An Auto-Pilot System Design Using Reduced Order Model Reference Adaptive Control
TAWFIK, A., WAHDAN, A. (1987). An Auto-Pilot System Design Using Reduced Order Model Reference Adaptive Control. EKB Journal Management System, 2(A.S.A.T. CONFERENCE 21-23 April 1987 , CAIRO), 987-997. doi: 10.21608/asat.1987.26196
A. T.Y. TAWFIK; A. M. WAHDAN. "An Auto-Pilot System Design Using Reduced Order Model Reference Adaptive Control". EKB Journal Management System, 2, A.S.A.T. CONFERENCE 21-23 April 1987 , CAIRO, 1987, 987-997. doi: 10.21608/asat.1987.26196
TAWFIK, A., WAHDAN, A. (1987). 'An Auto-Pilot System Design Using Reduced Order Model Reference Adaptive Control', EKB Journal Management System, 2(A.S.A.T. CONFERENCE 21-23 April 1987 , CAIRO), pp. 987-997. doi: 10.21608/asat.1987.26196
TAWFIK, A., WAHDAN, A. An Auto-Pilot System Design Using Reduced Order Model Reference Adaptive Control. EKB Journal Management System, 1987; 2(A.S.A.T. CONFERENCE 21-23 April 1987 , CAIRO): 987-997. doi: 10.21608/asat.1987.26196

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, Pages 987-997    PDF (2.19 M)
Document Type: Original Article
DOI: 10.21608/asat.1987.26196
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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