HERMES CubeSat Payload Thermal Balance Test and Comparison with Finite Volume Thermal Model

被引:3
|
作者
Quirino, Matteo [1 ]
Sciarrone, Giulia [2 ]
Piazzolla, Raffaele [3 ]
Fuschino, Fabio [4 ]
Evangelista, Yuri [3 ]
Morgante, Gianluca [4 ]
Guilizzoni, Manfredo [5 ]
Marocco, Luca [5 ]
Silvestrini, Stefano [1 ]
Fiore, Fabrizio [6 ]
Lavagna, Michele [1 ]
机构
[1] Politecn Milan, Dept Aerosp Sci & Technol, I-20156 Milan, Italy
[2] Sapienza Univ Roma, Dept Mech & Aerosp Engn, I-00185 Rome, Italy
[3] Natl Inst Astrophys, I-00133 Rome, Italy
[4] Natl Inst Astrophys, I-40129 Bologna, Italy
[5] Politecn Milan, Dept Energy, I-20156 Milan, Italy
[6] Natl Inst Astrophys, I-34143 Trieste, Italy
来源
APPLIED SCIENCES-BASEL | 2023年 / 13卷 / 09期
基金
欧盟地平线“2020”;
关键词
CubeSat; thermal balance test; Gamma Ray detector; OpenFOAM; thermal model;
D O I
10.3390/app13095452
中图分类号
O6 [化学];
学科分类号
0703 ;
摘要
Scientific payloads onboard CubeSats usually have complex geometries and occasionally narrower allowed temperature ranges with respect to the rest of the spacecraft. In these cases, the capability to correctly predict the thermal behaviour of the payload once in orbit is mandatory. To achieve this ability, a thermal balance test is required to correctly identify the thermal model of the payload. The test consists in the application of different external thermal boundary conditions together with the addition of heat dissipation to simulate the thermal load produced by active electronics during operation. Those experimental data are fundamental to validate the numerical thermal model and make its predictions reliable. This paper presents the configuration and procedures of the thermal balance test performed on the Demonstration Model of the payload to be embarked on each satellite of the HERMES constellation. The test data is compared with the results of a finite volume thermal model of the payload, proving the application of this method to be reliable for space thermal analyses. The obtained test results show the temperature jumps caused by the heat dissipation applied to active components. A weak correlation between the payload interface and internal equipment has been observed, thus proving that the payload is almost decoupled from the Service Module temperature variations. Based on test outcomes, some modifications in the payload design have been implemented, with the aim to lower the operative temperature on critical, temperature-sensitive equipment.
引用
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页数:28
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