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Rotorcraft Simulation Fidelity Assessment for Low-Speed Maneuvering with Additive System Identification

Lu, L, Agarwal, D, Padfield, GD, Cameron, N and White, M Rotorcraft Simulation Fidelity Assessment for Low-Speed Maneuvering with Additive System Identification. Journal of Aircraft. ISSN 1533-3868 (Accepted)

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High fidelity rotorcraft flight simulation relies on the availability of a quality flight model that further demands a good level of understanding of the complexities arising from aerodynamic couplings and interference effects. This paper explores rotorcraft flight dynamics in the low-speed regime where such complexities abound and presents a new additive system identification approach in the time-domain to aid identification of nonlinear dynamics and fidelity assessment. The new approach identifies flight model parameters sequentially, based on their contribution to the local dynamic response of the system, in contrast with conventional approaches where parameter values are identified to minimize errors over a whole maneuver. In these early investigations, identified low-order rigid-body linear models show good comparison with flight test data from the National Research Council of Canada’s Advanced System Research Aircraft. The approach is extended to explore nonlinearities attributed to so-called maneuver wake distortion effects emerging in larger maneuvers. First results show good correlation with a proposed nonlinear model structure, demonstrated by its capability to capture the time response and variations of the stability and control derivatives with response magnitude.

Item Type: Article
Additional Information: © 2020 AIAA
Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics
Divisions: Engineering
Publisher: American Institute of Aeronautics and Astronautics
Date Deposited: 11 Aug 2020 10:29
Last Modified: 11 Aug 2020 12:01
URI: https://researchonline.ljmu.ac.uk/id/eprint/13475

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