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Auxiliary heat transfer mechanism, outboard load and space station

A technology for space stations and loads, which is applied to motor vehicles, transportation and packaging, devices for controlling the living conditions of spaceflight vehicles, etc., and can solve problems such as the inability to meet the small size and high power heat dissipation requirements of external loads

Active Publication Date: 2020-05-15
TECH & ENG CENT FOR SPACE UTILIZATION CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Because there is no heat convection in the space environment, and thermal radiation requires a large radiation surface, it cannot meet the small-size, high-power heat dissipation requirements of the external load. Usually, the external load (external exposure test load) is placed in the experimental process by heat conduction. The heat generated is transferred to the cold end of the bulkhead

Method used

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  • Auxiliary heat transfer mechanism, outboard load and space station
  • Auxiliary heat transfer mechanism, outboard load and space station
  • Auxiliary heat transfer mechanism, outboard load and space station

Examples

Experimental program
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Effect test

Embodiment 1

[0037] Such as Figure 1-6 As shown, an auxiliary heat transfer mechanism for the external load of the space station is used to conduct the heat of the heat dissipation surface of the external load 8 to the cold plate of the bulkhead of the space station, including a heat conduction assembly 1 and an electric propulsion mechanism, and the heat transfer of the heat conduction assembly 1 The end is used to connect with the heat dissipation surface of the external load 8, and the cold end of the heat conduction component 1 is located on the free side of the electric propulsion mechanism, and moves toward the cold plate of the bulkhead of the space station under the push of the electric propulsion mechanism.

[0038] After the electric propulsion mechanism is powered on, the cold end of the heat conduction component 1 is pushed to move toward the cold plate of the bulkhead of the space station. , the heat of the heat dissipation surface of the external load 8 can be conducted to t...

Embodiment 2

[0062] Such as Figure 1-6 As shown, an external load 8 includes the aforementioned auxiliary heat transfer mechanism for the external load of a space station.

[0063] Specifically, such as Figure 5-6 As shown, an auxiliary heat transfer mechanism for the external load of the space station is respectively installed on two opposite cooling surfaces of the external load 8, the fixed support of the auxiliary heat transfer mechanism is L-shaped, and the fixed support of the auxiliary heat transfer mechanism is One end is fixed on the lower edge of the two heat dissipation surfaces by screws, and the other end is fixedly connected to the limit frame, and there is a certain gap between the limit frame and the plane where the heat dissipation surface is located. Above the support; the axis direction of the output shaft of the motor is parallel to the cooling surface.

[0064] A docking adapter for docking with a load adapter on the bulkhead of the space station is installed on th...

Embodiment 3

[0068] Such as Figure 1-6 As shown, a space station includes a bulkhead 5, a load adapter 6, a cold plate slot 7 and the above-mentioned external load 8, and the load adapter 6 is fixedly mounted on the bulkhead 5; the external load 8 is detachably connected to the load On the adapter 6; the cold plate groove 7 is opened on the bulkhead 5; the hot end of the heat conduction component 1 is fixedly connected with the heat dissipation surface of the external load 8, and the cold end of the electric push component 3 and the heat conduction component 1 is inserted into the cold plate groove 7, A cold plate is provided on the side wall of the cold plate groove 7 .

[0069] Specifically, such as Figure 5-6 As shown in , there are two cold plate slots on the bulkhead, which are located on both sides of the load adapter.

[0070] The docking adapter on the external load 8 in embodiment 2 is docked with the load adapter and fixedly installed to realize the installation and positioni...

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Abstract

The invention relates to an auxiliary heat transfer mechanism, an outboard load and a space station. The auxiliary heat transfer mechanism is used for conducting heat of an outboard load radiating surface to a space station bulkhead cold plate, and comprises a heat conduction assembly and an electric pushing mechanism. The hot end of the heat conduction assembly is connected with an outboard loadradiating surface. The cold end of the heat conduction assembly is located on the free side of the electric pushing mechanism. Under the pushing of the electric pushing mechanism, the heat conductionassembly moves towards the space station bulkhead cold plate. After the electric pushing mechanism is powered on, the cold end of the heat conduction assembly is pushed to move towards the space station bulkhead cold plate; when the cold end of the heat conduction assembly abuts against the cold plate, the hot end of the heat conduction assembly is connected with the outboard load radiating surface such that the heat of the outboard load radiating surface can be conducted to the cold end of the heat conduction assembly through the hot end of the heat conduction assembly and then conducted to the space station bulkhead cold plate, therefore heat dissipation of the outboard load is achieved, unmanned outboard operation is achieved through the electric pushing mechanism, and heat dissipationof the outboard load is achieved only through electric signals.

Description

technical field [0001] The invention relates to the technical field of structural design of a heat transfer system for an external load of a space station, in particular to an auxiliary heat transfer mechanism, an external load and a space station. Background technique [0002] With the development of manned spaceflight technology, establishing a long-term habitable and working environment in outer space has become the focus of human spaceflight. With the establishment of the manned space laboratory and the planning of the manned space station, there will be a significant increase in space extravehicular exposure experiments. A large number of scientific experiments have been carried out in the space exposure environment abroad, from some simple material exposure experiments on the space laboratory (Skylab) in the United States in the 1970s to the Soviet Union (later Russia) in the Mir Systematic multidisciplinary exposure science experiments have been carried out on the sp...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/50B64G1/66
CPCB64G1/503B64G1/66
Inventor 王辅辅乔志宏王泽张璐王珂
Owner TECH & ENG CENT FOR SPACE UTILIZATION CHINESE ACAD OF SCI
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