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Nonlinear Missile Autopilot Design Based on Angle of Attack Normal Form

  • Published:2000-01 Issue:2 Volume:6 Page:154-164
  • ISSN:0947-3580
  • Container-title:European Journal of Control
  • language:en
  • Short-container-title:European Journal of Control

Author:

Siguerdidjane Houria,Devaud Emmanuel

Publisher

Elsevier BV

Subject

General Engineering

Reference27 articles.

1. Approximate output tracking for nonlinear non-minimum phase systen1 with an application to flight control;Benvenuti;International Journal of Robust and Nonlinear Control,1994

2. Stable inversion of nonlinear non-minimum phase system;Chen;International Journal of Control,1996

3. Un théorème sur 1a représentation entreé-sortie d’un système non linéaire;Conte;C. R. Académie des Sciences,1988

4. Nonlinear inversionbased output tracking;Devasia;IEEE Transactions on Automatic Control,1996

5. Some control strategies of high angle of attack missile autopilot;Devaud,1998

Cited by 6 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Constrained Reference Tracking via Structured Input–Output Finite-Time Stability;IEEE Transactions on Systems, Man, and Cybernetics: Systems;2022-12

2. Robust Missile Autopilot Design Using Two Time-Scale Separation;IEEE Transactions on Aerospace and Electronic Systems;2018-06

3. Nonlinear system controllability analysis and autopilot design for bank-to-turn aircraft with two flaps;Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering;2018-03-26

4. Missile acceleration controller design using proportional–integral and non-linear dynamic control design method;Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering;2011-11-07

5. A Missile Autopilot Based on Feedback Linearization;European Journal of Control;2002-01
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