航空机载镍电阻温度传感器仿真及优化设计

Simulation and optimization design of aviation nickel resistance temperature sensor

为满足某型航空发动机对配套镍电阻温度传感器动态热响应的技术要求,构建传感器动态热响应分析数学模型,完成6组设计方案的仿真分析,通过样件试制和试验验证,确定最优设计方案。研究表明:采用热扩散系数较高的铜制感温元件骨架材料、填充非金属导热硅脂、骨架结构为螺旋状的传感器动态热响应最快,时间常数仿真结果为17.3 s,样件测试结果为16.58 s,满足动态热响应技术要求。

In order to meet the dynamic thermal response requirements of a aviation nickel resistance temperature sensor, the mathematical model was constructed, and the simulation analysis of six groups of design schemes was completed. The optimal design was determined through trial productions and verification tests. The sensor of a helical skeleton, which was composed of copper and filled with thermal conductive silicon grease, had the fastest dynamic thermal response. The simulation result of time constant was 17.3 s, and the test result was 16.58 s. This design of the sensor can meet the technical requirements.