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In-flight simulation investigation of rotorcraft pitch-roll cross couplingAn in-flight simulation experiment investigating the handling qualities effects of the pitch-roll cross-coupling characteristic of single-main-rotor helicopters is described. The experiment was conducted using the NASA/Army CH-47B variable stability helicopter with an explicit-model-following control system. The research is an extension of an earlier ground-based investigation conducted on the NASA Ames Research Center's Vertical Motion Simulator. The model developed for the experiment is for an unaugmented helicopter with cross-coupling implemented using physical rotor parameters. The details of converting the model from the simulation to use in flight are described. A frequency-domain comparison of the model and actual aircraft responses showing the fidelity of the in-flight simulation is described. The evaluation task was representative of nap-of-the-Earth maneuvering flight. The results indicate that task demands are important in determining allowable levels of coupling. In addition, on-axis damping characteristics influence the frequency-dependent characteristics of coupling and affect the handling qualities. Pilot technique, in terms of learned control crossfeeds, can improve performance and lower workload for particular types of coupling. The results obtained in flight corroborated the simulation results.
Document ID
19890005747
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Watson, Douglas C. (NASA Ames Research Center Moffett Field, CA, United States)
Hindson, William S. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1988
Subject Category
Aircraft Stability And Control
Report/Patent Number
NAS 1.15:101059
A-89016
NASA-TM-101059
Accession Number
89N15118
Funding Number(s)
PROJECT: RTOP 505-66-51
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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