The non-linear strength-work of all body constructions the helicopter is - 2 during failure landing

• Autorzy: Fraczek K. S.
• Języki publikacji: EN

Abstrakty

EN

The article presents the phases of helicopter's flight during the failure of the power - driven system. On the basis of Federal Regulations part 27, which demands the throw from the height of 19 inches, some computer simulations of dynamical construction work were performed. Accordingly to the F.R.27 a thin wall constructions cannot be damaged permanently. In order to show the correct work of the helicopters construction a structure model was built using the finite element method. The paper contains only the work of some main elements, which influence the safety of passengers. The final conclusions were formulated based on the assessment of the method of analysis and based on the results of analytical simulations done on the movements and increasing inertia forces were introduced to the model. In order to analyse the construction its work of resistance was assessed as well as the safety factor. Due to the increasing load, we observed that a deformation of some elements was increasing in a non-linear manner. Therefore the analysis had to be done using the non-linear methods. The loads during landing without power are too much more as during optimal method, which was been presents in [1], the probability landing on ice with failure engine is very small, the non-linear analysis was necessary, because loads on deformed structure were bigger than in linear analysis, the landing without power is all safe in all extremely situations. The article describes construction's prototype.

Słowa kluczowe

EN

transport; helicopter; mechanic; FEM; non-linear analysis

• 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: 2008
• Tom: Vol. 15, No. 4
• Strony: 133--138
• Opis fizyczny: Bibliogr. 4 poz., rys.

Twórcy

autor

Fraczek K. S.

• Institute of Aeronautics Department of New Technology Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.: + 48 22 8460011,

Bibliografia

• [1] Bibik, P., Gajda, K., Narkiewicz, J., Metoda optymalnego sterowania śmigłowca w autorotacji, Journal of Aeronautica Integra 1/2008.
• [2] Federal Requirements of Aeronautics Part 27 - Waszyngton, D. C.
• [3] Frączek, K., A., Method of non-linear dynamics on purpose construction light helicopter IS -2, Journal of KONES2006 Vol. 13. No. 3.
• [4] Szablewski, K., Jancelewicz, B., Łucjanek, W., Wstęp do konstrukcji śmigłowców, WKŁ 2002.