考虑胎压变化影响的某型号飞机主轮流固耦合有限元分析

本文研究飞机着陆过程中轮胎受冲击载荷发生大变形,引起轮胎内充气压力变化对轮毂受力状况的影响。采用CATIA建立该型号机轮轮毂及轮胎的模型,运用ANSYS对机轮组件进行静强度分析。为衡量充气压力变化,引入空气单元及流固耦合迭代。结果表明,在飞机着陆过程中胎压变化为6%。仿真结果和径侧向载荷试验对比,轮胎变形误差不大于4%,轮毂形变误差不大于3%。本文对于对偏置单腹板轮毂的强度校核具有实际参考价值。

Structure Optimization of a Certain Type of Aircraft Nose Wheel Hub

A non-linear multi-laminated static state finite element (FE) model of a transport aircraft wheel assembly facing impact load is simulated. In this model, the inflation pressure is varying while tyre deforming. Software CATIA is used to build the geometry model, ANSYS is used to set up the static-state analysis. To simulate the variation of inflation pressure, fluid element and fluid-structure coupling is used. Material nonlinearity (rubber hyperelastic behavior), geometric nonlinearity (the large deformation of the tyre), and the contact nonlinearity (the contact between the tyre and rigid wall) are studied. Compared with the experimental tests, the error in wheel deformation and tyre deflection is not greater than 3% and 4%, the tyre pressure is 6% greater than the initial one. Compared with FE model without iterations, the results come closer to the experimental data.