang, Diao Xinghua, et al. Design of nonlinear optimal controller for multi-missile formation[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(3): 401-406. doi: 10.13700/j.bh.1001-5965.2013.0268(in Chinese)
shu

Design of nonlinear optimal controller for multi-missile formation

doi: 10.13700/j.bh.1001-5965.2013.0268
  • 1.

    School of Aeronautics and Astronautics, Air Force Engineering University, Xi'an 710038, China

  • 2. Unit 94857 of the People's Liberation Army, Wuhu 241007, China

  • Received Date: 17 May 2013
  • Publish Date: 20 Mar 2014
    Abstract
  • To solve the formation control problem of multi-missile formation, the optimal control theory of affine nonlinear system was adopted to design the formation controller of missiles based on leader-follower approach. Firstly, precise linearization based on differential geometry theory was used to linearize the nonlinear motion model of the missile. Secondly, according to the relative motion model of leader and follower, the desired follower track including the states of leader and the desired formation relative distances was given, and system model with follower track errors was formulated. Finally, riccati matrix differential equation solution based on steady state solution was introduced to solve the optimal control problem and a three-dimensional nonlinear optimal formation controller was designed. Simulation results show that the controller is robust to leader maneuver, and is capable of forming and keeping formation figuration rapidly, stably and exactly.

     

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