Integrated Aircraft-Controller Design Using Linear Matrix Inequalities
Integrated_Aircraft.pdf (1.617Mb)Abstract
A new methodology is presented for solving the problem of optimizing the aircraft parameters, such as the size of its control surfaces, while meeting open- and closed-loop static and dynamic performance requirements. The approach proposed involves rewriting these requirements as linear matrix inequalities and solving a related constrained optimization problem for which efficient numerical solutions are available.
Description
AIAA Journal of Guidance and Control, vol. 19, no.2, pp. 445-452, March-April 1996.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.Collections
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