Evaluation method of the uncertainty of the temperature measurement for meteorological sounding rocket

被引：0

作者：

Sun Y. ^{[1
]}

Chen S. ^{[2
]}

Wan L. ^{[3
]}

Jin B. ^{[3
]}

Sheng Z. ^{[4
]}

Wang X. ^{[1
]}

机构：

[1] Beijing Aerospace Control Center, Beijing

[2] The PLA Unit 32021, Beijing

[3] Shanghai Changwang Meteorological Technology Co., Ltd, Shanghai

[4] College of Meteorology and Oceanography, National University of Defense Technology, Changsha

来源：

Guofang Keji Daxue Xuebao/Journal of National University of Defense Technology | 2021年 / 43卷 / 06期

关键词：

Data processing; Meteorological sounding rocket; Temperature measurement; Uncertainty evaluation;

D O I：

10.11887/j.cn.202106007

中图分类号：

学科分类号：

摘要：

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. © 2021, NUDT Press. All right reserved.

引用

页码：49 / 59

页数：10

共 15 条

[1] FAN Zhiqiang, Analysis of atmospheric environment detection data in near space, (2018)
[2] SHI Dongbo, HU Xiong, TU Cui, Et al., Near space environment detection technology-sounding rocket falling sphere, Equipment Environmental Engineering, 15, 7, pp. 89-92, (2018)
[3] SHI Dongbo, TU Cui, WEI Feng, Et al., Research and design of an expanding falling ball technology suitable for atmospheric environment detection in near space, (2019)
[4] LUO Laiyu, Research and design of a falling ball technology suitable for atmospheric environment detection in near space, Business Story, 7, (2017)
[5] Bollermann B., A study of 30 km to 200 km meteorological rocket sounding systems: volume 1, part 1-literature and data review, (1970)
[6] SUN Yu, CHEN Shuchi, SHAO Shengli, Et al., Study on the evaluation method of the uncertainty of the wind measurement for meteorological sounding rocket, Meteorological Science and Technology, 49, 2, pp. 174-183, (2021)
[7] SHENG Z, JIANG Y, WAN L, Et al., A study of atmospheric temperature and wind profiles obtained from rocketsondes in the Chinese midlatitude region, Journal of Atmospheric and Oceanic Technology, 4, pp. 722-735, (2015)
[8] Guide to meteorological instruments and methods of observation [M], (2008)
[9] WAGNER N K., Theoretical time constant and radiation error of a rocketsonde thermistor, Journal of Meteorology, 18, 5, pp. 606-614, (1961)
[10] WAGNER N K., Theoretical accuracy of a meteorological rocketsonde thermistor, Journal of Applied Meteorology, 3, 4, pp. 461-469, (1964)

← 1 2 →