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在研究以往飞机载荷校准试验时非静定支持与约束方式的基础上,首次提出了飞机六自由度静定支持与约束方法;根据载荷校准试验得到的飞机受力分析结果,对飞机起落架支持与约束载荷进行了分解和简化,建立了飞机六自由度静定支持与约束工程模型;结合某型飞机的载荷校准试验对该方法进行了试验验证,结果表明:采用该方法可实现对飞机约束载荷的理论计算和实时监控,保证了飞机机翼等复杂结构部件在高载校准工况下试验过程的安全、可控;使飞机机翼的试验载荷量级提高到了限制载荷的43%,机翼载荷建模精度可控制在3%以内。
On the basis of studying the non-static support and restraint methods in the past aircraft load calibration tests, the six-degree-of-freedom support and restraint method of the aircraft was firstly proposed. Based on the results of the aircraft stress analysis of the load calibration test, the aircraft landing gear support And constraint load are decomposed and simplified. The six-degree-of-freedom support and constraint engineering model of the aircraft is established. The method is verified with the load calibration test of a certain type of aircraft. The results show that this method can be used to control the aircraft The theoretical calculation and real-time monitoring of the load ensure the safety and controllability of the testing process of complex structural components such as aircraft wings under high load calibration conditions. The test load of the aircraft wing is increased to 43% of the limit load. Wing load modeling accuracy can be controlled within 3%.