WO2021058838A1 - Conjunto desplegable para antenas - Google Patents
Conjunto desplegable para antenas Download PDFInfo
- Publication number
- WO2021058838A1 WO2021058838A1 PCT/ES2019/070635 ES2019070635W WO2021058838A1 WO 2021058838 A1 WO2021058838 A1 WO 2021058838A1 ES 2019070635 W ES2019070635 W ES 2019070635W WO 2021058838 A1 WO2021058838 A1 WO 2021058838A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- segments
- deployable
- antennas
- deployed
- reflective surface
- Prior art date
Links
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
- H01Q15/14—Reflecting surfaces; Equivalent structures
- H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
- H01Q15/161—Collapsible reflectors
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/08—Means for collapsing antennas or parts thereof
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/1235—Collapsible supports; Means for erecting a rigid antenna
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
Definitions
- the present invention relates to a deployable assembly for antennas, mainly used in space systems, particularly to a deployable assembly for deploying large parabolic reflectors.
- the assembly is suitable for multiple purposes, not only for deploying large reflectors, but also for building large antennas for Earth observation and for telecommunications, for building folding groups of satellites, and even for building space debris capture systems.
- Document US 4030102 A referring to a "deployable reflector structure”, describes a support structure that when deployed resembles a spoke wheel that is retractable into a compact volume by virtue of its foldable rim and rolled spokes, which is an efficient and stable structure for storing, deploying and supporting surfaces such as radar and communications antennas, shielding, ground detection, solar cell arrays and solar energy reflectors.
- Document US 3617113 A describes a deployable reflector assembly comprising a deployable reflector, a series of deployable panels surrounding and operatively connected to said deployable reflector, said series of deployable panels comprising a first deployable set of panels interconnected to substantially form an open cylinder at the time of deployment and a second deployable set of panels operatively connected to said first deployable set of panels, said second set of panels being interconnected to form a substantially flat ring upon deployment that lies in a plane that is substantially perpendicular to the central axis of said cylinder formed by said first deployed set of panels and deployment means operatively connected to said sets of deployable panels to deploy said sets of deployable panels.
- Document WO 2009153454 A2 presents a hinged folding structure consisting of a set of elements articulated by hinges, in which each of the elements has a hinge at each end that allows it to be connected to the end of another element through a hinge axis. (X, Y), all the pivoting pins of the hinges being constructed in such a way that the structure can adopt two extreme positions, namely, a deployed position in which the elements are more or less continuous with each other to form an ellipse, and a folded position in which the elements meet each other, approximately parallel to each other.
- the elements and the hinges are connected both to means for controlling the unfolding of the elements, and to assisting means to ensure the simultaneity of the unfolding or folding of the elements.
- Document EP 2482378 A1 discloses a deployed antenna having a larger aperture diameter via four-sided connections provided in at least three stages and including: six deployment mechanisms arranged radiantly from a central axis to support a portion of the outer edge of a reflective mirror flexible surface: and a deployment drive mechanism disposed at a bottom of a center of the six deployment mechanism arrangement, to deploy the six deployment mechanisms.
- Each of the six deployment mechanisms includes a first four-sided connection, a second four-sided connection, and a third four-sided connection arranged in order from a central axis position, around which the six deployment mechanisms are arranged. , toward an outer side of each of the six deployment mechanisms, so that each of the six deployment mechanisms is structured so that it can be folded in three stages.
- WO 2013135298 Al describes a mechanical support ring structure for supporting a deployable space reflector antenna.
- the mechanical support ring structure is convertible from a folded state to a deployed state and comprises a ring-shaped pantograph having a plurality of circumferentially disposed pantograph sections that are deployable to convert the mechanical support ring structure from the folded state. to the deployed state, and a plurality of circumferentially arranged support bars, each pantograph section being arranged between a pair of support bars, wherein each pantograph section comprises one or more pairs of transversely intersecting pantograph bars in a respective crossover position.
- Document EP 2768077 A1 describes a spatial deployable structure capable of changing from a substantially cylindrical configuration to a substantially flat polygonal configuration with n sides, comprising: n pairs of segments, each pair of segments being formed by two individual segments, forming one side of the polygon of the deployed structure, in such a way that the individual segments have a substantially vertical lower base with a prismatic shape, the segments being substantially symmetrical with each other with respect to said lower base, having their longest direction parallel to the side of the polygon formed in the unfolded configuration of the structure; 2n unions that join the segments to each other at their ends; and a deployment system based on the simultaneous folding of all the segments that form the structure with respect to their contiguous segments, on the corresponding joints, so that the hinge axis and the axis of the cone are parallel to the plane of the polygon in the configuration deployed, always maintaining the same deployment angles between the same type of joints.
- an object of the invention is to provide a deployable assembly for reflectors used in space systems that is capable of overcoming the aforementioned drawbacks.
- the invention provides a deployable assembly for antennas, comprising:
- each pair of segments corresponding to one side of an unfolded polygon shape
- a deployable mast between two segments in which the deployable mast is gathered between the two segments before being deployed, the deployable mast terminating in a feeder that electromagnetically feeds the antenna and that includes a fastening element to keep the structure closed when it is retracted, so that the feeder acts as a structural support element when it is retracted and an electromagnetic feeder for the antenna when it is deployed,
- the largest reflector diameter can be achieved by varying only the length of the segments, and the contour of the circular to elliptical reflector can be achieved by varying only the angles between the segments ).
- the kinematics of the segments during deployment make their centers of gravity follow a straight linear pattern, facilitating validation by testing with a gravity compensation device.
- the global center of mass does not move during deployment, they can be fixed or deployable.
- the structural support of the feeder is an integral part of the collected structure and, when the invention is deployed and used as a reflector antenna, it plays the role of feeder in the focal position.
- the deployable assembly of the invention provides performance superior to those found to date in conventional systems known in the art.
- Two clamping mechanisms (could be clamp bands) hold the folded assembly during launch and deployment suffices.
- the folded assembly is very compact and robust, allowing a small size of the system within the available volume of the launcher
- the unfolded frame design can easily accommodate different sizes for larger or smaller reflectors and satellites.
- This structure is suitable for multiple purposes, not only for deploying large reflectors but also for building large antennas for Earth observation and for telecommunications, to build groups of coordinated folding satellites launched together, and even to build space debris capture systems.
- the deployed structure of the invention is also self-supporting, so that no auxiliary elements are needed to obtain rigidity, guidance and shape during deployment.
- Figure 1 is an isometric view of a large deployable reflector connected to a satellite.
- Figures 2A, 2B and 2G are schematic general views of the object of the invention in the collected, deployed and fully deployed (operative) positions, respectively.
- Figure 3 is a more detailed view of the collected assembly, in the launch configuration within the available volume of the fairing.
- Figure 4 shows the assembly deployed in the operative arrangement.
- Figure 5 is a simplified view of! collected and unfolded assembly (feeder, mast, cable net and reflective surface not shown).
- Figures 6A to 6F show the main steps in the deployment of the structure and the assembly.
- Figure 7 shows the deployable assembly of the invention in an intermediate position of the deployment process.
- Figures 2A, 2B and 2G show the deployable antenna assembly of the Invention in various stages.
- Figure 2A shows the stowed (or stowed) position
- Figure 2B shows an intermediate position in which the assembly is being deployed
- Figure 2C shows the fully deployed position.
- FIGS 6A to 6F also show the deployable antenna assembly of the invention in various stages, with more intermediate positions.
- Figure 7 is a detailed view of the deployable assembly of the invention in an intermediate position of the deployment process, in which all its elements can be seen.
- the deployed set for antennas shown in these figures includes:
- the structure is capable of changing from a folded position with a substantially cylindrical shape to a deployed position with a substantially flat polygonal shape with n sides, as can be seen in Figure 5.
- the drop-down set for antennas also includes:
- a deployable mast 3 (also called “boom”) between two segments 4, 5, in which the deployable mast 3 remains tucked between the two segments 4, 5 before being deployed, the deployable mast 3 terminating in a feeder 1 that electromagnetically feeds the antenna and comprising a fastening element 2 to keep the structure closed when it is folded up, in such a way that the feeder 1 plays the role of structural support element when it is picked up and electromagnetic feed of the antenna when it is deployed,
- the deployable pole 3 is located between two segments 4, 5 on the same side of the polygonal shape, as can be seen, for example, in Figures 6B to 6F.
- the drop-down pole 3 remains folded, secured and protected between two segments 4, 5 before being unfolded to reach the focal length.
- Figures 6A to 6D show the successive steps for the formation of the polygonal shape with n sides
- Figures 6D to 6F show the deployment of the mast 3.
- the deployable antenna assembly of the invention is fully deployed.
- Figure 5 is a simplified view of the deployable assembly of the invention, mainly showing the structure, in which the feeder 1, the mast 3, the cable network 7 and the reflective surface 9 are not represented.
- feeder 1 can play the role of: - a fixing element for the segments 4, 5 when it is retracted, by means of the clamping element 2 (see figure 3, for example), and
- the fastening element 2 can be, for example, a fastening band similar to those used in similar applications in spacecraft systems.
- the unfolded polygonal shape has n sides, corresponding to the n pairs of segments 4, 5.
- a hexagonal shape has been chosen (see, for example, Figure 5).
- Each pair of segments is made up of two symmetrical segments 4, 5, with a hinge joint as a connecting element between them.
- the deployable ring structure of the invention has sufficient space within it to contain the necessary subsystems of the spacecraft. It can contain everything necessary to form a complete satellite, such as power systems, flight and attitude control and communication with the Earth, although it can also be conceived as a payload, coupled to a larger satellite.
- Figures 5 and 7 also show n angular connections of hinge 6 between each two adjacent sides of the polygon shape, thus located at each corner of the polygon shape.
- the shape can be defined as a regular or non-regular polygon, in order to achieve a circular or elliptical contour of the reflecting surface 9.
- Figures 5 and 7 also show a set of supports 15 that protrude from the back of the segments 4 , 5 to shape the outline of the reflective surface 9.
- the movement of the unfolding of the structure is carried out by motors in each of the hinge angle connections 6. Coordination can be ensured by mechanical means and / or position sensors as feedback signals when necessary. The end position can be guaranteed by end stops, and the irreversibility of the deployed end configuration can be secured with locks, if desired.
- the cable network 7 comprises several tension cables to ensure that the reflective surface 9 conforms to the desired shape when deployed. As can be seen in figure 7, the tensioning cables can be held by the tensioning elements 8 that protrude from the back of the segments 4, 5, capable of tensioning the tensioning cables.
- the reflective surface 9 is a paraboloid formed by cables working in tension, as described above.
- the contour of the reflective surface 9 it can be circular or elliptical
- the reflective surface 9 is folded, limited and protected within the structure collected during launch (see Figures 3 and 6A).
- the collected structure protects the reflective surface 9 from contact and prevents damage to the feeder 1.
- Figure 3 also shows a lower fastener 10 (eg, a fastener band) that remains with the launcher after separation. It also shows the range of collected height 14 available within the launcher, which defines the diameter of the reflective surface 9.
- a lower fastener 10 eg, a fastener band
- Figure 5 also shows the minor axis 11 and the major axis 12 of the contour of the reflective surface 9 when it is elliptical. It also shows the diameter 13 of the frame in the stowed position.
- the present invention represents a spatial closed loop deployable assembly with a structure capable of changing from a substantially cylindrical configuration to a substantially planar polygonal configuration having n sides:
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- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerials With Secondary Devices (AREA)
- Details Of Aerials (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
Description
Claims
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201980100685.8A CN114503361B (zh) | 2019-09-24 | 2019-09-24 | 天线可展开组件 |
IL291576A IL291576B1 (en) | 2019-09-24 | 2019-09-24 | Deployable mounting for antennas |
PCT/ES2019/070635 WO2021058838A1 (es) | 2019-09-24 | 2019-09-24 | Conjunto desplegable para antenas |
US17/762,673 US11784415B2 (en) | 2019-09-24 | 2019-09-24 | Deployable assembly for antennas |
CA3151901A CA3151901A1 (en) | 2019-09-24 | 2019-09-24 | Deployable assembly for antennas |
EP19797318.3A EP4024606B1 (en) | 2019-09-24 | 2019-09-24 | Deployable assembly for antennae |
JP2022518317A JP7459237B2 (ja) | 2019-09-24 | 2019-09-24 | アンテナ用展開式アセンブリ |
ES19797318T ES2950826T3 (es) | 2019-09-24 | 2019-09-24 | Conjunto desplegable para antenas |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/ES2019/070635 WO2021058838A1 (es) | 2019-09-24 | 2019-09-24 | Conjunto desplegable para antenas |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2021058838A1 true WO2021058838A1 (es) | 2021-04-01 |
Family
ID=68424919
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/ES2019/070635 WO2021058838A1 (es) | 2019-09-24 | 2019-09-24 | Conjunto desplegable para antenas |
Country Status (8)
Country | Link |
---|---|
US (1) | US11784415B2 (es) |
EP (1) | EP4024606B1 (es) |
JP (1) | JP7459237B2 (es) |
CN (1) | CN114503361B (es) |
CA (1) | CA3151901A1 (es) |
ES (1) | ES2950826T3 (es) |
IL (1) | IL291576B1 (es) |
WO (1) | WO2021058838A1 (es) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2021058838A1 (es) * | 2019-09-24 | 2021-04-01 | Airbus Defence And Space, S.A. | Conjunto desplegable para antenas |
US11688932B2 (en) * | 2020-02-07 | 2023-06-27 | Hedron Space Inc. | Satellite antenna |
Citations (10)
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EP2482378A1 (en) | 2011-01-31 | 2012-08-01 | NEC TOSHIBA Space Systems, Ltd. | Deployable antenna |
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JP6556583B2 (ja) * | 2015-10-02 | 2019-08-07 | 株式会社テクノソルバ | 展開式リフレクタ及び展開式リフレクタ用展開構造物 |
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2019
- 2019-09-24 WO PCT/ES2019/070635 patent/WO2021058838A1/es unknown
- 2019-09-24 CA CA3151901A patent/CA3151901A1/en active Pending
- 2019-09-24 US US17/762,673 patent/US11784415B2/en active Active
- 2019-09-24 JP JP2022518317A patent/JP7459237B2/ja active Active
- 2019-09-24 EP EP19797318.3A patent/EP4024606B1/en active Active
- 2019-09-24 IL IL291576A patent/IL291576B1/en unknown
- 2019-09-24 CN CN201980100685.8A patent/CN114503361B/zh active Active
- 2019-09-24 ES ES19797318T patent/ES2950826T3/es active Active
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US3617113A (en) | 1969-05-15 | 1971-11-02 | Fairchild Hiller Corp | Deployable reflector assembly |
US4030102A (en) | 1975-10-23 | 1977-06-14 | Grumman Aerospace Corporation | Deployable reflector structure |
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WO2009153454A2 (fr) | 2008-06-18 | 2009-12-23 | Conseil Et Technique | Structure articulee deployable |
EP2482378A1 (en) | 2011-01-31 | 2012-08-01 | NEC TOSHIBA Space Systems, Ltd. | Deployable antenna |
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EP3480885A1 (en) * | 2017-11-01 | 2019-05-08 | Elta Systems Ltd. | Deployable antenna reflector |
Also Published As
Publication number | Publication date |
---|---|
CA3151901A1 (en) | 2021-04-01 |
US20220359992A1 (en) | 2022-11-10 |
EP4024606C0 (en) | 2023-07-12 |
CN114503361B (zh) | 2024-06-04 |
JP7459237B2 (ja) | 2024-04-01 |
IL291576A (en) | 2022-07-01 |
EP4024606A1 (en) | 2022-07-06 |
IL291576B1 (en) | 2024-06-01 |
CN114503361A (zh) | 2022-05-13 |
US11784415B2 (en) | 2023-10-10 |
JP2022553508A (ja) | 2022-12-23 |
EP4024606B1 (en) | 2023-07-12 |
ES2950826T3 (es) | 2023-10-13 |
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