DETERMINATION OF THE THRUST REQUIREMENT FOR A FIGHTER AIRCRAFT ENGINE VIA MISSION ANALYSIS
In order to initiate the design process for a new aeroengine, it would be necessary that a matching study be performed between the aircraft under design and its prospective power plant. In this work wing loading and engine thrust reqiurements are determined. Within this context thrust level is determined for a fighter jet whose mission profile is pre-determined.
While the mission profile is being decided upon a typical first-day-of-the-war mission scenario for a new generation fighter aircraft is considered. Mission legs were handled individually and the solution space is restricted by drawing the corresponding constraint curve for each one. A point within the feasible solutions region is selected regarding the state-of-the-art. For the determined mission profile the appropriate sea level thrust to take-off weight ratio / happens to be around 1.2. At the design point the selected thrust loading is 7.0 kPa. As a result of mission analysis it has been observed that the aircaft spends 1.9% of its take-off weight as ammunition and 58% of its initial take-off weight as fuel. The overall duration for the mission is calculated to be 98 minutes.
 Oates G.C., “Aircraft Propulsion Systems Technology and Design”, AIAA Education Series, ISBN 978-0930403249, 1989.
 Mattingly J.D., “Elements of Propulsion: Gas Turbines ad Rockets”, AIAA Education Series, ISBN 978-1563477799.
 Mattingly J.D.,Heiser, W.H., Pratt, D.T., “Aircraft Engine Design”, AIAA Education Series, 2002.
 Duman S., “Parametric Cycle Analysis and Fan Design of a Low By-Pass Ratio Turbofan Engine”, Lisans Bitirme Tezi, İTÜ Uçak ve Uzay Bilimleri Fakültesi, 2010.
 Aviation Week and Space Technology, 2009 Aerospace Source Book, 2009.
 Janes Information Group, “Janes All The World’s Aircraft”, 92nd Edition, ISBN 978-0710623072, 2001.
 International Civil Aviation Organization, “Manual of the ICAO Standard Atmosphere”, Doc 7488-CD, Third Edition,ISBN 92-9194-004-6 , 1993.
 International Organization for Standardization, “Standard Atmosphere”, ISO 2533:1975, 1975.
 Raymer D.P., “Aircraft Design: A Conceptual Approach”, AIAA Education Series, ISBN 978-1563478291, 2006.
 Jonas, E, “Aircraft Design Lecture Notes”, U.S. Air Force Academy, Colorado Springs, CO, ABD, 1984.
 Knowledge Design Inc., “Missile Index”, http://missile.index.ne.jp/en, 2004.
The manuscript with title and authors is being submitted for publication in Journal of Aeronautics and Space Technologies. This article or a major portion of it was not published, not accepted and not submitted for publication elsewhere. If accepted for publication, I hereby grant the unlimited and all copyright privileges to Journal of Aeronautics and Space Technologies.
I declare that I am the responsible writer on behalf of all authors.