Repeatable locking and separating device

A separation device, repeated locking technology, applied in the direction of the docking device of the aerospace vehicle, can solve the problems of inability to meet on-orbit maintenance and service, non-reusable structure, damage to electronic components, etc., to achieve high reliability, vibration and shock Small, easy-to-maintain effects

Active Publication Date: 2019-10-22
BEIJING SATELLITE MFG FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, there are insurmountable shortcomings in the pyrotechnic locking and separating device, which is stronger than the vibration and impact when unlocking and separating, and may cause damage to additional products such as electronic components. After unlocking, there will be more additional pollutants, and its structure cannot be reused. A series of shortcomings such as can not meet the needs of on-orbit maintenance and service

Method used

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  • Repeatable locking and separating device
  • Repeatable locking and separating device
  • Repeatable locking and separating device

Examples

Experimental program
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Effect test

Embodiment 1

[0032] A re-lockable separation device comprising:

[0033] Bracket 61, vertical shaft 62, worm 63, turbine 64, horizontal shaft 65, cam 66, chute 67, pin shaft 68, locking hook 69, first bearing, second bearing, third bearing;

[0034] The vertical shaft 62 is fixedly connected with the worm 63, the vertical shaft 62 is mounted on the bracket 61 through the first bearing; the worm wheel 64 is fixedly connected with the horizontal shaft 65, and the horizontal shaft 65 is mounted on the bracket 61 through the second bearing On; the worm 63 cooperates with the turbine 64 for transmission;

[0035] Described chute 67 is installed on the cross shaft 65 by the 3rd bearing, a cam 66 is respectively installed on the both sides of described chute 67, and two cams 66 are fixedly connected with cross shaft 65, and two cams 66 are all provided with guide groove; the chute 67 is provided with a cavity and a waist groove, and the locking hook 69 is inserted into the cavity; the pin shaft ...

Embodiment 2

[0043] This embodiment is applied to on-orbit spacecraft or satellites, and relevant components need to be locked and separated. Such as figure 1 , 2 Shown is a schematic diagram of this embodiment applied to an on-orbit spacecraft or satellite locking and separation environment. The local structure of an on-orbit spacecraft is composed of an inner side plate 1 and an outer side plate 2, and the inner and outer side plates are supported by a bracket plate 3 , the on-orbit replacement module 5 can be inserted and removed on the rail through a mechanical arm or other mechanism, and when the on-orbit replacement module 5 is inserted into the designated position of the spacecraft, the unlocking end 7 is locked by the mechanical arm or other mechanism. When the on-rail replacement module 5 needs to be replaced, the unlocking end 7 is also operated by a mechanical arm or other mechanism to unlock, and then the on-rail replacement module 5 is pulled out.

[0044] The device of this...

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Abstract

The invention discloses a repeatable locking and separating device, and belongs to the technical field of repeatable connection and separation. The device comprises a support 61, a vertical shaft 62,a worm 63, a turbine 64, a cross shaft 65, cams 66, a sliding groove 67, a pin shaft 68, a locking hook 69, a first bearing, a second bearing and a third bearing; the vertical shaft 62 is fixedly connected with the worm 63, and the vertical shaft 62 is installed on the support 61 through the first bearing; the turbine 64 is fixedly connected with the cross shaft 65, and the cross shaft 65 is mounted on the support 61 through the second bearing; the worm 63 is in matched transmission with the turbine 64, the sliding groove 67 is mounted on the cross shaft 65 through the third bearing, each cam66 is mounted on each side of the sliding groove 67, the two cams 66 are fixedly connected with the cross shaft 65, and guide grooves are formed in the two cams 66 correspondingly; and a concave cavity and a kidney groove are formed in the sliding groove 67, the locking hook 69 is inserted into the concave cavity, the pin shaft 68 is arranged on the locking hook 69, and the two ends of the pin shaft 68 penetrate through the kidney groove and are inserted into the guide grooves of the two cams 66. The device has the advantages that the operation is simple, multiple locking and separating can berealized, the vibration impact is small, and the maintenance is easy.

Description

technical field [0001] The invention relates to a repeatable locking and separating device, which is applied to the scene where on-orbit spacecraft components need to trigger locking and separating, and belongs to the technical field of repeatable connection and separation. Background technique [0002] With the rapid development of the global aerospace industry, especially the construction and application of space stations, space shuttles, and space robots in the field of deep space exploration and on-orbit services, the connection and separation of spacecraft or spacecraft components is an important aspect of on-orbit maintenance, A key technology for service and support, widely used in space. [0003] With the development of aerospace technology, the application of connection and separation technology has become increasingly common, followed by the wide application of locking and separation mechanisms. At present, the connection and separation between large compartments ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
CPCB64G1/64
Inventor 田昀王存义岳洪浩龚康姚旗杨飞张玉良王涛崔佳涛
Owner BEIJING SATELLITE MFG FACTORY
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