FEM analysis of the helicopter landing gear hinge

Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F60162694%3AG43__%2F23%3A00537219" target="_blank" >RIV/60162694:G43__/23:00537219 - isvavai.cz</a>
Result on the web
<a href="http://aerospatial-2018.incas.ro/files/final_list_of_participants_section_4-aerospatial_2.pdf" target="_blank" >http://aerospatial-2018.incas.ro/files/final_list_of_participants_section_4-aerospatial_2.pdf</a>
DOI - Digital Object Identifier
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Result language
angličtina
Original language name
FEM analysis of the helicopter landing gear hinge
Original language description
During a long-term operation of a transport helicopter Mi-171 a premature damage of landing gear hinge occur in form of a crack. The article presents the analyses of helicopter operation conditions, landing gear load and landing gear structure in order to determine the load conditions of the hinge. The hinge is than analysed using the Finite Element Method system ANSYS to represent the load conditions leading to the hinge damage and identified are critical load states. Finally, proposed are the operation recommendations and geometrical modifications of the hinge to reduce the risk of the damage.
Czech name
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Czech description
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Project
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Continuities
I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Publication year
2018
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

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