论文部分内容阅读
本研究首先建立飞机机身有限元模型,此模型的模态和全机地面共振试验测得模态相吻合。然后研究起落架缓冲器受力,并编制程序,计算出相关的曲线,LMS仿真平台调用上述曲线对单个起落架进行仿真,在单个起落架仿真结果和落震试验结果吻合的基础上,对某型飞机进行刚性机身全机落震仿真研究。最后调用机身有限元模型进行柔性机身全机落震仿真研究,对刚性机身、柔性机身全机落震仿真结果进行对比,结果表明柔性机身全机着陆起落架载荷峰值比刚性机身载荷峰值降低,起落架功量图更为平缓。
In this study, the finite element model of the fuselage of the aircraft was first established. The modalities of this model were consistent with those of the whole ground resonance test. Then the landing gear bumper force is studied and the program is compiled to calculate the relevant curve. The LMS simulation platform invokes the above curve to simulate a single landing gear. Based on the coincidence between the simulation result of a single landing gear and the drop test, Aircraft simulation of the whole body off-axis simulation of rigid fuselage. Finally, the finite element model of the fuselage was used to carry out the simulation study on the whole body of the flexible fuselage. The simulation results of the whole body and the whole body of the rigid fuselage and the flexible fuselage were compared. The results show that the peak value of the full body landing gear load of the flexible fuselage is higher than that of the rigid body The peak value of body load decreases, landing gear power figure is more gentle.