Computational simulation of fully trimmed flight of a helicopter in hover

• Autorzy: Stalewski Wieńczysław , Zalewski Wiesław , Surmacz Katarzyna , Pulfer Maximilian , Hirsch Frieder

Identyfikatory

DOI

10.2478/kones-2019-0021

• Języki publikacji: EN

Abstrakty

EN

In trimmed flight of a helicopter, all the forces and moments, aerodynamic, inertial, and gravitational, are in balance. Keeping the helicopter in trimmed state, needs a precise adjustment of flight controls. The methodology of simulation of a fully trimmed flight of rotorcraft has been developed and applied to simulate hover of a helicopter. The presented approach is based on a solution of Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations. In contrast to typical solutions of such problem, in the newly developed methodology, the flight controls corresponding to the trimmed-flight conditions are also determined based on the solution of URANS equations. The methodology is based on coupling of several computational models of Computational Fluid Dynamics and Flight Dynamic. The URANS equations are solved in a three-dimensional region surrounding the flying helicopter, using the ANSYS FLUENT code. The approach is truly three-dimensional, with truly modelled geometry and kinematics of main and tail rotor blades. This applies to modelling of blade flapping and lead-lag motion, too. The trimming procedure uses six independent parameters (i.e. collective and cyclic pitch of main rotor blades, collective pitch of tail rotor blades, pitch, and bank angles of a helicopter) that should be adjusted so as to balance all forces and moments acting on the helicopter. The detailed description of the developed methodology as well as the results of simulation of trimmed hover of the helicopter was presented.

Słowa kluczowe

EN

helicopter flight simulation; hover; trimmed flight; URANS

• 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: 2019
• Tom: Vol. 26, No. 1
• Strony: 175--181
• Opis fizyczny: Bibliogr. 4 poz., rys.

Twórcy

autor

Stalewski Wieńczysław

• Institute of Aviation Krakowska Av. 110/114, 02-256 Warszawa, Poland tel.:[phone] fax: [phone]

autor

Zalewski Wiesław

• Institute of Aviation Krakowska Av. 110/114, 02-256 Warszawa, Poland tel.:[phone] fax: [phone]

autor

Surmacz Katarzyna

• Institute of Aviation Krakowska Av. 110/114, 02-256 Warszawa, Poland tel.:[phone] fax: [phone]

autor

Pulfer Maximilian

• Kopter Germany GmbH

autor

Hirsch Frieder

• Kopter Germany GmbH

Bibliografia

• [1] Inc., ANSYS FLUENT User's Guide. Release 18.5. Available from: http://www.ansys.com.
• [2] Peters, D. D., Barwey, D., A general theory of rotorcraft trim, Mathematical Problems in Engineering, Vol. 2, Is. 1, pp. 1-34, 1996.
• [3] Peters, D. A., Chouchane, M., Fulton, M., Helicopter trim with flap-lag-torsion and stall by an optimized controller, Journal of Guidance, Control, and Dynamics, Vol. 13, No. 5, pp. 824-834, 1990.
• [4] Hassan, H. S., Bayoumy, A. M., El-Bayoumi, G. M., Abdelrahman, M. M., Modelling, Trimming and Simulation of a Full-Scale Helicopter, 7th International Conference on Aerospace Sciences & Aviation Technology, ASAT-17, Cairo, Egypt 2017. 181

Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2019).