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Aircraft/Engine Integration for an Advanced Fighter Considering Mission Specifics FREE

[+] Author Affiliations
G. Rauh, W. Anders

Messerschmitt—Boelkow—Blohm GmbH, Muenchen

Paper No. 86-GT-295, pp. V002T02A020; 9 pages
doi:10.1115/86-GT-295
From:
  • ASME 1986 International Gas Turbine Conference and Exhibit
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • Dusseldorf, West Germany, June 8–12, 1986
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7929-0
  • Copyright © 1986 by ASME

abstract

In this paper propulsion system integration is considered for an advanced twin engined, high performance agile air to air fighter aircraft in view of its requirements for extreme flight conditions and maneuvers.

The propulsion system mainly consists of air inlets, engines and nozzle/afterbody systems.

The air inlet, a propulsion subsystem within the aircraft manufacturers responsibility, is physically well integrated with the aircraft flight control system, processing hardware being part of it.

The engine itself, as the most complex propulsion subsystem and not within the aircraft manufacturers responsibility, is to have very simple and clearly defined interfaces with the aircraft. Its integration must therefore be on this basis i.e. functional.

A central utility data bus allows for easy communication between the engine control system and all relevant aircraft systems through a single point interface in normal operation.

This improved communication allows for better performance, operation and handling of the engine.

A special feature of the propulsion system is the vectoring nozzle system with thrust deflection for maneuvers at high angles of attack beyond maximum lift. This system is also integrated with the flight control system.

Copyright © 1986 by ASME
This article is only available in the PDF format.

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