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. 2019 Feb 17;19(4):827.
doi: 10.3390/s19040827.

Quasi-All-Passive Thermal Control System Design and On-Orbit Validation of Luojia 1-01 Satellite

Lin Yang  1   2   3 , Qiang Li  4 , Lin Kong  5   6 , Song Gu  7   8   9 , Lei Zhang  10   11   12
Affiliations

Quasi-All-Passive Thermal Control System Design and On-Orbit Validation of Luojia 1-01 Satellite

Lin Yang et al. Sensors (Basel). .

Abstract

In order to resolve the large fluctuations in temperature range problem of Luojia 1-01 satellite caused by low heat inertia and poor thermal conductivity of structure, a quasi-all-passive thermal control system (TCS) design is presented under the conditions of limited resources including mass and power consumption. The effectiveness of the TCS design is verified by both ground thermal balanced test and related telemetry data of on-orbit performance. Firstly, according to the structural features and working modes of the satellite, isothermal design was implemented and the effectiveness was verified by thermal analysis using finite element method. Secondly, based on the results of the thermal analysis, thermal design was optimized and verified by the thermal balanced test. Finally, the thermal design was proved to be effective by temperature data acquired from telemetry data of on-orbit performance, and the thermal analysis model was improved and updated based on the results of thermal balanced test and temperature data of on-orbit performance. The on-orbit data indicates that temperature of optical camera stables at about 12 °C, temperature of battery stables at 19 °C, temperature of instruments inside and outside the satellite cabin is ranging from 10 °C to 25 °C. Temperature fluctuation range of optical camera is less than 2 °C when it is not imaging. Temperature fluctuation range of instruments not facing the sun is less than 4 °C. The data suggests that the temperature level of the satellite meets general design requirements, and the quasi-all-passive TCS design of the satellite is practicable.

Keywords: on-orbit performance; quasi-all-passive; temperature fluctuation; thermal analysis; thermal balanced test.

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Conflict of interest statement

The authors declare no conflict of interest. Together We declare that we have no financial and personal relationships with other people or organizations that can inappropriately influence our work, there is no professional or other personal interest of any nature or kind in any product, service and/or company that could be construed as influencing the position presented in, or the review of, the manuscript entitled.

Figures

Figure 1
Figure 1
Luojia 1-01 satellite coordinate system.
Figure 2
Figure 2
Exploded view of the Luojia 1-01 Satellite.
Figure 3
Figure 3
Shock absorbers in the Luojia 1-01 satellite (without the side solar panels).
Figure 4
Figure 4
Variation curve of heat flux density on the satellite’s surface.
Figure 5
Figure 5
Radiating regions of the Luojia 1-01 satellite. (a) Radiating region of the +Y panel. (b) Radiating region of the −Y panel.
Figure 6
Figure 6
Thermal analysis model of the Luojia 1-01 satellite.
Figure 7
Figure 7
Analysis result of the temperature variation curve of the camera under high temperature conditions.
Figure 8
Figure 8
Analysis result of the temperature variation curve of the camera under low temperature conditions.
Figure 9
Figure 9
Analysis result of the temperature variation curve of the battery under high temperature conditions.
Figure 10
Figure 10
Analysis result of the temperature variation curve of the battery under low temperature conditions.
Figure 11
Figure 11
Analysis result of the temperature variation curve of the solar panels under high temperature conditions.
Figure 12
Figure 12
Analysis result of the temperature variation curve of the solar panels under low temperature conditions.
Figure 13
Figure 13
Schematic diagram of the testing devices.
Figure 14
Figure 14
Testing site of Luojia 1-01.
Figure 15
Figure 15
Temperature variation curve of the inside instruments on the Luojia 1-01.
Figure 16
Figure 16
Temperature variation curve of the outside instruments in the Luojia 1-01.
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References

    1. Lin L.X. Technology development and application prospects of CubeSat. Spacecr. Eng. 2013;22:90–98. (In Chinese)
    1. Lin L.X., Zhang X.L. Discussion on conception of cluster, constellation and formation flying. Spacecr. Eng. 2012;21:97–102. (In Chinese)
    1. Tsitas S. 6U CubeSat commercial applications. Aeronaut. J. 2012;116:1176. doi: 10.1017/S0001924000006692. - DOI
    1. Robert H.M., Seah P.H. Global commerce in small satellites: Trends and new business models; Proceedings of the 28th Annual AIAA/USU Conference on Small Satellites; Washington, DC, USA. 4–7 August 2014; pp. 1–6.
    1. Zhou Y.Q., Luo C., Ni T., Ye S.L. Development trend of the commercialized microsatellite industry. Space Int. 2016;5:37–43. (In Chinese)

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