Immersion nitrogen thermostat

Abstract

The invention discloses an immersion type nitrogen thermolator which comprises a thermolator container and a controller. The centers of the bottom and the top of the thermolator container are provided with a nitrogen inlet and a nitrogen outlet. The nitrogen inlet communicates with one end of a heat exchanger assembly. The nitrogen outlet communicates with the other end of the heat exchanger assembly. The heat exchanger assembly is arranged in an inner container barrel, the barrel is filled with liquid nitrogen so as to exchange heat with introduced nitrogen, a heat exchanger is further surrounded by a liquid nitrogen coil pipe assembly, and therefore supplemented liquid nitrogen is injected into the inner container barrel from a liquid supplementing inlet through a liquid nitrogen supplementing outlet pipeline. The bottom of the thermolator container is provided with a liquid outlet, and the top of the thermolator container is provided with an atmospheric valve, a pressure gage and a liquid level meter. A temperature sensor is arranged on a nitrogen exhaust manifold. The controller sets the target control height of the liquid level meter according to the difference between the target temperature and the nitrogen exhaust temperature measured by the temperature sensor. By adjusting the opening of a liquid supplementing adjusting valve, the liquid level height of liquid nitrogen stored in the thermolator container is fed back and controlled to reach the target control height, and the nitrogen outlet temperature is adjusted to reach the target temperature.

Description

technical field [0001] The invention relates to the technical field of spacecraft vacuum heat test, in particular to a temperature regulating device in vacuum heat test. Background technique [0002] When a spacecraft is in orbit, the space environment changes drastically periodically. The huge temperature difference causes serious thermal deformation of many components on the spacecraft, so it is necessary for the space environment simulator to provide a simulated environment with a background temperature of a large temperature difference. At the same time, there are a variety of large flexible structures on the spacecraft. In order to verify the working performance of these structures in the space environment, it is also necessary to conduct structural deployment tests in the space environment simulator. At present, the test method of combining the liquid nitrogen system and the infrared heat flow simulation device conventionally configured in the space environment simula...

AI Technical Summary

Problems solved by technology

[0004] Under normal conditions, the temperature of the heat sink is cooled by liquid nitrogen, and its surface temperature is a constant temperature, which cannot provide the simulation of the state of heat flow change in the space environment required by the spacecraft

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