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Two-phase fluid loop condenser device for spacecraft

A fluid circuit and condenser technology, which is applied in the field of two-phase fluid circuit condenser devices for spacecraft, can solve the problem of large contact thermal resistance between the condensation pipeline and the honeycomb structure, poor processing of body-mounted radiators, and small diameter of the condensation pipeline and other problems, to achieve the effect of low cost, simple processing, and overcoming processing

Inactive Publication Date: 2021-01-29
BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the structure of the remote sensor is usually a non-planar structure, and the body-mounted radiator for this structure is not easy to process
In addition, in order to realize the processing and development of super-large structures, most of the camera structures adopt aluminum honeycomb structures with high strength, good rigidity and light weight. The contact thermal resistance between the pipeline and the honeycomb structure is relatively large

Method used

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  • Two-phase fluid loop condenser device for spacecraft
  • Two-phase fluid loop condenser device for spacecraft
  • Two-phase fluid loop condenser device for spacecraft

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Embodiment Construction

[0043] Below in conjunction with the accompanying drawings, the specific implementation of the present invention will be described in further detail, the following examples are used to illustrate the present invention, but not to limit the scope of the present invention.

[0044] Such as Figure 2 to Figure 5 As shown, a two-phase fluid circuit condenser device for a spacecraft proposed by the present invention includes: a pipeline pressure plate 2, a mounting plate 7, a pipeline 8, mounting plate screws 9 and pressure plate screws 10;

[0045] The mounting plate 7 is a plate-shaped metal structure, and its surface is processed with a pipeline channel 5 for installing the pipeline 8, and the pipeline 8 is fastened and installed in the pipeline channel 5 through the pipeline pressure plate 2 and the pressure plate screw 10, The mounting plate 7 is fastened and assembled with the radiator 1 through the mounting plate screws 9, and the heat conducting installation between the mou...

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Abstract

The invention discloses a two-phase fluid loop condenser device for a spacecraft. The two-phase fluid loop condenser device comprises a pipeline pressing plate, a mounting plate, a pipeline, a mounting plate screw and a pressing plate screw; the mounting plate is of a plate-shaped metal structure, a pipeline channel is machined in the surface of the mounting plate and used for mounting a pipeline,the pipeline is mounted in the pipeline channel in a fastened mode through a pipeline pressing plate and the pressing plate screw, the mounting plate and a radiator are assembled in a fastened mode through the mounting plate screw, and the mounting plate and the radiator are mounted in a heat conduction mode; the pipeline pressing plate is of a narrow-strip-shaped metal sheet structure, through holes are machined in the two sides of the pipeline pressing plate and used for the pressing plate screw to penetrate through, and the contact face of the pipeline pressing plate and the pipeline is aplane; and a pressing plate mounting threaded hole and a mounting plate through hole are formed in the mounting plate, the pressing plate mounting threaded hole is used for achieving assembly of the pressing plate screw, and the mounting plate through hole is used for achieving penetration of the mounting plate screw. The device can be coupled with aerospace remote sensor structures of different structural forms, can be mounted with body-mounted radiators of different sizes and different shapes, and is low in development difficulty and low in manufacturing cost.

Description

technical field [0001] The invention relates to a two-phase fluid circuit condenser device for spacecraft, belonging to the field of aerospace thermal control. Background technique [0002] With the continuous development of aerospace remote sensing technology, optical remote sensors have higher and higher temperature requirements for their core components (such as CCD components or CMOS components), and it is necessary to use two-phase fluid circuit technology for thermal control design. The system composition of the two-phase fluid circuit is as follows: figure 1 shown. It includes a driving device 11, an evaporator 12, a condenser 14, a radiator 15, a connecting pipeline 13, and the like. When the aerospace remote sensor is used in orbit, it is necessary to dissipate the heat generated by the two-phase fluid circuit to the space within a certain temperature range and achieve thermal balance. In the two-phase fluid circuit system, in order to realize heat dissipation, t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F28D15/02F28F9/013F28F21/08
CPCF28D15/0266F28D15/0275F28F9/0131F28F21/083F28F21/084F28F21/085
Inventor 孟庆亮赵振明张焕冬颜吟雪张明佳
Owner BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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