Deployable assembly for antennas

a technology of antennae and assembly parts, which is applied in the direction of collapsible antennas, antenna details, antennas, etc., can solve the problems of high number of devices needed to keep the structure folded, high number of articulations and moving assemblies, and limited number of flight configurations and applications

Active Publication Date: 2022-11-10
AIRBUS DEFENCE & SPACE SAU
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent aims to provide a solution for reflectors used in space systems that overcomes existing limitations. The invention is a deployable assembly for reflectors that solves the problems that previously existed.

Problems solved by technology

However, they have some drawbacks, like the high number of devices necessary to keep the structure folded during launch, the high number of articulations and moving assemblies and the very limited number of flight configurations and applications.

Method used

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Embodiment Construction

[0051]FIGS. 2A, 2B and 2C show the deployable assembly for antennae of the invention in several stages. FIG. 2A shows the stowed position, FIG. 2B shows an intermediate position in which the assembly is being deployed, and FIG. 2C shows the fully deployed position.

[0052]FIGS. 6A to 6F also show the deployable assembly for antennae of the invention in several stages, with more intermediate positions.

[0053]FIG. 7 is a detailed view of the deployable assembly of the invention in an intermediate position of the deployment process, in which all of its elements can be seen.

[0054]The deployable assembly for antennae shown in these figures comprises:[0055]a structure comprising:[0056]n pairs of segments 4, 5, each pair of segments 4, 5 corresponding to one side of a deployed polygonal shape,[0057]n hinge joints between the two segments 4, 5 of a side, and[0058]hinged angular links 6 between every two adjacent sides, and[0059]a reflective surface 9.

[0060]The structure is configured to change...

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PUM

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Abstract

A deployable assembly for antennae includes a structure having a reflective surface and n pairs of segments, each pair of segments corresponding to one side of a deployed polygonal shape. N hinge joints are between the two segments of a side. N hinged angular links are between every two adjacent sides. The structure is changeable from a stowed substantially cylindrical shape into a deployed substantially planar polygonal shape with n sides. A deployable boom is between two segments. The boom lays stowed between the two segments before deployment and ends in a feeder electromagnetically feeding the antenna and includes a clamping element for keeping the structure closed when stowed. The feeder acts as structural support element when stowed and electromagnetic feeder for the antenna when deployed. A cable network shapes the reflective surface, with corresponding cables held by tensor elements protruding from the back of the segments.

Description

[0001]This application is a National Stage of PCT / ES2019 / 070635, filed Sep. 24, 2019, which application is incorporated herein by reference. To the extent appropriate, a claim of priority is made to the above-disclosed applicationFIELD OF THE INVENTION[0002]The present invention relates to a deployable assembly for antennae, mainly used in space systems, particularly to a deployable assembly to deploy large parabolic reflectors. The assembly is suitable for multiple purposes not only to deploy large reflectors but also to build large antennas for Earth observation and telecom, to build foldable clusters of satellites and even to build space debris capture systems.BACKGROUND[0003]There are many deployable reflector antenna structures already known in the state of the art.[0004]U.S. Pat. No. 4,030,102 A, referred to a “Deployable reflector structure”, discloses a supporting structure that deployed resembles a spoked wheel which is retractable into a compact volume by virtue of hinged ...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): H01Q15/16H01Q1/12
CPCH01Q15/161H01Q1/1235H01Q1/288H01Q1/08
Inventor PLAZA MORA, JOSÉ LUISCESPEDOSA CASTÁN, FERNANDO JOSÉ
Owner AIRBUS DEFENCE & SPACE SAU
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