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ADAPTIVE FLIGHT CONTROL DESIGN FOR NONLINEAR MISSILE
Antonios Tsourdos* Brian A. White*
* Department of Aerospace, Power and Sensors,
Royal Military College of Science,
Cranfield University,
Shrivenham, SN6 8LA, England, UK
An autopilot combining an indirect adaptive controller with approximate feedback linearisation is proposed in order to achieve asymptotic tracking. Adaptation is introduced to enhance closed-loop robustness, while approximate feedback linearisation is used to overcome the problem of unstable zero dynamics. Computer simulations show that this approach offers a possible autopilot design for non-linear missiles with uncertain parameters.
Keywords: non-linear control, feedback linearisation, flight control, missile system, adaptive control
Session slot T-Tu-E06: Advances in Missile Guidance and Control/Area code 8a : Aerospace
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