## 5 Conclusions  
In response to the problems of existing methods, a method to achieve in situ high-accuracy temperature detection in near space was proposed by analyzing the actual measurement environment. By designing a new type of temperature sensor and analyzing the sources of error in the actual measurement process and their influencing factors, we achieved high-precision temperature values by applying a temperature error compensation method. In this way, we can apply it to the in situ high-precision detection of near space temperature. The conclusions are as follows. Figure 15: Variation in aerodynamic heat with relative air speed at two sensor points. 1. The temperature sensor has a microbridge structure with a short response time using silver as the radiation-proof coating. The smaller the emissivity of the anti-radiation coating, the more minor the radiation heat generated. The choice of silver as the radiation-proof coating results in a small radiation heat error and improves the measurement accuracy of the temperature sensor. 2. The optimized near space temperature error model shows that the resulting measurement errors include aerodynamic heat, solar radiation, and Joule heat. Aerodynamic heat has the greatest effect on temperature error, and solar radiant heat has the least impact. Therefore, in the actual calculation process, the magnitude of the pneumatic heat needs to be calculated precisely. 3. The aerodynamic heat error at the front end of the radiosonde is the largest, and the temperature error at the rear end is the smallest. The temperature sensor is arranged at the front end of the radiosonde. The aerodynamic heat error of the front end of the sensor is the largest, the rear end has the slightest temperature error, and the Pt thin film is installed at the back end of the sensor. Additionally, reducing the descent speed can effectively decrease the aerodynamic heat. 4. As the air pressure increases, there will be the following changes: the response rate of the temperature sensor increases, and the steady-state temperature is closer to the ambient temperature, i.e., the temperature error decreases. The temperature of the sensor rises rapidly and then slowly. As a result, a more precise calculation of the temperature error is necessary for the low-pressure environment at high altitudes. 5. By establishing the temperature error model, we can significantly enhance the accuracy of obtaining temperature values in near space. This method can be applied to in situ high-precision temperature detection data in near space. Conceptualization and methodology, G.W. and C.H. ; Software, G.W. ; Validation, G.W. and C.H. ; Investigation, G.W. and C.H. ; Writing--original draft preparation, G.W. ; Writing--review and editing, C.H. ; Visualization, G.W. and D.Z. ; Supervision, D.Z. and C.H. ; Funding acquisition, D.Z. All authors have read and agreed to the published version of the manuscript. This research was funded by the National Key R&D Program of China under Grant No. 2021 YFB3201502 and the National Natural Science Foundation of China (Grant No. 61827901; No. 62088101; No. 62203056). Not applicable. Not  
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