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Space capture docking mechanism

A docking mechanism and space capture technology, which can be applied to aerospace vehicle docking devices, motor vehicles, aerospace equipment, etc., and can solve the problems of complex capture and docking devices and high cost

Inactive Publication Date: 2020-04-28
LANZHOU INST OF PHYSICS CHINESE ACADEMY OF SPACE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] However, for the capture and docking device, the capture and docking device in the prior art is more complicated and the cost is higher

Method used

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Embodiment Construction

[0029] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0030] The present invention provides a space capture docking mechanism, such as figure 1 As shown, it is composed of a space capture docking mechanism a and a docking mechanism b, and the peripheral equipment is a spacecraft A and an aircraft B, wherein the aircraft A is a space service platform, and the aircraft B is a space vehicle.

[0031] Such as Figure 1 to Figure 5 The space capture docking mechanism a includes: electrical connector a1, cylinder body 2, fixed frame 3, liquid circuit breaker a4, positioning pin 5, claw 6, active end guide valve 7, claw rotation axis a8, claw rotation Shaft b9, ball screw nut 10, ball screw 11, bearing cover 12, bearing a13, bevel gear a14, bevel gear b15, transmission shaft 16, bevel gear 17, key 18, motor reducer 19, bevel gear 20 , motor 21, bearing b22, bevel gear support rod 23.

[0032] The docking mechanis...

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Abstract

The invention discloses a space capture docking mechanism. The space capture docking mechanism comprises a docking mechanism a and a docking mechanism b, peripheral equipment comprises an aircraft A and an aircraft B, and the docking mechanism a comprises an electric connector a, a cylinder, a fixing frame, a liquid path disconnector a, a positioning pin, a holding claw, an active end guide flap,a holding claw rotating shaft a, a holding claw rotating shaft b, a ball screw nut, a ball screw, a bearing end cover, a bearing a, a bevel gear a, a bevel gear b, a transmission shaft, a bevel gear,a key, a motor reducer, a bevel gear ring, a motor, a bearing b and a bevel gear ring supporting rod; and the docking mechanism b comprises an electric connector b, a driven end mounting bottom plate,a passive end base, a liquid path disconnector b and a passive end guide flap. Guiding positioning docking, active capturing, active tightening, blind plugging electric connector plugging, liquid path breaker plugging and rigid locking of an aircraft interface and a spacecraft parking platform can be achieved through a simple structure.

Description

technical field [0001] The invention belongs to the field of space application equipment, and in particular relates to a space capture docking mechanism. Background technique [0002] The high-orbit aircraft platform is developing towards a service station, and a large number of aircraft parking interfaces are arranged on the parking platform to achieve on-orbit service capabilities. Space vehicles such as space stations and manned spacecraft have arranged a large number of exposure load test platforms on the outer wall of the cabin to expand the exposure test capabilities of space vehicles. At present, the International Space Station has used various forms of load docking and locking interface devices and capture docking devices to support exposure experiment tasks; the on-orbit verification projects implemented by the United States and other countries use various forms of capture and docking devices to support aircraft docking experiment tasks. [0003] However, for the c...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
CPCB64G1/646
Inventor 崔志武康永丁成斌董占敏柳明明张富华
Owner LANZHOU INST OF PHYSICS CHINESE ACADEMY OF SPACE TECH
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