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Flight evaluation of modifications to a digital electronic engine control system in an F-15 airplaneThe third phase of a flight evaluation of a digital electronic engine control system in an F-15 has recently been completed. It was found that digital electronic engine control software logic changes and augmentor hardware improvements resulted in significant improvements in engine operation. For intermediate to maximum power throttle transients, an increase in altitude capability of up to 8000 ft was found, and for idle to maximum transients, an increase of up to 4000 ft was found. A nozzle instability noted in earlier flight testing was investigated on a test engine at NASA Lewis Research Center, a digital electronic engine control software logic change was developed and evaluated, and no instability occurred in the Phase 3 flight evaluation. The backup control airstart modification was evaluated, and gave an improvement of airstart capability by reducing the minimum airspeed for successful airstarts by 50 to 75 knots.
Document ID
19830038375
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Burcham, F. W., Jr.
(NASA Flight Research Center Edwards, CA, United States)
Myers, L. P.
(NASA Flight Research Center Edwards, CA, United States)
Zeller, J. R.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 83-0537
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: Reno, NV
Start Date: January 10, 1983
End Date: January 13, 1983
Accession Number
83A19593
Distribution Limits
Public
Copyright
Other

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