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
  • H01Q15/162—Collapsible reflectors composed of a plurality of rigid panels
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
  • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
  • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
  • B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
  • B64G1/2222—Folding
  • B64G1/2224—Folding about multiple axes
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
  • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
• • 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
  • H01Q1/27—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
  • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
  • H01Q3/12—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems
  • H01Q3/16—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems for varying relative position of primary active element and a reflecting device

Definitions

• a segmented structure in particular for a satellite antenna reflector, provided with at least one rotational and translational deployment device.
• 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 connecting arm which is secured at one end to the rear face of the secondary panel and which is connected by a second of its ends to the rear face of the main panel via a part of structure;
• a displacement system arranged in said structural part and comprising at least: A rotation unit able to generate a rotation of said link arm around a so-called reference axis, said connecting arm being arranged so that a rotation of said rotation unit makes it possible to bring said secondary panel directly into the one or the other of a first position and a second position relative to said main panel, said first position and said second position being situated, in a lateral plane, substantially respectively at said storage position and at a position associated with said the deployed position; and
• a translation unit capable of generating a translation of said link arm along said reference axis so as to move said secondary panel with respect to said main panel in a direction transverse to said lateral plane.
• the secondary panel of the segmented structure can be deployed in a simple, efficient and space-saving manner, from the storage position to the deployed position, as specified below.
• the reference axis is defined by the combination of the interface plane of the secondary panel with the main panel in the storage position and in the deployed position, with the relative position of said secondary and main panels.
• the rotation unit comprises an electric motor coupled to a gear and acting between a structural member secured to the rear face of the main panel and said second end of the connecting arm; and or
• the translation unit comprises an electrically actuated screw / nut system and acting between a structural element integral with the rear face of the main panel and said second end of the connecting arm.
• said structural element comprises a support which is provided with fixing feet integral with the rear face of the main panel.
• the connecting arm is connected at the level of at least one of its ends by a recess;
• the connecting arm is provided at least at the first end thereof (which is connected to the secondary panel) of a flexible element.
• the segmented structure comprises:
• the two secondary panels are arranged symmetrically with respect to each other, in a central symmetry relative to a central point of said main panel.
• 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 storage position in the deployed position:
• the method also comprises a step d) of rotating said connecting arm to which the secondary panel is connected, by means of the rotation unit, in a second direction of rotation opposite to said first direction of rotation, to bring said secondary panel into contact with said main panel in the deployed position.
• translations and rotations for the two secondary panels are preferably performed simultaneously.
• Figure 1 is a schematic perspective view of a particular embodiment of a segmented structure illustrating the invention and comprising a central main panel, and two secondary panels, each of which is in a storage position.
• Figures 2 to 4 illustrate several successive steps of deployment of secondary panels with respect to a main panel of a segmented structure.
• Figures 5A and 5B are side views of a segmented structure respectively in a storage position and in a translated position.
• FIGS. 6A and 6B to 12A and 12B respectively illustrate, schematically and in perspective, various successive stages of deployment of secondary panels relative 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.
• the present invention relates to a segmented structure 1 of the type comprising, as shown in FIG.
• At least two panels namely at least a first panel 2 said main comprising a front face 2A and a rear face 2B, and at least a second panel 3, 4 said secondary also comprising a front face 3A, 4A and a rear face 3B, 4B; and
• At least one deployment device 5 which is connected to the rear faces 2B and 3B, 4B respectively of the main panel 2 and of a secondary panel 3, 4.
• This deployment device 5 is able to bring the secondary panel 3, 4 with which it is associated, in one or other of the two following positions, relative to the main panel 2:
• front face and "rear face”, the two faces of a panel, the front face 3A, 4A of a secondary panel 3, 4 being superimposed at least partially on the rear face 2B of the main panel 2, each front face 2A, 3A, 4A corresponding in the case of an antenna reflector to the reflective face.
• segmented structure 1 having an axis of symmetry X-X (FIG. 1), comprises:
• each of the deployment devices 5 of the segmented structure 1 comprises, as represented in FIG.
• a linking arm 6 which is secured, by a first 6A of its ends, to the rear face 3B, 4B of said secondary panel 3, 4, and which is connected, by a second 6B of its ends, to the rear face 2B said main panel 2 via a structural part 7;
• said displacement system 8 comprises:
• a rotation unit 9 (FIG. 3) able to generate a rotation of the connecting arm 6.
• the linking arm 6 is arranged so that a rotation of the rotation unit 9 makes it possible to bring the secondary panel 3, 4 directly into one or the other of a first position PA (FIGS. 6A and 6B) and of a second position PB (FIGS. 8A and 8B) relative to said main panel 2.
• Said first and second positions PA and PB correspond, laterally (that is to say in a lateral plane substantially corresponding to the average plane of the main panel 2), substantially respectively at the storage position P1 and at a position associated with the deployed position P2.
• This associated position can be either directly the deployed position P2, or a position Pi close to the latter; and
• a translation unit 10 (FIG. 2) able to generate a translation of the link arm 6 so as to move the secondary panel 3, 4 with respect to the main panel 2 in a transverse direction (L axis), which is substantially transverse to the main panel 2.
• the rotation unit 9 is formed to generate the rotation of the link arm 6 about a reference axis L, as illustrated by an arrow F1, F2 in FIG. 3, and the translation unit 10 is formed. so as to generate the translation of the link arm 6 along the same reference axis L, as illustrated by an arrow E1, E2 in Figure 2.
• this reference axis L is defined by the combination of the plane of interface of the secondary panel 3, 4 considered with the main panel 2 in the storage position P1 and in the deployed position P2, with the relative position of said secondary panel 3, 4 and said main panel 2.
• Such a deployment device 5 makes it possible to perform an efficient and advantageous deployment of the secondary panel 3, 4, with which it is associated, from the storage position P1 to the deployed position P2, as specified below.
• segmented structure 1 may comprise conventional fastening systems (not shown) of the different panels 2, 3 and 4 in the storage position P1. These attachment systems are released before deployment, so that each deployment device 5 can implement the deployment specified below.
• Each displacement system 8 is arranged on the structure 7.
• This structure 7 comprises a structural element (or frame) 13 which is fixed to the central main panel 2, via fixing feet 14, for example via three feet 14 ( Figure 3).
• the connecting arm 6 ensures the transmission of translational and rotational movements between the displacement system 8 (or motorization) and the secondary panel 3, 4.
• Each arm 6 is connected to the secondary panel 3, 4 and the drive system by a recess 11 (shown only in Figure 2 for reasons of simplification of the drawing).
• the installation of the arms on the secondary panel 3, 4 has flexibility, generated by a flexible element 12 (shown only in Figure 2 for simplification of the drawing), which is provided for all degrees of freedom.
• the present invention thus provides for pivoting and translating, along the same axis L, the secondary panel 3, 4 from the storage position P1 to its deployed position P2.
• the translation makes it possible to make the necessary shift to the superposition of the structures.
• each rotation unit 9 comprises an electric motor (not shown) coupled to a gear and acting between the structural portion 13 secured to the rear face 2B of the main panel 2 and the end 6B of the arm link 6.
• each translation unit 10 comprises a screw / nut system (not shown) actuated electrically and also acting between the structural part 13 integral with the rear face 2B of the main panel 2 and the end connecting arm 6.
• FIGS. 2 to 4 Different successive positions of a deployment of two secondary panels 3 and 4 are shown in FIGS. 2 to 4.
• the two secondary panels 3 and 4 are stored above the main panel 2.
• the attachment points (not shown) between the secondary panels 3, 4 and the central panel 2 are released.
• a first phase consists of translating (towards the rear in the direction of the arrows E1 and E2) along the axes L, as shown in FIG. 2, to disengage the two secondary panels 3 and 4 from their fastening systems on the main panel 2 to bring the secondary panels in the first position PA ( Figures 6A and 6B).
• This translation can be done simultaneously in order to avoid a collision between, respectively, the two connecting arms 6 and the secondary panels 3 and 4.
• This translation is also illustrated in FIGS. 5A and 5B, FIG. 5A corresponding to FIG. storage position P1 before the translation, and Figure 5B corresponding to the position PA after the translation along the reference axis L, as illustrated by the arrow E2.
• the link arms 6 have at their ends 6B a sliding pivot connection.
• a second phase consists of rotating along the axes L in directions of rotation indicated by arrows F1 and F2 in FIG. 3 (to move the link arms 6 as illustrated by arrows G1 and G2), in order to bring about the secondary panels 3, 4 in the second position PB (FIGS. 9A and 9B).
• a third phase consists of translating (forwards), in the direction E3 and E4 opposite to the directions E1 and E2, along the axes L to engage the secondary panels 3 and 4 in guidance and capture systems, which realize a rigid mechanical connection between the secondary panels 3 and 4 and the main panel 2.
• the flexibility introduced (via the flexible elements 12) in the recesses 11 of the connecting arms 6 on the secondary panels 3 and 4 are put to contribution.
• the rotation of the second phase continues by a few degrees. Then, after the translation of the third phase, an inverse rotation along the axes L in opposite directions F1 and F2 is performed and allows the engagement of the secondary panels 3 and 4 in the alignment and capture systems. During this last phase, the flexibilities introduced (via the flexible elements 12) into the recesses 11 of the connecting arms 6 on the secondary panels 3 and 4 are used.
• the deployment device 5 also comprises means (not shown) (for example a central unit) for controlling, in particular, the electric motors of the rotation and translation units 9 and 10.
• the main panel 2 constitutes the central part of the antenna reflector. It contains the accommodating structures of the displacement system 8. This main panel 2 also receives the releasable fastening systems of the secondary panels 3, 4 when they are in the storage position P1. These elements allow the assembly of three panels 2, 3 and 4 to support the mechanical environments (quasi-static and dynamic) during integration, transport and flight phases.
• the main panel 2 is also provided with usual capture and alignment systems (not shown) of the secondary panels 3, 4 in the deployed position P2.
• the main panel 2 is connected to the main structure of the payload (eg the satellite structure) via a deployment arm and releasable fastening systems (not shown), of the usual type.
• the secondary panels 3, 4 are complementary to the overall reflecting surface to be reconstituted. In the storage position P1, they are maintained on their periphery by the releasable fixing systems arranged on the central main panel 2. The secondary side panels 3, 4 also receive the complement of the capture and alignment systems.
• the two secondary panels 3, 4 are arranged symmetrically with respect to each other, in a central symmetry relative to a central point (not shown) of the main panel 2.
• the operation of the deployment device 5, for the deployment of a secondary panel 3, 4, from the storage position P1 of FIGS. 1 and 2, to the deployed position P2 of FIGS. 4, 12A and 12B, is as follows :
• FIGS. 6A, 6B to 12A, 12B illustrate different successive stages of the deployment of secondary panels 3 and 4 with respect to the main panel 2.
• X being an integer between 6 and 12
• Fig. XA illustrates a plan view
• Fig. XB shows the same perspective view.
• the deployment is represented successively, step by step, each time first for the secondary panel 4, then for the secondary panel 3.
• FIGS. 7A and 7B show the result of the rotation (in the direction F2) of the secondary panel 4 from the position PA to the position PB;
• FIGS. 8A and 8B show the result of the rotation (in the direction F1) of the secondary panel 3 from the position PA to the position PB;
• FIGS. 9A and 9B show the result of the translation (in the direction E4) of the secondary panel 4 of the position PA at a position Pi in the mean plane of the main panel 2;
• FIGS. 10A and 10B show the result of the translation (in the direction E3) of the secondary panel 3 from the position PB to the position Pi in the mean plane of the main panel 2;
• FIG. 11A and 11B show the result of the rotation (in opposite direction F2) of the secondary panel 4 from the position Pi to the storage position P2;
• FIGS. 12A and 12B show the result of the rotation (in the opposite direction F1) of the secondary panel 3 from the position Pi to the P2 storage position.
• the same deployment method is thus implemented for the two secondary panels 3 and 4 so as to obtain a fully deployed position of the segmented structure 1 (FIGS. 12A and 12B).
• the device 5 can also bring the segmented structure 1 of the deployed position P2 to the storage position P1, if this were necessary, for example for a validation operation, by carrying out the above operations in the reverse order (d, c, b, a), with each operation (rotation, translation) implemented in the opposite direction to that indicated above for the deployment.
• the segmented structure 1 also comprises means not shown to allow precise final positioning between a secondary panel 3, 4 and the main panel 2, as well as means for locking the panels in the fully deployed position of the segmented structure 1.

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• Engineering & Computer Science (AREA)
• Remote Sensing (AREA)
• Physics & Mathematics (AREA)
• Aviation & Aerospace Engineering (AREA)
• Astronomy & Astrophysics (AREA)
• General Physics & Mathematics (AREA)
• Electromagnetism (AREA)
• Aerials With Secondary Devices (AREA)
• Details Of Aerials (AREA)

Applications Claiming Priority (2)

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Country Status (5)

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• 2013
  • 2013-12-30 FR FR1303110A patent/FR3015955B1/fr not_active Expired - Fee Related
• 2014
  • 2014-12-10 EP EP14824038.5A patent/EP3089913A1/de not_active Withdrawn
  • 2014-12-10 CA CA2931924A patent/CA2931924A1/fr not_active Abandoned
  • 2014-12-10 WO PCT/FR2014/000268 patent/WO2015101723A1/fr active Application Filing
  • 2014-12-10 US US15/102,491 patent/US20160322710A1/en not_active Abandoned

Non-Patent Citations (1)

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