飞行器气动参数测试系统设计

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。

Design of aircraft aerodynamic parameters test system

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.