On-orbit reusable multifunctional electromagnetic interface device

An electromagnetic interface and multi-functional technology, which is applied in the docking device of aerospace vehicles, transportation and packaging, space navigation equipment, etc., can solve the problems that cannot meet the needs of standardized launch interfaces and subsequent on-orbit services, and achieve no feathers. The effect of flow pollution, less energy consumption, and light weight

Active Publication Date: 2020-11-13
BEIJING SATELLITE MFG FACTORY
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  • Description
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Problems solved by technology

Unable to meet the needs of the future with one arrow and multiple sat

Method used

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  • On-orbit reusable multifunctional electromagnetic interface device
  • On-orbit reusable multifunctional electromagnetic interface device
  • On-orbit reusable multifunctional electromagnetic interface device

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Embodiment Construction

[0039] The present invention will be further elaborated below in conjunction with embodiment.

[0040] Aiming at the needs of micro-satellites on-orbit service in the future, the present invention proposes an on-orbit reusable multi-functional electromagnetic interface device, which uses electromagnetic force as a driving source, has a light and small structure, and realizes on-orbit self-adsorption, reliable docking and Multi-media transmission and other functions; based on electromagnetic force control, adjustable speed release can be achieved for micro-satellites of different weights, and the device can be reused in orbit, suitable for the release of micro-satellites with one arrow and multiple satellites or repeated use in on-orbit services condition.

[0041] An in-orbit reusable multifunctional electromagnetic interface device, such as figure 1 As shown, it includes the active end 1 and the passive end 2; realize the docking and separation of the active end 1 and the pass...

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Abstract

The invention relates to an on-orbit reusable multifunctional electromagnetic interface device, and belongs to the technical field of space connection and separation mechanism design. The device comprises an active end and a passive end. Butt joint and separation of the driving end and the driven end are achieved; the driving end comprises a driving end shell, three positioning electromagnets, three damping bases, an annular permanent magnet, a sleeve, a push rod, a coil, a wire column, a spring base, a spring and a sliding rod. The passive end comprises a passive end main body, three lock shafts and three point-shaped permanent magnets. According to the variable-speed separation device based on the electromagnetic force, the magnitude of the electromagnetic force is adjusted by controlling the voltage and the current and facing the actual weight and separation speed requirements of a star load in an unknown task, autonomous variable-speed separation of a star is promoted, the separation speed is adjustable, and the response is fast; meanwhile, the functions of on-orbit docking, transmission of inter-satellite substances or energy such as machinery, electricity, gas and liquid, variable-speed catapulting and the like of micro satellites are achieved, multi-level system connection is conducted, and a light and small device is formed.

Description

technical field [0001] The invention belongs to the technical field of space connection and separation mechanism design, and relates to a reusable multifunctional electromagnetic interface device on rails. Background technique [0002] In recent years, with the continuous breakthrough of new technologies, micro-satellites are small in weight and volume, and their in-orbit application forms are flexible. Therefore, the in-orbit applications of small and micro-miniature satellites are increasing. In order to adapt to the in-orbit service of micro-satellites or constellations in the future, how to realize the in-orbit interface device of light, small and multi-functional micro-satellites, how to realize the tasks of autonomous docking, life extension, functional reorganization and rapid reorganization of micro-satellites in orbit, etc. Solved technical problems. [0003] In micro-satellite orbit service missions, the traditional connection and separation interface forms based ...

Claims

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Application Information

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IPC IPC(8): B64G1/10B64G1/64
CPCB64G1/10B64G1/645B64G1/646
Inventor 姚旗肖燕妮田昀李腾飞陈余军龚康高鑫王建宇
Owner BEIJING SATELLITE MFG FACTORY
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