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A piloted simulation study of the effects of controller force gradient in VTOL hovering flightA study of the effect of control force gradient on the VTOL visual hovering task was conducted on the NASA-Ames Research Center Six-Degree-of-Freedom Motion Simulator. Lateral control force-gradient characteristics were evaluated in combination with three different types of stabilization systems: An unstabilized (acceleration) system, a rate-stabilized system, and two attitude-stabilized systems. The effects of gust disturbances were included in the control force evaluation for the attitude systems. A force gradient of 1.0 lb/in was within the optimum range for all control systems and conditions evaluated in this study.
Document ID
19730008288
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Fry, E. B. (NASA Ames Research Center Moffett Field, CA, United States)
Gerdes, R. M. (NASA Ames Research Center Moffett Field, CA, United States)
Schroers, L. G. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1973
Subject Category
Aircraft
Report/Patent Number
NASA-TM-X-62230
Report Number: NASA-TM-X-62230
Accession Number
73N17015
Funding Number(s)
PROJECT: RTOP 721-04-00-01-00
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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