Self-circulating heat management and power generation system for lunar base
A power generation system and heat management technology, applied in solar thermal power generation, solar heating systems, solar collectors in specific environments, etc., can solve problems such as low-temperature waste heat exceeding the working temperature range, inability to apply to space and aerospace, and heat transfer. To achieve the effect of saving electricity demand
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Embodiment 1
[0026] In this example, a self-circulating thermal management and power generation system used in a lunar base, the working fluid is R600, and the circulation process is illustrated for daytime or extreme daytime conditions.
[0027] In daytime or extreme daytime conditions, the temperature of the cold plate is 30°C, the waste heat utilization is 6.3kW, after being heated by the directional solar collector 4, the temperature is 40°C, the evaporation pressure is 0.4MPa, and the expansion ratio of the turbine 5 is 2.5, The outlet pressure of the turbine 5 is 0.15MPa, the condensing temperature of the directional space radiator 10 is -10°C, the condensing pressure is 0.07MPa, the evaporation temperature of the refrigeration evaporator 13 is -15°C, and the space ambient temperature is 4K. The above parameters are taken as The working parameters illustrate the cycle flow, but the parameters involved in the implementation process do not limit the present invention.
[0028] 1. The l...
Embodiment 2
[0036] In this embodiment, a self-circulating heat management and power generation system used in a lunar base, the working fluid is R600, and the circulation process is illustrated for the night or polar night state.
[0037] During daytime or extreme daytime conditions, the temperature of the cold plate 2 is 30°C, the waste heat utilization is 6.3kW, the temperature is 40°C after being heated by the directional solar collector 4, the evaporation pressure is 0.4MPa, and the expansion ratio of the turbine 5 is 2.5 , the outlet pressure of the turbine 5 is 0.15MPa, the condensation temperature of the directional space radiator 10 is -10°C, the condensation pressure is 0.07MPa, the evaporation temperature of the refrigeration evaporator 13 is -15°C, and the space environment temperature is 4K, the above parameters As working parameters, the cycle flow is described, but the parameters involved in the implementation process do not limit the present invention.
[0038] 1. The liqui...
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