scholarly journals Simulation of the thermal control system of nanosatellite using the loop heat pipes under the orbital flight conditions

2021 ◽  
Vol 22 (1) ◽  
pp. 23-35
Author(s):  
Yu Wang ◽  
Oleg V. Denisov ◽  
Liliana V. Denisova
Keyword(s):  
Control System ◽  
Thermal Regime ◽  
Thermal Power ◽  
Heat Removal ◽  
Heat Pipes ◽  
Thermal Control ◽  
Thermal Design ◽  
Loop Heat Pipes ◽  
Thermal Control System ◽  
Design Power

One of the key problems in the development of nanosatellites is to provide a given temperature range for the operation of the on-board computer. The constantly increasing information load leads to the need to use more advanced processors with high thermal design power (TDP). The indicated thermal regime of processors can be achieved using remote heat removal systems - miniature loop heat pipes. Using a model of nanosatellite as an example, a thermal control system with miniature loop heat pipes is designed. The simulation was carried out in the Siemens NX program in the elliptical and geostationary orbits of the Earth. The cooling schemes of the processor with a thermal power of 15 W using one and two loop heat pipes are considered. Calculations showed that the use of loop heat pipes can reduce the processor temperature to acceptable values. The anisotropy of the thermal conductivity coefficient in the reinforcement plane of the composite material of the nanosatellite case can have a significant effect on the temperature of the processor. This opens up prospects for the use of anisotropic composite materials to ensure the thermal regime of the nanosatellite.

Thermal Control System of Microsatellite with Loop Heat Pipes

2012 ◽  
Author(s):  
Naoko Iwata ◽  
Hiroyuki Ogawa ◽  
Joaquín Molleda ◽  
Takeshi Takashima ◽  
Tadayuki Takahashi
Keyword(s):  
Control System ◽  
Heat Pipes ◽  
Thermal Control ◽  
Loop Heat Pipes ◽  
Thermal Control System

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

Sensors ◽  
2019 ◽  
Vol 19 (4) ◽  
pp. 827 ◽  
Author(s):  
Lin Yang ◽  
Qiang Li ◽  
Lin Kong ◽  
Song Gu ◽  
Lei Zhang
Keyword(s):  
Thermal Analysis ◽  
Control System ◽  
Temperature Fluctuation ◽  
Thermal Control ◽  
Temperature Data ◽  
Thermal Design ◽  
Analysis Model ◽  
Telemetry Data ◽  
Thermal Control System ◽  
Fluctuation Range

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.

Thermal analysis and optimization of the electronic crates of Alpha Magnetic Spectrometer

2020 ◽  
Vol 64 (1-4) ◽  
pp. 271-279
Author(s):  
Fayi Yan
Keyword(s):  
Control System ◽  
Particle Physics ◽  
Space Station ◽  
Heat Pipes ◽  
Thermal Control ◽  
Magnetic Spectrometer ◽  
Modeling And Simulations ◽  
Thermal Control System ◽  
Operational Temperature ◽  
Alpha Magnetic Spectrometer

Alpha Magnetic Spectrometer (AMS-02) is a particle-physics detector from a module attached to the outside of the International Space Station (ISS). The temperature of the components in AMS-02 must be kept within their different operational ranges but also must be stable over both time and volume. Thermal modeling and simulations for the radiator and the electronic crates of AMS-02 were carried out by applying the Crank–Nicholson implicit solution. Based on reducing the temperature gradient of the radiator and the mass of the thermal control system, the layout of the heat pipes in the radiator was optimized to solve the overheating issue of the electronic crates. The non-operational and operational temperature dissipation for the thermal control system was calculated. The analysis results for the radiator and the electronic crates can meet the running requirements of AMS-02 on the ISS.

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