ESTIMATION OF FATIGUE DURABILITY IN A ZONE OF A JOINT OF LOOPS OF FASTENING OF THE BACK LUGGAGE HATCH OF THE PASSENGER PLANE
DOI:
https://doi.org/10.20535/2305-9001.2013.68.33976Keywords:
fatigue, aircraft, coefficient of reliability, fuselage, fitting, longevity equivalent tension, main tension.Abstract
Modern aviation rules and other normative documents that regulate the order of providing of unconcern and economic efficiency of airplane for to the terms of tireless durability of construction produce the increased requirements to the volume and quality of calculations on the tiredness of basic elements of construction of glider of airplane. The resource of power construction of airplane is determined in this article – compartment of fuselage. For the estimation of tireless durability a FEM was used in the zone of joint of loop of hinge-plate of back luggage hatch. Methodology of determination of tireless descriptions of elements of construction of airplane was also described. 2 pictures of CAD of model of the examined zone and 5 pictures of FEM are presented in the article.References
Strizhius V.E., Semernin A.V. Moscow: Nauchnyj vestnik MGTU GA, Serija: «Ajeromehanika, prochnost', podderzhanie letnoj godnosti VS», 2010. 46 p.
Obespechenie bezopasnosti konstrukcii po uslovijam prochnosti pri dlitel'noj jekspluatacii [Maintenance of safety of a design on durability conditions at long operation]. MOS k AP 25.571. Direktivnoe pis'mo AR MAK ot 30.12.96 g., No 5–96.
Aviacionnye pravila. Chast' 25. Normy letnoj godnosti samoletov transportnoj kategorii [Aviation rules. Part 25. Norms of the flight validity of planes of a transport category]. Moscow: MAK, 2004.
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2014-12-17
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