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Nonlinear Dynamic Inversion Baseline Control Law: Architecture and Performance PredictionsA model reference dynamic inversion control law has been developed to provide a baseline control law for research into adaptive elements and other advanced flight control law components. This controller has been implemented and tested in a hardware-in-the-loop simulation; the simulation results show excellent handling qualities throughout the limited flight envelope. A simple angular momentum formulation was chosen because it can be included in the stability proofs for many basic adaptive theories, such as model reference adaptive control. Many design choices and implementation details reflect the requirements placed on the system by the nonlinear flight environment and the desire to keep the system as basic as possible to simplify the addition of the adaptive elements. Those design choices are explained, along with their predicted impact on the handling qualities.
Document ID
Acquisition Source
Armstrong Flight Research Center
Document Type
Conference Paper
Miller, Christopher J.
(NASA Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
August 25, 2013
Publication Date
August 8, 2011
Subject Category
Aircraft Stability And Control
Report/Patent Number
Meeting Information
Meeting: AIAA Guidance, Navigation, and Control Conference
Location: Portland, OR
Country: United States
Start Date: August 8, 2011
End Date: August 11, 2011
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Work of the US Gov. Public Use Permitted.
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