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现代飞机的设计要求是高可靠性、长寿命和低维修成本,这使得飞机结构的耐久性设计成为飞机研制过程中的重要环节。该文立足于工程实际,通过材料为国产铝合金7050-T7451的某型飞机关键部位模拟件在飞-续-飞随机谱下多种应力水平的耐久性试验,为评定疲劳关键件的耐久性设计提供试验基础,并根据试验结果,评估连接型式,钉传比对结构细节原始疲劳质量的影响。
Modern aircraft design requirements are high reliability, long life and low maintenance costs, which makes the durability of the aircraft structure design an important part of the aircraft development process. Based on the engineering practice, the durability test of various stress levels under the fly-continuation-fly random spectrum was carried out through the simulation of the key parts of a certain type of aircraft made of aluminum alloy 7050-T7451 made of the material. To evaluate the durability of the fatigue- The design provides the basis for the test and, based on the test results, evaluates the effect of the type of connection and nail penetration on the original fatigue quality of the structural details.