WO2015082778A1 - Structure segmentée, en particulier pour réflecteur d'antenne de satellite - Google Patents
Structure segmentée, en particulier pour réflecteur d'antenne de satellite Download PDFInfo
- Publication number
- WO2015082778A1 WO2015082778A1 PCT/FR2014/000254 FR2014000254W WO2015082778A1 WO 2015082778 A1 WO2015082778 A1 WO 2015082778A1 FR 2014000254 W FR2014000254 W FR 2014000254W WO 2015082778 A1 WO2015082778 A1 WO 2015082778A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- panel
- segmented structure
- movable carriage
- rear face
- main panel
- Prior art date
Links
Classifications
-
- 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
-
- 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
- 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
- H01Q15/162—Collapsible reflectors composed of a plurality of rigid panels
Definitions
- Segmented structure in particular for satellite antenna reflector
- the present invention relates to a segmented structure.
- This segmented structure comprises at least two panels linked together and intended to be deployed in space.
- Such an antenna reflector generally comprises a rigid structure (called shell) provided with a reflective surface and reinforcement means at the rear of this surface, which participate in the maintenance of the hull and the connection with the satellite.
- the large size of the hull of such a reflector poses congestion problems when sending space in a satellite provided with such a reflector using a space launcher.
- a segmented structure provided with several panels, in particular a three-panel structure comprising a central panel and two end panels.
- This segmented structure further includes an end panel deployment device, which is adapted to bring the end panel relative to the main panel:
- each end panel can thus take a storage position for transport in the space launcher and a deployed position when the satellite is in space.
- the present invention relates to a segmented structure, in particular for a satellite antenna reflector, comprising at least two panels and a deployment device making it possible to realize in space an efficient and advantageous deployment of these two panels.
- said segmented structure of the type comprising:
- first so-called main panel comprising a front face and a rear face
- second so-called secondary panel also comprising a front face and a rear face
- At least one deployment device connected to the rear faces respectively of said main and secondary panels and adapted to bring said secondary panel in one or other of the two following positions, relative to said main panel:
- a storage position in which said secondary panel is at least partially superimposed on said main panel on the rear face of the latter, the front face of said secondary panel being directed in the same direction as the front face of said main panel;
- said deployment device comprises:
- a translation system comprising a mobile carriage, guided in translation, said mobile carriage being provided with a connecting arm which is connected to the rear face of said secondary panel, said translation system being able to generate a translational movement of said panel; secondary to said main panel; and - A rotation system capable of generating at least one rotation of said link arm at an outer end of the translation means.
- the secondary panel of the segmented structure can be deployed efficiently and advantageously in space, from the storage position to the deployed position, as specified below.
- said translation system comprises:
- a guiding structure configured to guide the mobile carriage in translation during a movement
- a drive unit configured to move the movable carriage along the guide structure.
- said drive unit comprises:
- a pulley system comprising two pulleys arranged at two ends of the guide structure, and a first rotational transmission link comprising a closed-loop link surrounding and connecting the two pulleys, said carriage being fixed to said first transmission link rotation;
- said drive means comprise a rotary motor which is connected via a second rotational transmission link to said first pulley of the pulley system (for example via an additional pulley), so as to rotate.
- the connecting arm is connected via a pivot connection to a structural member secured to the rear face of the secondary panel;
- said guide structure comprises a ramp-like structure along which the carriage is guided, said ramp-shaped structure being fixed on the rear face of the main panel and having a height, relative to this the rear face, gradually reducing from the inside to the outside.
- said guiding structure comprises a guide roller connected to the movable carriage, said guiding roller being arranged laterally in a longitudinal guiding opening made in the guiding structure so as to be able to be displaced, by turning, along this longitudinal opening.
- said rotation system comprises:
- the link arm of which a first end, at the connection with the mobile carriage, is configured to come into contact with the stop, said stop and said first end being configured to cooperate so as to cause said arm to pivot; binding at said first end;
- said drive means configured to drive in rotation a structural member secured to the rear face of the secondary panel, relative to a second end of the connecting arm, during the pivoting of said link arm.
- said drive means comprise two pulleys respectively arranged at both ends of the link arm and interconnected via a third rotational transmission link.
- said rotation system comprises an auxiliary external end provided on the guide structure and said auxiliary external end is bent so as to generate a rotation of the connecting arm fixed to the mobile carriage during a guiding the movable carriage along this curved auxiliary outer end.
- the segmented structure comprises:
- At least two deployment devices associated respectively with said secondary panels.
- one or more (2, 3, ...) devices for deployment by secondary panel can be provided.
- the present invention also relates to:
- a satellite antenna reflector which comprises a segmented structure as mentioned above;
- a satellite which comprises at least one such segmented structure or such an antenna reflector.
- the present invention also relates to a method of deploying a segmented structure as mentioned above.
- this method comprises successive steps consisting, during the deployment of the stored position in the deployed position: a) to perform a translation of the movable carriage provided with the link arm to which said secondary panel is connected, using said translation system, in a direction of translation outwardly of the main panel so as to bring the movable carriage to the outer end of the translation system; and
- step b) consists in performing a double rotation, namely:
- FIG. 1 is a schematic perspective view of a particular embodiment of a segmented structure illustrating the invention and comprising a central panel as well as two secondary panels, one of which is in a storage position and the other in an unfolded position.
- Figure 2 is a schematic perspective view similar to that of Figure 1, but for which both panels are in an extended position.
- Figures 3 to 6 are schematic partial views, in perspective, of a particular embodiment of a deployment device.
- Figures 7 and 9 are schematic partial views, in perspective, of a particular embodiment of a rotation system of a deployment device.
- Figures 8 and 10 illustrate a pivoting of a connecting arm.
- FIGS. 11A to 11C illustrate, in diagrammatic perspective view, different successive stages of deployment of a secondary panel with respect to a main panel of a segmented structure.
- the segmented structure 1, illustrating the invention and shown schematically in Figure 1 in particular, is intended, particularly although not exclusively, to a telecommunication satellite antenna reflector.
- Such an antenna reflector generally comprises, when it is deployed in space, a rigid structure (called shell) provided with a reflective surface, as well as reinforcement and holding means (not shown) at the rear of this structure, which contribute to the maintenance of the hull and the connection with the satellite.
- this structure is of segmented type, that is to say that it is formed of several segments or panels. More specifically, the present invention relates to a segmented structure 1 of the type comprising:
- At least two panels namely at least one first panel 2 said main comprising a front face 2A and a rear face 2B ( Figures 1 and 2), and at least a second panel 3, 4 said secondary also comprising a front face 3A , 4A and a back face 3B, 4B; and
- At least one deployment device 5 which is connected to the rear faces 2B and 3B respectively of the main panel 2 and a secondary panel (the panel 3 in the example of Figures 1 and 2).
- This deployment device 5 is able to bring the secondary panel 3, in one or the other of the two following positions, relative to the main panel 2:
- FIGS. 2 and 11C An extended position P2 as shown in FIGS. 2 and 11C, in which the secondary panel 3 is positioned beside and against the main panel 2 so as to form a continuous assembly at least on their front faces 2A and 3A.
- segmented structure 1 comprises:
- one or more (2, 3, ...) deployment devices 5 can be provided by secondary panel 3, 4.
- one 4 of the secondary panels 3 and 4 is in the deployed position P2, and the other 3 of said secondary panels 3 and 4 is in the storage position P1.
- the deployment device of the deployed secondary panel 4 (which is similar to that of the secondary panel 3) is not shown in this FIG. 1 and the secondary panel 4 is only partially shown in dashed lines. .
- each of the deployment devices 5 of the segmented structure 1 comprises:
- a translation system 6 comprising a movable carriage 7, guided in translation from an inner end 6A to an outer end 6B.
- the mobile carriage 7 is provided with a connecting arm 9 which is connected to the rear face 3B, 4B of said secondary panel 3, 4.
- Said translation system 6 is able to generate a translational movement of said secondary panel 3, 4 by report to said main panel 2, as illustrated by three successive positions A1, A2 and A3 of the connecting arm 9 in Figure 3; and a rotation system 8 capable of generating at least one rotation of said linking arm 9 at an external end 6B (FIG. 3) of the translation system 6, so as to generate a rotational movement of said secondary panel 3, 4 with respect to said main panel 2.
- the link arm 9 is linked:
- Such a deployment device 5 (comprising a pivoting system assembly and a connecting arm, carried by a carriage movable in translation) makes it possible to achieve an efficient and advantageous deployment of the secondary panel 3, 4, with which it is associated, of the storage position P1 at the deployed position P2, as specified below.
- Said translation system 6 comprises, as represented in FIG. 3:
- a guide structure 14 configured to guide the movable carriage 7 in translation during a movement in the direction indicated by an arrow E; and - a drive unit 15 configured to move the movable carriage 7 along the guide structure 14.
- Said guide structure 14 comprises a structure 16 made in the form of a plate and having a ramp shape.
- This structure 16 is fixed on the rear face 2B of the main panel 2 and has a height, with respect to this rear face 2B, gradually decreasing from the inside towards the outside, that is to say from one end 16A to an outer end 16B of the structure 16 ( Figure 3).
- the guiding structure 14 furthermore comprises, at the inner end 16A of the structure 16, two transverse plane elements 19A and 19B intended to laterally support the structure 16, as represented for example in FIGS. 2 and 3.
- the two transverse plane elements 19A and 19B are part of reinforcement means of the segmented structure 1, such as those provided at the rear of the reflecting surface in the case of an antenna reflector.
- the connecting arm 9 comprises two parts of arms 17 and 18, of flat shape, identical and arranged parallel to one another.
- Each of said arm portions 17 and 18 comprises two elongated planar segments, upper 17A, 18A and lower 17B, 18B, which are connected together forming a bend.
- the pivot connection 11 is provided at the free end (upper) between the two upper segments 17A and 18A.
- the structural element 12 which is arranged between these two segments 17A and 18A is partially and transparently shown in FIG. 4.
- the link arm 9 is connected to the mobile carriage 7 by pivot connection via the free end (lower) of the two segments 17B and 18B lower.
- Said guide structure 14 further comprises a guide roller 20 connected to the movable carriage 7 (FIGS. 4 and 6).
- the guide roller 20 is arranged laterally in a longitudinal guide opening 21 formed in the guide structure 14 so as to be able to be displaced, by turning, along this longitudinal opening 21.
- said drive unit 15 comprises:
- a pulley system 23 comprising two pulleys 24A and 25 arranged at two ends of the guide structure 14, and a rotational transmission link 26 comprising a closed-loop link (preferably a cable) surrounding and connecting the two pulleys 24A and 25, as shown in particular in Figure 3.
- Said carriage 7 is fixed to said rotational transmission link 26 at one end 7A ( Figure 6); and
- Said drive means 27 configured to rotate a first 24A of said two pulleys 24A and 25 of the pulley system 23 as shown in FIGS. 3 and 5.
- Said drive means 27 comprise a conventional rotary motor 28, shown schematically in FIG. 5, which is connected via a rotational transmission link 29 (preferably a cable) to a pulley 24B which is connected to the pulley 24A of the pulley system 23, so as to drive it in rotation, as illustrated by arrows F2.
- the rotary motor 28 preferably an electric motor, generates a rotation illustrated by arrows F1 in Fig. 5, the pulley 24B is rotated as illustrated by arrows F2.
- the latter then rotates the pulley 24A (arrows F3 in Figure 3) which causes the carriage 7 and the link arm 9 (via the link 26) to move in the direction E ( Figure 3).
- the motor 28 allows speed control and a direction of rotation for a reversible deployment.
- the rotation system 8 (able to generate the rotation of the translation system 6) can be realized in different ways.
- said rotation system 8 comprises:
- the abutment 30 and said end 31A are configured to cooperate so as to generate a pivoting the link arm 9 at said end 31A about a point of contact 32, as illustrated by different positions H1 to H5 in Fig. 8; and
- said drive means 33 comprise two pulleys 34 and 35 arranged respectively at both ends of the link arm 9 and interconnected by a rotational transmission link 36 (preferably a cable).
- the pulley 35 is rotated by the abutment and the translation, and it transmits the rotational movement to the pulley 34, which causes the pivoting of the structural element 12 in the direction of an arrow G2 (when the pivoting of the link arm in the direction of an arrow G1), as shown in FIG. 10.
- FIG. 10 shows different successive positions B1, B2, and B3 during the pivoting so as to arrive at the position B3 which makes it possible to position the secondary panel 3 in the general plane of the main panel 2.
- said rotation system may include an auxiliary outer end provided on the guide structure. This auxiliary outer end is bent so as to generate a rotation of the link arm attached to the carriage during a guide of the carriage along the curved auxiliary outer end.
- the deployment device 5 also comprises means not shown (for example a central unit) for controlling, in particular, the rotary motor 28 (electric motor).
- segmented structure 1 may comprise usual holding means (not shown) of the different panels 2, 3 and 4 in the storage position P1. These holding means are released before deployment, so that each deployment device 5 can implement the deployment specified below.
- the operation of said deployment device 5, for the deployment of a 3 of said secondary panels 3, 4 from the stored position P1 of Figures 1 and 11A to the deployed position P2 of Figures 2 and 11C, is as follows:
- FIGS. 11A to 11C illustrate various successive stages of the deployment of the secondary panel 3 with respect to the main panel 2, Fig. 11B showing an intermediate position Pi between positions P1 and P2;
- Step b) consists in performing a double rotation, as shown in FIG. 10, namely:
- the device 5 can also bring the segmented structure of the deployed position P2 to the stored position P1, if this were necessary, for example for a validation operation, by carrying out the above operations in the reverse order (b , a), with each operation (rotation, translation) implemented in the opposite direction.
- segmented structure 1 may comprise means not shown to allow precise final positioning between a secondary panel 3, 4 and the main panel 2, for example in the situation of FIG. 11C for the secondary panel 3, as well as means for locking the panels in the fully deployed position of the segmented structure 1.
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- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Electromagnetism (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerials With Secondary Devices (AREA)
- Details Of Aerials (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/100,870 US20160372821A1 (en) | 2013-12-06 | 2014-11-26 | Segmented structure, in particular, for a satellite antenna reflector |
CA2931298A CA2931298A1 (fr) | 2013-12-06 | 2014-11-26 | Structure segmentee, en particulier pour reflecteur d'antenne de satellite |
EP14809916.1A EP3078078A1 (fr) | 2013-12-06 | 2014-11-26 | Structure segmentée, en particulier pour réflecteur d'antenne de satellite |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR13/02853 | 2013-12-06 | ||
FR1302853A FR3014599B1 (fr) | 2013-12-06 | 2013-12-06 | Structure segmentee, en particulier pour reflecteur d'antenne de satellite |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2015082778A1 true WO2015082778A1 (fr) | 2015-06-11 |
Family
ID=50624621
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2014/000254 WO2015082778A1 (fr) | 2013-12-06 | 2014-11-26 | Structure segmentée, en particulier pour réflecteur d'antenne de satellite |
Country Status (5)
Country | Link |
---|---|
US (1) | US20160372821A1 (fr) |
EP (1) | EP3078078A1 (fr) |
CA (1) | CA2931298A1 (fr) |
FR (1) | FR3014599B1 (fr) |
WO (1) | WO2015082778A1 (fr) |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1043802A2 (fr) * | 1999-04-08 | 2000-10-11 | Hughes Electronics Corporation | Système d'arrimage compact de réflecteurs paraboliques segmentés |
US6505381B1 (en) * | 1999-07-30 | 2003-01-14 | Trw Astro Aerospace | Pulley actuated translational hinge system |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4314253A (en) * | 1980-04-11 | 1982-02-02 | Compact Video Sales, Inc. | Portable folding microwave antenna |
JPS59126305A (ja) * | 1983-01-10 | 1984-07-20 | Nippon Telegr & Teleph Corp <Ntt> | 展開形アンテナ反射鏡 |
-
2013
- 2013-12-06 FR FR1302853A patent/FR3014599B1/fr not_active Expired - Fee Related
-
2014
- 2014-11-26 WO PCT/FR2014/000254 patent/WO2015082778A1/fr active Application Filing
- 2014-11-26 CA CA2931298A patent/CA2931298A1/fr not_active Abandoned
- 2014-11-26 EP EP14809916.1A patent/EP3078078A1/fr not_active Withdrawn
- 2014-11-26 US US15/100,870 patent/US20160372821A1/en not_active Abandoned
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1043802A2 (fr) * | 1999-04-08 | 2000-10-11 | Hughes Electronics Corporation | Système d'arrimage compact de réflecteurs paraboliques segmentés |
US6505381B1 (en) * | 1999-07-30 | 2003-01-14 | Trw Astro Aerospace | Pulley actuated translational hinge system |
Also Published As
Publication number | Publication date |
---|---|
FR3014599A1 (fr) | 2015-06-12 |
FR3014599B1 (fr) | 2016-01-01 |
EP3078078A1 (fr) | 2016-10-12 |
US20160372821A1 (en) | 2016-12-22 |
CA2931298A1 (fr) | 2015-06-11 |
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