Highly Integrated Digital Engine Control System in an F-15 Airplane

Burcham Jr., Frank W. and Haering Jr., Edward A. (1984) Highly Integrated Digital Engine Control System in an F-15 Airplane. Technical Report NASA TM-86040, Research Engineering, NASA Dryden Flight Research Center.

Full text available as: PDF - Requires Adobe Acrobat Reader or other PDF viewer.

Abstract

The highly integrated digital electronic control (HIDEC) program will demonstrate and evaluate the improvements in performace and mission effectiveness that result from integrated engine-airframe control systems. This system is being used on the F-15 airplane at the Dryden Flight Research Facility of NASA Ames Research Center. An integrated flightpath management mode and an integrated adaptive engine stall margin mode are being implemented into the system. The adaptive stall margin mode is a highly integrated mode in which the airplane flight conditions, the resulting inlet distortion, and the engine stall margin are continuously computed; the excess stall margin is used to uptrim the engine for more thrust. The integrated flightpath management mode optimizes the flightpath and throttle setting to reach a desired flight condition. The increase in thrust and the improvement in airplane performance is discussed in this paper.

EPrint Type:	NASA Technical Memorandum
Keywords:	Integrated control, Digital control, Engine control, F-15 aircraft, Flightpath optimization
Subjects:	Aircraft/Project: F-15 HIDEC (01 - 09) Aeronautics: (07) Aircraft Propulsion And Power Aircraft/Project: F-15
ID Code:	638
Deposited On:	03 Febuary 2006
Additional Information:	12 pages. This paper was prepared as Paper 84-1259 for the 20th AIAA/ASME/SAE Joint Propulsion Conference, Cincinnati, Ohio, June 11-13, 1984.