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A light, small, weak-collision, soft-drawing docking mechanism

A docking mechanism, light and small technology, applied in the docking device of aerospace vehicles, etc., can solve the problems of large collision force, poor versatility, complex structure, etc., and achieve the effect of small collision force, light weight and simple mechanism

Inactive Publication Date: 2014-09-03
SHANGHAI AEROSPACE SYST ENG INST
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  • Abstract
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  • Application Information

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Problems solved by technology

[0005] In order to solve the problems of large capture collision force, complex structure, large mass and poor versatility in the prior art

Method used

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  • A light, small, weak-collision, soft-drawing docking mechanism
  • A light, small, weak-collision, soft-drawing docking mechanism
  • A light, small, weak-collision, soft-drawing docking mechanism

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Embodiment Construction

[0018] The present invention will be described in detail below in conjunction with the drawings:

[0019] The light, small and weak collision flexible shaft docking mechanism of the present invention is characterized in that the device includes: a capture and lock separation device installed on an active aircraft, including a capture buffer component and two identical rigid connection components; The structural lock and electromagnetic unlocking mechanism on the passive aircraft; the capture buffer assembly includes a flexible shaft spherical head 101, a preload spring 102, a spring sleeve 103, a flexible shaft 104, a preload stop spherical block 105, and a cam stop block 106, active end housing 107, motor and reducer 108, screw nut drive mechanism 109, electromagnetic unlocking mechanism A110, guide shaft 111, guide slider 112, end housing 113, wherein the soft shaft spherical head 101 is One ends of the flexible shaft 104 are connected together, the flexible shaft sleeve 117 is...

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Abstract

A light, small, weak-collision, soft-shaft docking mechanism: it is characterized in that the device includes: a capture, locking and separation device installed on an active aircraft, including a capture buffer assembly and two identical rigid connection assemblies; it is installed on a passive aircraft The structural lock and electromagnetic unlocking mechanism; the capture buffer assembly includes a flexible shaft spherical head [101], a preload spring [102], a spring sleeve [103], a flexible shaft [104], a preload stop spherical block [ 105], cam limit block [106], driving end housing [107], motor and reducer [108], screw nut driving mechanism [109], electromagnetic unlocking mechanism A [110], guide shaft [111] , guide slider [112], end face housing [113], the rigid connection assembly is composed of spherical head [114], shaft [115], electromagnetic unlocking mechanism B [116], flexible shaft sleeve [117], the passive end It includes a housing [201], a structural lock A [202], an electromagnetic unlocking mechanism C [203], an electromagnetic unlocking mechanism D [204], and a structural lock B [205].

Description

Technical field [0001] The invention relates to a docking mechanism, in particular to a light, small and weak collision soft shaft type docking mechanism. technical background [0002] The docking mechanism is mainly used in the aerospace field to realize the capture, locking, separation and release of the two aircraft. [0003] At present, similar devices at home and abroad are generally more complicated, and most of them have a relatively large capture range and buffer capacity, and are suitable for capture and docking separation between spacecraft with relatively large masses. Most of the space docking mechanisms used for micro-satellites abroad are in the conceptual design stage, and generally have a relatively complex transmission device, which makes the mechanism more complex, larger in quality, and poor in versatility, and cannot be reused multiple times. [0004] At present, no description or report of a technology similar to the present invention has been found, and similar...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/64
Inventor 刘艳靳宗向邵济明耿海峰杨新海杨晟曦
Owner SHANGHAI AEROSPACE SYST ENG INST
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