## 1 Introduction  
Near space refers to the airspace connecting the sky and space at an altitude of 20-100 km, where it is difficult for general aircraft to operate. It has an important strategic position [1, 2, 3, 4]. The atmospheric environmental parameters in near space, including temperature, pressure, and wind, are critical meteorological parameters that can directly affect space activities, so it is essential to detect these parameters accurately [5, 6, 7, 8]. Its environmental conditions are complex, with temperatures down to minus 70 \({}^{\circ}\)C, ultra-low pressure, and a complex wind field [9, 10]. In addition, there are also environmental interference factors, such as irradiation and electromagnetism, which affect the high-precision detection of atmospheric environmental parameters in near space [6]. The space-based platform is equipped with multi-parameter radiosodes, forming a sizeable all-height detection cluster with fast maneuvering speed and high coverage. This platform can continuously detect environmental parameters such as temperature, density, wind field, and pressure at fixed points [11, 12]. The sounding rocket platform possesses fast maneuverability and high coverage height, while the airship platform exhibits characteristics of high mobility and increased carrying capacity [13, 14]. The sounding rocket platform cooperates with the airship platform. It is equipped with radiosondes to overcome the harsh environmental impact of near space and obtain fixed-point continuous detection of ecological parameters. When the radiosonde rises to a specific position with the platform, it is ejected and descends while the parachute opens. Due to the thin air, the radiosonde will drop with a vertical acceleration close to the acceleration of gravity. When reaching a low altitude, the air resistance increases, and the descent rate slows. During in situ temperature detection, many temperature measurement errors can occur [5]. According to the radiosonde temperature correction model given by the World Meteorological Organization, the factors that cause temperature measurement errors include aerodynamic heat, temperature hysteresis, solar radiation, solar radiation reflected by the ground and clouds, environmental long-wave radiation, radiation from sensors to the environment, heat conduction of the support structure, and Joule heat, which need to be decoupled to obtain the actual atmospheric temperature value [15; 16]. Aerodynamic heat: due to the thin atmosphere in near space, the falling speed can reach hundreds of meters per second during the dropping of the radiosonde [4]. The temperature sensor directly exposed to the air compresses the air in front of it, and the gas temperature rises--that is, aerodynamic heat. Therefore, the temperature field where the temperature sensor is located is not the actual atmospheric temperature field but the temperature field superimposed by aerodynamic heat [17; 18]. Joule heat: during the working process of the resistance temperature sensor, a large Joule heat is generated due to the enormous resistance value, which significantly impacts its thermal field characteristics. This directly causes temperature measurement errors [19]. Solar radiation: the intensity of solar radiation in near space is significant, and the amount of solar radiation will lead to the change in temperature error caused by the solar radiation heating effect. In addition, the change in air pressure and the sensor surface material will also cause different temperature errors of solar radiation. Other radiation: after entering the Earth's atmosphere, the solar radiation will be absorbed, reflected, scattered by various components in the air, and then absorbed and reflected by the ground after reaching the ground. This part reflects solar radiation from the ground and clouds, which will increase the sensor's temperature.