Fatigue life stimation of structural element of MI-24 Helicopter

• Autorzy: Baraniecki R. , Kaniewska M.
• Języki publikacji: EN

Abstrakty

EN

Operated helicopter is submitted to varying loads spectrum. Important, for the sake of assurance structure integrity, is definition of the actual value of loads which act on individual structure element. The object of this analysis was the Mi-24 helicopter swashplate lever arm. Life estimation of this element with analytical method, for the sake of complicated geometry, can be problematical. It would be necessary to use considerable generalization which would certainly decrease results reliability. Numerical analysis allows one to create arbitrary shapes but it is necessary to properly define boundary condition. These work presents methodology for determining fatigue life of the structure element with use of strain gauges, which serve to define the real flight loads. Next step was to determine accurate element shape with the aid of 3D scanner ATOSIII. Geometry was imaged in CAD/CAM environment. After importing the geometry model to MSC.Patran the numerical model was developed. The analysis was done in the scope of linear static analysis. Estimation of fatigue life was done with the aid of MSC.Fatigue computer program. Fatigue life was estimated according to the Palmgren's - Miner's cumulation damage rule. Test was done in order to define potential fatigue damage sites and defining fatigue life of element. That allows verifying plane overhaul life and fully using helicopters potential next to keeping requested level of safety.

Słowa kluczowe

EN

fatigue life; damage; S-N curve; spectrum loads; numerical calculations

• 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: 2011
• Tom: Vol. 18, No. 2
• Strony: 9--15
• Opis fizyczny: Bibliogr. 7 poz., rys.

Twórcy

autor

Baraniecki R.

autor

Kaniewska M.

• Air Force Institute of Technology, Division for Reliability and Safety of Aeronautical Systems' Ksiecia Boleslawa Street 6, 01-494 Warszawa, Poland phone:[phone], fax: [phone],

Bibliografia

• [1] [1] Lyebyedyeb, A. A., Kobal'chook, B. I., Giginyak, F. F., Lamashyebskiy, V. P., Mexanichyeskiye cboystba konsmpyktsionnih matyerialob pri clozhnom napryazhyennom sostoyanii –Cprabochnik, Akadyemiya Naook Ukrainskoy SSR Institut Problyem Prochnosti, Kiyeb Naookoba Doomka 1983. Linear Static, Normal Modes, and Buckling Analysis Using MSC/NASTRAN and MSC/PATRAN Volume 1, The MacNeal-Schwendler Corporation 1998.
• [2] Skorupa, M., Metoda naprężenia nominalnego, http://kwit.imir.agh.edu.pl/mskorupa/pdf/04.pdf
• [3] Numeryczna analiza stanu wytężenia materiału w skrzydle śmigłowca Mi-24, Sprawozdanie Nr 86/31/2009 ITWL, Warszawa 2009.
• [4] Skalowanie czujników tensometrycznych zabudowanych na elementach demontowalnych śmigłowca Mi-24D nr fabryczny 103174 (nr boczny 174), Sprawozdanie Nr 116/31/2008 ITWL, Warszawa 2008.
• [5] Sprawozdanie z pomiaru obciążeń konstrukcji śmigłowca Mi-24D systemem KAM-500, Sprawozdanie Nr 10/36/2009 ITWL. Warszawa 2009.
• [6] Wyznaczanie profilu średniego śmigłowców Mi-24, Sprawozdanie Nr 36/31/2008 ITWL, Warszawa 2008.
• [7] Wyznaczenie trwałości wybranych elementów struktury w śmigłowcu Mi-14, Sprawozdanie Nr 29/31/2004 ITWL, Warszawa 2004.