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Multifunctional structure cable for spacecraft and manufacturing method of multifunctional structure cable

A multi-functional, spacecraft technology, applied in the direction of electrical components, can solve problems such as cumbersome assembly procedures, reduce system reliability, and signal interference, and achieve the goals of improving flexibility and reliability, increasing payload ratio, and eliminating negative volume Effect

Active Publication Date: 2017-06-13
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] 2) The lines in the spacecraft are criss-crossed and the connection relationship is complex, which is prone to signal interference and reduces system reliability;
[0006] 3) The required quantity is large, the installation workload is large, and the assembly procedure is relatively cumbersome;
[0007] 4) The scalability and redundancy of the spacecraft system are poor, and it is difficult to reconfigure the system according to the needs

Method used

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  • Multifunctional structure cable for spacecraft and manufacturing method of multifunctional structure cable
  • Multifunctional structure cable for spacecraft and manufacturing method of multifunctional structure cable
  • Multifunctional structure cable for spacecraft and manufacturing method of multifunctional structure cable

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preparation example Construction

[0044] Another aspect of the present invention also provides a preparation method for the above cable, comprising the following steps:

[0045] 1) Open cable laying grooves and device installation grooves on the substrate according to the optimized design of the circuit;

[0046]2) Embed the cable in the electrical laying groove, reserve the cable outlet at the device installation groove, and reserve the cable inlet on one side of the substrate;

[0047] 3) GD414 silicone rubber is filled in the cable laying groove, the substrate is encapsulated with a packaging plate, and the substrate is cured with silica gel to obtain a multifunctional structural cable for spacecraft.

[0048] The optimized design here refers to the cable layout design to reduce the crossover of cables. It can be carried out according to the existing method.

[0049] Preferably, the conditions for curing the silica gel are as follows: the heating rate is 3° C. / min to 5° C. / min, and the temperature is rais...

Embodiment 1

[0059] The specific method of cable laying is as follows: use a cutter to open a groove with a certain width and depth on the PMI foam sandwich composite structure (the size is 1mm to 2mm larger than the diameter of the cable), and after the cable is embedded, fill it with GD414 silicone rubber for fixing. , put the PMI foam sandwich composite structure into a large temperature control box to cure the silicone rubber. During the curing process, the temperature rise rate was controlled at 3°C / min, and the maximum temperature was controlled at 65°C for 20 hours.

Embodiment 2

[0061] The specific method of cable laying is as follows: use a cutter to open a groove with a certain width and depth on the PMI foam sandwich composite structure (the size is 1mm to 2mm larger than the diameter of the cable), and after the cable is embedded, fill it with GD414 silicone rubber for fixing. , put the PMI foam sandwich composite structure into a large temperature control box to cure the silicone rubber. During the curing process, the temperature rise rate was controlled at 5°C / min, and the maximum temperature was controlled at 75°C for 10 hours.

[0062] Finally, for the matrix obtained in Example 1 or 2, the overall structure is packaged with a carbon fiber composite material panel, so as to realize the space between spacecraft cables (electric wires, data lines, signal lines, etc.) ), and at the same time between the PMI foam sandwich composite structure and the PMI foam sandwich composite structure, a flexible flat matrix cable connector is used to realize the...

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Abstract

The invention provides a multifunctional structure cable for a spacecraft, in which a structure and a cable are integrated into a whole, and a manufacturing method of the multifunctional structure cable, belonging to the technical field of aerospace structure design. The multifunctional structure cable is of a multifunctional structure obtained by organically integrating a circuit cable, a USB (universal serial bus) cable, a signal line, other cables and pipelines with a composite material structure together and performing integrated design according to the designability of an aerospace composite material structure. The novel structure has multifunctional characteristics, namely, not only not losing a bearing function owned by an original composite material structure of the spacecraft, but also having functions of a cable, such as electric conduction, information transmission and the like, and the novel structure further has functions of a traditional cable wrapping skin layer, a protective jacket and the like. The multifunctional structure cable eliminates parasitic mass and negative volume of a traditional cable, is conducive to realizing structural module design and manufacture, shortening the research and assembly period of products and improving the effective load ratio of the spacecraft.

Description

technical field [0001] The invention relates to the technical field of spacecraft structure design, in particular to a multifunctional structural cable for spacecraft that integrates the structure and the cable and a preparation method thereof. Background technique [0002] Cables, including circuit cables (power lines), data lines, signal lines, etc., are filled in a large number of spacecraft structures. They are essential channels for powering systems or functional devices and for signal and data transmission between components. In the traditional spacecraft design, the spacecraft is divided into sub-systems such as structure, propulsion, control, and electronics. Each sub-system is designed and manufactured separately, and finally assembled together. A major disadvantage of this separate design method Yes, the interior of the spacecraft is filled with thousands of independent cables, such as various power lines and various signal lines, etc., to meet the needs of power s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02G3/04H02G3/00
CPCH02G3/00H02G3/04H02G3/0425
Inventor 李东旭张峰彭超义尹昌平刘望
Owner NAT UNIV OF DEFENSE TECH
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