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Preliminary design-lift/cruise fan research and technology airplane flight control systemThis report presents the preliminary design of a stability augmentation system for a NASA V/STOL research and technology airplane. This stability augmentation system is postulated as the simplest system that meets handling qualities levels for research and technology missions flown by NASA test pilots. The airplane studied in this report is a T-39 fitted with tilting lift/cruise fan nacelles and a nose fan. The propulsion system features a shaft interconnecting the three variable pitch fans and three power plants. The mathematical modeling is based on pre-wind tunnel test estimated data. The selected stability augmentation system uses variable gains scheduled with airspeed. Failure analysis of the system illustrates the benign effect of engine failure. Airplane rate sensor failure must be solved with redundancy.
Document ID
19770004121
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Gotlieb, P. (Boeing Aerospace Co. Seattle, WA, United States)
Lewis, G. E. (Boeing Aerospace Co. Seattle, WA, United States)
Little, L. J. (Boeing Aerospace Co. Seattle, WA, United States)
Date Acquired
September 3, 2013
Publication Date
November 1, 1976
Subject Category
Aircraft Stability And Control
Report/Patent Number
D180-20216-1
NASA-CR-137971
Accession Number
77N11064
Funding Number(s)
CONTRACT_GRANT: NAS2-9177
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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