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High-stiffness low-impact sealed connection separation device and method for spacecraft

A connection and separation device, low-impact technology, applied in the docking device of aerospace vehicles, equipment for space navigation, aircraft for space navigation, etc., can solve the problems of low impact, low connection stiffness and load-bearing capacity, and achieve low separation Impact force, effect of small impact

Active Publication Date: 2018-12-21
SHANGHAI SATELLITE ENG INST
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AI Technical Summary

Problems solved by technology

[0004] At present, some separation technologies have relatively low connection stiffness and load-carrying capacity (such as less than 15000N) under low-impact performance; while some high-rigidity and large-load connection separations are difficult to achieve low-impact characteristics (such as within 10000Hz, greater than 6000g)

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  • High-stiffness low-impact sealed connection separation device and method for spacecraft

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Embodiment Construction

[0025] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0026] The preferred embodiments of the present invention are given below in conjunction with the accompanying drawings to describe the technical solution of the present invention in detail.

[0027] Figure 1 to Figure 5 As shown, the high-rigidity and low-impact sealed connection and separation device for spacecraft provided by the present invention includes a connection main structure 1 , an expansion tube stop ring 2 , and an expansion tube 3 .

[0028] A high-rigidity, low-impact, sealed connectio...

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Abstract

The invention provides aHigh-stiffness low-impact sealed connection separation device and method for a spacecraftused for , Connection and separation in orbit for the spacecraft, and can realize on-orbit unlocking and separation on demand according to requirements, the device comprises a connecting main body structure and a local connecting unit fixedly connected with the connecting main body structure, A limit ring of that expansion tube is arranged at the separation interface, an expansion tube is arranged between the limit ring of the expansion pipe and the connecting main body structure, Before unlocking, the stiffness of the system is provided by the connecting main structure and the local connecting unit. During unlocking, the system is unlocked by the low impact of the local connecting unit, and then, under the action of the expansion pipe, the connecting main structure and the limiting ring of the expansion pipe are cut off along the separation surface, so as to realize the separation of the system on the orbit. The device of the invention has the characteristics of large connection rigidity, large bearing capacity, good system tightness, small unlocking impact and the like.

Description

technical field [0001] The invention relates to a high-rigidity and low-impact sealed connection and separation device and method for spacecraft on-orbit. Background technique [0002] The connection and separation technology of the spacecraft is used to realize the firm connection between the spacecraft body and components, between the compartments, between the spacecraft and the launch vehicle, and between the spacecraft. At the same time, it can realize on-orbit release and separate. [0003] Two performances that are mainly concerned with the connection and separation technology: one is the stiffness of the system connection, and the other is the unlocking impact of the system separation; the connection stiffness is related to the overall stiffness characteristics of the system to be separated, and the impact performance during the unlocking process of the system is related to The subsequent engineering application unlocking impact is related to the mechanical environme...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
CPCB64G1/645
Inventor 王智磊张如变杜三虎赵枝凯杨铭波
Owner SHANGHAI SATELLITE ENG INST
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