Aerodynamic model identification of turboprop aircraft based on flight test data

• Autorzy: Muhammad H. , Hariowibowo H.
• Języki publikacji: EN

Abstrakty

EN

The aerodynamic model of an aircraft can be considered as a mathematical representation of the forces and moments acting on the aircraft. These forces and moments are usually approximated by polynomials as function of aircraft’s state variables. The coefficients in the polynomials are known as the aerodynamic parameters. These aerodynamic parameters are of importance in the evaluation of aircraft performance and stability-control characteristics of an aircraft. These parameters also can be used in the design of, for example, automatic flight control systems and mathematical model of flight simulator. This paper will discuss the principles of the aerodynamic model identification of the aircraft based on flight test data using parameter identification techniques. The paper starts with discussion of a mathematical model of an aircraft. Next, parameter identification techniques will be described. Two techniques often used for estimation of the aerodynamic parameters will be discussed. Results of the modelling and estimation of the aerodynamic parameters, state trajectory of the aircraft, bias errors in the instrumentation system, and calibration factors of the vane-angle of attack from flight test data of the N-250 turboprop aircraft will be presented in this paper. Original achievement of that paper is the mathematical model of a turboprop aircraft.

Słowa kluczowe

EN

turboprop aircraft; flight testing; parameter identification

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2013
• Tom: Vol. 20, No. 3
• Strony: 275---282
• Opis fizyczny: Bibliogr. 5 poz., rys.

Twórcy

autor

Muhammad H.

• Institut Teknologi Bandung Faculty of Mechanical and Aerospace Engineering Department of Aeronautics and Astronautics Jl. Ganeca 10, Bandung 40132, Indonesia tel.: [phone], fax: [phone]

autor

Hariowibowo H.

• Indonesian Aerospace Industries Flight Test Division Jl. Pajajaran 154, Bandung, Indonesia tel.: [phone], fax: [phone]

Bibliografia

• [1] Mulder, J. A., van Staveren, W. H. J. J., van der Vaart, J. C., Flight Dynamics, Lecture Notes AE3-302, Faculty of Aerospace Engineering, Delft University of Technology, Delft, The Netherlands.
• [2] Klein, V., Morelli, E. A., Aircraft System Identification, AIAA Education Series, U.S.A. 2006.
• [3] Maine, R. E., Iliff, K. W., Identification of Dynamic Systems–Application to Aircraft, Part 1: The Output Error Approach, AGARDograph No. 300, AGARD Flight Test Techniques Series Volume 3, NATO, 1985.
• [4] Mulder, J. A., Sridhar, J. K., Breeman, J. H., Identification of Dynamic Systems–Application to Aircraft, Part 2: Nonlinear Analysis and Manoeuvre Design, AGARDograph No. 300, AGARD Flight Test Techniques Series Vol. 3, NATO, 1994.
• [5] Muhammad, H., Parameter Identification, Lecture Notes AE5033, Faculty of Mechanical and Aerospace Engineering, InstitutTeknologi Bandung, Bandung, Indonesia 2012.