Abstract
This paper presents a development, as well as an investigation of a Model Matching Controller (MMC) design based on the Self-Tuning Regulator (STR) framework for high performance aircraft with direct application to an F-16 aircraft flight control system. In combination with the Recursive Least Squares (RLS) identification, the MMC is developed and investigated for effectiveness on a detailed model of the aircraft. The popular robust Quantitative Feedback Theory (QFT) controller is also outlined and used to represent a baseline controller, for performance comparison during four simulated test flight maneuvers. In each of the four maneuvers, the proposed MMC provided consistently stable and satisfactory performance, including the challenging pull-up and pushover maneuvers. The baseline stationary controller has been found to become unstable in two of the four maneuvers tested. It also performs satisfactorily-to-arguably poorly in the remaining two as compared to the MMC. Simulation results presented in this investigation support a clear argument that the proposed MMC provides superior performance in the realm of automatic flight control.
Highlights
Challenges in automatic flight control are predominant over those in many systems due to the uncertainties that are involved in the aircraft itself, as well as its surroundings [1,2,3,4,5]
A development as well as investigation of a Model Matching Controller for a high performance (F-16) aircraft based on the Self-Tuning Regulator (STR) framework has been presented
The proposed controller includes Recursive Least Squares identification algorithm and an Model Matching Controller (MMC) technique, both to be implemented in real time to produce adaptive systems that will track a reference signal optimally as the model undergoes various thirty second flight simulations
Summary
This paper presents a development, as well as an investigation of a Model Matching Controller (MMC) design based on the SelfTuning Regulator (STR) framework for high performance aircraft with direct application to an F-16 aircraft flight control system. The popular robust Quantitative Feedback Theory (QFT) controller is outlined and used to represent a baseline controller, for performance comparison during four simulated test flight maneuvers. The baseline stationary controller has been found to become unstable in two of the four maneuvers tested. It performs satisfactorily-to-arguably poorly in the remaining two as compared to the MMC. Simulation results presented in this investigation support a clear argument that the proposed MMC provides superior performance in the realm of automatic flight control
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