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Development and validation of a piloted simulation of a helicopter and external sling loadA generalized, real time, piloted, visual simulation of a single rotor helicopter, suspension system, and external load is described and validated for the full flight envelope of the U.S. Army CH-54 helicopter and cargo container as an example. The mathematical model described uses modified nonlinear classical rotor theory for both the main rotor and tail rotor, nonlinear fuselage aerodynamics, an elastic suspension system, nonlinear load aerodynamics, and a loadground contact model. The implementation of the mathematical model on a large digital computing system is described, and validation of the simulation is discussed. The mathematical model is validated by comparing measured flight data with simulated data, by comparing linearized system matrices, eigenvalues, and eigenvectors with manufacturers' data, and by the subjective comparison of handling characteristics by experienced pilots. A visual landing display system for use in simulation which generates the pilot's forward looking real world display was examined and a special head up, down looking load/landing zone display is described.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Shaughnessy, J. D.
(NASA Langley Research Center Hampton, VA, United States)
Deaux, T. N.
(Sperry Support Services Hampton, Va., United States)
Yenni, K. R.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1979
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
Accession Number
Funding Number(s)
PROJECT: RTOP 505-08-26-01
Distribution Limits
Work of the US Gov. Public Use Permitted.
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