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Robust control of hypersonic vehicles considering propulsive and aeroelastic effectsThe influence of propulsion system variations and elastic fuselage behavior on the flight control system of an airbreathing hypersonic vehicle is investigated. Thrust vector magnitude and direction changes due to angle of attack variations affect the pitching moment. Low structural vibration frequencies may occur close to the rigid body modes influencing the angle of attack and lead to possible cross coupling. These effects are modeled as uncertainties in the context of a robust control study of a hypersonic vehicle model accelerating through Mach 8 using H-infinity and mu synthesis techniques. Various levels of uncertainty are introduced into the system. Both individual and simultaneous appearance of uncertainty are considered. The results indicate that the chosen design technique is suitable for this kind of problem provided that a fairly good knowledge of the effects mentioned above is available. The order of the designed controller is reduced but robust performance is lost which shows the need for fixed order design techniques.
Document ID
19930067360
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Buschek, Harald
(NASA Langley Research Center Hampton, VA, United States)
Calise, Anthony J.
(Georgia Inst. of Technology Atlanta, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA Guidance, Navigation and Control Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers. Pt. 1 (A93-51301 22-63)
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 93-3762
Accession Number
93A51357
Funding Number(s)
CONTRACT_GRANT: NAG1-1451
Distribution Limits
Public
Copyright
Other

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