Flight Evaluation of Modifications to a Digital Electronic Engine Control System in an F-15 Airplane

Burcham Jr., Frank W. and Myers, Lawrence P. (1983) Flight Evaluation of Modifications to a Digital Electronic Engine Control System in an F-15 Airplane. Technical Report NASA TM-83088, Research and Engineering, NASA Dryden Flight Research Center.

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Abstract

The 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 DEEC 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 DEEC 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.

EPrint Type:	NASA Technical Memorandum
Keywords:	Control, Propulsion, Digital
Subjects:	(01 - 09) Aeronautics: (07) Aircraft Propulsion And Power Aircraft/Project: F-15
ID Code:	1978
Deposited On:	29 May 2009
Additional Information:	11 pages. Prepared for the Twenty-First Aerospace Sciences Conference sponsored by the American Institute of Aeronautics and Astronautics, Reno, Nevada, January 10-13, 1983.