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Separating device and satellite and rocket separating device with buffering structure

A technology of separation device and buffer structure, which is applied to the docking device of space navigation vehicle, etc., can solve problems such as reducing the stability of satellites, and achieve the effects of low development cost, simple structure and convenient installation.

Inactive Publication Date: 2016-02-03
ZHEJIANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Although the above structure has a certain buffering effect, in actual use, it needs to be installed between the satellite and the separation part, which will have a certain impact on the installation strength of the satellite and the separation part, reducing the stability of the satellite

Method used

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  • Separating device and satellite and rocket separating device with buffering structure
  • Separating device and satellite and rocket separating device with buffering structure
  • Separating device and satellite and rocket separating device with buffering structure

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Embodiment Construction

[0035] Such as Figure 1-10 As shown, the separation device with a buffer structure in this embodiment is a satellite-rocket separation device applied to the separation of satellites and rockets, including: a satellite 1, a separation base plate 2, two protective covers 3, two buffer members 4, two Titanium rod 5, four nuts 6, four screws 7, four spring washers and flat washers, pyrotechnics 8, satellite ejection mechanism 9 and four satellite support seats 10, each buffer 4 is placed in a protective cover 3 , The satellite 1 is provided with two flanges 101 connecting the titanium rod 5, the protective cover 3 with the buffer 4 is installed on the satellite flange 101, and the nut 6 adopts a double nut anti-loosening structure.

[0036] The diameter of the titanium rod 5 of the present embodiment is 4mm, and the buffer member 4 is a honeycomb cylinder composed of a hollow hexagonal prism with a height of 10mm and a diameter of 10mm. The wall thickness of the hexagonal prism ...

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Abstract

The invention discloses a separating device with a buffering structure. The separating device comprises a main body component, a separating component, pull rods and a pull rod cutting mechanism, wherein the pull rods are connected with the main body component and the separating component and press the main body component on the supporting surface of the separating component. A satellite is provided with a flange, and the ends, connected with the main body component, of the pull rods penetrate from one side of the flange and are locked through fasteners on the other side of the flange. The separating device is characterized in that buffering parts are installed on the side, with the fasteners fixed, of the flange, directly face the ends of the pull rods and are used for preventing half broken pull rods from exiting from the flange. The invention further discloses a satellite and rocket separating device with the buffering structure. According to the invention, the buffering parts are arranged at the ends of the pull rods for absorbing impact generated when the pull rods are broken, a separating buffering device is fixed through a pure mechanical structure, the shock absorbing and buffering effect is remarkable, the structure is simple, installation is convenient, the work is stable, and the development cost is low.

Description

technical field [0001] The invention relates to the technical field of separation and buffering of aerospace vehicles, in particular to a separation device with a buffer structure and a star-arrow separation device. Background technique [0002] A large number of pyrotechnic separation devices are used on spacecraft, such as explosive bolts, unlocking bolts, pin pullers, separation nuts, cutters, etc., to perform interstage separation, release part components, start or close some subsystems, and star-rocket separation , Sun wing deployment and other key actions. [0003] The pyrotechnic separation device uses the high-pressure gas generated by the explosion of the pyrotechnic product carrying the impact as the power, and the action is accompanied by the release of structural preload and structural impact. These loads are transmitted to various parts of the spacecraft through the structure in the form of stress waves, which will cause The severe instantaneous impact response...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
Inventor 滕来金仲和
Owner ZHEJIANG UNIV
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