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Real-time hybrid computer simulation of a small turboshaft engine and control systemThe development of an analytical model of a small turboshaft engine designed for helicopter propulsion systems is described. The model equations were implemented on a hybrid computer system to provide a real time nonlinear simulation of the engine performance over a wide operating range. The real time hybrid simulation of the engine was used to evaluate a microprocessor based digital control module. This digital control module was developed as part of an advanced rotorcraft control program. After tests with the hybrid engine simulation the digital control module was used to control a real engine in an experimental program. A hybrid simulation of the engine's electrical hydromechanical control system was developed. This allowed to vary the fuel flow and torque load inputs to the hybrid engine simulation for simulating transient operation. A steady-state data and the experimental tests are compared. Analytical model equations, analog computer diagrams, and a digital computer flow chart are included.
Document ID
19840013480
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Hart, C. E. (NASA Lewis Research Center Cleveland, OH, United States)
Wenzel, L. M. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1984
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.15:83579
E-1968
NASA-TM-83579
Accession Number
84N21548
Funding Number(s)
PROJECT: RTOP 505-34-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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