火箭探空GPS高度反算气压误差传递建模与仿真

Modeling and simulation for error propagation of pressure reverse calculation from GPS altitude of rocket sounding

针对气象火箭探空系统20km以上高空气压测量的工程需求,基于压高公式建立了GPS高度和温度反算气压的数学模型,并对该模型的误差传递进行了分析,给出了其系统误差、随机误差的计算方法。最后,以标准大气参数作为样本数据,对20～70km高空的气压参数及其准确度进行了仿真反算和误差分析。结果表明:利用GPS高度和温度反算高空气压参数,其系统误差仅取决于数值计算方法误差;20～35km区间,其标准偏差可满足WMO不超过±1hPa的要求;35～70km区间,其相对标准偏差小于5%。

According to measurement requirements of rocket sounding system for high-altitude pressure （above 20km）, based on barometric formula, a mathematical model about pressure reverse calculation is built on the data of GPS altitude and temperature. Then, the error propagation of this model is founded and calculation methods for system deviation and random deviation are given out. Finally, the standard atmosphere is chosen as a representative example and the pressure data and its accuracy are simulated and analyzed from 20 km to 70 kin. The results show that according to the pressure reverse calculation method, the system deviation is only influenced by the numeric method and its standard deviation is less than ±1 hPa from 20 km to 35 kin, which could satisfy the demand of WMO meteorological observation guideline. The relative standard deviation can be controlled in 50% from 35 km to 70 km.