Star structure weight reduction device combined with thermal management

A technology that combines heat and stars, and is applied in the direction of thermal protection devices for aerospace vehicles, devices for living conditions control of aerospace vehicles, and aerospace safety/emergency devices to achieve good thermal insulation effect, weight reduction, and reasonable device structure.

Pending Publication Date: 2022-07-29
SHANGHAI SATELLITE ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At this time, it is difficult to meet the design requirements by generally reducing the number of components to meet the demand for weight reduction, and it is necessary to find a new way to solve the weight reduction problem of satellites.

Method used

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  • Star structure weight reduction device combined with thermal management
  • Star structure weight reduction device combined with thermal management
  • Star structure weight reduction device combined with thermal management

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0039] A star structure weight reduction device combined with thermal management provided by the present invention includes a radiant heat exchange isolation device 1, a screw 2, a wrapping fixing buckle 3 and a star frame, and the radiant heat is exchanged through the screw 2 and the wrapping fixing buckle 3 respectively. The isolation device 1 is fixed on the side of the star frame so as to reduce the weight of the satellite as a whole, and the binding and fixing buckle 3 is buckled on the radiation heat exchange isolation device. Preferably, the outer diameter of the radiant heat exchange isolator is equal to the inner diameter of the star frame. Wherein, a layer of polyimide film is added on the outer surface of the radiation heat exchange isolation device 1, and the thickness of the polyimide film is formed by spraying, and the thickness is 20-30 μm. Preferably, a layer of 25 μm polyimide film sprayed with SR107 white paint is added to the outer surface of the radiation h...

Embodiment 2

[0045] The second embodiment is formed on the basis of the first embodiment. By further limiting the connection components, the connection between the radiation heat exchange isolation device and the star frame is basically realized, and the reliability and stability of the overall structure are strengthened. . specific:

[0046] The radiant heat exchange isolation device 1 also includes a nylon wire 4, and the nylon thread 4 passes through the acrylic fiber wire hole to bundle and reinforce the radiant heat exchange isolation device 1 to the star frame. The close connection between the radiation heat exchange isolation device 1 and the star frame is further strengthened to ensure the tightness of the connection relationship.

[0047] In the above embodiment, a new approach is provided for reducing the weight of the satellite, which has the characteristics of convenient installation, good reliability and light weight.

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PUM

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Abstract

The invention provides a star structure weight reduction device combined with heat management, which relates to the field of space equipment and comprises a radiation heat exchange isolation device and a star frame, and the radiation heat exchange isolation device is fixed on the side surface of the star frame through screws and binding fixing hasps. The radiant heat exchange isolation device is an assembly composed of a plurality of isolation units, each isolation unit is composed of a double-face aluminized polyester film and polyester mesh cloth at intervals, and a layer of 25-micron polyimide film sprayed with SR107 white paint is additionally arranged on the outer surface of the radiant heat exchange isolation device. The invention provides a new way for reducing the weight of the satellite, and has the characteristics of convenience in installation, good reliability and light weight.

Description

technical field [0001] The present invention relates to the field of space equipment, and in particular, to a weight reduction device of a star structure combined with thermal management. Background technique [0002] With the continuous increase of satellite research and development tasks in my country, satellites are becoming larger and more complex, especially satellites carrying out deep space exploration missions, which need to carry a large number of detection equipment for deep space exploration. Due to the limitation of the current launch capacity of launch vehicles, a new generation of large launch vehicles is still in the development process, and the satellite will encounter problems such as overweight and overenvelope during launch, which requires the satellite to optimize its weight reduction design to adapt to the current The launch capability of the launch vehicle. [0003] During the development of existing satellites, weight reduction and optimization measur...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/58B64G1/46
CPCB64G1/58B64G1/46
Inventor 陈占胜周砚耕赵吉喆靳春帅马昌健
Owner SHANGHAI SATELLITE ENG INST
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