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A straight forward application of feedback linearization to the missileautopilot design for acceleration control may be limited due to the nonminimumcharacteristics and the model uncertainties. As a remedy, this paper presents acascade structure of an acceleration controller based on approximate feedbacklinearization methodology with a time-delay adaptation scheme. The inner loopcontroller is constructed by applying feedback linearization to the approximatesystem which is a minimum phase system and provides the desired accelerationsignal caused by the angle-of-attack. This controller is augmented by thetime-delay adaptive law and the outer loop PI (proportional-integral)controller in order to adaptively compensate for feedback linearization errorbecause of model uncertainty and in order to track the desired accelerationsignal. The performance of the proposed method is examined through numericalsimulations. Moreover, the proposed controller is tested by using an interceptscenario in 6DOF nonlinear simulations.

Missile Acceleration Controller Design using PI and Time-Delay Adaptive Feedback Linearization Methodology