| Citation: | WANG Yupeng, HE Qian, XIA Feng, et al. Spatial motion aircraft lift-rising structure fatigue life verification method with coupled multiparameter[J]. Journal of Aerospace Power, 2025, 40（5）：20230566 doi: 10.13224/j.cnki.jasp.20230566
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A structure fatigue life verification method for large aircraft lift-rising components was presented considering the spatial complex motion flap, the real-time direction of the load, multisystem and multiparameter cooperation control and system operation security. A spatial trajectory simulation method based on differential flatness theory was employed to ensure accurate real-time load direction during the flap unfixed-axis rotation. A velocity optimization model of following mechanism and a sequential control method were built to realize multiparameter accurate and dynamic cooperative control. To ensure the operation security of test system, a linkage protection mechanism combined with a communication monitoring method based on high-frequency polling pattern were established for abnormal condition of coupled test system. A spatial motion aircraft lift-rising structure life verification method with coupled multiparameter was established based on accurate load of spatial complex motion flap, multisystem and multiparameter cooperative control and complicated system security protection and the method was validated by a large transport aircraft flap fatigue test. The result showed that the maximum angle error of the load was 1.8°, relative dynamic error of the load was 2.69%, response time of subsystem security protection was 18 ms. The method can meet the requirements of flap fatigue life verification in load accuracy and system operation security protection, and provide a technical support for major project. The method can also provide referential technologies for motion mechanism fatigue life and reliability verification.
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