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Decoupling control synthesis for an oblique-wing aircraftInterest 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.
Document ID
19860016867
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Alag, G. S. (University of Western Michigan Kalamazoo, United States)
Kempel, R. W. (NASA Ames Research Center Moffett Field, CA, United States)
Pahle, J. W. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1986
Subject Category
Aircraft Stability And Control
Report/Patent Number
H-1339
NAS 1.15:86801
NASA-TM-86801
Meeting Information
Meeting: American Control Conference
Location: Seattle, WA
Country: United States
Start Date: June 18, 1986
End Date: June 20, 1986
Accession Number
86N26339
Funding Number(s)
PROJECT: RTOP 533-06-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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