• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The deployable structure comprises a distance mast (10) and two storage rollers (11, 12) each supporting a flexible solar generator (30), the two storage rollers being articulated on the mast. The mast comprises at least one longitudinal rod (101) and two lateral arms (103, 104) inclined angularly in two opposite directions and symmetrical with respect to the longitudinal rod (101), each lateral arm (103, 104) having an end provided with a hollow guide (105, 106). Each storage roll (11,12) has a longitudinal axis (54) having a bent end forming a pivot (13, 14) respectively hinged inside the hollow guide (105, 106) of a corresponding lateral arm, the pivot (13, 14) of each storage roll having an axis of revolution (55, 56) different from the longitudinal axis (54, 57) of the corresponding storage roll (11, 12).
    公开号:FR3044639A1
    申请号:FR1502511
    申请日:2015-12-02
    公开日:2017-06-09
    发明作者:Yannick Baudasse；Stephane Vezain；Olivier Bardel；Didier Stanek
    申请人:Thales SA；
    IPC主号:
    专利说明:

    Deployable structure comprising a set of solar generators, deployment system of such a deployable structure and satellite comprising such a system
    The present invention relates to a deployable structure comprising a set of solar generators, a deployment system of such a deployable structure and a satellite comprising such a system. It applies to the field of space equipment that must be deployed in orbit and more particularly to solar generators installed on a satellite.
    The space-deployable structures, of the solar generator type for example, generally consist of rigid panels hinged together, these panels being, in the stored position, stacked one above the other. These structures have the advantage of having a controlled kinematics but have the disadvantage of a large surface mass and inertia. In addition, the rigid structures occupy, in the stored position, a large space under the cap of a launcher. The space allocated to the deployable structures, under the cap of a launcher, being limited, it is important to reduce the size of these deployable structures when they are in the stored position so as to optimize the surface in the deployed position.
    In order to counter these disadvantages, it is known, in particular from document FR 2 998 876, to produce flexible solar generators which have many advantages of competitiveness with respect to rigid panels. In particular, they have a superior design capacity and an increase in the useful area in the deployed position.
    US 8 894 017 discloses a set of deployable solar generators articulated at the end of a mast fixed on a face of a satellite. Different segments supporting flexible solar generators are mounted end to end and hinged together. However, in the stored position, the segments supporting the flexible solar generators are not operational, which requires the addition of a rigid solar panel, mounted on the mast, which, in the stored position, comprises active solar cells oriented towards the outside of the satellite to power the satellite. Furthermore, it is necessary to add orientation means of the rigid solar panel to be able to use it also in the deployed position. In addition, the deployment of the mast and solar generators is performed sequentially, which requires several different commands to fully deploy the entire deployable structure.
    The object of the invention is to provide a deployable structure comprising a set of solar generators and a deployment system of this deployable structure does not have the disadvantages of deployable structures and existing deployment systems, with the advantage of being little bulky, simple to perform, having a simplification of the deployment sequences and associated commands, to have a solar cell area operational stored position and allowing simultaneous deployment of the mast and flexible solar generators.
    For this, the invention relates to a deployable structure comprising a set of solar generators, the deployable structure comprising a distance mast and two storage rolls each supporting a flexible solar generator, the two storage rollers being articulated on the mast, the mast having a first end called base, a second end opposite the base and having at least one longitudinal rod located between the first and the second end. The mast further comprises two lateral arms mounted at the second end, the two lateral arms being inclined angularly in two opposite directions and symmetrical with respect to the longitudinal rod, each lateral arm having an end provided with a hollow guide. Each storage roll has a longitudinal axis having a bent end forming a pivot respectively hinged inside the hollow guide of a corresponding lateral arm, the pivot of each storage roll having an axis of revolution different from the longitudinal axis of the corresponding storage roller.
    Advantageously, the two lateral arms of the mast can be secured to the longitudinal rod.
    Alternatively, the rod may comprise two distinct longitudinal parts, respectively called first rod and second rod, the second rod being parallel to the first rod and articulated on an axis of rotation located at the second end of the mast, the axis of rotation being perpendicular at the first and the second rod, the two lateral arms being secured to the second rod.
    Advantageously, each flexible solar generator may comprise an end end rigidly attached to a respective fixed rigid anchor, and the deployable structure may further comprise at least one rigid flap fixed to the rigid anchor, in the extension of a flexible solar generator, the rigid flap comprising solar cells permanently oriented towards the Sun.
    Alternatively, in the stored position, each flexible solar generator may be partially wound around the storage roller, and have an end portion provided with solar cells permanently oriented towards the sun.
    Advantageously, the hollow guides of each lateral arm of the mast may be oriented at 45 ° relative to the mast and relative to the respective longitudinal axes of the storage rollers. The invention also relates to a deployment system comprising a deployable structure and further comprising a single motor having a rotor mounted on the base of the mast, the rotor having an axis of rotation perpendicular to the longitudinal rod of the mast, a first pulley located at the base of the mast and having an axis of revolution aligned with the axis of rotation of the rotor, two driving pulleys of the storage rollers, rotatably respectively attached to the bent ends of each storage roll, return pulleys fixed to the side arms of the mast and a set of cables connecting the first pulley to the pulleys of each storage roller is driven by means of the return pulleys, the drive pulleys having an axis of respective rotation coinciding with a longitudinal axis of the respective hollow guides.
    Advantageously, each drive pulley of a storage roller may have an axis of rotation at an angle of 45 ° with respect to the longitudinal axis of the corresponding storage roller and relative to the longitudinal rod of the mast. The invention finally relates to a satellite comprising such a deployment system. Other features and advantages of the invention will become clear in the following description given by way of purely illustrative and non-limiting example, with reference to the accompanying schematic drawings which show: FIG. 1: a face diagram, in stored position an example of a deployable structure comprising two storage rolls on which respective flexible solar generators are wound, and an associated deployment system, according to the invention; FIG. 2: a diagram, in perspective, in stored position, of an exemplary deployable structure comprising a single storage roll on which is wound a flexible solar generator and an associated deployment system, according to the invention; FIG. 3a: a perspective diagram illustrating the deployable structure of FIG. 2, after unlocking, according to the invention; FIGS. 3b, 3c, 3d: perspective diagrams, illustrating the deployable structures of FIGS. 1 and 2, respectively at the beginning, during and at the end of deployment, according to the invention; FIG. 4a: a cross-sectional diagram, in the stored position, of a deployable structure comprising two storage rollers provided with respective flexible solar generators, in which each solar generator further comprises a rigid flap in the extension of the flexible support, according to a embodiment of the invention; FIG. 4b: a cross-sectional diagram showing the deployment direction of the deployable structure according to FIG. 4a, according to the invention; FIG. 5a: two diagrams, in perspective, in stored position, of an alternative embodiment of the deployable structure comprising two storage rollers provided with respective flexible solar generators, in which, in the stored position, the flexible solar generators are partially wound, according to the invention; FIG. 5b: a cross-sectional diagram, in the stored position, of the deployable structure according to FIG. 5a, according to the invention; FIG. 5c: a cross-sectional diagram, showing the direction of deployment of the deployable structure according to FIG. 5a, according to the invention; FIGS. 6a, 6b, 6c: three successive sequences, in perspective, of the deployment of the deployable structure of FIG. 5a, according to the invention; FIG. 7 is a sectional diagram of an example of a satellite comprising flexible solar generators in stored position, under the cap of a rocket, according to the invention.
    The deployable structure, represented in the position stored in FIG. 1, comprises a mast 10 of separation and two storage rollers 11, 12, on which are wound flexible solar generators, the two storage rolls, for example cylindrical, support each a flexible solar generator and each comprise a pivot 13, 14 respectively articulated on the mast. In the stored position, the two storage rolls 11, 12 are parallel to the mast 10 and the flexible solar generators are wound around the two storage rolls. The mast comprises a longitudinal rod 101 located between a first end 102 of the mast called base and a second end opposite the base, and two lateral arms 103, 104 located at the second end of the mast. The two lateral arms 103, 104 are inclined angularly in two opposite directions and symmetrical with respect to the longitudinal rod 101. The two lateral arms 103, 104 may be secured to the rod 101. The two lateral arms may also consist of a one-piece, metal or composite fitting.
    Each lateral arm 103, 104 has an end provided with a cylindrical hollow guide 105, 106 whose longitudinal axis 55, 56 is angularly inclined with respect to the longitudinal rod 101 of the mast 10. Each storage roll 11, 12 has a longitudinal axis having a bent end forming the pivot 13, 14 hinged inside the corresponding hollow guide 105, 106. The pivot 13, 14 of each storage roll has an axis of revolution 55, 56 different from the longitudinal axis 54, 57 of the storage roller 11, 12 corresponding. The articulation between the pivot 13, 14 of each storage roller 11, 12 and the corresponding hollow guide 105, 106, allows rotation of the pivot about its axis of revolution.
    As illustrated in particular in FIGS. 3c and 3d, the respective hollow guides 105, 106 of each lateral arm 103, 104 of the mast and the axes of revolution of the pivots 13, 14 of each storage roll can preferably be oriented in a direction at an angle of 45 ° with respect to the longitudinal rod of the mast and relative to the respective longitudinal axes of the storage rollers so as to minimize the number of sequences necessary for the deployment of the structure and the proper positioning of the rolls of storage in the deployed position. In particular, this allows, in the deployed position, to obtain a positioning of the longitudinal axis of the storage rollers perpendicular to the mast rod, as shown in FIG. 3c, and thus to allow solar generators to be deployed in one direction. parallel to the mast rod as shown in Figure 3d. Of course, it is also possible to choose an orientation of the hollow guides in a direction making an angle of value different from 45 ° relative to the longitudinal rod 101 of the mast 10 and relative to the respective longitudinal axes of the storage rollers 11, 12 . In Figures 2 and 3a a single storage roll is shown to simplify these figures, but of course, this deployment kinematics is valid for two rollers positioned symmetrically with respect to the central mat 10, as shown in each of Figures 3b, 3c , 3d on which two examples of deployment kinematics of deployable structures respectively comprising a storage roll and two storage rolls, are shown.
    The deployment system of the deployable structure comprises a single motor 20, of the type regulating motor, having a stator intended to be fixed on a face 40 of the body 41 of a satellite and a rotor mounted directly on the base 102 of the mast, the rotor having an axis of rotation 50 perpendicular to the rod 101 of the mast. The rotor of the motor 20 is intended to drive the mast 10 in rotation about the axis of rotation 50 in order to deploy it. The deployment system also comprises a first pulley 21, located at the base of the mast and intended to be fixed on the face 40 of the body 41 of the satellite, two driving pulleys 22, 23 of the rotating storage rollers, respectively fixed at the bent ends of each storage roll, return pulleys 24, 25 secured to the side arms of the mast and a cable assembly 26 connecting the first pulley 21 to the drive pulleys 22, 23 of the storage roll via pulleys 24, 25. The first pulley 21 has an axis of revolution aligned with the axis of rotation 50 of the rotor of the motor 20. The drive pulleys 22, 23 have an axis of revolution coinciding with the axis of rotation. respective hollow guides 105, 106 and have the function of deploying the storage rollers during the deployment of the mast, the deployment of the mast 10 and the storage rollers 11,12 being made simultaneously. The return pulleys 24, 25 are fixed on the mast, for example at the junction between the longitudinal rod and each lateral arm, their axis of rotation being oriented in a direction perpendicular to the mast. The first pulley 21 is engaged via cables on the return pulleys 24, 25 and then on the drive pulleys 22, 23. The drive pulleys are directly fixed on the bent ends of the storage rollers and their axes of rotation. are respectively oriented in the same direction as the longitudinal axes of the hollow guides and are therefore inclined angularly with respect to the longitudinal rod of the mast. For example, when the longitudinal axes of the respective hollow guides of each lateral arm of the mast form an angle of 45 ° relative to the longitudinal rod of the mast and relative to the respective axes of revolution of the storage rollers, the axis of rotation of the each drive pulley also has an angle equal to 45 °, relative to the axis of revolution of the corresponding storage roller and relative to the longitudinal rod of the mast.
    Although only one return pulley is visible in the various figures, for each storage roller to be deployed, two return pulleys, diametrically opposed on the mast, are necessary to have a closed cable way, starting from the fixed pulley until to the drive pulley via a first deflection pulley and then returning from the drive pulley to the fixed pulley via the second deflection pulley. In Figures 3b, 3c, 3d, the cable path is shown in solid lines on the visible face of the deployable structure, and in dashed lines on the opposite face which is hidden. For each storage roll, it is possible to use a single cable or two different cables, back and forth, to complete the complete path. Two different cable trays are necessary to deploy the two storage rolls 11, 12, the first pulley 21 being common to the two cable trays respectively dedicated to the two storage rolls.
    Each storage roll 11, 12 supports a flexible solar generator 30 which, in the stored position, is wrapped around the respective storage roll. Each flexible solar generator conventionally comprises a flexible support on which solar cells are mounted. The flexible support of each flexible solar generator comprises a first end capable of being wound around said storage roll and a second end end rigidly attached to a fixed rigid anchor 33. Advantageously, according to a first embodiment corresponding to FIGS. 3b, 3c, 3d, and FIGS. 4a and 4b, the rigid anchor 33 can be arranged diametrically opposite with respect to the face 40 of the body 41 of the satellite and the deployable structure may further comprise a rigid flap 31 fixed to the rigid anchor 33, in the extension of the flexible solar generator 30, the rigid flap being equipped with solar cells. In this case, in the stored position, the flexible substrate is completely wrapped around the storage roll while the rigid flap remains deployed permanently. As shown in FIG. 4a, the rigid flap 31 has a rear face oriented towards the face 40 of the body 41 of the satellite and a front face permanently oriented towards the outside of the satellite, the front face of the rigid flap 31 being equipped with solar cells 32, permanently oriented towards the Sun, during all the stored and deployed phases of the deployable structure. FIG. 4b illustrates, in dotted lines, the direction of deployment of a flexible solar generator 30 when the deployable structure further comprises a rigid flap 31 fixed in the extension of a corresponding flexible solar generator.
    According to an alternative embodiment of the invention, as shown in FIG. 5a, the longitudinal rod of the mast 10 may comprise two distinct parts 201, 202. The two distinct parts consist of a first longitudinal rod 201 fixed between the two ends mast and a second longitudinal rod 202 articulated on an axis of rotation 51 located at the second end of the mast. The second rod is parallel to the first rod and the axis of rotation 51 is perpendicular to the first and second rods of the mast. The two lateral arms 103, 104, angularly inclined and arranged symmetrically with respect to the mast, are secured to the second rod 202. In this embodiment of the invention, the solar generator does not have a rigid flap, but for the set of solar generators can provide energy during all the stored and deployed phases of the deployable structure, the rigid anchor 33 can be positioned facing the face 40 of the body 41 of the satellite as shown in Figure 5b and each Flexible solar generator 30 may, in the stored position, be partially wound around the storage roll 11, 12 and have an end portion 35 partially unwound and provided with solar cells permanently oriented towards the sun.
    FIG. 5c illustrates, in dotted lines, the direction of deployment of a flexible solar generator according to this variant embodiment of the invention, in which the solar generator does not comprise a rigid flap. The partially unwound end portion 35, or respectively, the rigid flap 31, provides the necessary energy to the satellite during the ballistic phase where the satellite is placed in orbit, and also contributes, together with flexible solar generators, to the supply of the satellite with electrical energy during the orbital phase of the satellite.
    This deployment system allows a simultaneous deployment of the mast 10 and the two rollers 11, 12 using a single motor 20 mounted at the base 102 of the mast. Different successive deployment sequences, concerning the simplified case where a single roller is mounted on a mast which has only one longitudinal rod 101, are illustrated in FIGS. 3a, 3b, 3c, 3d. When two storage rollers are mounted on the mast, the two rollers are deployed simultaneously and symmetrically with respect to the mast. In the stored position, as represented in FIG. 2, the storage rollers 11, 12 on which solar generators are wound, are arranged with their respective longitudinal axis parallel to the rod of the mast and are locked, in the stored position, on stacking feet 58 attached to a satellite face. The rigid solar panels 31 with solar cells 32 facing outwards, are also locked on dedicated stacking feet 59, fixed on the face 40 of the satellite.
    The triggering of deployment of the deployable structure begins with the unlocking of the rigid solar panels 31, then the rollers 11, 12 as shown in Figure 3b, and then by the operation of the rotor of the motor 20 located at the base of the mast. When the rotor of the motor 20 is actuated in rotation about its axis of rotation 50, it drives the mast 10 in rotation, which causes a winding of the cable 26 around the first pulley 21. The winding of the cable causes a voltage at a level of a return pulley 25 which rotates and transmits this tension to the drive pulley 23 which is also rotated. The axis of rotation of the drive pulley being integral with the bent end forming the pivot 13, 14 of the storage rollers 11, 12, the rotation of the drive pulley then triggers the rotation of the storage rollers which deploying. The driving of the mast by the rotor of the motor 20 thus causes, by means of the pulleys, the simultaneous deployment of the rollers 11, 12. To pass from the stored position to the deployed position, the mast 10 undergoes a rotation of 90 ° around the axis of rotation 50 of the motor rotor 20. During this rotation of the mast, to be correctly oriented, each storage roller 11, 12 must rotate 180 ° about the axis 55, 56 of the pivot 13 , 14 oriented at 45 ° and the drive pulley must rotate 180 °. For this, each drive pulley 22, 23 must have a winding diameter less than half the winding diameter the first pulley 21 at the base of the mast. When the mast and the rollers are in the deployed position, the mast and the rollers are locked in this position and the deployment of the flexible generators is realized. The deployment of each solar generator can be carried out in a known manner, autonomously, for example by means of one or more meter-ribbons fixed on a flexible fabric supporting the flexible solar generators.
    FIGS. 6a, 6b, 6c illustrate different deployment sequences in the embodiment variant where two storage rollers 11, 12 are mounted on the mast 10 and where the mast comprises two longitudinal rods 201, 202. In the stored position, the second Rod 202 of the mast, equipped with two lateral arms 103, 104 on which are articulated the two storage rollers, is folded against the first rod 201, the lateral arms being oriented towards the base 102 of the mast. In order to ensure the deployment of the two rods 201,202 of the mast and the storage rollers 11, 12, outward and return cables are fixed on the first pulley 21 located at the base of the mast, which is fixed relative to the body of the satellite , and on a second pulley 61 mounted on the second longitudinal rod. In addition, return cables are fixed on the drive pulleys 22, 23 of the rollers and on return pulleys 24, 25, 63 mounted on the lateral arms and on the first rod of the mast. The deployment principle is similar to that described with reference to FIGS. 3a, 3b, 3c, 3d. Actuation of the motor 20 at the base 102 of the mast rotates the first rod of the mast, which causes the synchronized deployment of the entire deployable structure, including the second longitudinal rod of the mast, through system of cables and pulleys.
    As shown in FIG. 7, a satellite equipped with at least one deployable structure according to the invention, comprising two solar generators wound around two respective rollers 11, 12, can be arranged in a narrow rocket cap. It is also possible, to balance the box 41 of the satellite, to arrange two deployable structures, 70, 71 according to the invention, on two opposite faces 40, 72 of the satellite box. Deployable structures are, of course, respectively associated with a dedicated deployment system.
    Although the invention has been described in connection with particular embodiments, it is obvious that it is not limited thereto and that it includes all the technical equivalents of the means described and their combinations if they are within the scope of the invention. In particular, the number and location of the different return pulleys is not limited to the examples specifically described.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Deployable structure comprising a set of solar generators, the deployable structure having a mast (10) away and two storage rollers (11, 12) each supporting a flexible solar generator (30), the two storage rolls (11). , 12) being articulated on the mast (10), the mast (10) having a first end (102) called a base, a second end opposite the base and comprising at least one longitudinal rod (101) situated between the first and the second end, characterized in that the mast (10) further comprises two lateral arms (103, 104) mounted at the second end, the two lateral arms being inclined angularly in two opposite directions and symmetrical with respect to the rod (101) longitudinal, each lateral arm (103, 104) having an end provided with a hollow guide (105, 106), and in that each storage roller (11, 12) has a longitudinal axis (54) having one end bend forming a pivot (13, 14) respectively articulated inside the hollow guide (105, 106) of a corresponding lateral arm, the pivot (13, 14) of each storage roller having an axis of revolution (55) different from the longitudinal axis (54) of the corresponding storage roll (11, 12).
    [2" id="c-fr-0002]
    2. Deployable structure according to claim 1, characterized in that the two lateral arms (103, 104) of the mast (10) are secured to the rod (101) longitudinal.
    [3" id="c-fr-0003]
    3. Deployable structure according to claim 1, characterized in that the rod (101) comprises two distinct longitudinal parts, respectively called first rod and second rod, the second rod (202) being parallel to the first rod (201) and articulated on an axis of rotation (51) located at the second end of the mast, the axis of rotation (51) being perpendicular to the first and the second rod (201, 202), the two lateral arms (103, 104) being secured to the second rod (202).
    [4" id="c-fr-0004]
    4. Deployable structure according to claim 2, characterized in that each flexible solar generator (30) has an end end rigidly attached to a respective rigid anchor (33), and in that it further comprises at least one rigid flap (31) fixed to the rigid anchor (33), in the extension of a flexible solar generator (30), the rigid flap (31) having solar cells permanently oriented towards the Sun.
    [5" id="c-fr-0005]
    5. Deployable structure according to claim 3, characterized in that, in the stored position, each flexible solar generator (30) is partially wound around the storage roller (11, 12), and has an end portion (35) provided with solar cells permanently oriented towards the Sun.
    [6" id="c-fr-0006]
    6. Deployable structure according to one of claims 4 or 5, characterized in that the hollow guides of each side arm (103, 104) of the mast (10) are oriented at 45 ° relative to the mast (10) and relative to the respective longitudinal axes (54) of the storage rollers (11, 12).
    [7" id="c-fr-0007]
    7. Deployment system comprising a deployable structure according to one of claims 1 to 6, characterized in that it further comprises a single motor (20) having a rotor mounted on the base (102) of the mast (10), the rotor having an axis of rotation (50) perpendicular to the longitudinal rod (101) of the mast, a first pulley (21) located at the base of the mast and having an axis of revolution aligned with the axis of rotation (50) of the rotor, two driving pulleys (22, 23) of the storage rollers (11, 12), in rotation, respectively fixed to the bent ends of each storage roller, return pulleys (24, 25) fixed on the lateral arms of the mast and a set of cables (26) connecting the first pulley (21) to the drive pulleys (22, 23) of each storage roller through the return pulleys (24, 25), the pulleys drive having a respective axis of rotation coinciding with a longitudinal axis of the guides cre ux (105,106) respectively.
    [8" id="c-fr-0008]
    8. Deployment system according to claim 7, characterized in that each drive pulley (22, 23) of a storage roll (11, 12) has an axis of rotation at an angle of 45 ° to the longitudinal axis of the corresponding storage roller and with respect to the longitudinal rod (101) of the mast (10).
    [9" id="c-fr-0009]
    9. Satellite, characterized in that it comprises at least one deployment system according to one of the preceding claims.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3044639B1|2018-01-05|
    US20170158358A1|2017-06-08|
    JP2017100714A|2017-06-08|
    EP3176095B1|2019-01-30|
    CA2950105A1|2017-06-02|
    EP3176095A1|2017-06-07|
    JP6854632B2|2021-04-07|
    US10214302B2|2019-02-26|
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    法律状态:
    2016-11-28| PLFP| Fee payment|Year of fee payment: 2 |
    2017-06-09| PLSC| Search report ready|Effective date: 20170609 |
    2017-11-27| PLFP| Fee payment|Year of fee payment: 3 |
    2019-11-28| PLFP| Fee payment|Year of fee payment: 5 |
    2021-09-10| ST| Notification of lapse|Effective date: 20210806 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1502511|2015-12-02|
    FR1502511A|FR3044639B1|2015-12-02|2015-12-02|DEPLOYABLE STRUCTURE COMPRISING A SET OF SOLAR GENERATORS, SYSTEM FOR DEPLOYING SUCH A DEPLOYABLE STRUCTURE AND SATELLITE COMPRISING SUCH A SYSTEM|FR1502511A| FR3044639B1|2015-12-02|2015-12-02|DEPLOYABLE STRUCTURE COMPRISING A SET OF SOLAR GENERATORS, SYSTEM FOR DEPLOYING SUCH A DEPLOYABLE STRUCTURE AND SATELLITE COMPRISING SUCH A SYSTEM|
    US15/364,008| US10214302B2|2015-12-02|2016-11-29|Deployable structure comprising a set of solar generators, system for deploying such a deployable structure and satellite comprising such a system|
    CA2950105A| CA2950105A1|2015-12-02|2016-11-30|Deployable structure comprising a set of solar generators, system for deploying such a deployable structure and satellite comprising such a system|
    JP2016233835A| JP6854632B2|2015-12-02|2016-12-01|Deployable structures containing a set of photovoltaic devices, systems deploying such deployable structures, and artificial satellites containing such systems.|
    EP16201613.3A| EP3176095B1|2015-12-02|2016-12-01|Deployable structure comprising a set of solar generators, system for deploying such a deployable structure and satellite comprising such a system|
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