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Title: |
Decoupling control synthesis for an oblique-wing aircraft
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Author(s): |
Alag, G. S.; Kempel, R. W.; Pahle, J. W.
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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.
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NASA Center: |
Dryden Flight Research Center
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Publication Date: |
JAN 1, 1986
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Document Source: |
Other Sources |
No Digital Version Available: |
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Document ID: |
19870026068
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Accession ID: |
87A13342
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Publication Information: |
Number of Pages = 9 |
Keywords: |
AIRCRAFT CONTROL; ASYMMETRY; AUTOMATIC CONTROL; CROSS COUPLING; DECOUPLING; EIGENVALUES; FEEDFORWARD CONTROL; FLIGHT CONTROL; LATERAL CONTROL; LONGITUDINAL CONTROL; OBLIQUE WINGS; AERODYNAMIC FORCES; EQUATIONS OF MOTION; LINEAR EQUATIONS;
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Notes: |
IN: 1986 American Control Conference, 5th, Seattle, WA, June 18-20, 1986, Proceedings. Volume 1 (A87-13301 03-63). New York, Institute of Electrical and Electronics Engineers, 1986, p. 472-480. Previously announced in STAR as N86-26339. |
Accessibility: |
Unclassified; Copyright; Unlimited; Publicly available; |
Updated/Added to NTRS: |
2004-11-03 |
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