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Rotorcraft control system design for uncertain vehicle dynamics using quantitative feedback theoryQuantitative Feedback Theory describes a frequency-domain technique for the design of multi-input, multi-output control systems which must meet time or frequency domain performance criteria when specified uncertainty exists in the linear description of the vehicle dynamics. This theory is applied to the design of the longitudinal flight control system for a linear model of the BO-105C rotorcraft. Uncertainty in the vehicle model is due to the variation in the vehicle dynamics over a range of airspeeds from 0-100 kts. For purposes of exposition, the vehicle description contains no rotor or actuator dynamics. The design example indicates the manner in which significant uncertainty exists in the vehicle model. The advantage of using a sequential loop closure technique to reduce the cost of feedback is demonstrated by example.
Document ID
19950039583
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Hess, R. A.
(Univ. of California, Davis, CA United States)
Date Acquired
August 16, 2013
Publication Date
April 1, 1994
Publication Information
Publication: American Helicopter Society, Journal
Volume: 39
Issue: 2
ISSN: 0002-8711
Subject Category
Aircraft Stability And Control
Accession Number
95A71182
Funding Number(s)
CONTRACT_GRANT: NCC2-624
Distribution Limits
Public
Copyright
Other

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