Flight Evaluation of a Digital Electronic Engine Control System in an F-15 Airplane. Meeting Paper AIAA-1982-1080, Research Engineering, NASA Dryden Flight Research Center

Myers, Lawrence P. and Mackall, Karen G. and Burcham Jr., Frank W. and Walter, Wayne A. (1982) Flight Evaluation of a Digital Electronic Engine Control System in an F-15 Airplane. Meeting Paper AIAA-1982-1080, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

A full-authority digital electronic engine control (DEEC) was flight tested on an F100-PW-100 turbofan engine installed in an F-15 airplane at NASA Dryden Flight Research Facility. The engine pressure ratio (EPR) control mode was demonstrated. Airstarts were successful at both 40-percent and 25-percent spooldown rotor speeds to an airspeed of 200 knots. Nonaugmented throttle transients and engine performance were satisfactory. The backup control (BUC) was quite successful throughout the entire F-15 envelope. The failure-detection and accommodation feature was effective in detecting failures. No automatic transfers to the backup control occurred. All augmentor transients were successful with a maximum segment-1 limiting feature. With full augmentation, successful transients were expected to be accomplished at a Mach number of 0.8 at 47,000 ft, based on altitude cell test results. During flight, however, augmentor anomalies were encountered that limited successful operation to 0.8 Mach at 40,000 ft.

EPrint Type:	Other
Keywords:	Digital Electronic Engine Control (DEEC), F-15 airplane
Subjects:	Aircraft/Project: F-15
ID Code:	1557
Deposited On:	05 June 2007
Additional Information:	14 pages. AIAA/SAE/ASME 18th Joint Propulsion Conference, Cleveland, Ohio, June 21-23, 1982.