Decoupling Control Synthesis For an Oblique-Wing Aircraft

Alag, Gurbux S. and Kempel, Robert W. and Pahle, Joseph W. (1986) Decoupling Control Synthesis For an Oblique-Wing Aircraft. Technical Report NASA TM-86801, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

Interest in oblique-wing aircraft has surfaced periodically since the 1940's. This concept offers some substantial aerodynamic performance advantages but also has significant aerodynamic and inertial cross-coupling between the aircraft longitudinal and lateral-directional axes. This paper presents a technique for synthesizing a decoupling controller while providing the desired stability augmentation. The proposed synthesis procedure uses the concept of a real model-following control system. Feedforward gains are selected on the assumption that perfect model-following conditions are satisfied. The feedback gains are obtained by using eigensystem assignment, and the aircraft is stabilized by using partial state feedback. The effectiveness of the control laws developed in achieving the desired decoupling is illustrated by application to linearized equations of motion of an oblique-wing aircraft for a given flight condition.

EPrint Type:	NASA Technical Memorandum
Keywords:	Asymmetric aircraft control, Eigensystem synthesis, Flight control systems, Multivariable control systems, Perfect model-following
Subjects:	(01 - 09) Aeronautics: (08) Aircraft Stability And Control
ID Code:	541
Deposited On:	25 January 2006
Additional Information:	12 pages. Prepared as American Automatic Control Council paper for presentation at American Control Conference, Seattle, Washington, June 18-20, 1986. Dr. Alag is affiliated with Western Michigan University.