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Volume 30 Issue 05
May  2004
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Journal of Beijing University of Aeronautics and Astronautics  > 2004  >  30(05): 395-399.
Liu Xi, ong, Deng Zhidanget al. Research on the method of simulating road roughness numerically[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(9): 843-846. (in Chinese)
Citation: Wang Peng, Chen Wanchun, Zou Hui, et al. Agile turn control considerations for air-to-air missile with reaction jets control system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2004, 30(05): 395-399. (in Chinese)
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Agile turn control considerations for air-to-air missile with reaction jets control system

  • 1.

    School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • 2. Changfeng Electromechanical Technology Design Academy, China Aerospace Science & Industry Corp, Beijing 100830, China

  • Received Date: 03 Jan 2003
  • Publish Date: 31 May 2004
    Abstract
  • The control problem of the air-to-air missile during the agile turn phase was investigated using the reaction jets control system, which can increase the off-borsight capability of short-range air-to-air missile and the capability of intercepting the rear hemispherical target. A method was proposed to control the orientation of the missile velocity by controlling the attitude of the missile, and this method proved feasible in theory. Considering the on-off property of thereaction jets control system, the sliding mode control method is used for attitude control. A sufficient condition for the reachability of the sliding mode is that the moment provided by the reaction jets control system should be no less than the maximum aerodynamical pitch moment. The feedback gain can be selected by nonlinear simulation or optimization. The results of nonlinear simulation showed once again the feasibility of the agile turn method proposed here. The sliding mode attitude control method also prove effective according to the results.

     

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    • References(1)
  • [1] Solis R E. An analysis of the vertical launch phase of a missile concept . AIAA-83-0569,1983 [2] 彭冠一,张福安,林维菘,等.防空制导武器制导控制系统设计[M].北京:宇航出版社,1996.450~466 Peng Guanyi, Zhang Fu'an, Lin Weisong, et al. Guidance and control system design of guided antiair weapons[M]. Beijing:Space Navigation Press, 1996. 450~466 (in Chinese) [3] Taur D R, Chern J S. Optimal thrust vector control of tactical missiles . AIAA-97-3475,1997 [4]Thukral A, Innocenti M. A sliding mode missile pitch autopilot synthesis for high angle of attack maneuvering [J]. IEEE Trans on Control Systems Technology, 1998, 6(3):359~371 [5]McFarland M B, Calise A J. Neural-adaptive nonlinear autopilot design for an agile anti-Air missile . AIAA-96-3914, 1996 [6]Menon P K, Iragavarapu V R. Adaptive techniques for multiple actuator blending .AIAA-98-4494, 1998 [7]Wise K A, Broy D J. Agile missile dynamics and control [J].Journal of Guidance, Control and Dynamics, 1998, 21(3):441~449
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