• 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 object of the invention is a deployable satellite mast consisting of an inflatable tube (1) stored in accordion (1a) before deployment (1b) and deployable by filling the tube with a gas which comprises a device stiffening and deployment aid external to the mast, said device comprising one or more shrouds (2a, 2b) wound on a reel device (3, 31, 32, 33, 34) on the side of a first end and hung on the tube at one second from their ends, said stays taking place from the reel during deployment of the mast.
    公开号:FR3071822A1
    申请号:FR1759266
    申请日:2017-10-04
    公开日:2019-04-05
    发明作者:Alexis Villemain
    申请人:ArianeGroup SAS；
    IPC主号:
    专利说明:

    The present invention relates to structural supports for satellites of the mast type which can be deployed by inflation.
    Technological background
    A type of mast deployable by inflation is known in the space field. This mast is an inflatable tube folded in an accordion in a tetragonal pattern before deployment and cylindrical in shape after deployment. Such a mast supports a structure deployed when the satellite is stationary and can be stiffened after inflation as described in document FR 2876983 A1.
    Its deployment can also be controlled by an internal structure as described in document FR 2877315 A1.
    Such masts can be made from metallic films, composites and are unfolded thanks to the increase in pressure of a gas injected at their base. The pressure pushes on the upper face of the tube and allows the mast to lengthen until obtaining a cylindrical shape.
    They can be used in particular for carrying structures such as panels forming sails, for example desorbitation assistance panels as described in document FR3032183 A1.
    Brief description of the invention
    The present invention is in the context of the production of a mast supporting large structures such as solar panels. The solar panels of satellites must offer a surface of capture of important light which leads to important constraints at the level of a mast carrying them. Such a mast must therefore be stiffened and its deployment must be better controlled, in particular to guarantee correct and uniform deployment of the solar panels.
    In this context, the present invention provides a deployable mast for satellite consisting of an inflatable tube stored in an accordion before deployment and deployable by filling the tube with a gas characterized in that it comprises a stiffening device and aid for deployment external to the mast, said device comprising one or more guy wires wound on a reel device on the side of a first of their ends and hooked on the tube to a second of their ends, said guy lines unwinding from the reel during the mast deployment.
    The stiffening device may in particular comprise at least one pair of shrouds arranged at 180 ° relative to the a> e of the mast.
    According to a first embodiment, the shrouds of the pair of shrouds are wound on a single reel device.
    According to an alternative embodiment, the reel device comprises a reel per guy, the reels of a pair of guy lines.
    In this case, the reels can in particular be synchronized by a connecting cable arranged to take place from a first of the reels and wind in opposition on a second of the reels during the unwinding of the shrouds.
    Advantageously, at least some of the shrouds are fixed on the free end of the tube becoming the top of the mast after deployment.
    Alternatively or additionally, at least some of the shrouds are fixed on an intermediate part of the tube.
    The stiffening device can comprise at least two pairs of shrouds arranged in intersecting planes at the level of the axis of the mast and forming a non-zero angle between them.
    According to a particular embodiment, the shroud (s) are ropes whose composition comprises polymers which solidify by UV irradiation or ropes which can be stiffened by polymerization by the Joule effect.
    The reel (s) can also include a brake device for maintaining the tension of the shrouds when the mast is deployed.
    Advantageously, at the base of the mast, the shrouds can be kept apart from the mast by arms formed by fixed beams or foldable rods perpendicular or inclined relative to the mast.
    According to a particular embodiment, at least one spring is arranged either at the top of the shrouds or at the end of the shroud on the reel side or on both sides.
    Advantageously, flexible tabs pierced in the middle to let the cable pass can surround the cable.
    Brief description of the drawings
    Other characteristics and advantages of the invention will become apparent on reading the following description of nonlimiting examples of embodiment of the invention with reference to the drawings which represent:
    in Figure 1, a schematic representation of the deployment of a mast of the prior art;
    in FIGS. 2A to 2D, schematic examples in side view of embodiments of masts according to the invention;
    in Figures 3A and 3B, perspective views of exemplary embodiments of the invention;
    in FIGS. 4A to 4C, examples of embodiments of reel means of the invention;
    in Figures 5, 6 and 7, perspective views of reels applicable to the invention.
    in Figure 8, a particular embodiment of the mast.
    Detailed description of embodiments of the invention
    The present invention relates to structures that can be deployed on satellite and to a structure that can in particular support solar panels and adapted to withstand the stresses and deformations generated by these panels such as the stresses and deformations generated by the thermal environment and the satellite movements. It meets technical needs which are to help guide the mast during its deployment and to bring stiffness to the mast after deployment.
    It relates to a deployable mast 1 as shown diagrammatically in FIG. 1 and mainly consisting of an inflatable tube 10 stored in accordion 1a before deployment and deployable by filling the tube with gas in a sequence as shown, the deployed tube 1b forming a supporting structure.
    To assist the deployment of the tube and stiffen it, the invention provides shrouds external to the tube as shown in Figures 2A to 2C.
    The shrouds are flexible structures of the cable or wire type which can be made from different materials: metal, composite, polymers, etc.
    FIG. 2A represents a deployed mast provided with a pair of shrouds 21 which are fixed on the free end of the tube 10 becoming the top of the mast after deployment.
    FIG. 2B represents a deployed mast comprising a pair of guy wires 22 fixed on an intermediate part of the deployed tube.
    FIG. 2C represents a deployed mast comprising two pairs of shrouds 21, 22. A pair of guy lines 21 is attached to the top of the mast and a pair of guy lines 22 is attached to an intermediate portion of the deployed tube.
    In the example of FIGS. 2A to 2C, the lower part of the shrouds is fixed at a distance from the mast on fixed beams 51. In the example of FIG. 2D the lower part of the shrouds is kept apart from the mast by folding rods 52 possibly perpendicular to the mast and lower strands 23 of the shrouds serve to tension the shrouds.
    The stiffening and deployment aid device external to the mast of the invention comprises, according to FIGS. 4A to 4C, reels on which the shrouds are wound when the tube is stored folded and from which the shrouds are unwound during deployment of the mast.
    In the example of FIG. 4A, a single reel 33 receives two shrouds 21, 21 ′ of a pair of coplanar shrouds, pulleys 3a at the end of beams 50 guide the shrouds. The reel is for example as shown in FIG. 5. This reel is a triple reel which comprises a first cylinder 33a for winding a first shroud of a pair of shrouds, a second cylinder 33b for winding a second shroud of the pair of shrouds and, in this embodiment, of a third cylinder 33c receiving a cable internal to the tube and hooked to the free end of the tube and used to control the unwinding of the shrouds when the mast is deployed, l free end of the tube pulling on the internal cable. In this configuration, the diameter of the cylinders is adapted so that the unwinding of the shrouds is synchronized with the deployment of the mast.
    In the example of FIG. 4B, each guy of the pair of guys has a reel 32, 32 '. These reels are synchronized by a connecting cable 40 connecting them more particularly shown in FIG. 4C. This connecting cable 40 is unwound from a first reel, for example the reel 32 and is wound on the second reel, for example the reel 32 'during the deployment of the mast.
    The reels are produced according to the example of FIG. 6. They comprise a first cylinder 32a receiving the shroud 21, a second cylinder the connecting cable 40.
    The reel shown in Figure 7 is an example of reel receiving a head shroud 21 and a guy 22 hanging on an intermediate part of the mast. In this case, the cylinders receiving the shrouds are of a diameter adapted to maintain an identical tension for these shrouds during the deployment of the mast.
    The shrouds can be “flexible” cables of different metallic, composite, polymer, etc. materials. or stiffenable ropes such as or stiffenable ropes by polymerization by Joule effect after circulation of an electric current in the rope. Another embodiment can employ guy lines comprising a material which can be polymerized under UV. In the latter case, once unrolled and subjected to UV irradiation from the sun, the shrouds can stiffen and even better contribute to the erection of the mast.
    Still with a view to controlling the deployment of the mast, the reel (s) may include a brake device for maintaining the tension of the shrouds during the deployment of the mast.
    FIG. 3A describes in perspective an embodiment with two pairs of coplanar shrouds arranged at 180 ° relative to the axis of the mast.
    According to FIG. 3B, the stiffening device comprises four pairs of shrouds 21, 21 ', 22, 22' arranged two by two in intersecting planes at the level of the axis of the mast. In the example, by taking a plane P defined by the mast and a straight line A perpendicular to the mast, plane in which the solar panels are located, for example, the plane comprising a first pair of guy wires fixed to the top of the mast and a first pair guy lines fixed in the intermediate part of the mast made with the plane P at an angle a while the plane comprising the plane comprising the second pair of guy wires fixed at the top of the mast and the second pair of guy wires fixed in the middle part of the mast makes an angle B with plane P.
    According to the example of FIG. 9, to collect the thermal expansions of the shrouds according to their material, the thermal expansions of the mast in elongation, the floating of the stay opposite to the other which would work in traction a slight tension at the end of deployment without restricting the plasticization by inflation of the mast of the springs added either at the top of the shrouds, such that the spring 71 is at the end of the shroud such that the spring 72 on the reel side is on both sides. The springs can be of the coil spring type or of the elastic cable type in the upper part of the shroud, on the other hand in the lower part of the shroud, as the spring is initially wound on the reel, a spring of the elastic cable type then acting after the complete unwinding guy lines will be preferred.
    In the case where a central cable is positioned inside the tube, a way must be found to prevent the cable from hitting the mast wall after deployment. It is in this case possible to position, as shown in FIG. 8, flexible tongues 61, 62, for example in kapton, drilled in the middle to let the cable pass. These tabs which surround the cable can in particular be glued between the folds of the mast according to item 63.
    The invention therefore proposes a guying of the mast which brings stiffness to the mast in flexion and traction after deployment and a synchronized unwinding of the guy wires which provides assistance in guiding the mast during deployment of the mast.
    权利要求:
    Claims (13)
    [1" id="c-fr-0001]
    1 - Deployable mast for satellite consisting of an inflatable tube (1) stored in accordion (1a) before deployment (1b) and deployable by filling the tube with a gas characterized in that it comprises a stiffening device and aid for deployment external to the mast, said device comprising one or more guy lines (2a, 2b) wound on a reel device (3, 31, 32, 33, 34) on the side of a first of their ends and hung on the tube at one second from their ends, said shrouds unwinding from the reel when the mast is deployed.
    [2" id="c-fr-0002]
    2 - deployable mast according to claim 1 for which the stiffening device comprises at least one pair of shrouds arranged at 180 ° relative to the axis of the mast.
    [3" id="c-fr-0003]
    3 - Deployable mast according to claim 2 for which the shrouds of the pair of shrouds are wound on a single reel device (33).
    [4" id="c-fr-0004]
    4 - Deployable mast according to claim 2 for which the reel device comprises a reel (32, 32 ') by shroud, the reels of a pair of shrouds being synchronized by a connecting cable (40) arranged to take place from a first (32) reels and wind in opposition on a second (32 ') reels during the unwinding of the shrouds.
    [5" id="c-fr-0005]
    5 - Deployable mast according to any one of the preceding claims for which at least some of the shrouds (2a) are fixed on the free end of the tube becoming the top of the mast after deployment.
    [6" id="c-fr-0006]
    6 - Deployable mast according to any one of the preceding claims for which at least some of the shrouds (2b) are fixed on an intermediate part of the tube.
    [7" id="c-fr-0007]
    7 - Deployable mast according to any one of the preceding claims, in which the stiffening device comprises at least two pairs of shrouds (21, 22, 21 ', 22') arranged in intersecting planes at the level of the axis of the mast.
    [8" id="c-fr-0008]
    8 - Deployable mast according to any one of the preceding claims for which the shroud (s) are ropes whose composition comprises polymers which solidify by UV irradiation or ropes which can be stiffened by polymerization by Joule effect.
    [9" id="c-fr-0009]
    9 - Deployable mast according to claim 3 or 4 for which the reel or reels comprise a brake device for maintaining the tension of the shrouds during
    5 of the mast deployment.
    [10" id="c-fr-0010]
    10- deployable mast according to any one of the preceding claims for which at the base of the mast, the shrouds are kept apart from the mast by arms (50) formed by fixed beams (51) or foldable rods (52) perpendicular or inclined to the mast.
    10
    [11" id="c-fr-0011]
    11- deployable mast according to any one of the preceding claims for which at least one spring (71,72) is disposed either at the top of the shrouds (71) or at the end of the shroud side of the reel (72) or on both sides.
    [12" id="c-fr-0012]
    12- deployable mast according to any one of the preceding claims for which flexible tongues (61, 62) pierced in the middle
    [13" id="c-fr-0013]
    15 to pass the cable surround the cable.
    类似技术:
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    FR3109368A1|2021-10-22|DRONE CHASSIS
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    同族专利:
    公开号 | 公开日
    FR3071822B1|2020-11-27|
    EP3645400A1|2020-05-06|
    US20200247564A1|2020-08-06|
    WO2019068649A1|2019-04-11|
    EP3645400B1|2021-08-11|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3606719A|1968-07-12|1971-09-21|Fairchild Hiller Corp|Erectable structures|
    JPH03197300A|1989-12-26|1991-08-28|Mitsubishi Electric Corp|Expanding structure for space|
    US20040194397A1|2001-02-21|2004-10-07|Brown Michael A.|Elongated truss boom structures for space applications|
    WO2006136675A1|2005-06-22|2006-12-28|Astrium Sas|Deployable light structure capable of being rigidified after being deployed, method for making same, and use thereof for equipping a space craft|
    US20090260301A1|2008-04-22|2009-10-22|Prueitt Melvin L|Compressed-Air Rigid Building Blocks|CN111509358A|2020-04-30|2020-08-07|燕山大学|Single-degree-of-freedom panel antenna folding and unfolding unit and panel antenna folding and unfolding mechanism|
    CN111987456A|2020-07-24|2020-11-24|南京理工大学|Integrated low-profile UV antenna for micro-nano satellite|FR2876983B1|2004-10-22|2007-02-16|Eads Space Transp Sa Sa|RIGIDIFICATION OF INFLATABLE DEPLOYMENT STRUCTURES ESPECIALLY FOR SPATIAL USE|
    FR2877315B1|2004-10-29|2007-02-02|Eads Space Transp Sas Soc Par|DEVICE FOR CONTROLLING THE DEPLOYMENT OF INFLATABLE STRUCTURES|
    FR3032183B1|2015-02-03|2018-06-22|Arianegroup Sas|AEROPREINING SYSTEM FOR SATELLITE DESORBITATION|CN110844120A|2019-11-26|2020-02-28|北京航天长征飞行器研究所|Large-scale rigidization space inflation expansion rod piece and sail hanging structure|
    法律状态:
    2018-10-31| PLFP| Fee payment|Year of fee payment: 2 |
    2019-04-05| PLSC| Publication of the preliminary search report|Effective date: 20190405 |
    2019-10-28| PLFP| Fee payment|Year of fee payment: 3 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 4 |
    2021-10-21| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1759266A|FR3071822B1|2017-10-04|2017-10-04|DEPLOYABLE SATELLITE MAT|
    FR1759266|2017-10-04|FR1759266A| FR3071822B1|2017-10-04|2017-10-04|DEPLOYABLE SATELLITE MAT|
    US16/652,893| US20200247564A1|2017-10-04|2018-10-01|Deployable satellite mast|
    EP18783406.4A| EP3645400B1|2017-10-04|2018-10-01|Deployable satellite mast|
    PCT/EP2018/076664| WO2019068649A1|2017-10-04|2018-10-01|Deployable satellite mast|
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