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Simulation model of a twin-tail, high performance airplaneThe mathematical model and associated computer program to simulate a twin-tailed high performance fighter airplane (McDonnell Douglas F/A-18) are described. The simulation program is written in the Advanced Continuous Simulation Language. The simulation math model includes the nonlinear six degree-of-freedom rigid-body equations, an engine model, sensors, and first order actuators with rate and position limiting. A simplified form of the F/A-18 digital control laws (version 8.3.3) are implemented. The simulated control law includes only inner loop augmentation in the up and away flight mode. The aerodynamic forces and moments are calculated from a wind-tunnel-derived database using table look-ups with linear interpolation. The aerodynamic database has an angle-of-attack range of -10 to +90 and a sideslip range of -20 to +20 degrees. The effects of elastic deformation are incorporated in a quasi-static-elastic manner. Elastic degrees of freedom are not actively simulated. In the engine model, the throttle-commanded steady-state thrust level and the dynamic response characteristics of the engine are based on airflow rate as determined from a table look-up. Afterburner dynamics are switched in at a threshold based on the engine airflow and commanded thrust.
Document ID
19920024293
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Buttrill, Carey S.
(NASA Langley Research Center Hampton, VA, United States)
Arbuckle, P. Douglas
(NASA Langley Research Center Hampton, VA, United States)
Hoffler, Keith D.
(Vigyan Research Associates, Inc., Hampton VA., United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1992
Subject Category
Aircraft Stability And Control
Report/Patent Number
NASA-TM-107601
NAS 1.15:107601
Accession Number
92N33537
Funding Number(s)
CONTRACT_GRANT: NAS1-18585
PROJECT: RTOP 505-64-30-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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