摘要
为实现飞行器在实际飞行过程中受不同梯度气压影响的实时测试,设计了一种飞行器气动参数测试系统。针对压力敏感头在测试过程中温度漂移的问题,在恒流激励下,采用高精度元器件完成压力传感器的零点和灵敏度温度补偿,介绍了各个模块的设计。通过最小二乘法进行曲线拟合得到补偿数据,经过测试,压力测量精度优于0.1%,验证了设计方案的可行性。
To achieve real time tests of aircraft during actual flight affected by different pressure gradients,design a test system of aerodynamic parameters of aircraft. Aiming at temperature drift problem of pressure-sensitive head during testing,excited by constant current,use high-precision components to complete temperature compensation of zero point and sensitivity,introduce design of each modules. Test result shows that measurement precision of pressure parameters better than 0. 1 %,verify feasibility of the design.
出处
《传感器与微系统》
CSCD
2015年第2期113-115,135,共4页
Transducer and Microsystem Technologies
关键词
恒流源
压力传感器
温度补偿
气动参数
constant current source
pressure sensor
temperature compensation
aerodynamic parameter
