Перевод названия: Aircraft landing gear wheels actuator
Тип публикации: статья из журнала
Год издания: 2017
Ключевые слова: электромеханический привод, зубчатое колесо, вентильно-индукторный двигатель, electromechanical actuator, gear-wheel, brushless induction motor
Аннотация: Показана схема электромеханического привода колеса шасси самолёта, внутри цилиндрических зубчатых колёс которого установлены бесколлекторные вентильно-индукторные двигатели. Приведены результаты расчётов мотор-редуктора. Экспериментальный образец такого привода показал несомненные преимущества по сравнению с другими приводами. КонсПоказать полностьютруктивное решение мотор-редуктора в колесе шасси самолета не имеет аналогов в России и за рубежом. According to the item of the State Program “Development of the aviation industry for 2013-2025” creation of scientific and technological capacity ensuring global leadership in aviation technology and product promotion of domestic aviation industry on the domestic and foreign markets should ensure high competitiveness of domestic aircraft by introduction of innovative developments. Operation and maintenance analysis of the existing civil aircraft park revealed that while aircraft aerodrome maneuvering the hundreds of kilograms of kerosene are wasted, and drive trucks waste tens of kilograms of fuel. When kerosene burns in an aircraft engine, and fuel burns in combustion engine the atmosphere is contaminated by noxious substances. While aircraft maneuvering on the runway the noise level is 90 dB. Using combined actuator in landing gearwheels will allow decrease negative effect on the environment and eliminate completely the majority of shortcomings. The paper presents the schematic diagram of electromechanical landing gear wheel actuator in which brushless switched-reluctance motors are mounted inside cylindrical gearwheels. Due to low cost materials implementation, small size and weight, low energy consumption and high efficiency maintainability better design and operating characteristics of aircraft landing gear wheel actuator are ensured. While motor-reducer design, specifics of its operation in the landing gear wheel were accounted for. The results of motor-reducer computation, which demonstrated the wide specter of implementation of such kind of actuator for various types of aircraft components, such as landing gear wheels actuators, high-lift device’s elements are given. The presented motor-reducer possesses diversified structural concepts, which allows use it for various types of aircraft both civil and military oriented, as well as for unmanned aerial vehicles (UAV) and spacecraft of various kinds. The prototype of motor-reducer, used for UAV’s high-lift devices, displayed its apparent advantage compared to the other actuators, such as design compactability, manufacturability and cost effectiveness. Implementation of the above-described structure will allow fuel consumption saving by both an aircraft, and airfield servicing facilities. The structural concept of the motor-reducer in aircraft landing gear wheel does not have counterparts either in Russia or abroad.
Журнал: Вестник Московского авиационного института
Выпуск журнала: Т. 24, № 3
Номера страниц: 109-113
ISSN журнала: 08696101
Место издания: Москва
Издатель: Федеральное государственное бюджетное образовательное учреждение высшего образования "Московский авиационный институт (национальный исследовательский университет)"