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Information × Registration Number 0212U000070, 0108U009952 , R & D reports Title Aircraft Structures Life Prediction Theory under the random loading conditions popup.stage_title Head Fomichev Petro, Registration Date 13-01-2012 Organization National aerospase university Kharkiv Aviation Institute popup.description2 The scientific work covers the development and implementation of theoretical methods and software for calculation of loads and durability for the aircraft wing subjected to random loading in the turbulent atmosphere. The aim of the work is to increase the operational safety and lifetime of aircraft, as well as to reduce the time and costs of designing, testing and refinement of structure. The object of investigation is an aircraft structure which is designed for the given lifetime taking into account the economic efficiency and minimal weight requirements, and which is operated under the random loading. The subjects of investigation are laws of random flight loading and laws of fatigue damage accumulation in structural elements. Analytic methods were used to study loads acting on the wing during the flight. The finite element method was extensively used for calculations of stress state of structure. Damaging force factors were analyzed using probabilistic and statistical methods basing on the mathematical simulation of dynamic loading process. Experimental researches were held at specialized test stands designed in NIL "Prochnost". The scientific novelty of the investigation consists of the new method development for calculation of durability of regular and irregular zones of structures subjected to random loading which is conditioned by atmosphere turbulence and therefore is typical for aircraft operation. The method is an advancement of the method previously developed in "KhAI" for durability calculation up to crack initiation under programmed loading, basing on the energetic fracture criterion and fatigue and cyclic strain properties of material. For the first time the problem of durability calculation under random loading was solved without empirical coefficients relating to the durability under specific loading spectrum. The method allows to exclude additional testing of structural elements when choosing the rational design during the designing or modernization of aircraft structure. The method also allows to determine the damage equivalent for testing program or spectrum of operational loads, and to determine the allowable stresses ensuring the durability of regular zones of structure. The obtained results could be used to cut the required volume of fatigue testing and total costs of designing, testing, modernization and operation of aircraft. The economic impact of the project is ensured by the increasing of aircraft lifetime and reliability due to the optimization of structure and typical flight. Product Description popup.authors Бойко Тетяна Сергіївна Вакуленко Сергій Володимирович Гребенюк Ярослав Володимирович Заруцький Анатолій Вікторович Колишкін Антон Сергійович Кучерявий Євген Федорович Мандзюк Сергій Федорович Пінчук Діамар Олександрович Решетнікова Рената Юсуфівна Тишецький Олег Іванович Третьяков Олексій Сергійович Трубчанин Ігор Юрьєвич Фомичов Петро Олександрович Черних Олексій Олексійович popup.nrat_date 2020-04-02 Close