The invention belongs to the technical field of structural strength design, and discloses a helicopter blade pin fatigue life evaluation method considering folding and mooring overload, and the method comprises the following steps: 1, evaluating the blade pin load and fatigue damage of a blade in a folding state; 2, evaluating the load and fatigue damage of the blade pin under mooring overload; and 3, evaluating the fatigue life of the blade pin under the folding state superposition mooring overload.
本发明属于结构强度设计技术领域,公开了一种考虑折叠和系留过载的直升机桨叶销疲劳寿命评估方法,步骤如下:步骤一:评估桨叶折叠状态下的桨叶销载荷及疲劳损伤;步骤二:评估系留过载下桨叶销载荷及疲劳损伤;步骤三:评估折叠状态叠加系留过载下的桨叶销疲劳寿命。
Helicopter blade pin fatigue life evaluation method considering folding and mooring overload
考虑折叠和系留过载的直升机桨叶销疲劳寿命评估方法
2025-01-03
Patent
Electronic Resource
Chinese
IPC: | B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung |