基于MEMS的航空压力传感器结构力学分析

Structural Mechanics Analysis on Aviation Pressure Sensor Based on MEMS

基于应力驱动的两相局部/非局部积分模型,研究了航空压力传感器中的微尺度欧拉梁的的力学特性。通过将本构方程转换为Volterra积分方程,再利用拉普拉斯变换可得到积分—微分方程的一般解,最后通过边界条件和约束方程可以获取微尺度欧拉梁在不同边界条件下的弯曲解析解和弯曲数值解。对于屈曲和自由振动问题,通过求线性齐次方程组的非零解可以获得屈曲载荷和振动频率,无量纲化结果可以表明一致的强化效应,即不同边界条件下,随着非局部参数的增大,挠度减小,而屈曲载荷和振动频率增大。研究结果可以为微尺度压力传感器的结构设计和优化提供支持。

Taking the sensitive element of the micro-scale aeronautical pressure sensor as the research object,a twophase local/nonlocal integral equation driven by the static bending,buckling and free vibration of the micro-scale Euler beam is established.The stress-strain relationship is the Fredholm integral equation,which can be transformed into Volterra integral equation,the general solution is obtained by solving the integral-differential equation through Laplace transform,in which the unknown constant is determined by the boundary conditions related to the constitutive relation and additional constraint equations,and finally the bending deflection of the Euler beam under different boundary conditions can be obtained.For bucking and free vibration and in order to obtain a unique solution,the analytical and numerical solutions of the buckling load and free vibration frequency are obtained by finding the no-zero solution of the linear homogeneous equations.They are dimensionless.The results obtained show consistency reinforcement effect.The research results provide support for the structural design and optimization of microscale pressure sensors.