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Spacecraft module flexible docking mechanism

A technology for docking mechanism and spacecraft, which is applied in docking devices for aerospace vehicles, spacecraft for space navigation, aircraft, etc. It can solve the problems of lack of compliant attitude adjustment ability, low rigidity of flexible rods, and low connection rigidity, etc., so as to reduce unnecessary Stable phenomenon, smooth attitude adjustment process, low disturbance effect

Active Publication Date: 2019-07-12
HARBIN INST OF TECH +1
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  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

The existing flexible cone-rod docking mechanism uses a flexible rod to reduce the reaction force during the docking process. The rigidity of the flexible rod is very low, and it does not have the ability to adjust the attitude. It needs to directly rely on the rigid attitude adjustment parts to adjust the attitude.
At the same time, this docking mechanism has only one docking rod, the connection rigidity is low, and there may be large vibrations in the process of bringing the two stars closer, and it is only suitable for the docking of light and small spacecraft

Method used

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  • Spacecraft module flexible docking mechanism

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Embodiment Construction

[0032] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention.

[0033] see Figure 1-11Describe this embodiment, a kind of spacecraft module flexible docking mechanism, it comprises active end docking module 4 and passive end docking module 5, the quantity of described active end docking module 4 is a plurality of, and described multiple active end docking modules 4 are installed On the same circumference of the active aircraft 1, the number of the passive terminal docking modules 5 is the same as that of the active terminal docking modules 4, and they are installed on the passive aircraft 2. The installation position and installation radius of the passive terminal docking modules 5 are all docked with the active terminal Corresponding to the module 4, the active end docking module 4 includes a guide head 34, a flexible rod 36, a separation ...

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Abstract

The invention provides a spacecraft module flexible docking mechanism, belongs to the technical field of spacecraft docking, and specifically relates to a spacecraft module flexible docking mechanism.The problems that the existing rigid conical rod type docking mechanism is complicated in structure, a special energy absorbing mechanism is required, disturbance to the stars is great are solved, and the problems of low connection rigidity and large jitter of the existing flexible conical rod type docking mechanism are solved. The spacecraft module flexible docking mechanism comprises an activeend docking module and a passive end docking module,the active end docking module comprises a guiding head, a flexible rod, a separating component, a connecting and unlocking component, and a drivingcomponent, and the passive end docking module comprises a guiding cone, a bearing section, and a passive end flange.The spacecraft module flexible docking mechanism is mainly used for space docking tasks with spacecraftswhich are sensitive to impact and require precise operation with the aid of autonomous power or robotic arms.

Description

technical field [0001] The invention belongs to the technical field of docking of space vehicles, in particular to a flexible docking mechanism of spacecraft modules. Background technique [0002] The existing rigid cone-rod docking mechanism uses the rigid rod to contact the docking cone to achieve capture, and the reaction force generated during the docking process needs to be absorbed by a special buffer device. During the capture process, it completes the rigid preliminary attitude adjustment at the same time, which greatly disturbs the star. The existing flexible cone-rod docking mechanism uses a flexible rod to reduce the reaction force during the docking process. The rigidity of the flexible rod is very low, and it does not have the capability of compliant attitude adjustment. It needs to directly rely on rigid attitude adjustment components for attitude adjustment. At the same time, this docking mechanism has only one docking rod, the connection stiffness is low, an...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
CPCB64G1/646
Inventor 杨飞潘博刘卫李伟杰张伟伟姜博文庄原姜生元
Owner HARBIN INST OF TECH
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