The invention belongs to the technical field of aircraft fatigue tests, and particularly relates to a full-aircraft fatigue test loading design method based on internal force and service life control. The minimum influence of a test loading scheme on stress/life is directly taken as a design optimization target, and the influence of a test centralized loading scheme on test assessment is quantified, so that the whole-aircraft fatigue test is closer to assessment verification under an external field actual flight load, and the test quality and the test result reliability are improved.
本发明属于飞机疲劳试验技术领域,具体涉及一种基于内力与寿命控制的全机疲劳试验加载设计方法。直接以试验加载方案对应力/寿命的影响最小为设计优化目标,量化试验集中加载方案对试验考核的影响,使全机疲劳试验更加接近外场实际飞行载荷下的考核验证,提高试验质量和试验结果可靠性。
Full-aircraft fatigue test loading design method based on internal force and life control
一种基于内力与寿命控制的全机疲劳试验加载设计方法
23.01.2024
Patent
Elektronische Ressource
Chinesisch
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 |
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