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To design a reduced-order controller with loosing little accuracy.
Singular perturbation approach by quasi-steady state approximation and by Matrix block diagonalization technique is used.
It is shown that few errors occur between the uncorrected and corrected solutions for the fast subsystems while a few errors occur between the two kinds of solutions for the slow subsystems. The uncorrected solution is admissible for most dynamics. If not, it is recommended that the corrected solution be used.
Proportional feedback control gain is obtained by Pole placement method, which may produce an unwanted overshoot in the response.
This paper shows that the corrected controller is successfully applied in the aircraft dynamics and control.
Approximate controller design for singularly perturbed aircraft systems
Aircraft Engineering and Aerospace Technology ; 77 , 4 ; 311-316
2005-08-01
6 pages
Article (Journal)
Electronic Resource
English
Approximate controller design for singularly perturbed aircraft systems
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