An Auto-Pilot System Design Using Reduced Order Model Reference Adaptive Control | ||||
International Conference on Aerospace Sciences and Aviation Technology | ||||
Article 39, Volume 2, A.S.A.T. CONFERENCE 21-23 April 1987 , CAIRO, April 1987, Page 987-997 PDF (2.19 MB) | ||||
Document Type: Original Article | ||||
DOI: 10.21608/asat.1987.26196 | ||||
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Authors | ||||
A. T.Y. TAWFIK1; A. M. WAHDAN2 | ||||
1Ph. D. student, A/C Main Workshop-Helwan, E.A.F. | ||||
2Associate Professor, Dpt. of elect. & Computer, Ain Shams University. Cairo, Egypt - Working now at College of computer and information sciences, King Saud Univ., Kingdom of Saudi Arabia. | ||||
Abstract | ||||
In this paper, the singularly-perturbed design of an auto-pilot system of a high speed fighter aircraft, for the same authors (1985), is modified. The previous suboptimal design based on singular perturbation technique was proper only for aircraft operation near its nominal flight conditions. The new proposed adaptive design would be adequate for all possible changes of aircraft dynamics. The plant with varying parameters, representing aircraft, is controlled to behave nearly similar to a chosen first order reference model. The proposed discrete model reference adaptive control design uses an adaptive algorithm of Suzuki and Takashima (1978), based on augmented error signal concept and Popov's hyperstability theorem. Computer simulation results are presented to demonstrate the usefulness of the proposed design. | ||||
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