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CN-121990185-A - Power generation and radiation refrigeration integrated system for high-power calculation satellite

CN121990185ACN 121990185 ACN121990185 ACN 121990185ACN-121990185-A

Abstract

The invention discloses a power generation and radiation refrigeration integrated system for a high-power calculation satellite. The system comprises an integrated functional panel, a photovoltaic power generation unit, an active radiation refrigeration unit and a closed pump drive heat transmission loop, wherein the integrated functional panel comprises a panel body, the panel body is provided with a first surface and a second surface which are opposite, the panel body blocks heat conduction and heat radiation between the first surface and the second surface, the photovoltaic power generation unit is arranged on the first surface, the active radiation refrigeration unit is arranged on the second surface, the active radiation refrigeration unit is provided with an outer surface with spectrum selective radiation refrigeration characteristics, the active radiation refrigeration unit comprises an inner micro-channel structure thermally coupled with the outer surface, and the closed pump drive heat transmission loop is connected with a heating electronic element and the inner micro-channel structure in the satellite body. The invention can improve the satellite heat dissipation efficiency and optimize the power generation performance, realize the heat and electricity integrated management of the high-efficiency calculation satellite platform, improve the reliability and efficiency of the whole system and reduce the whole weight of the energy system.

Inventors

  • Abulimiti Alex
  • ZHOU XIN
  • BIAN XIANGGUO
  • FU QIANG

Assignees

  • 光合泰智(杭州)科技有限公司

Dates

Publication Date
20260508
Application Date
20260326

Claims (10)

  1. 1. The power generation and radiation refrigeration integrated system for the high-power calculation satellite is characterized by comprising an integrated functional panel, a photovoltaic power generation unit, an active radiation refrigeration unit and a closed pump drive heat transmission loop, wherein the integrated functional panel comprises a panel body, the panel body is provided with a first surface and a second surface which are opposite, and the panel body blocks heat conduction between the first surface and the second surface; The active radiation refrigeration unit is provided with an outer surface with spectrum selective radiation refrigeration characteristics, and comprises an internal micro-channel structure thermally coupled with the outer surface; The closed pump driving heat transmission loop is connected with the heating electronic element in the satellite body and the internal micro-channel structure, and is used for conveying heat from the heating electronic element to the active radiation refrigeration unit and dissipating the heat in a heat radiation mode through the outer surface.
  2. 2. The integrated power generation and radiation refrigeration system for high power computing satellites of claim 1 wherein the area ratio of the first surface to the second surface is from 0.8:1 to 1.2:1.
  3. 3. The integrated power generation and radiation refrigeration system for high power computing satellites of claim 2 wherein the panel body is a thermally insulating structural layer having a heat transfer coefficient no higher than 0.01W/m-K.
  4. 4. The integrated power generation and radiation refrigeration system for high power computing satellites of claim 3 wherein said panel body is of aerogel reinforced honeycomb sandwich structure with a core layer filled with nanoporous silica aerogel having a thickness of 5mm.
  5. 5. The integrated power generation and radiation refrigeration system for high-power satellite according to claim 1, wherein the outer surface of the active radiation refrigeration unit is a spectrum selective radiation refrigeration coating, the reflectivity is more than or equal to 95% in the solar spectrum band of 0.2-2.5 μm, the absorptivity is less than or equal to 5%, and the emissivity is more than or equal to 95% in the infrared heat radiation band of 8-13 μm.
  6. 6. The integrated power generation and radiation refrigeration system for high power computing satellites of claim 5 wherein the external surface of the active radiation refrigeration unit is a multilayer thin film interference structure or a multi-scale micro-nano porous alumina coating, wherein the multilayer thin film interference structure comprises alternately deposited layers of SiO 2 and Si 3 N 4 , and the multi-scale micro-nano porous alumina coating is a multi-stage pore structure with pore size distribution of 50nm-5 μm on the surface.
  7. 7. The integrated power generation and radiation refrigeration system for high power computing satellites according to claim 1 wherein the internal microchannel structure comprises a plurality of parallel microchannels, an inlet manifold and an outlet manifold, wherein the microchannels have a width of 30-100 μm and a depth of 150-300 μm; the inlet manifold is communicated with the micro-channels and is used for uniformly distributing heat transfer working media to each micro-channel; And the outlet manifold is communicated with the micro-channels and is used for collecting the heat transfer working medium flowing out of each micro-channel.
  8. 8. The integrated power generation and radiation refrigeration system for high power computing power satellite according to claim 7, wherein the internal micro-channel structure is a jet enhanced manifold micro-channel structure, wherein the inlet manifold is provided with a jet nozzle, the diameter of the jet nozzle is 20-100 μm, and the jet enhanced manifold micro-channel structure enables the panel equivalent heat dissipation power density of the active radiation refrigeration unit by reducing the heat exchange temperature difference between the heat transfer working medium and the radiation surface.
  9. 9. The integrated power generation and radiation refrigeration system for the high-power computing power satellite according to claim 1, wherein FC-72 perfluorocarbon liquid is filled in the closed pump drive heat transmission loop to serve as a heat transfer working medium, the heat transfer working medium is dielectric cooling liquid, the freezing point is lower than-50 ℃, and the boiling point is higher than 100 ℃.
  10. 10. A high power satellite comprising said satellite body and an integrated power generation and radiation refrigeration system for a high power satellite according to any one of claims 1 to 9.

Description

Power generation and radiation refrigeration integrated system for high-power calculation satellite Technical Field The invention relates to the technical field of spacecraft energy and thermal control, in particular to a power generation and radiation refrigeration integrated system for a high-power computing satellite. Background With the deep convergence of aerospace technology and artificial intelligence technology, the concept of space data centers is moving from theory to practice. Both "orbital edge" computation satellites for earth observation real-time processing and "orbital clouds" composed of computation satellite constellations place extremely high demands on the computation power of the satellite platform. To meet this demand, a satellite is beginning to deploy AI chips such as a graphics processor with high power consumption, a general-purpose server, and a neural network processor dedicated to deep learning acceleration. The power consumption of the devices can reach hundreds of watts or even up to kilowatts, so that the local heat flux density of the satellite is dramatically increased, and the traditional spacecraft thermal control technology faces serious challenges. In conventional spacecraft designs, the energy system and the thermal control system are typically independent of each other. The energy system relies on solar panels to convert light energy into electrical energy, while the thermal control system relies on radiators to dissipate waste heat to deep space. Each of these two systems occupies valuable space on the satellite outer envelope, and there is a direct competition in layout. Taking an active heat control system of an international space station as an example, a single radiator reaches 740.7 kg, the unfolding area is about 42.5 square meters, the heat dissipation power is only 14kW, and the heat dissipation power density is about 312W/m < 2 >. Such inefficient and cumbersome systems obviously fail to meet the demands of miniaturized, high power, power-computing satellites for future mass deployment. More importantly, the conventional design has a technical prejudice that the solar panel needs to absorb as much sunlight as possible, and the radiator needs to absorb as little sunlight as possible while efficiently emitting infrared rays. Therefore, it is generally considered that these two functions cannot be realized on the same structure, which results in a state that the satellite design is in a compromise state between the power generation area and the heat dissipation area for a long time, and severely restricts the improvement of satellite calculation power. While the development of some advanced materials and techniques, such as spectrally selective radiant refrigerant materials, offer new possibilities for addressing these issues, the main limitation in current applications is how to effectively integrate these new techniques into existing spacecraft designs. Most of the prior attempts stay in laboratory stage or small-scale test, and lack successful cases of large-scale practical application. Therefore, it is necessary to design a new system, which can improve the heat dissipation efficiency of the satellite and optimize the power generation performance, realize the thermoelectric integrated management of the high-efficiency computing satellite platform, improve the reliability and efficiency of the whole system, and reduce the whole weight of the energy system. Disclosure of Invention The invention aims to overcome the defects of the prior art and provides a power generation and radiation refrigeration integrated system for a high-power computing satellite. The integrated power generation and radiation refrigeration system for the high-power calculation satellite comprises an integrated functional panel, a photovoltaic power generation unit, an active radiation refrigeration unit and a closed pump driving heat transmission loop, wherein the integrated functional panel comprises a panel body, the panel body is provided with a first surface and a second surface which are opposite, and the panel body blocks heat conduction between the first surface and the second surface; The active radiation refrigeration unit is provided with an outer surface with spectrum selective radiation refrigeration characteristics, and comprises an internal micro-channel structure thermally coupled with the outer surface; The closed pump driving heat transmission loop is connected with the heating electronic element in the satellite body and the internal micro-channel structure, and is used for conveying heat from the heating electronic element to the active radiation refrigeration unit and dissipating the heat in a heat radiation mode through the outer surface. The area ratio of the first surface to the second surface is 0.8:1 to 1.2:1. The panel body is a heat insulation structure layer, and the heat transfer coefficient is not higher than 0.01W/m.K. The panel body adopts an aerogel rein