DocumentCode :
3167964
Title :
Anti-windup compensation of rate saturation in an experimental aircraft
Author :
Brieger, Oliver ; Kerr, Murray ; Leissling, D. ; Postlethwaite, Ian ; Sofrony, Jorge ; Turner, Matthew C.
Author_Institution :
Inst. of Flight Syst., Braunschweig
fYear :
2007
fDate :
9-13 July 2007
Firstpage :
924
Lastpage :
929
Abstract :
This paper describes the design, flight testing and accompanying analysis of two anti-windup (AW) compensators for an experimental aircraft - the German Aerospace Center´s (DLR) advanced technologies testing aircraft (ATTAS). The AW compensators were designed to reduce the deleterious effects of rate-saturation of the aircraft´s actuators on handling qualities. The AW compensators were flight-tested and assessed using the resulting pilot comments, in the form of handling qualities ratings (HQR´s) and pilot-involved-oscillation ratings (PIOR´s), and flight test data. These media demonstrate that the AW compensators improved the predictability and handling of the aircraft. The results also provide an initial understanding of the relationship between the theory and design choices for AW controllers and the response of the piloted aircraft during periods of rate saturation.
Keywords :
actuators; aircraft control; compensation; control nonlinearities; control system analysis; control system synthesis; German Aerospace Center; actuators; advanced technologies testing aircraft; anti-windup compensator design; experimental aircraft; flight testing; handling qualities ratings; pilot-involved-oscillation ratings; rate saturation; Actuators; Aerospace control; Aerospace engineering; Aerospace testing; Aircraft propulsion; Cities and towns; Control systems; Stability; System performance; Systems engineering and theory;
fLanguage :
English
Publisher :
ieee
Conference_Titel :
American Control Conference, 2007. ACC '07
Conference_Location :
New York, NY
ISSN :
0743-1619
Print_ISBN :
1-4244-0988-8
Electronic_ISBN :
0743-1619
Type :
conf
DOI :
10.1109/ACC.2007.4282674
Filename :
4282674
Link To Document :
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