气象探空火箭气温测量不确定度评估方法
2021,43(6):49-59
孙宇
北京航天飞行控制中心, 北京 100094，sun_yu86@163.com
陈书驰
中国人民解放军
万黎
上海长望气象科技股份有限公司, 上海 201209
金波
上海长望气象科技股份有限公司, 上海 201209
盛峥
国防科技大学 气象海洋学院, 湖南 长沙 410073
王鑫
北京航天飞行控制中心, 北京 100094
北京航天飞行控制中心, 北京 100094，sun_yu86@163.com
陈书驰
中国人民解放军
万黎
上海长望气象科技股份有限公司, 上海 201209
金波
上海长望气象科技股份有限公司, 上海 201209
盛峥
国防科技大学 气象海洋学院, 湖南 长沙 410073
王鑫
北京航天飞行控制中心, 北京 100094
摘要：
在气象火箭测温修正模型基础上,通过误差分析理论,对温度修正及其不确定度评估方法进行研究。根据火箭探空仪在空中下落过程中大气密度变化规律,建立温度修正数学模型,推导得到温度修正公式。根据误差理论,分析影响温度修正的八项误差因素,并逐项给出温度修正误差表达式。以气象火箭实测数据为例,运用上述公式,对探空火箭温度反演不确定度进行分析计算。结果表明:温度反演不确定度在50~60 km较大,最大为3.6 K；40~50 km不确定度为0.3~0.9 K；40 km以下,不大于0.3 K。影响温度不确定度的因素主要是气动加热修正项、滞后效应修正项、结构热传导修正项和传感器对环境热辐射修正项。数据处理时采用参考大气或标准大气仅进行一次修正是不够的,需进行迭代修正,单次修正结果与迭代修正结果差异最大可达5.6 K。
在气象火箭测温修正模型基础上,通过误差分析理论,对温度修正及其不确定度评估方法进行研究。根据火箭探空仪在空中下落过程中大气密度变化规律,建立温度修正数学模型,推导得到温度修正公式。根据误差理论,分析影响温度修正的八项误差因素,并逐项给出温度修正误差表达式。以气象火箭实测数据为例,运用上述公式,对探空火箭温度反演不确定度进行分析计算。结果表明:温度反演不确定度在50~60 km较大,最大为3.6 K；40~50 km不确定度为0.3~0.9 K；40 km以下,不大于0.3 K。影响温度不确定度的因素主要是气动加热修正项、滞后效应修正项、结构热传导修正项和传感器对环境热辐射修正项。数据处理时采用参考大气或标准大气仅进行一次修正是不够的,需进行迭代修正,单次修正结果与迭代修正结果差异最大可达5.6 K。
基金项目：
Evaluation method of the uncertainty of the temperaturemeasurement for meteorological sounding rocket
SUN Yu
Beijing Aerospace Control Center, Beijing 100094, China,sun_yu86@163.com
CHEN Shuchi
The PLA Unit 32021, Beijing 100094, China
WAN Li
Shanghai Changwang Meteorological Technology Co., Ltd, Shanghai 201209, China
JIN Bo
Shanghai Changwang Meteorological Technology Co., Ltd, Shanghai 201209, China
SHENG Zheng
College of Meteorology and Oceanography, National University of Defense Technology, Changsha 410073, China
WANG Xin
Beijing Aerospace Control Center, Beijing 100094, China
Beijing Aerospace Control Center, Beijing 100094, China,sun_yu86@163.com
CHEN Shuchi
The PLA Unit 32021, Beijing 100094, China
WAN Li
Shanghai Changwang Meteorological Technology Co., Ltd, Shanghai 201209, China
JIN Bo
Shanghai Changwang Meteorological Technology Co., Ltd, Shanghai 201209, China
SHENG Zheng
College of Meteorology and Oceanography, National University of Defense Technology, Changsha 410073, China
WANG Xin
Beijing Aerospace Control Center, Beijing 100094, China
Abstract：
Based on the temperature correction model of meteorological sounding rocket, through error analysis theory, research on the method of temperature correction and uncertainty evaluation was conducted. According to the law of atmospheric density change during the falling process of rocketsonde, the mathematical model of temperature correction was established, and the formula of temperature correction was deduced. According to the error theory, eight error factors which affect the temperature correction were analyzed, and the expression of error in temperature correction was given one by one. Taking measured data as an example, using the above formula, the uncertainty of temperature inversion of sounding rocket was analyzed and calculated. The results show that the uncertainty of temperature inversion is larger in 50~60 km, and the maximum is 3.6 K; uncertainty in 40~50 km is 0.3~0.9 K; uncertainty in less than 40 km is no more than 0.3 K.The main factors that affect the uncertainty of temperature are aerodynamic heating correction, lag effect correction, structural heat conduction correction, and sensor correction for environmental heat radiation. It is not enough to use the reference atmosphere or the standard atmosphere for only single correction in data processing. Iterative correction is needed, and the maximum difference between iterative correction results and single correction results is 5.6 K.
Based on the temperature correction model of meteorological sounding rocket, through error analysis theory, research on the method of temperature correction and uncertainty evaluation was conducted. According to the law of atmospheric density change during the falling process of rocketsonde, the mathematical model of temperature correction was established, and the formula of temperature correction was deduced. According to the error theory, eight error factors which affect the temperature correction were analyzed, and the expression of error in temperature correction was given one by one. Taking measured data as an example, using the above formula, the uncertainty of temperature inversion of sounding rocket was analyzed and calculated. The results show that the uncertainty of temperature inversion is larger in 50~60 km, and the maximum is 3.6 K; uncertainty in 40~50 km is 0.3~0.9 K; uncertainty in less than 40 km is no more than 0.3 K.The main factors that affect the uncertainty of temperature are aerodynamic heating correction, lag effect correction, structural heat conduction correction, and sensor correction for environmental heat radiation. It is not enough to use the reference atmosphere or the standard atmosphere for only single correction in data processing. Iterative correction is needed, and the maximum difference between iterative correction results and single correction results is 5.6 K.
收稿日期：
2020-05-07
2020-05-07
