the Creative Commons Attribution 4.0 License.

the Creative Commons Attribution 4.0 License.

# Radiation correction and uncertainty evaluation of RS41 temperature sensors by using an upper-air simulator

### Sang-Wook Lee

### Sunghun Kim

### Young-Suk Lee

### Byung Il Choi

### Woong Kang

### Youn Kyun Oh

### Seongchong Park

### Jae-Keun Yoo

### Joohyun Lee

### Sungjun Lee

### Suyong Kwon

### Yong-Gyoo Kim

An upper-air simulator (UAS) has been developed at the
Korea Research Institute of Standards and Science (KRISS) to study the
effects of solar irradiation of commercial radiosondes. In this study, the
uncertainty in the radiation correction of a Vaisala RS41 temperature sensor is evaluated using the UAS at KRISS. First, the effects of environmental parameters including the temperature (*T*), pressure (*P*), ventilation speed (*v*), and irradiance (*S*) are formulated in the context of the radiation correction. The considered ranges of *T*, *P*, and *v* are −67 to 20 ^{∘}C, 5–500 hPa, and 4–7 m s^{−1}, respectively, with a fixed *S*_{0}=980 W m^{−2}. Second, the uncertainties in the
environmental parameters determined using the UAS are evaluated to calculate their contribution to the uncertainty in the radiation correction. In addition, the effects of rotation and tilting of the sensor boom with respect to the irradiation direction are investigated. The uncertainty in the radiation correction is obtained by combining the contributions of all uncertainty factors. The expanded uncertainty associated with the radiation-corrected temperature of the RS41 is 0.17 ^{∘}C at the coverage factor *k*=2 (approximately 95 % confidence level). The findings obtained by reproducing the environment of the upper air by using the ground-based facility can provide a basis to increase the measurement accuracy of radiosondes within the framework of traceability to the International System of Units.

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The measurement of temperature and humidity in the free atmosphere is of significance for weather prediction, climate monitoring, and aviation safety assurance. Radiosondes are telemetry devices that include various sensors to perform in situ measurements and transmit the measured data to a ground receiver while the device is carried by a weather balloon to an altitude of approximately 35 km. Since their development in the 1930s, radiosondes have been widely used to measure various essential climate variables (ECVs) such as the temperature, water vapour, pressure, wind speed, and wind direction in the upper-air atmosphere. Owing to their high accuracy of 0.3 to 0.4 K claimed by manufacturers (Vaisala), radiosonde measurements provide a reference for other remote sensing techniques such as those based on satellite and lidar. However, evaluation methods for their sensor accuracy are not fully disclosed to users. Operation principles of laboratory set-ups, algorithms to correct measurement errors, and corresponding uncertainty evaluations are prerequisites for a reference data product. The dependence of accuracy evaluation based only on manufacturer data may lead to inhomogeneities in data records due to the use of different radiosonde models.

To ensure the quality control of measurements in the upper air, the Global Climate Observing System (GCOS) Reference Upper-Air Network (GRUAN) was founded in 2008. The key objective of the GRUAN is to perform high-quality measurements of selected ECVs from the surface to the stratosphere to monitor climate change. To this end, the required temperature measurement accuracy in the troposphere and stratosphere has been specified as 0.1 and 0.2 K, respectively (GCOS, 2007).

The main source of error in the temperature measured by radiosondes is solar
radiation during sounding in daytime. The temperature sensors of most
commercial radiosondes are exposed to solar radiation, which leads to
radiative heating of the temperature sensor. According to the last
intercomparison of high-quality radiosonde systems (Nash et al.,
2011), radiation correction values applied by manufacturers were distributed
from 0.6 to 2.3 K at 10 hPa. More recently, according to the radiation
correction of the Vaisala RS41 (Vaisala, 2022), it is increased from 0.53 to
1.16 K at 10 hPa as the solar angle is elevated from 0 to
90^{∘}. Correcting the radiation effect is challenging because the
temperature of sensors is also affected by other thermal exchange processes
such as conduction from the sensor boom, convective cooling by air
ventilation, and long-wave radiation from sensors. To minimize the effect of
radiative heating of radiosonde temperature sensors, the size of the sensors has
been reduced (de Podesta et al., 2018), and highly reflective coatings
are used (Luers and Eskridge, 1995; Schmidlin et al., 1986).
Moreover, the sensor boom has been redesigned to reduce the thermal
conduction to sensors. Nevertheless, the effect of solar irradiation cannot
be eliminated and thus should be corrected properly.

Many researchers have attempted to correct the radiation effect on radiosonde temperature sensors through theoretical and experimental techniques. The early theoretical approaches were based on heat transfer equations governing the thermal exchange between the sensor and surrounding media (Luers, 1990; McMillin et al., 1992). However, the application of these approaches requires complete knowledge regarding the material properties of the sensor and sensor boom and air characteristics in a wide range of temperatures, and the aerodynamic characteristics for a specific sensor geometry must be determined.

A few researchers performed in-flight experiments to derive a formula to correct the radiation effect. Radiation correction was estimated by using radiosondes equipped with four thermistors having coatings with different spectral responses, i.e. emissivities and absorptivities (Schmidlin et al., 1986). A correction formula was derived by establishing the relationship between the irradiance and increase in the temperature via radiative heating during daytime sounding (Philipona et al., 2013). Two identical thermocouples were used to measure the temperature difference when only one sensor was exposed to solar radiation, and the other was shielded. As a result, radiation correction was obtained by a linear function of geopotential height, which gives 1 K at 32 km. However, the effect of the shield could not be eliminated.

Other groups adopted a chamber system for radiation correction by simulating the upper-air environments including the solar radiation. The GRUAN conducted experiments by using a chamber that could imitate the pressure, air ventilation, and solar irradiance by using a vacuum pump, fan, and lamp or sunlight, respectively (Dirksen et al., 2014). Recently, the same group conducted experiments by using a new laboratory set-up including a wind tunnel with various functionalities and improved uncertainties in processing the GRUAN data for the Vaisala RS41 sensors (von Rohden et al., 2022). However, these experiments were conducted at room temperature, and thus, the influence of the ambient temperature on the radiation error was not investigated. Notably, a previous study based on a chamber system reported that the solar-irradiation-induced temperature rise of sensors increases as the air temperature is decreased (Lee et al., 2018a).

Recently, the Korea Research Institute of Standards and Science (KRISS)
developed an upper-air simulator (UAS) that can simultaneously control the
temperature, pressure, air ventilation, and irradiation (Lee et al.,
2020). This UAS has been also used to calibrate the relative humidity
sensors of commercial radiosondes at low temperatures (down to −67 ^{∘}C) (Lee et al., 2021).

In this study, the uncertainty in the radiation correction of a Vaisala RS41
temperature sensor is evaluated using the UAS developed at KRISS (Lee et al., 2020). It is shown how the uncertainty in each environmental parameter and radiosonde movements in the UAS contributes to the uncertainty of the RS41 through a radiation correction formula obtained by a series of radiation experiments. The layout of the UAS is described in Sect. 2, along with the addition of new functions to consider the effect of the rotation and tilting of the sensor, which are important improvements from the previous version of the UAS. As described in Sect. 3, a radiation correction formula for the RS41 sensor is derived through a series of experiments involving varying temperature (*T*), pressure (*P*), and ventilation speed (*v*) values in the following ranges: −67 to 20 ^{∘}C, 5–500 hPa, and 4–7 m s^{−1}, respectively, with a fixed irradiance *S*_{0} = 980 W m^{−2}. The effects of sensor rotation and tilting with respect to the incident irradiation are also investigated. Section 4 describes the evaluation of the uncertainties associated with the environmental parameters and sensor motions and positions controlled in the UAS to calculate the contribution of these factors to the uncertainty in the
radiation correction. This study can help enhance the measurement accuracy
of radiosondes within the framework of traceability to the International
System of Units (SI) by providing a methodology for radiation correction in
an environment similar to that which may be encountered by radiosondes.

## 2.1 Temperature control of the radiosonde test chamber by using a climate chamber

Figure 1a shows the test chamber of the UAS with an installed radiosonde
for the radiation correction. The test chamber is inside a climate chamber
(Tenney Environmental, Model C64RC) with a 1219 mm × 1219 mm × 1219 mm working space. The temperature of the test chamber is controlled by the climate chamber. Air is precooled before entering into the climate chamber by passing through a heat exchanger in a separate bath (Kambič Metrology, Model OB-50/2 ULT) with a temperature lower than that of the climate chamber by about 5 ^{∘}C. The temperature of the precooled air is then adjusted to that of the climate chamber while passing through the second heat exchanger (9.3 m in length) in the climate chamber before entering into the test chamber. The radiosonde is installed upside down, as shown in Fig. 1b, and the air flows into the test chamber from the bottom. The temperature of the test chamber is measured using a calibrated platinum resistance thermometer (PRT).

## 2.2 Pressure and ventilation speed control through sonic nozzles and a vacuum pump

To control the air ventilation speed at low pressures, sonic nozzles, also
known as critical flow Venturi, are used. The sonic nozzles are fabricated
as toroidal-throat Venturi nozzles to comply with the ISO 9300 standard
(ISO, 2005) and calibrated using a low-pressure gas flow standard system
at KRISS (Choi et al., 2010). Thus, the reference value and SI
traceability of the ventilation speed are obtained by using the sonic
nozzles in the UAS. Sonic nozzles can be used to achieve a specific maximum
constant flow when the ratio of the downstream pressure (*P*_{e}) to the upstream pressure (*P*_{o}) is smaller than a certain critical point (${P}_{\mathrm{e}}/{P}_{\mathrm{o}}<{P}_{\mathrm{c}}/{P}_{\mathrm{o}}$). The test chamber lies in the
downstream region of the sonic nozzles, in which the pressure is lowered
using a vacuum pump (WONVAC, Model WOVP-0600) to attain the critical
condition. Six sonic nozzles with different throat diameters are used to
generate air ventilation speeds ranging from 4 to 7 m s^{−1} in the pressure range of 5–500 hPa. The generated airflow is measured through laser Doppler velocimetry (LDV) (Dantec, Model BSA F60) to investigate the spatial gradient in the test chamber. An Ar ion laser (3 W) with a wavelength of 514.5 nm is used for the LDV with a focal length of 400.1 mm and nominal beam spacing of 33 mm.

## 2.3 Irradiation control by using a solar simulator

Solar irradiation is imitated by using a solar simulator with a xenon DC arc
lamp (Newport, Model 66926-1000XF-R07). The virtual sunlight is irradiated
onto the radiosonde temperature sensor and the sensor boom through quartz
windows of the test chamber. A constant irradiance of 980 W m^{−2} at the position of the radiosonde sensors inside the test chamber
is adopted throughout this study. The two-dimensional distribution of the
irradiance is recorded at the radiosonde sensor location by using a
calibrated Si photodiode (Thorlabs, Model SM05PD2A). The spatial uniformity
of the irradiance around the sensor position is within ±5 %. In
addition, the irradiance is monitored to check its drift during the
experiments by using a photodiode-based pyranometer (Apogee, Model
SP-110-SS) installed behind the test chamber. The pyranometer is calibrated
at KRISS, and the uncertainty is 1 % of the measured value with a coverage
factor *k* = 1.

## 2.4 Installation of the RS41

The uncertainty associated with the radiation correction for a commercial radiosonde (Vaisala, RS41) is evaluated using the UAS. A complete RS41 unit including the sensor boom, antenna, and main body is installed upside down in the test chamber, as shown in Fig. 1a and b. The sensor boom is placed parallel to the airflow (dashed blue arrows). The sensor boom is irradiated (dotted red arrows) by the solar simulator in a perpendicular manner through quartz windows (50 mm × 70 mm). The temperature recorded by the RS41 is collected through remote data transmission as in the case of soundings by the Vaisala sounding system MW41. Radiation correction by the manufacturer is applied only during the sounding state. The RS41 unit remains at the pre-sounding state in the manual sounding mode throughout the data acquisition, and thus, raw temperature with no radiation correction is obtained.

## 2.5 Rotation and tilting of the sensor boom

A radiosonde exhibits continuous movements such as pendulum and rotational
motions during sounding. The geometry of the temperature sensor of the
Vaisala RS41 is a rod shape, and thus the rotation and tilt affect the
effective irradiance and the direction of air ventilation. Other radiosondes
using spherical bead thermistors would be less affected by the rotation and
tilt. Thus, the angle of the sensor boom with respect to the radiation
direction or airflow may constantly vary. To consider this aspect, the UAS
is modified to be able to simulate these situations through rotating and
tilting of the sensor boom in the test chamber. Figure 1c–e illustrate
the mechanisms in the test chamber that enable the (Fig. 1d) rotation of the
radiosonde around the vertical axis and (Fig. 1e) tilting of the sensor boom from the (Fig. 1c) normal position. The rotation cycle and tilt are controlled using stepper motors. Rotation cycles of 5, 10, and 15 s are employed. The
maximum tilt is 27^{∘} with respect to the vertical axis. Effects of
the rotation and incident angle of irradiation are studied and incorporated
into the uncertainty evaluation of the radiation correction of the sensor.

## 3.1 Effect of pressure

Radiation error is the temperature difference between the sensor with
irradiation and air (*T*_{on}−*T*_{air}). However, the air temperature
measured in the current chamber system does not represent that in the free
atmosphere since the air is heated by irradiation for a short time while
passing through the test section. It is difficult to measure true air
temperature in a shaded area in the test chamber using an independent
thermometer because the test section is also slightly heated by the
irradiation. The temperature measured below the window is continuously
increased by a few tens of millikelvins while repeating the experiments for 10 min.
Thus, the radiation correction value (Δ*T*_{rad}) is obtained by the difference in the temperatures with irradiation (*T*_{on}) and without irradiation (*T*_{off}) as previously reported (Lee et al., 2020): $\mathrm{\Delta}{T}_{\mathrm{rad}}={T}_{\mathrm{on}}-{T}_{\mathrm{off}}$. The duration of irradiation is 120 s, and the measurement is repeated three times.

It has been reported that Δ*T*_{rad} significantly increases as the pressure (*P*) decreases from 100 to 7 hPa in the UAS (Lee et al.,
2020). In this study, the pressure range is extended (5–500 hPa) to
formulate the corresponding effect at a more practical scale. Figure 2a
shows Δ*T*_{rad} as a function of pressure from 5 to 500 hPa with varying temperature (*T*) from −67 to 20 ^{∘}C. The
data represent the mean and the standard deviation of three repeated
measurements on a single RS41 unit. The biggest standard deviation was 0.014 ^{∘}C. The enhanced increase in Δ*T*_{rad} is observed at low
pressures for all measured temperatures because the convective cooling
process is weakened as the air density decreases at low pressures. The
effect of temperature is well distinguished in the low-pressure range (5 to
50 hPa), whereas it is not clearly observable in the high-pressure range
(100 to 500 hPa). This phenomenon can be attributed to the fact that the uncertainty in
Δ*T*_{rad} becomes relatively larger with respect to Δ*T*_{rad} as Δ*T*_{rad} is decreased at high pressures in the UAS.

To parameterize a radiation correction formula in terms of *T* and *P*, Δ*T*_{rad} at each temperature is fitted individually by using an empirical polynomial function of log_{10}*P*, as indicated by dashed lines in Fig. 2a. The fitting equations represented in Fig. 2a are as follows:

where *A*_{0}(*T*), *B*_{0}(*T*), and *C*_{0}(*T*) are fitting coefficients with
functions of *T*, having units of ^{∘}C, ^{∘}C ⋅ [log
hPa]^{−1}, and ^{∘}C ⋅ [log hPa]^{−2}, respectively.
The irradiation intensity *S*_{0} is set as 980 W m^{−2}
throughout this study.

## 3.2 Effect of temperature

The following *T* values are used in the test chamber: −67,
−55, −40, −20, 0, and 20 ^{∘}C. As shown in Fig. 2a, Δ*T*_{rad} gradually increases as the temperature reduces, especially in the low-pressure range of 5–50 hPa. To incorporate the temperature effect in Eq. (1), the coefficients are fitted with empirical linear functions as follows:

where *a*_{0}, *a*_{1}, *b*_{0}, *b*_{1}, *c*_{0}, and *c*_{1} are fitting
coefficients. Information regarding these coefficients is summarized in
Table 1.

The residuals obtained using Eq. (1) and the associated fitting coefficients
listed in Table 1 are presented in Fig. 2b. The fitted values
agree with the measurement data within ±0.03 ^{∘}C.

In order to understand the observed temperature effect theoretically, the
temperature sensor is modelled as a sphere made of platinum (Pt) with a
diameter (*D*) of 1 mm. The Pt sphere is placed in the middle of an airflow
(*v*) with varied temperature (*T*_{a}) and pressure (*P*_{a}), as shown in Fig. 3a. The sphere is heated by the absorption of the solar irradiance (*S* = 1000 W m^{−2}) and cooled by the forced air convection (5 m s^{−1}), similar to the experiment. The radial and angular
temperature distribution of the sphere is neglected and assumed to be
uniform. Then, the steady-state temperature of the sphere (*T*_{s}) is simply decided by the energy balance of the heat transfer exchange as follows:

with

where *α* is the absorptivity of the metal sphere, *S* is the solar
irradiance, and *h* is the heat transfer coefficient (Incropera and
Dewitt, 2002; Luers and Eskridge, 1995). The net heat transfer by longwave
radiation from the Pt sphere is not considered because it is negligible
(∼ 10^{−6} W) compared to that by the convective heat
transfer in Eq. (5). The heat transfer coefficient *h* is determined by several
parameters concerning the diameter of the sphere (*D*) and the properties of
air, including thermal conductivity (*k*); viscosity (*μ*); heat capacity
(*C*_{p}); and Reynolds number (*Re* = *ρ**v**D**μ*^{−1}), where *ρ* and *v* are the density of air and wind speed, respectively.

The radiation correction (*T*_{s}−*T*_{a}) at *T*_{a} = 20 and −70 ^{∘}C is calculated by Eq. (5) and displayed together with the experimental values (mean and standard deviation of three repeated experiments) as shown in Fig. 3b. The properties of air (N_{2}) used for the calculation refer to the NIST Chemistry WebBook (Linstrom and Mallard, 2001). In general, the calculated radiation correction of the Pt sphere is elevated as the pressure decreases as in the case of the
experiment. This is because the heat transfer coefficient is reduced by
about 35 % as the density of air is decreased with varying pressure from
*P*_{a} = 50 to 5 hPa. Interestingly, the temperature effect on the calculated radiation correction is also observed to be similar to the experiment. The theoretical value is roughly consistent with the experimental value within the uncertainty in Δ*T*_{rad} (0.1 ^{∘}C) as obtained in Sect. 4.9. A decrease in thermal conductivity of air by about 26 % at −70 ^{∘}C is mainly responsible for the decrease in the heat transfer coefficient and thereby the increase in the radiation correction at low temperature (−70 ^{∘}C). The thermal conductivity of air plays an important role for the heat transfer at the boundary between the air and the Pt sphere. The same phenomenon was also observed for thermistors even though there is no apparent air ventilation (Lee et al., 2018a), which may emphasize the role of thermal conductivity of air. The parameters and their values used for the calculation of radiation correction at *T*_{a} = 20 and −70 ^{∘}C with *P*_{a} = 5 hPa are summarized in Table 2.

It was previously observed that the temperature rise of the RS92 was initially
fast due to the small thermal mass of the sensor and subsequently slow
(Dirksen et al., 2014). More recently, the temperature of the RS41
oscillated when the radiosonde was rotating under irradiation
(von Rohden et al., 2022). These observations
are attributed to the fact that the heating of the sensor boom with a comparably large
area is coupled to the heating of the temperature sensor. Since the
conductive heat transfer from the sensor boom is missing in the above
theoretical calculation, the comparison in Fig. 3b may show the effect of
the sensor boom on Δ*T*_{rad}. Interestingly, the growth of Δ*T*_{rad} of the theoretical calculation is less steep than that of the
experiment as the pressure is decreased to 5 hPa. This may imply that the
heat transfer from the sensor boom becomes significant especially at low
pressures.

## 3.3 Estimation of the low-temperature effect

The effect of low temperature on Δ*T*_{rad} is represented by the ratio (%) of Δ*T*_{rad} to the corresponding value at 20 ^{∘}C (Δ*T*_{rad_20}), as shown in Fig. 4a.
The data represents the mean and the standard deviation of three repeated
measurements on a single RS41 unit. The temperature effect ($\mathrm{\Delta}{T}_{\mathrm{rad}}/\mathrm{\Delta}{T}_{\mathrm{rad}\mathrm{\_}\mathrm{20}}$) gradually increases as the
temperature and pressure decrease. $\mathrm{\Delta}{T}_{\mathrm{rad}}/\mathrm{\Delta}{T}_{\mathrm{rad}\mathrm{\_}\mathrm{20}}$ is 119 % at *T* = −67 ^{∘}C and *P* = 5 hPa. To obtain the information required to estimate the low-temperature effect by using only Δ*T*_{rad} at 20 ^{∘}C with varied *P*,
$\mathrm{\Delta}{T}_{\mathrm{rad}}/\mathrm{\Delta}{T}_{\mathrm{rad}\mathrm{\_}\mathrm{20}}$ × 100 is
fitted with empirical linear functions:

where *D*(*T*), represented in hPa^{−1}, and *E*(*T*), which is dimensionless, are fitting coefficients with functions of *T*. *D*(*T*) and *E*(*T*) are fitted by linear functions of *T* as follows:

where *d*_{0}, *d*_{1}, *e*_{0}, and *e*_{1} are fitting coefficients. The
information regarding these coefficients is summarized in Table 3.

The residuals obtained using Eqs. (6), (7), and (8) are represented in Fig. 4b. The estimated values agree with the measurement data within ±1.5 % (left *y* axis), corresponding to approximately ±0.01 ^{∘}C (right *y* axis). Using Eq. (6), the radiation correction for
low temperatures can be estimated through only the room-temperature
measurement. Since the temperature dependency is weak at higher pressures,
there is no need to estimate the low-temperature effect at 50–500 hPa, and
the estimation using Eq. (6) is limited within 5–50 hPa.

## 3.4 Effect of ventilation speed

To investigate the effect of ascending speed of radiosondes, the air
ventilation speed (*v*) in the test chamber is systematically varied in the
range of 4–7 m s^{−1}. Figure 5a shows Δ*T*_{rad} as
a function of the ventilation speed with the temperature varying from −67 to 20 ^{∘}C. Δ*T*_{rad} decreases as the
ventilation speed increases, primarily owing to the enhancement in the
convective cooling. Because the pressure is fixed at 50 hPa, the temperature
effect is clearly visible in Fig. 5a. The measurement data at each
temperature are fitted using a linear function (dashed lines) to formulate
the effect of the ventilation speed. The slope of the linear functions
indicates that an increase of 1 m s^{−1} in *v* induces a decrease
of 0.02–0.03 ^{∘}C in Δ*T*_{rad}. Figure 5b shows Δ*T*_{rad} as a function of the ventilation speed with the pressure varying from 5 to 300 hPa. The measurement data at each pressure are fitted
using a linear function (dashed lines). The slopes are distributed from
−0.04 to −0.02 ^{∘}C (m s^{−1})^{−1}.

Although the effect of the ventilation speed is coupled with the temperature
and pressure effects, the coupling represented by the variation in slopes in
Fig. 5a and b is minor in the range of 4–7 m s^{−1}.
Therefore, the effect of the ventilation speed can likely be treated as an
independent parameter. Thus, the ventilation effect is formulated
considering the average slope in Fig. 5a and b, which is −0.027 ^{∘}C (m s^{−1})^{−1}. This result is incorporated into Eq. (1) at *v* = 5 m s^{−1}:

The residual obtained by applying Eq. (9) is shown in Fig. 5c. The fitted
values agree with the measurement data within ±0.04 ^{∘}C.
The linear relationship between the ventilation speed and the radiation
correction in Eq. (9) is only valid in the range of 4–7 m s^{−1}. When *v* is higher than 7 m s^{−1} or lower than 4 m s^{−1}, the formula underestimates the correction value.

## 3.5 Effect of irradiation intensity

The linear relationship between Δ*T*_{rad} and the irradiance (*S*) is confirmed with reference to the existing studies based on theoretical and experimental approaches (Luers, 1990; McMillin et al., 1992; Lee et al., 2016). *S* is independent of *T*, *P*, and *v*. As previously observed, the variation in the other parameters results in a change in only the slope of the linear functions (*h* in Eq. 5), and the linearity is not altered (Lee et al., 2018c, b). Because all the experiments performed in this
study adopt a fixed *S*_{0} = 980 W m^{−2}, and the empirical fitting coefficients are accordingly obtained, the effect of the irradiation intensity can be incorporated into Eq. (9) by using the linear relationship between Δ*T*_{rad} and *S* as follows:

The radiation correction (Δ*T*_{rad}) is then scaled with the actual irradiance (*S*) by the factor of $S{S}_{\mathrm{0}}^{-\mathrm{1}}$. Consequently, Eq. (10) considers the radiation correction of the RS41 temperature sensor under simultaneously varying *T*, *P*, *v*, and *S*.

## 3.6 Effect of sensor boom rotation

The spinning motion of radiosondes during sounding is imitated by rotating
the radiosonde in the test chamber, as shown in Fig. 1d. The rotation axis
is the temperature sensor itself, not the centre of the boom in this work.
Therefore, the temperature sensor only spins on the spot, and thus the
distance between the sensor and the solar simulator does not change during
the rotation. The amplitude of the temperature oscillation is investigated
by varying the rotation cycle (5, 10, and 15 s) under irradiation, as
shown in Fig. 6a. The maximum peak (*T*_{on_max}) and
minimum peak (*T*_{on_mim}) appear alternately during the
rotation. The difference between the peaks (*T*_{on_max}−*T*_{on_min}) for 5 s duration is 0.01–0.02 ^{∘}C, which is around the measurement resolution of the RS41 (0.01 ^{∘}C), but
is increased with the rotation period. Each peak appears twice in a single
cycle, as clearly observed in the 15 s cycle. The exposed surface of the
sensor boom depends on the incidence angle and passes through a maximum
twice during a full rotation. The sensor boom experiences irradiation in the
perpendicular and parallel directions at *T*_{on_max} and
*T*_{on_min}, respectively. This finding suggests that the
conductive heat transfer from the boom to the sensor influences
*T*_{on_max}.

Figure 6b shows *T*_{on_max}−*T*_{on_min}
as a function of pressure under different rotation cycles. The pressure
effect is clearly visible when the rotation cycle is 15 s. Because the
experiment is conducted at *T* = 25 ^{∘}C and *v* = 5 m s^{−1}, the effect of rotation at the lowest considered temperature (−67 ^{∘}C) is estimated using Eqs. (6), (7), and (8). At *P* = 5 hPa, the value of *T*_{on_max}−*T*_{on_min} at −67 ^{∘}C is 20 % higher than that at 25 ^{∘}C.

The maximum value of *T*_{on_max}−*T*_{on_min} in the UAS (0.05 ^{∘}C) is much smaller than that of von Rohden et al. (2022) (0.3 ^{∘}C). In the work of von Rohden et al. (2022), although the distance from the light source to the sensor is constant, that to the sensor boom changes with rotation. This may be the reason why the maximum peak appears once in a full cycle when the sensor boom is close to the light source, and the *T*_{on_max}−*T*_{on_min} is bigger than this work. It should be highlighted that the relatively small *T*_{on_max}−*T*_{on_min} with respect to Δ*T*_{rad} observed in
this work suggests that the contribution of the thermal conduction to
Δ*T*_{rad} is small compared to that by the direct irradiation of the sensor.

## 3.7 Effect of solar incident angle

The incident angle of irradiation to sensors primarily depends on the solar
elevation angle and, during soundings, may also vary due to pendulum motion
of the radiosonde. To investigate the effect of the solar incident angle,
the sensor boom is tilted by *θ* with respect to the normal direction
in the test chamber, as shown in Fig. 1e. Figure 7a shows Δ*T*_{rad} as a function of pressure when the sensor boom is in the normal and tilted (*θ* = 27^{∘}) positions. Δ*T*_{rad} in the tilted position (red circle) is lower than that in the normal position (black square) because the effective irradiance (*S*_{eff}) is reduced by the tilting (${S}_{\mathrm{eff}}=S\times \mathrm{cos}\mathrm{27}{}^{\circ}$). Because Δ*T*_{rad} is proportional to *S*_{eff}, the ratio $\mathrm{\Delta}{T}_{\mathrm{rad}\mathrm{\_}\mathrm{tiled}}/\mathrm{\Delta}{T}_{\mathrm{rad}\mathrm{\_}\mathrm{normal}}$
should be cos 27^{∘}. The ratio roughly follows the theoretical
value (dotted blue line). However, this value is slightly higher and lower
than cos 27^{∘} at pressure values less and more than 50 hPa,
respectively. At higher pressures, this deviation can be explained by the
effect of ventilation, which intensifies in the case of tilting of the
sensor boom. However, the reason for the deviation from the theoretical
value at low pressures remains unclear. In this paper, the effect of solar
incident angle (or tilt angle, *θ*) is considered by using *S*_{eff} (*S*×cos *θ*), and thus Eq. (10) is revised into its final form as follows:

Figure 7b shows the difference between Δ*T*_{rad_tilted} and $\mathrm{\Delta}{T}_{\mathrm{rad}\mathrm{\_}\mathrm{normal}}\times \mathrm{cos}\mathrm{27}{}^{\circ}$ as a function of the pressure. Because the experiment is
conducted at *T* = 25 ^{∘}C, the effect of the solar incident angle
at the lowest considered temperature (−67 ^{∘}C) is estimated
using Eqs. (6), (7), and (8). At *P* = 5 hPa, $\mathrm{\Delta}{T}_{\mathrm{rad}\mathrm{\_}\mathrm{tilted}}-\mathrm{\Delta}{T}_{\mathrm{rad}\mathrm{\_}\mathrm{normal}}\times \mathrm{cos}\mathrm{27}{}^{\circ}$ at −67 ^{∘}C is 20 %
higher than that at 25 ^{∘}C. This value is used for the uncertainty
due to the tilting of the sensor boom in Sect. 4.7.

## 4.1 Uncertainty factors

The uncertainty factors that contribute to the uncertainty budget of the radiation correction are summarized in Table 4, in addition to the experimental ranges considered in this work.

## 4.2 Uncertainty in the temperature, *u*(*T*)

The temperature of the test chamber is measured using a PRT installed in a
shaded area. The PRT is calibrated at KRISS, and the calibration uncertainty
is 0.025 ^{∘}C with the coverage factor *k* = 1. The resistance of
the PRT is measured using a digital multimeter calibrated at KRISS.
Moreover, the stability of the temperature measured using the PRT is
considered in determining *u*(*T*). The uncertainty components
and their contributions to *u*(*T*) are listed in Table 5.

## 4.3 Uncertainty in the pressure, *u*(*P*)

The pressure of the test chamber is measured using three pressure gauges for
different pressure ranges. The gauges are calibrated at KRISS, and the
calibration uncertainty is considered in determining *u*(*P*).
Moreover, the stability of the pressure measured using each pressure gauge
is considered to determine *u*(*P*). The uncertainty components
and their contributions to *u*(*P*) are listed in Table 6.

## 4.4 Uncertainty in the ventilation speed, *u*(*v*)

The SI traceability of the ventilation speed in the test chamber of the UAS
is ensured by calibrating the sonic nozzles at KRISS. The calibration
uncertainty of the sonic nozzles is 0.09 % (*k* = 1). The stability of the ventilation speed in the test chamber is considered to determine *u*(*v*). The spatial gradient of the ventilation speed in the test chamber
is measured through the LDV at KRISS. The measurement dimension using the
LDV was 30 mm × 30 mm around the sensor (central) location with 5 mm intervals (49 points). Thus, the outermost measurement points were spaced 10 mm apart from the walls of the test chamber (50 mm × 50 mm). The measurement was performed under the condition of *v* = 4.67 m s^{−1} (reference value), *P* = 550 hPa, and room temperature. The flow regime is turbulent because the Reynolds number is high (∼ 10^{5}) under this
experimental condition. The average and the standard deviation by the LDV
over the entire measurement area were 4.63 and 0.47 m s^{−1}, respectively. Although the flow rate of the outermost
points tends to be smaller than others, no significant spatial gradient is
observed. This may be because of the spacing (10 mm) between the outermost
measurement points and the walls of the test chamber. The difference between
the reference and the measurement average is assumed to have a rectangular
probability distribution for the calculation of the uncertainty in the spatial
gradient. Then, the standard uncertainty of this estimate is the half width
of the distribution divided by $\sqrt{\mathrm{3}}$ (ISO, 2008). The
uncertainty components and their contributions to *u*(*v*) are
summarized in Table 7.

## 4.5 Uncertainty in the irradiance, *u*(*S*)

The irradiance in the test chamber is measured using a pyranometer. The
pyranometer is calibrated at KRISS, and the calibration uncertainty is 9.8 W m^{−2} at *k* = 1. The stability of the irradiance measured
using the pyranometer is considered to determine *u*(*S*). The
uncertainty of the solar simulator will be negligible compared to that of
the actual radiation field in atmospheric soundings due to the lack of
knowledge. In addition, the two-dimensional spatial uniformity of the
irradiance in the test chamber is measured by moving the pyranometer. The
spatial gradient is within ±5 %, and a rectangular probability
distribution is assumed for the uncertainty calculation. The uncertainty
components and their contributions to *u*(*S*) are summarized in
Table 8.

## 4.6 Uncertainty due to sensor rotation

Since the sensor boom position for *T*_{on_max} during the
rotation corresponds to the normal position, the uncertainty due to sensor
rotation is obtained based on *T*_{on_max}−*T*_{on_min}, as shown in Fig. 6b. The value estimated for *T* = −67 ^{∘}C and *P* = 5 hPa is used to include sufficient
uncertainty. The values are assumed to have a rectangular distribution, and
thus, the corresponding standard uncertainty (*k* = 1) is obtained
considering the half-maximum value (0.03 ^{∘}C) divided by $\sqrt{\mathrm{3}}$. The reason for using the half maximum is that *T*_{on_max}−*T*_{on_min} is about double *T*_{on_max}−*T*_{on} or *T*_{on}−*T*_{on_min}. Consequently, the
uncertainty due to sensor rotation is 0.017 ^{∘}C (*k* = 1).

## 4.7 Uncertainty due to tilting of the sensor

The uncertainty due to tilting of the sensor boom is obtained using
${T}_{\mathrm{on}\mathrm{\_}\mathrm{tilted}}-{T}_{\mathrm{on}\mathrm{\_}\mathrm{normal}}\cdot \mathrm{cos}\mathrm{27}{}^{\circ}$, as shown in Fig. 7b. The value estimated for *T* = −67 ^{∘}C and *P* = 5 hPa is used to include sufficient uncertainty. The values are assumed to have a rectangular distribution, and thus, the corresponding standard uncertainty (*k* = 1) is obtained considering the maximum value (0.045 ^{∘}C) divided by $\sqrt{\mathrm{3}}$. Consequently, the
uncertainty due to sensor rotation is 0.026 ^{∘}C (*k* = 1).

## 4.8 Uncertainty due to fitting error

Because Eq. (11) is used for the final radiation correction, the residuals
shown in Figs. 2b and 5c must be considered in determining the
uncertainty. The residuals are assumed to have a rectangular distribution,
and thus, the corresponding standard uncertainty (*k* = 1) is obtained
considering the maximum absolute value divided by $\sqrt{\mathrm{3}}$. Consequently,
the uncertainty due to the fitting error is 0.023 ^{∘}C (*k* = 1).

## 4.9 Uncertainty budget for radiation correction

The uncertainties in *T*, *P*, *v*, and *S* contribute to the uncertainty in the
radiation correction by the uncertainty propagation law based on Eq. (11):

where *u*(parameter) represents the standard uncertainty in each
parameter at *k* = 1, and the partial differential terms represent the
sensitivity coefficients. The sensitivity coefficients of the uncertainties
due to sensor rotation, tilting of the sensor, and fitting error are 1
because they directly contribute to the uncertainty in the radiation
correction. The uncertainty budget for the radiation correction (Δ*T*_{rad}) based on the conducted experiments is presented in Table 9.

## 4.10 Uncertainty budget for the corrected temperature, *T*_{cor}

The corrected temperature (*T*_{cor}) is obtained by subtracting Δ*T*_{rad} from the raw temperature (*T*_{raw}) as follows:

Thus, the uncertainty in the corrected temperature, *u*(*T*_{cor}), is calculated as follows:

where *u*(*T*_{raw}) is the standard uncertainty in the raw temperature (*k*=1). The uncertainty in Δ*T*_{rad}, indicated in Table 9,
must be rescaled in proportion to the actual solar irradiance for Eq. (17).
Therefore, the uncertainty in Δ*T*_{rad} is scaled up to a level of solar constant (∼ 1360 W m^{−2}) by a factor of
$\mathrm{1360}/\mathrm{980}$ based on the linear relationship between Δ*T*_{rad} and *S*.

The calibration uncertainty associated with the temperature sensor must be
considered to account for the uncertainty in the raw temperature,
*u*(*T*_{raw}). Consequently, the expanded uncertainty in the corrected
temperature of the RS41 is 0.138 ^{∘}C (*k* = 2), as indicated in
Table 10. The calibration uncertainty in the RS41 temperature
sensor, *U*(*T*_{raw}) (*k* = 2), is specified by the manufacturer
(Vaisala, 2022). Since Vaisala provides additional uncertainty in
reproducibility in sounding (0.15 ^{∘}C when *P* > 100 hPa,
0.3 ^{∘}C when *P* < 100 hPa) (Vaisala, 2022), this should be
added to the total uncertainty in the corrected temperature when the
radiation correction formula in Eq. (11) is applied to soundings.

## 4.11 Comparison of RS41 radiation correction specified by Vaisala and that obtained through the UAS

The radiation correction of the RS41 by the UAS is based on Eq. (11) for
different pressure ranges. In order to apply the correction formula to
actual soundings, the effective irradiance to the sensor should be known.
However, radiosondes constantly change positions with respect to the solar
irradiation through rotation and pendulum motion; the calculation of
effective irradiance resorts to the mean of effective irradiance over the motion of radiosondes. Figure 8a shows a schematic diagram of a radiosonde with parameters that affect the effective irradiance *S*_{eff} on the sensor. Then, the effective irradiance to the sensor can be calculated as follows:

*S*_{dir} is solar direct irradiance, *θ* is boom tilting angle, *α* is solar elevation angle, and *φ* is azimuthal angle. The effective irradiation area (${A}_{\mathrm{eff}}/{A}_{\mathrm{0}}$) on the sensor boom is averaged over rotation (*φ*) with a fixed tilting angle *θ* = 45^{∘} and plotted as a function of the solar elevation angle as shown in Fig. 8b. Using this effective irradiance, the radiation correction by the UAS is obtained and compared with that of the manufacturer at two different *α* values (45 and 90^{∘}), as shown in Fig. 9. For the UAS correction, the solar direct irradiance is assumed to be 1360 W m^{−2} at all pressure values. To simulate the albedo effect, the radiation correction with additional irradiance of 400 W m^{−2} is also calculated. Consequently, the radiation correction of the UAS is smaller than the Vaisala by about 0.5–0.7 ^{∘}C at −70 ^{∘}C and 5 hPa when only the solar direct irradiance (1360 W m^{−2}) is considered with the solar elevation angle *α* = 45–90^{∘}. When the albedo effect is additionally included (400 W m^{−2}), the gap between the two corrections is reduced to 0.04–0.4 ^{∘}C at −70 ^{∘}C and 5 hPa with *α* = 45–90^{∘}. Since solar direct irradiance (1360 W m^{−2}) and additional diffuse irradiance (400 W m^{−2}) are applied for all pressures, the radiation correction of this work can be exaggerated at high pressures. The radiation correction of the UAS is smaller than that of the manufacturer at low pressures, which is consistent with the recent finding using an independent laboratory set-up. In the work of von Rohden et al. (2022), the radiation correction was smaller than the manufacturer's by 0.35 K at 35 km. The radiation corrections of the manufacturer and the UAS at some representative conditions are summarized in Table 11.

The UAS developed at KRISS provides a unique opportunity to correct the
solar radiation effect on commercial radiosondes by reproducing the
environments that may be encountered by radiosondes by simultaneously
controlling *T*, *P*, *v*, and *S*. The following ranges of *T*, *P*, and *v* are considered in this study: −67 to 20 ^{∘}C, 5–500 hPa, and 4–7 m s^{−1}, respectively, with a fixed *S*_{0} = 980 W m^{−2}. The functionalities of rotating and tilting the
sensor boom are added considering the previous report on the UAS (Lee
et al., 2020) to investigate the effect of the radiosonde motions with
respect to the solar irradiation direction during ascent. The correction
formula for the radiation effect on a Vaisala RS41 temperature sensor is
derived through a series of experiments with varying environmental
parameters as well as motions and positions of the radiosonde sensor. In addition, an
empirical formula is derived to estimate the low-temperature effect by using
only the inputs of room-temperature measurements.

The uncertainty associated with the radiation correction is evaluated by
combining the contribution of each uncertainty factor. The uncertain factors
considered for the radiation correction are *T*, *P*, *v*, and *S* as well as the sensor rotation, sensor tilting, and data-fitting-induced errors. The uncertainty budget for the radiation correction of the RS41 temperature sensor is 0.1 ^{∘}C at *k* = 2. When the uncertainty in the absolute temperature measurement (calibration uncertainty) is included, the uncertainty in the corrected temperature is estimated to be 0.17 ^{∘}C at *k* = 2. The radiation correction values by the UAS are provided when the solar constant (1360 W m^{−2}) is used for *S* for the comparison with those by
the manufacturer. The radiation correction by the UAS depends on effective
solar irradiance. Thus, the measurement of solar irradiance in situ and the
calculation of effective irradiance are desirable to reflect the conditions
such as clouding, solar elevation angle, and radiosonde movement, thereby
obtaining more accurate correction values. To measure the solar irradiance
in situ, a radiosonde model using dual temperature sensors with different
emissivity values has already been tested using the UAS. The temperature
difference in the two sensors of the radiosonde is recorded with varying
environmental parameters in the UAS to be reversely used to measure solar
irradiance in situ during sounding. In this sense, the approach based on
dual sensors is different from previous works that estimate the air
temperature using several other temperatures measured by sensors with
different emissivity (Schmidlin et al., 1986).

As the UAS can support wired and wireless data acquisition, it can be used for any type of commercial radiosonde to derive the radiation correction along with the corresponding uncertainty. Therefore, the UAS can help enhance the measurement accuracy of commercial radiosondes within the framework of the SI traceability.

The operation programme of the upper-air simulator based on LabVIEW software is available upon request.

The laboratory experiment data used for Figs. 1 to 9 are available upon request.

SWL analysed the experimental data and wrote the manuscript. SKi and YSL conducted experiments. BIC built the humidity control system, WK and YKO built the airflow control system, and SP and JKY established the solar simulator set-up. JL conducted theoretical calculation. SL and SKw developed the measurement software. YGK designed the experiments.

The contact author has declared that neither they nor their co-authors have any competing interests.

Publisher’s note: Copernicus Publications remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.

This research has been supported by the Korea Research Institute of Standards and Science (grant no. GP2021-0005-02).

This paper was edited by Roeland Van Malderen and reviewed by Ruud Dirksen and one anonymous referee.

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