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A procedure for establishing an approximate helicopter performance model
Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
2011 (English)In: 3rd CEAS Air&Space Conference: CEAS 2011 Post-Conference Proceedings, Bologna, Italy: Con-fine Ed. Monghidoro , 2011, 952-959 p.Conference paper (Other academic)
Abstract [en]

The main performance characteristics of a heli- copter is its fuel consumption. This paper re- ports the current state in an ongoing project seeking a fast and approximative implementa- tion of mathematical models for helicopter per- formance predictions, primarily in terms of fuel consumption. The model is limited to a subset of the normal operation modes, only including hover, climb and forward. Also, the focus is on smaller rotors, i.e. sub-scale rotors in the range of 1.5m to 4.0m in diameter as used in unmanned airborne vehicles (VTOL-UAV). The presented work consists of three parts; the heli- copter performance mathematical model and the numerical optimization method used for dealing with its implicit nature, the approximation grid scheme and the simulation of flight paths. The overall objective of the project is to establish an computational efficient approximative model us- able for onboard condition monitoring of the he- licopter performance and fuel consumption. 

Place, publisher, year, edition, pages
Bologna, Italy: Con-fine Ed. Monghidoro , 2011. 952-959 p.
Keyword [en]
rotorcraft, helicopter, rotor, mathematical model, UAV
National Category
Aerospace Engineering
URN: urn:nbn:se:liu:diva-71718ISBN: 978-88-96427-42-2OAI: diva2:453416
3rd CEAS Air&Space Conference, 21st AIDAA Congress, San Giorgio Maggiore Island - Venice, Italy, 24-28 October 2011
Available from: 2011-11-10 Created: 2011-11-02 Last updated: 2014-03-03Bibliographically approved

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Sethson, Magnus
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