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A mathematical model of the UH-60 helicopterThis report documents the revisions made to a ten-degree-of-freedom, full-flight envelope, generic helicopter mathematical model to represent the UH-60 helicopter accurately. The major modifications to the model include fuselage aerodynamic force and moment equations specific to the UH-60, a canted tail rotor, a horizontal stabilator with variable incidence, and a pitch bias actuator (PBA). In addition, this report presents a full set of parameters and numerical values which describe the helicopter configuration and physical characteristics. Model validation was accomplished by comparison of trim and stability derivative data generated from the UH-60 math model with data generated from a similar total force and moment math model.
Document ID
19840015585
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Hilbert, K. B.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1984
Subject Category
Aircraft Stability And Control
Report/Patent Number
NASA-TM-85890
USAAVSCOM-TM-84-A-2
NAS 1.15:85890
A-9646
Accession Number
84N23653
Funding Number(s)
PROJECT: RTOP 505-42-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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