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首先建立机身的有限元模型,该模型的模态与全机地面共振(GVT)试验测得模态相吻合。然后分析起落架缓冲器受力,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与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分析。最后调用机身有限元模型进行柔性机身全机落震仿真分析,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。该方法可为起落架设计提供更加准确的设计参考。
First of all, a finite element model of the fuselage is established. The modal of this model is consistent with the measured modal of the whole ground resonance (GVT) test. Then analyze the force of the landing gear buffer, and program to calculate the relevant curve, LMS simulation platform to call the curve of a single landing gear simulation, a single landing gear simulation results and drop test results on the basis of a Plane aircraft simulation of the whole body off-line simulation of rigid body. Finally, the finite element model of the fuselage is used to carry out the simulation analysis of the whole body of the flexible fuselage. The comparison of the simulation results of the whole body and the whole body of the rigid fuselage and the flexible fuselage is carried out. The results show that: The fuselage peak load is reduced, landing gear power map is more gentle. This method can provide a more accurate design reference for landing gear design.