Journal of Institute of Control, Robotics and Systems (제어로봇시스템학회논문지)

Institute of Control, Robotics and Systems (제어로봇시스템학회)
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Study on Missile Aerodynamic Characteristics with Three Loop Acceleration Autopilot Structure

3-루프 가속도 오토파일롯 구조를 갖는 유도탄의 공력특성 연구

  • Published : 2002.08.01
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Abstract

We study how the missile autopilot with three loop acceleration structure is related to the aerodynamic characteristics. First, the relationships between the response characteristics of wingless-tail controlled missile and aerodynamics are derived. Next the maximum allowable performance limit of autopilot and the design direction for a missile shape are indicated using the property of zero. The method proposed in this paper may give a help to the missile autopilot system design and determination of the shape of aerodynamic. Also, the validity of proposed method is demonstrated via numerical example.

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References

  1. Kenneth E. Cockeham, 'The effect of autopilot configuration on missile response,' Naval Postgraduate School, 1989
  2. P. Apkarian and Journal-M. Biannic, 'Self-scheduled $H_{\infty}$ control of missile via linear matrix inequalities,' Journal of Guigance, Control, and Dynamics, Vol. 18, No. 3, pp.532-538, May-June 1995 https://doi.org/10.2514/3.21419
  3. J. J. Zhu and M. C. Mickle, 'Missile autopilot design using a new linear time-varying control technique,' Journal of Guigance, Control, and Dynamics, Vol. 20, No. 1, pp.150-157, January-Febuary 1997 https://doi.org/10.2514/2.4009
  4. J.-H. Oh and I.-J. Ha, 'Missile autopilot design via functional inversion and time-scaled transformation, 'IEEE Transactions on Aerospace and Electronic Systems, Vol. 33, No. 1, pp.64-76, January 1997 https://doi.org/10.1109/7.570709
  5. F.W. Nesline and M. L. Nesline, 'How autopilot requirements constrain the aerodynamic design of homing missiles,' Proceedings of American Control Conference, Vol. 2, pp. 716-730, 1984