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A light and small micro-satellite deployment device

A micro-satellite, light and small technology, applied in transportation and packaging, aerospace vehicles, aircraft, etc., can solve the problems of large solar wing deployment weight, low reliability, and long development cycle

Active Publication Date: 2020-10-23
BEIJING SATELLITE MFG FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem solved by the present invention is: in view of the current prior art, the problem of large weight, complex structure, long development period, slow response and low reliability in the deployment of the micro-satellite solar wing, and the limitation of a certain point of the unlocking mechanism will affect the whole Even the unlocking of the machine mechanism is easy to affect the situation, and a light and small micro-satellite deployment device is proposed

Method used

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  • A light and small micro-satellite deployment device
  • A light and small micro-satellite deployment device
  • A light and small micro-satellite deployment device

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Embodiment Construction

[0024] A light and small micro-satellite deployment device, which has two working states of solar wing compression and solar wing expansion, such as figure 1 As shown, it includes a centralized compression limit assembly 1 , a distributed release assembly 2 , a flexible hinge assembly 3 and a rope 4 . The centralized compression limit assembly 1 is a trigger device with a single trigger source. In order to meet the requirements of micro-satellites, the trigger source can be a pyrotechnic or non-pyrotechnic trigger device, such as a memory alloy pin puller, a paraffin unlocker, etc. And in the compressed state, a limit is provided for the rope 4, and the rope is connected to the distributed release component 2, and the number of ropes is set according to the task requirements. The flexible hinge component 3 is the driving device for the deployment of the solar wing. It is not loaded in the compressed state. In the unfolded state, after the distribution and release component com...

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Abstract

The invention discloses a light mini satellite unfolding device which is applicable to compression, release and unfolding of loads such as a small-size or mini satellite solar wing. The light mini satellite unfolding device comprises a centralized compression limiting component (1), a distribution release component (2), a flexible hinge component (3) and a fixing rope (4). A self-guided self-unfolded locked flexible unfolding component is used, an allocation type unlocking component of one-point compression and multi-point breakage is used in match, single-point reliable compression, synchronous release or self-unfolding and self-locking functions of a solar wing plate are achieved, and the mechanism is small in overall impact, high in reliability, light in weight and applicable to mini satellites.

Description

technical field [0001] The invention relates to a light and small micro-satellite deployment device, which belongs to the field of space deployment mechanism design. Background technique [0002] The invention proposes a novel satellite solar wing pressing, releasing, unfolding and locking device, which is suitable for the pressing, releasing and unfolding of loads such as small or tiny satellite solar wings. In recent years, the in-orbit application of small and micro satellites has been increasing. With the continuous breakthrough of new technologies, the weight and surface area of ​​satellites have been continuously reduced, so that the form of surface-mounted batteries restricts the total available power of satellites and cannot meet the requirements of mission diversification. Under certain circumstances, the demand for increasing the total power requires a deployable solar wing to ensure that the power of the satellite cannot be reduced with the reduction in weight. T...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/44
CPCB64G1/443
Inventor 姚旗肖燕妮张国华崔超龚康李咚咚盛望京梁春组
Owner BEIJING SATELLITE MFG FACTORY
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