• 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 present invention relates to a deployable assembly (30) comprising a support structure (25), a set (20) of panels (21, 22), each of the panels (21, 22) being connected to the adjacent panel by a hinge defining an axis intermediate rotation device, adapted to pass from a stored configuration in which the panels (21, 22) are folded over each other in an expanded configuration, by rotation of the panels (21, 22) about the respective intermediate axes of rotation, wherein the panels are disposed substantially in the same plane, a hinge device (26) defining a major axis of rotation of the assembly (20) of panels (21, 22) relative to the carrier structure (25). According to the invention, the assembly (20) of panels (21, 22) is rotatable about the intermediate axes of rotation and the main axis of rotation to move from the stored configuration to the deployed configuration and the assembly (20) of panels (21, 22) is only rotatable about the main axis of rotation in the deployed configuration so as to orient the assembly (20) of panels (21, 22) with respect to the supporting structure ( 25).
    公开号:FR3041608A1
    申请号:FR1501981
    申请日:2015-09-25
    公开日:2017-03-31
    发明作者:Julien Ducarne；Julien Grave；Xavier Reutenauer
    申请人:Thales SA；
    IPC主号:
    专利说明:

    DEPLOYABLE ASSEMBLY
    The present invention relates to a deployable assembly comprising a supporting structure and a set of panels, for example a satellite and a solar generator composed of several solar panels. It applies in particular to the field of space equipment that must be deployed in orbit and more particularly to space equipment for satellites, such as solar generators. Nevertheless, the deployable assembly according to the invention can be applied to any other field where it is necessary to articulate one or more panels with respect to an object. The panel can be rigid or flexible.
    A solar generator consists of deployable and adjustable solar panels. A solar panel is a technological energy device consisting of solar photovoltaic collectors intended to convert solar radiation into electrical energy. On a satellite, the solar generator makes it possible to ensure the supply of electrical energy and to operate the equipment on board. A solar generator can be mounted on a satellite requiring a precise pointing, as is the case for a high resolution observation satellite. Solar panels may have undesired low-frequency vibration modes because they disturb the control of the line of sight. An observation satellite often points to the Earth. On the other hand, solar panels do not always see the sun, which poses a problem of supply of energy. To counter this problem, it is possible to mount more solar panels on the satellite, but this solution has the disadvantage of a surplus of mass and space, especially when launching the satellite which is contained under the cap of the rocket.
    There are satellites that can be oriented according to their activity phase. In the observation phase, the satellite is completely oriented towards the terrestrial ground, a reduced solar flux arrives on the solar generator. In energy storage phase, the satellite is oriented so that its solar panels are oriented optimally towards the sun, that is to say with the surface normal to the rays. Nevertheless, when the satellite passes over its station on the ground, it reorients itself towards it to transfer to it the information of its mission. It is therefore difficult to reconcile the observation mission with energy recharge.
    In addition, the satellite turns its back to the sun and the telescope looks at the cold space at a temperature of about 3 Kelvin, instead of looking towards the Earth while being in an environment at a temperature of about 10 to 30 ° C . These situations complicate the regulation and thermal design of the telescope.
    Moreover, when the satellite is back to the sun, the telescope cavity is sometimes facing the 'relative wind' related to the orbital speed. Particles of this environment can erode or deform the internal components of the cavity. Over the required life of the telescope, it is possible to make the telescope robust to such environmental constraints, but this means a higher requirement of telescope quality, thereby implying additional costs.
    Some satellites have two hinge arms. One of the arms is in the plane of the solar panels and allows the deployment of solar panels from the configuration stored on the satellite to the deployed configuration. The second arm is motorized and can direct the generator to the sun, the second arm ending for example by two branches, the arm is connected to the satellite, the two branches are connected to the solar generator. The arm allows a 360 ° rotation of the solar generator. Thus, it is possible for the satellite to orient itself so as to point completely towards the ground and to direct its solar generator towards the sun to ensure the supply of energy. But this solution requires the presence of two joints between the satellite and the solar generator: the joint dedicated to the deployment of solar panels and the joint dedicated to the orientation of the solar generator. This configuration is not optimal for the stiffness of the solar generator. The imaging must be done very precisely. The satellite must be able to change its attitude, sometimes quickly, with good stability and high pointing accuracy. The presence of two joints between the satellite and the solar generator generates a problem of damping. Indeed, during the change of attitude of the satellite, the solar generator can then be subjected to a first bending mode excited by the operation of the satellite but not controlled by the motorized arm ensuring the orientation of the solar generator. The vibrations then make the stabilization of the pointing difficult. The invention aims to overcome all or part of the problems mentioned above by proposing a deployable assembly with a single articulation, that is to say without a second orientation arm, to gain rigidity and control better the vibration. To this end, the subject of the invention is a deployable assembly comprising: a supporting structure, a set of panels, each of the panels being connected to the adjacent panel by a hinge defining an intermediate axis of rotation, capable of passing from a stored configuration in which the panels are folded over each other in an expanded configuration, by rotating the panels about the respective intermediate axes of rotation, wherein the panels are arranged substantially in the same plane, • a hinge device defining a main axis of rotation of the panel assembly relative to the supporting structure, characterized in that the panel assembly is rotatable about the intermediate axes of rotation and the main axis of rotation to move from the stored configuration to the deployed configuration and in that the set of panels is only rotatable around the main axis of rotation in deployed configuration so as to orient the set of panels relative to the supporting structure.
    According to one embodiment, each of the panels having edges, the main axis of rotation is on a first edge of a first of the panels and the intermediate axes of rotation are on non-adjacent edges.
    According to another embodiment, the main axis of rotation and the intermediate axes of rotation are parallel axes.
    According to another embodiment, the main axis of rotation being on a first edge of a first panel, the hinge device comprises two bearings on the first edge of the first panel so as to make the moving panel assembly in rotation around the main axis of rotation.
    According to another embodiment, the hinge device comprises a first bearing on the first edge of the first panel, the hinge device comprises a control device comprising a geared motor coupled to the first bearing for orienting the panel assembly, and the control device comprises at least one damper coupling the geared motor and the first bearing.
    According to another embodiment, the deployable assembly comprises a sensor capable of determining the position of the panel assembly, and it comprises a servo-control of the geared motor as a function of the position of the panel assembly around the main axis of rotation.
    According to another embodiment, the hinge device comprises a second bearing on the first edge of the first, and the control device comprises a prestressing means associated with the second bearing to prevent any play in the first and second bearings .
    According to a particular embodiment, the panels of the deployable assembly are solar panels and the carrier structure is a satellite. The invention will be better understood and other advantages will appear on reading the detailed description of an embodiment given by way of example, a description illustrated by the attached drawing in which: FIG. 1 schematically represents a set of expandable and orientable panels according to the prior art, • Figure 2 schematically shows a set of expandable and orientable panels according to the invention, • Figure 3 shows a device for articulating a set of panels relative to a supporting structure FIG. 4 schematically represents a servo-control loop of a gearmotor as a function of the position of the panel assembly, according to the invention; FIG. 5 represents various successive positions around the Earth of a satellite d observation according to the invention.
    For the sake of clarity, the same elements will bear the same references in the different figures. The invention is described in the field of space equipment, in the case where the panels are solar panels forming a solar generator and the carrier structure is a satellite. It is obvious that the invention can be applied to any other field in which a set of panels is connected to a carrier structure to form a deployable assembly, for example a set of telecommunication antenna panels.
    In this application, it is a question of a set of panels, each of the panels being connected to the adjacent panel by a hinge defining an intermediate axis of rotation, able to pass from a stored configuration in which the panels are folded over each other. other in an expanded configuration, by rotation of the panels about the respective intermediate axes of rotation, wherein the panels are disposed substantially in the same plane. The set of panels is connected to a supporting structure along an edge of one of the panels, called the first panel, by a main link defining a main axis of rotation. And each panel is connected along one of its edges to its neighboring panel by an intermediate link defining an intermediate axis of rotation. Each panel is rotatable about its intermediate link and the set of panels is rotatable about its main link. In stored configuration, the panels are folded over each other and are stacked at one side of the supporting structure. The stored configuration allows the storage of all the panels, especially during the orbit of the satellite when it is stored under the rocket cap, in a small space. In deployed configuration, the panels are arranged substantially in the same plane. To move from the stored configuration to the deployed configuration, the first panel rotated around the main link and each of the panels rotated about its intermediate link. The deployed configuration corresponds to the operational configuration of the set of panels. In other words, it is in deployed configuration that the set of panels is oriented according to the needs of the satellite. The set of panels in deployed configuration is oriented towards the sun when there is a need to convert solar radiation into electrical energy. While remaining in deployed configuration, this orientation is caused to be modified to maintain optimal orientation of the solar panels relative to the sun especially when the satellite moves in its orbit. The deployed configuration can also be called the operational configuration. In other words, in the deployed configuration the panels fulfill the function for which they are intended: the solar collectors provide electrical energy, the antenna panels receive or emit electromagnetic radiation ... In the stored configuration, the panels are stored against each other, for example in the launch phase of the satellite to allow them to take place in the cap of a launcher.
    Moreover, in the context of an application in the field of space equipment, the panels can be rigid or flexible. In the case of a flexible panel, it is possible to have a set of panels comprising for example at least one tape measure supporting a flexible membrane. The flexible membrane corresponds to a panel. In this example, the invention is to be understood analogously. The stored configuration in which the panels are folded over each other and stacked at one face of the supporting structure is to be understood as a configuration in which the tape measure and the panel, i.e. the flexible membrane, are wrapped around a mandrel and stored at one side of the supporting structure. And similarly, to move from the stored configuration to the deployed configuration, the first panel rotates around the main link. In other words, the flexible membrane passes in deployed configuration by deployment of the tape measure by rotating about the mandrel.
    Figure 1 shows schematically a set of panels 10, 12 deployable and orientable according to the prior art. In this example, only two panels 11 and 12 are shown. It is obvious that the assembly 10 may also include one or more other panels. The assembly 10 comprises an intermediate connection defining an intermediate axis of rotation 13 of the panel 12 relative to the first panel 11. The assembly 10 of panels is connected to a supporting structure 9, shown diagrammatically in dashed lines in the figure, by an arm 14 extending to the assembly 10 of panels by two arms 15, 16. The arms 15, 16 are connected to the first edge 17 of the first panel 11. The arm 14 is connected to a control device 18 which allows orient the assembly of panels towards the sun. The arm 14 associated with the control device 18 allows 360 ° rotation of the panel assembly 10. Thus, it is possible for the satellite to orient itself so as to point completely towards the ground and to orient the assembly of panels 11, 12 towards the sun to ensure the supply of energy. According to the prior art, there is therefore a hinge dedicated to the deployment of the panels and a hinge dedicated to the orientation of the assembly 10 of panels 11, 12. This configuration is not optimal for the stiffness of the assembly. 10 of panels. In fact, when the satellite changes its attitude, it is necessary to have a high pointing accuracy at the level of the onboard telescope. The presence of two joints between the satellite and the panel assembly generates a damping problem. Indeed, during the change of attitude of the satellite, the set of panels can then be subjected to a first bending mode, symbolized by the arrow 19, excited by the maneuver of the satellite but not controlled by the motorized arm 14 ensuring the orientation of the panel assembly.
    Figure 2 schematically shows a deployable assembly 30 according to the invention. The deployable assembly 30 comprises a support structure 25, a set of panels 21, 22 deployable and orientable. In this example, only two panels 21 and 22 are shown. It is obvious that the assembly 20 may also include one or more other panels. The assembly 20 comprises an intermediate link defining an intermediate axis of rotation 23 of the panel 22 relative to the first panel 21. The assembly 20 comprises a main link defining a main axis of rotation 24 of the panel 21 relative to the supporting structure 25 represented in dashed lines in the figure. Each of the panels 21, 22 is connected to the adjacent panel by a hinge defining the intermediate axis of rotation 23. The assembly 20 is able to pass from a stored configuration in which the panels 21, 22 are folded over each other to an expanded configuration, by rotation of the panels 21, 22 about the respective intermediate axes of rotation, in which the panels 21, 22 are arranged substantially in the same plane. The deployable assembly 30 comprises a hinge device 26 defining the main axis of rotation 24 of the assembly 20 of panels 21, 22 with respect to the supporting structure 25. According to the invention, the assembly 20 of panels 21 , 22 is rotatable about the intermediate axes of rotation 23 and the main axis of rotation 24 to move from the stored configuration to the deployed configuration and the assembly 20 of panels 21, 22 is only rotatable around the main axis of rotation 24 in deployed configuration so as to orient the assembly 20 of panels 21, 22 with respect to the carrier structure 25. It is therefore in deployed configuration, that is to say in operational configuration, that the assembly 20 of panels 21, 22 is orientable along the main axis of rotation 24. As explained above, during the attitude change of the satellite, the assembly 20 of panels 21, 22 may be subjected to a bending mode, symbolized in this figure by the arrow 27, excited by the operation of the satellite but is, thanks to the invention, controlled by the hinge device 26 ensuring the orientation of the assembly 20 of panels 21, 22.
    As already mentioned, the invention is not limited to a deployable assembly 30 comprising a set of panels 20 comprising two panels 21, 22. Each of the panels has edges, and the main axis of rotation is on a first edge. a first panel and the intermediate axes of rotation are advantageously on non-adjacent edges. This is particularly the case with rectangular panels, as shown in Figure 2, but this is true for any polygonal panel of degree greater than or equal to 4, that is to say, to 4 or more edges.
    Advantageously, and as shown in FIG. 2, the main axis of rotation 24 and the intermediate axes of rotation 23 are parallel axes. This is true for rectangular panels, but the main axis of rotation 24 and the intermediate axes of rotation 23 can also be parallel for panels of pentagonal, hexagonal, octagonal, and so on.
    As shown in FIG. 2, the articulation device can comprise two bearings 28, 29 on the first edge of the first panel 21 so as to make the assembly 20 of panels 21, 22 mobile in rotation about the main axis of rotation 24.
    FIG. 3 shows in more detail an example of a hinge device 26 of an assembly 20 of panels 21, 22 with respect to the supporting structure 25. The hinge device 26 may comprise a first bearing 28 on the first edge of the first panel 21. The articulation device 26 may comprise a control device 31 comprising a geared motor 32 coupled to the first bearing 28 intended to orient the assembly 20 of panels 21, 22. The control device 31 comprises at least one damper 33 coupling the gearmotor 32 and the first bearing 28. The damper 33 is intended to introduce a passive damping in the link between the geared motor 32 and the first bearing 28. In other words, the damper 33 serves to limit or eliminate the vibrations present at the geared motor when it directs all 30 panels through the first bearing 28. The damper 33 can be for example u no piece of flexible material such as rubber or plastic to damp vibrations of small amplitude, a spring or preferably a viscoelastic insert.
    According to a preferred embodiment, the articulation device 26 may comprise a second bearing 29 on the first edge of the first panel 21, and the control device 31 may comprise a prestressing means 34 associated with the second bearing 29 making it possible to avoid any play in the first and second bearings 28, 29. The prestressing means 34 constitutes an anti-backlash system by tensioning the articulation device 26 and the assembly 20 of panels 21, 22. The prestressing means can prestress the damper 33 and thus improves the control of the assembly 20 of panels 21,22.
    FIG. 4 schematically represents a servo-control loop 40 of the gearmotor 32 as a function of the position of the assembly 20 of panels 21, 22 around the main axis of rotation, according to the invention. The deployable assembly 30 comprises a sensor 41, visible in FIG. 3, able to determine the position of the assembly 20 of panels 21, 22. The deployable assembly 30 comprises a servocontrol of the gearmotor 32 as a function of the position of the 20 set of panels 21, 22. A setpoint 42 is transmitted to the geared motor 32 to guide the assembly 20 panels. The sensor 42 determines the position of the panel assembly 20. The information 43 of the position of the panel assembly 20 is transmitted to a comparator 44 which compares the information 43 with the instruction 42. If the information 43 is different from the instruction 42, the comparator 44 transmits a correction 45 to the geared motor so as to correct the orientation of the panel assembly. Thus, thanks to the servo loop, a precise orientation of the assembly of panels 20 is ensured. The sensor 41 may for example be an optical sensor which determines the position of the panel assembly 21, 22. The sensor 41 may also be a force sensor which determines, from the perceived force, the position of the sensor. This control loop may also advantageously receive a set of instructions developed by the attitude control system of the satellite itself, which comprises other sensors. In other words, it is possible to envisage the servo loop 40 as being a sub-loop of the satellite attitude and orbit control system.
    Figure 5 shows different successive positions around the Earth of a satellite 50 according to the invention. In other words, the carrier structure is the satellite 50. The deployable structure comprises an assembly 20 of panels 51, 52, 53, 54, each of the panels being connected to the adjacent panel by a hinge defining an intermediate axis of rotation, and the assembly of panels is only rotatable about the main axis of rotation in deployed configuration so as to orient the set of panels relative to the satellite 50. It may be noted in passing that the invention applies to a set of panels comprising more than two panels as shown in FIG. 5. The panel assembly 20 may comprise so-called main panels such as panels 51 and 52 and so-called secondary panels 53, 54, connected to one or more main panels by a connection intermediate. On the same principle, other panels can also be connected to the secondary panels, so as to form any possible configuration of the set of panels.
    FIG. 5 represents a satellite 50 on an observation mission around the Earth that must both point towards the ground to make one or more images of the Earth or download data to a station positioned on the ground and correctly orient the planet. 20 panels to the sun so as to charge the battery efficiently to operate the equipment aboard the satellite 50. With the invention, in a trajectory from the South Pole to the North Pole, we see that the satellite 50 points always towards the Earth, which makes it possible to realize the mission of observation as wished. And according to the position of the satellite 50 around the Earth and therefore according to its orientation relative to the sun, the set of panels is rotatable about the main axis of rotation in deployed configuration. Thus, the assembly of panels 20 is orientable relative to the support structure and oriented optimally to capture the solar flux. As the orientation of the set of solar panels is optimal, it is not necessary to provide too many. Thus, the satellite 50 can perform its observation mission without suffering a penalty of mass and congestion due to the solar panels.
    Thus, the satellite can always point to the Earth and the set of panels can be oriented towards the sun to provide the energy requirement and operate the onboard hardware on board the satellite. The invention therefore has the advantage of responding to both the pointing constraints towards the ground for the observation mission and the effective orientation of the set of panels towards the sun to charge the battery efficiently without mass penalty. since it is not necessary to provide too many solar panels.
    In general, the attitude of the satellite is determined by one or more stellar followers, better known under the English terminology "star tracker", optical device that measures the position of stars by photocells or cameras and which allows to deduce the attitude of the satellite. These optical devices can not look through the panels, which is problematic when the satellite is equipped with a large number of panel assemblies. The invention also solves this problem since it allows, as explained above, a saving of space due to a limited number of panels sets.
    In addition, as the satellite has only one main link for the orientation of the set of panels, control of the satellite is not penalized. Indeed, each additional connection between the supporting structure and the panels represents an additional weak point in terms of vibration mode. In the presence of several connections, it is necessary to dampen the modes of the panel assembly with mechanical systems adding a mass constraint, additional manufacturing cost and complexity of use. The invention solves this problem thanks to its articulation device of all the panels. The first bending mode is controlled by the hinge device which controls the vibration through the control device. If there is vibration in the panel assembly, the controller may send the command to the gearmotor to dampen the vibrations.
    Furthermore, the spacing between the first and the second bearing along the first edge of the first panel increases the stiffness of the panel assembly through a better rigidity and allows better frequency control.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    1. Deployable assembly (30) comprising: • a supporting structure (25, 50), • a set (20) of panels (21, 22; 51, 52, 53, 54), each of the panels (21, 22; , 52, 53, 54) being connected to the adjacent panel by a hinge defining an intermediate axis of rotation, adapted to pass from a stored configuration in which the panels (21, 22; 51, 52, 53, 54) are folded over. on each other in an expanded configuration, by rotation of the panels (21, 22; 51, 52, 53, 54) about the respective intermediate axes of rotation, in which the panels are arranged substantially in the same plane; articulation (26) defining a principal axis of rotation of the assembly (20) of panels (21, 22; 51, 52, 53, 54) relative to the supporting structure (25, 50), characterized in that assembly (20) of panels (21, 22; 51, 52, 53, 54) is rotatable about the intermediate axes of rotation and the main axis of rotation. otation to switch from the stored configuration to the deployed configuration and in that the assembly (20) of panels (21, 22; 51, 52, 53, 54) is only rotatable about the main axis of rotation in the extended configuration so as to orient the assembly (20) of panels (21, 22; 51, 52, 53, 54) by relative to the supporting structure (25, 50).
    [2" id="c-fr-0002]
    2. Deployable assembly (30) according to claim 1, each of the panels (21, 22; 51, 52, 53, 54) having edges, characterized in that the main axis of rotation is on a first edge of a first (21, 51) panels and that the intermediate axes of rotation are on non-adjacent edges.
    [3" id="c-fr-0003]
    3. Deployable assembly (30) according to any one of the preceding claims, characterized in that the main axis of rotation and the intermediate axes of rotation are parallel axes.
    [4" id="c-fr-0004]
    4. Deployable assembly (30) according to any one of the preceding claims, the main axis of rotation being on a first edge of a first (21, 51) of the panels, characterized in that the hinge device (26) ) comprises two bearings (28, 29) on the first edge of the first panel (21, 51) so as to rotate the movable panel assembly (20) about the main axis of rotation.
    [5" id="c-fr-0005]
    5. Deployable assembly (30) according to any one of the preceding claims, the main axis of rotation being on a first edge of a first (21, 51) panels, characterized in that the hinge device (26) ) comprises a first bearing (28) on the first edge of the first panel (21, 51), in that the hinge device (26) comprises a control device (31) comprising a geared motor (32) coupled to the first bearing (28) for orienting the assembly (20, 50) of panels, and in that the control device (31) comprises at least one damper (33) coupling the geared motor (32) and the first bearing (28).
    [6" id="c-fr-0006]
    6. Deployable assembly (30) according to the preceding claim, characterized in that it comprises a sensor (41) adapted to determine the position of the assembly (20) of panels, and in that it comprises a servo motor gearbox (32) depending on the position of the assembly (20) of panels around the main axis of rotation.
    [7" id="c-fr-0007]
    7. Deployable assembly (30) according to any one of claims 5 or 6, characterized in that the articulation device (26) comprises a second bearing (29) on the first edge of the first panel (21, 51), and in that the control device (31) comprises prestressing means (34) associated with the second bearing (29) to prevent any play in the first and second bearings (28, 29).
    [8" id="c-fr-0008]
    8. Deployable assembly (30) according to any one of the preceding claims, characterized in that the panels (21, 22; 51, 52, 53, 54) are solar panels and in that the carrier structure (25, 50 ) is a satellite.
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    同族专利:
    公开号 | 公开日
    EP3147223B1|2020-10-21|
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    FR3023264B1|2014-07-04|2017-11-24|Thales Sa|SATELLITE A MASTER VARIABLE COUPLE|CN109941462A|2017-12-20|2019-06-28|中国电子科技集团公司第四十八研究所|Mounting structure and installation method suitable near space aerostatics flexible photovoltaic component|
    CN112298610A|2020-09-30|2021-02-02|北京空间飞行器总体设计部|Solar wing and sectional type secondary unfolding hinge thereof|
    CN112623280A|2021-01-04|2021-04-09|上海宇航系统工程研究所|Two-degree-of-freedom solar cell array unfolding device|
    法律状态:
    2016-08-26| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-31| PLSC| Publication of the preliminary search report|Effective date: 20170331 |
    2017-08-29| PLFP| Fee payment|Year of fee payment: 3 |
    2018-08-28| PLFP| Fee payment|Year of fee payment: 4 |
    2019-08-29| PLFP| Fee payment|Year of fee payment: 5 |
    2020-08-26| PLFP| Fee payment|Year of fee payment: 6 |
    2021-08-26| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1501981A|FR3041608B1|2015-09-25|2015-09-25|DEPLOYABLE ASSEMBLY|FR1501981A| FR3041608B1|2015-09-25|2015-09-25|DEPLOYABLE ASSEMBLY|
    US15/263,068| US10207823B2|2015-09-25|2016-09-12|Deployable assembly|
    EP16188438.2A| EP3147223B1|2015-09-25|2016-09-13|Deployable assembly|
    KR1020160122294A| KR20170037551A|2015-09-25|2016-09-23|Deployable assembly|
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