ANALYSIS OF THE EXHAUSTION RATE OF RESOURCE INDICATORS OF POWER ELEMENTS OF IL-76 AIRCRAFT ACCORDING TO THE ACTUAL LOAD OF POWER STRUCTURE
DOI:
https://doi.org/10.54858/dndia.2021-17-11Keywords:
fatigue strength, relative damage at fatigue, resource consumption equivalent, resource consumption coefficient, operation according to technical conditionAbstract
Many leading specialists of aircraft design bureaus and industry research institutions still not consider individual (detailed) calculations of the durability of the main power structure elements of the aircraft on fatigue a mandatory element of working design. Until now, there is an opinion in the industry that field tests on fatigue of structural elements and glider units "by themselves" will reveal all potentially critical zones of structural elements and will allow to obtain an experimental assessment of the durability of these zones on fatigue. Therefore, full-scale calculations of the durability of individual structural elements of the aircraft on fatigue is practically not required, there is no special need for methods of such calculations. The consequence of such a policy was a clear lag in domestic industry methods for calculating the durability of elements of aircraft structures on fatigue from foreign ones.
Without diminishing the importance of field tests on the fatigue of the entire aircraft, the authors believe that this attitude to individual (detailed) calculations of durability on fatigue is a systemic error that has already led to the design of aircraft with serious shortcomings that directly affect safety and cost-effectiveness aircraft. These shortcomings are usually detected during the period of intensive operation of the entire fleet of aircraft, so field tests for fatigue of glider units (or glider as a whole) in practice are carried out for a long time, and the amount of fatigue tests of individual designs is limited.
The need for individual (detailed) calculations of the durability of the elements of the main power structure on fatigue, in particular the wings of the aircraft, to extend the operation of aircraft type IL-76 is obvious. Such studies make it possible to reasonably approach the choice of material, stresses, design and technological solutions of power elements, to ensure the optimal ratio between the durability of the structure on fatigue and economic efficiency of the aircraft as a whole.
References
Юхачов В.В., Харченко О.В., Пащенко С.В., Хільченко М.Ф. Коливання і ресурс авіаційних конструкцій. Під ред. О.В.Харченка. – Одеса, 2010. – 128с.
Барзилович Е.Ю., Савенков М.В. Статистические методы оценки состояния авиационной техники. – М.: Транспорт, 1987. – 240 с.
Ильичев В.Д. Расчет текущего безопасного ресурса конструкции. Труды ЦАГИ, 1972. – Вып.1391. – 24 с.
Иосилевич Г.Б. Детали машин. – М.: Машиностроение, 1988. – 368 с.
Зайцев В.Н., Рудаков В.Л. Конструкция и прочность самолетов, К.: Вища школа, 1978. – 487 с.
Гудков А.И., Лешаков П.С. Внешние нагрузки и прочность летательных аппаратов. – М.: Машиностроение, 1968. – 470 с.
Райхер В.Л., Француз Т.А. Рекомендации ЦАГИ по способам расчета усталостных повреждений и оценки ресурса конструкции самолетов. – Отчет ЦАГИ, 1971. – № 711. – 22 с.
Райхер В.Л., Цымбалюк В.И., Лейбов В.Г. Рекомендации по способам расчета повторяемости нагрузок, усталостного повреждения и оценке ресурса конструкции самолета на этапе проектирования. – Труды ЦАГИ, 1974, вып. 1219. – 45 с.
Справочник по авиационным материалам. Том 1, Том 3, – М.: Машиностроение, 1965. – З65 с.
Панасюк В.В. Деякі актуальні проблеми міцності матеріалів і довговічності конструкцій – Фізико-хімічна механіка матеріалів // 2009. – №2. – С. 5-22.
Вапник В.Н., Червоенекис А.Я. Теория распознавания образов. – М.: Наука, 1974. – 416 с.
Вентцель Е.С. Теория вероятностей // 10-е издание. – М.: Высшая школа, 2006. – 575 с.
