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Independent temperature and humidity control system and implementation method of airtight cabin of space vehicle

An independent control technology for space vehicles, applied in heating and ventilation control systems, air conditioning systems, space heating and ventilation, etc. problems, to achieve the effect of ensuring the accuracy of humidity control, realizing precise control, and ensuring the effect of humidity control

Active Publication Date: 2015-09-23
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

However, for my country's future long-term resident space missions, it is not only necessary to ensure the long-term comfort of the astronauts, but also to consider the influence of air temperature and humidity on the growth of microorganisms. There is strong coupling, and it is difficult to meet the dual control index requirements of air temperature and humidity in the sealed cabin, which will have a certain impact on the successful completion of my country's manned space missions

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  • Independent temperature and humidity control system and implementation method of airtight cabin of space vehicle

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Embodiment Construction

[0052] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0053] Such as figure 1 As shown, the integrated temperature and humidity control system is the temperature and humidity control method currently used in space sealed cabins. Through the ventilation regulating valve 106, the air 101 of the main ventilation road is divided into two parts: the dehumidification air branch 102 and the bypass air branch 105, The dehumidification air branch 103 is equipped with a condensing drier assembly 4. The condensing drier assembly 4 cools and dehumidifies the air under the cooling effect of the low temperature circuit 2. After cooling and dehumidifying, the air is mixed with the bypass air, and the temperature and humidity at the mixing point 6 are the control objects. . The low temperature circuit 2 itself does not have the function of active temperature regulation, and the temperature adjustment of the mixin...

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Abstract

The invention belongs to the technical field of thermal control of an environment of a sealed cabin of a space aircraft, and relates to an independent temperature and humidity control system for a sealed cabin of a space aircraft and an implementation method. By means of the design of the independent air temperature and humidity control system structure and the implementation method, decoupling control on the temperature and the humidity of air in the sealed cabin of the space aircraft is achieved, the defect that control requirements of double targets of the temperature and the humidity of the air are difficult to meet by means of an integrated temperature and humidity control system is overcome, and the detailed requirement for controlling the temperature and the humidity of the sealed cabin of a future space aircraft is met.

Description

technical field [0001] The invention relates to an independent temperature and humidity control system and an implementation method of a space vehicle airtight cabin, belonging to the technical field of space vehicle environmental thermal control Background technique [0002] With the development of human space technology, in recent years, manned space technology such as low-Earth orbit manned spacecraft and manned moon landing spacecraft has achieved rapid development in many countries, and manned missions have also shown a long-term development trend. As the passenger carrier of manned spacecraft and manned moon landing spacecraft, the airtight cabin is responsible for the important task of providing suitable temperature and humidity environment for the astronauts in the cabin. The research on the temperature and humidity control technology of the airtight cabin is very important to ensure the life safety of astronauts, The normal work of the equipment load in the cabin an...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F24F5/00F24F11/02F24F13/30
Inventor 满广龙刘东晓曹剑峰范宇峰韩海鹰
Owner BEIJING INST OF SPACECRAFT SYST ENG
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