• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
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    • 专利摘要:
    The invention relates to a structure (1) expandable deployable spontaneous, comprising at least two adjacent panels (2) hinged together, each panel having a non-flat surface at rest, the structure being adapted to be placed in a folded position in wherein the panels are folded over each other and held flat by compression and elastic deformation of their curvature or in an extended position in which the panels are aligned edge-to-edge on their adjoining edges and extending the extension of each other . A flexible connection (7) connecting the adjacent edges of the panels comprises at least one first traction link (4) holding the panels edge-to-edge in the deployed position, at least one second compression link (5) adapted to be plated on the faces external panels and having a length adapted so that the compression link remains energized as elastic deformation of the panels remains. The flexible link (7) further comprises at least one alignment link (6) adapted to prevent lateral displacement of the panels relative to each other. The deployable structure is adapted to form solar panels and / or antennas for satellites in space, particularly for microsatellites.
    公开号:FR3059304A1
    申请号:FR1661572
    申请日:2016-11-28
    公开日:2018-06-01
    发明作者:Christophe Casteras
    申请人:Centre National dEtudes Spatiales CNES；
    IPC主号:
    专利说明:

    Holder (s): NATIONAL CENTER FOR SPATIAL STUDIES CNES Public establishment.
    Extension request (s)
    Agent (s): CABINET BARRE LAFORGUE & ASSOCIES.
    (54) DEPLOYABLE STRUCTURE WITH SPONTANEOUS DEPLOYMENT.
    FR 3 059 304 - A1 (b /) The invention relates to a deployable structure (1) which can be deployed spontaneously, comprising at least two adjacent panels (2) hinged together, each panel having a non-planar surface at rest, the structure being adapted to be placed in a folded position in which the panels are folded over each other and held flat by compression and elastic deformation of their curvature or in a deployed position in which the panels are aligned edge to edge on their adjoining edges and extending the extension of each other. A flexible link (7) connecting the adjoining edges of the panels comprises at least a first traction link (4) keeping the panels edge to edge in the deployed position, at least one second compression link (5) adapted to be pressed on the faces external of the panels and having a suitable length so that the compression link remains under tension as long as an elastic deformation of the panels remains. The flexible link (7) further comprises at least one alignment link (6) adapted to prevent lateral movement of the panels relative to each other. The deployable structure is suitable for forming solar panels and / or antennas for satellites in space, particularly for microsatellites.
    i
    DEPLOYABLE STRUCTURE WITH SPONTANEOUS DEPLOYMENT
    The invention relates to a deployable structure, spontaneous deployment, consisting of panels hinged together. In particular, the invention relates to such a structure that can be used to form antennas or photovoltaic panels, for example in space, on board satellites, or even display panels which can be deployed on earth.
    In the space sector, it is often necessary to make use of large-scale structures, for example to form antennas or photovoltaic panels intended to supply a satellite with electrical energy. However, these structures must support the accelerations of launching and putting into orbit and are generally folded up in a compact form at the time of launching. Once in orbit, it is necessary to be able to deploy them and maintain them in the deployed position.
    There is known (EP 0 360 694) a structure comprising a plurality of panels connected to each other by hinges and articulated two by two to allow folding in accordion. These panels have a natural curvature at rest, said curvature being flattened by clamping means maintaining an elastic prestress when the panel is folded. Once in space, this structure is unfolded by means of external motor elements, for example by motorization means associated with the hinges (torsion springs) or even with a cable system. Once deployed, the panels then resume their natural arched shape which allows automatic locking in the deployed position. However, in such a structure, these deployment means represent a non-negligible mass and cost which it is useful to minimize.
    The present invention therefore aims to provide a deployable structure which does not have the drawbacks of the prior art. In particular, the present invention relates to such a structure capable of deploying at least partially spontaneously once the clamping means are inactivated in the folded position.
    The invention also aims to improve the reliability and precision of the connection between the panels of the structure.
    The invention further aims to provide a connection between the panels of the structure which has a reduced mass and a minimum size in particular in the direction of the thickness of the panels.
    The invention also aims to provide a deployable structure which has great flexibility and good resistance to mechanical stresses, both in tension or compression along the longitudinal axis of the structure once deployed and in stresses along axes forming an angle not zero with this longitudinal axis.
    Finally, the invention aims to provide a deployable structure which is simple and economical to manufacture and to implement.
    To do this, the invention relates to a deployable structure with spontaneous deployment, comprising at least two adjacent panels hinged together, adapted to deploy along a deployment axis, each panel having:
    a non-planar surface at rest, delimited by a non-rectilinear edge at rest, inscribed in a plane orthogonal to the deployment axis, parallel to an adjoining edge of the adjacent panel, each edge admitting at all points a tangent plane common to the surface of the two adjacent panels, a flexible connection connecting the adjoining edges of said panels, said structure being adapted to be able to be placed:
    in a folded position in which the panels are folded over one another so as to have facing main faces, called internal faces, the panels being held flat by compression and elastic deformation of their curvature, and
    - in a deployed position in which the panels are aligned edge to edge on their adjoining edges and extend in line with one another,
    - said flexible connection comprising at least a first link, known as a traction link, suitable for connecting at least one point the internal faces of the two adjacent panels in the folded position, and for keeping said adjacent panels edge to edge in the deployed position, characterized in that said flexible connection comprises at least one second link, called compression link, of a length suitable for, in the folded position, to be pressed against main faces, said external faces, opposite the internal faces of two adjacent panels, said link being adapted to remain under tension as long as an elastic deformation of the curvature of the panels remains.
    In the present text, the inner face of a panel therefore denotes the face of the panel which is opposite the face of the adjacent panel when the two panels are folded against one another by rotation around the flexible connection between the two panels. Similarly, the outside face of a panel denotes the face of the panel which is outside a set of two panels folded against each other. The concept of internal face (respectively external face) is thus a relative concept depending on the connection considered between panels and on their folding mode. In an accordion folding of three rectangular panels, one face of the median panel which has a flexible connection at each end may be an internal face with respect to one of its connections if the panel adjacent to this connection folds over this face and simultaneously an external face with respect to the other of its connections if the panel adjacent to this connection folds up on the opposite face.
    The deployment axis is also defined (between two adjacent panels) as an axis substantially orthogonal to the axis of articulation or folding between these two panels, in a plane parallel to the mean plane of the two panels in the deployed position. The axis of deployment between two adjacent panels can be parallel to a general direction of deployment of the structure when the latter is for example formed of rectangular panels, but each axis of deployment between two consecutive panels can deviate from this general direction deployment in the case of triangular or trapezoidal panels arranged alternately or the general direction of deployment may not be rectilinear when the panels are arranged so as to form a polygonal surface.
    In an advantageous embodiment, the adjacent panels have a non-planar adjusted surface whose generatrices are parallel to each other and parallel to the deployment axis.
    In this simpler version of the structure, each panel can have a single curvature and be in the form of a tile comprising a concave face and a convex face. As a variant, each panel may have a plurality of curvatures of parallel axes, the curvatures generating on a same face of the panel a succession of concave and convex zones, the panel then being in the form of corrugated sheet. In this variant, each panel can store, at equal width, a greater amount of elastic deformation energy for a smaller panel thickness. For the simplicity of the description, this will be done by taking for example panels with a single curvature having a concave face and a convex face, the panels with multiple curvatures being able to be deduced therefrom by means of a simple juxtaposition.
    Thus, when the structure comprises a plurality of panels having a curvature at rest such that the concave faces of all the panels are on the same side of the structure when the latter is deployed, when the structure is folded in accordion, two panels consecutive can be folded concave face against concave face, the concave faces thus forming the internal faces with regard to the connection between these two panels, or else convex face against convex face by folding the same connection in the opposite direction, the convex faces then forming the internal faces and the concave faces becoming the external faces.
    Thanks to each traction link which connects the internal faces of the panels, when these deploy, the panels are held edge to edge and a traction force can be transmitted from one panel to another without causing play between panels. A pull link has the function of pulling the panels towards each other in the deployed position. However, a tensile link can be subjected to a tearing force during the deployment of the structure if the edges of the panels tend to separate from one another under the effect of the elastic deformation of them. this.
    In the folded position, each compression link, the length of which is substantially equal to that of the traction links plus the sum of the thicknesses of the adjacent panels that it connects, has the effect of pressing the internal faces of the panels one against the other and to contribute to the elastic deformation of the curvature of the panels. The stresses of deformation of the panels are then supported by the tensile strength of each compression link and not by its possible assembly on the external face of the panel. Consequently, the reliability of the flexible connection is improved.
    The panels are then held in the folded position by clamping means such as latches, hooks, polymer links (which can be cut by a thermal knife to allow the deployment of the structure) or pyrotechnic devices such as bolts explosives crossing the thicknesses of the panels folded over each other, in particular in accordion (leporello). When the clamping means of the panels in the folded position are inactive (relaxed) and allow the panels to deploy, the compression link (s) which remain under tension as long as the potential energy of elastic deformation of the panels is non-zero, cooperate with the panels which are returned to their initial arched shape by exerting a torque tending to open the panels on either side of the connection towards the deployed position.
    Consequently, the deployment of the panels is at least partially assisted by the torque exerted by the compression links, until the potential elastic energy of deformation of the panels has dissipated and / or until the deployed position be reached.
    According to certain embodiments of the invention, at least one - in particular each - compression link is placed in a zone chosen to generate a non-zero elastic deformation force - in particular maximum - of the panels in the folded position. Such an area corresponds to that which would have a non-zero spacing - in particular maximum - between the panels in the folded position if they were superimposed without being flattened or deformed by the flexible connection. By preferentially placing the compression links in the zone or zones where the elastic deformation energy of the panels is not zero, and in particular where it is maximum, the deployment torque exerted by the compression links is non-zero and in particular maximum. These zones are preferably the lateral ends of the panels if these are arranged so that their facing internal faces are the convex faces or the middle part of the edge of the panel if the panels are arranged so that their internal faces are facing are the concave faces of the panels.
    In certain embodiments of the invention, each traction link is placed in an area where the elastic deformation force generated between two adjacent panels by their flattening in the folded position is minimal. Thus, during the deployment of the structure, the forces associated with the dissipation of the elastic energy stored in the panels are minimized in this area and the reliability of the traction link is increased. In addition, the traction links are preferably placed in such a way that the tensile forces which they undergo make it possible to ensure optimum support with respect in particular to the bending moments applied to the structure deployed around the main axes of inertia thereof.
    In certain embodiments of the invention, the flexible link also comprises at least one third link, called alignment link, comprising at least two flexible bands (flexible in bending) non-extensible (rigid in traction) juxtaposed fixed respectively and alternately between the external face and the internal face of two adjacent panels. With each alignment link, two adjacent panels connected by a flexible link are held substantially in the extension of one another, in particular in a direction normal to the surface of the panels in the vicinity of the alignment link. Likewise, the alignment link makes it possible to improve the lateral retention of the panels relative to one another, for example in a direction corresponding to an instantaneous axis of rotation of one panel relative to the other. To this end, a first strip of the alignment link is fixed on the external face of the first of the two panels, passes between the two panels, along an edge of the first panel opposite a corresponding edge of the adjacent panel to then be fixed on the internal face of the second panel. The second strip is fixed to the internal face of the first panel, passes along the edge of the latter and is then fixed to the external face of the second panel. The two strips are preferably juxtaposed so as to minimize misalignments at the joint. Of course, the alignment link can comprise more than two bands, the essential being that these bands are arranged alternately on the internal and external faces and intersect between the opposite edges of the two panels. The alignment links thus make it possible to best take up the cutting forces applied to the structure which could misalign the panels.
    In certain embodiments of the invention, the links comprise at least one strip of flexible material in flexion and not extensible in traction fixed on the corresponding faces of the panels. These links forming the flexible link - in particular the compression links and the traction links can be produced in various ways, for example with a plurality of plates or rods connected by hinges (one for the traction link and three for the link compression). However, advantageously, the most reliable and economical solution consists in fixing one or more strips of flexible non-extensible material on the internal faces to form the traction links and on the external faces to form the compression links. The material used for these bands is chosen to be relatively inextensible, that is to say that the Young's modulus of the material is such that the elongation of the bands is negligible relative to their length under the effect of the forces applied. , in particular for the compression links which support the elastic deformation forces of the panels. Likewise, this material is chosen to be flexible enough in bending to allow the folding and deployment of the panels. These strips can be fixed to the faces of the panels by gluing, bolting or riveting or any other fixing means.
    In certain embodiments of the invention, the flexible, non-extensible bands are metal bands. Alternatively or in combination, the flexible non-stretchy strips are made of mineral fiber fabric coated with flexible resin. For example, the flexible strips can be made of laminated stainless steel or of glass fiber, carbon or aramid fabric impregnated with a flexible resin or any other material meeting the requirements for flexibility and deformation of the flexible connection to obtain, for example a resin based on silicones, natural or synthetic rubber, elastomers, in particular fluoropolymers, etc.
    In certain embodiments of the invention, at least a portion of the non-extensible flexible strips are formed by an extension of the corresponding faces of the panels, that is to say in one piece with the panels. For example, when the panels are made of composite material comprising bundles of reinforcing fibers impregnated with a material such as a resin, it is possible to form the ties by using the same skein of reinforcing fibers to cover at least one part of two adjacent panels. Consequently, the link thus formed is naturally integral with the two panels between which it is arranged, which minimizes the manufacturing operations and improves reliability by eliminating parts and additional operations for fixing independent links between the panels.
    In certain embodiments of the invention, two adjacent panels are connected by at least three groups of links placed in the middle and at the ends of the opposite edges of said panels, each group of links comprising at least one traction link or one link of compression associated with at least one alignment link. Preferably, each group of links comprises the three types of link (traction, compression and alignment) in at least one copy of each. Various variants can be envisaged depending on the direction in which the panels are folded together: for example if the panels are folded concave face against concave face, the group of links placed in the middle part may include three compression links on the convex face, separated by two alignment links and one to three traction links on the other side, opposite the compression links. Each group of links placed at the ends may include a traction link closest to the ends, an alignment link and a compression link, in this order towards the middle part of the panels.
    The invention also relates to a deployable structure characterized in combination by all or some of the characteristics mentioned above or below.
    Other objects, characteristics and advantages of the invention will become apparent from the description which follows and from the appended drawings in which:
    - Figure 1 shows a schematic perspective view of a portion of structure according to the invention, in the deployed position;
    - Figures 2A, 2B and 2C are schematic side views respectively of the compression, traction and alignment links of a structure according to the invention, in the folded position and in the deployed position;
    - Figure 3 is a schematic sectional view of a structure according to the invention showing the position of the links on a series of at least three panels;
    - Figure 4 shows an example of deployable structure according to the invention in which the axis of deployment between two consecutive panels is not parallel to a general direction of rectilinear deployment of the structure; and
    - Figure 5 shows an example of deployable structure according to the invention in which a general direction of deployment of the structure is not straight.
    FIG. 1 represents a deployable structure 1, represented in the deployed state, comprising at least two panels 2 adjacent to each other by their edge 10. In the example shown, the panels 2 have at rest a regulated surface non-planar whose generatrices are parallel to each other and also parallel to a deployment axis 3 of the two panels considered so that the surfaces of the main faces are in line with one another ίο in their deployed position. The deployment axis 3 coincides with a general deployment direction 12 in this example. The panels 2 may have one or more curvatures with an axis parallel to the deployment axis and for example be in the form of a tile for a single curvature as shown in FIG. 1 or in the form of corrugated sheet for alternative curvatures ...
    In the example of FIG. 1, the panels 2 are arranged edge to edge, their convex face 8 and their concave face 9 being respectively placed on the same side of the structure. The panels 2 are connected to each other by a flexible link 7 allowing them to be folded against each other by rotation along a folding axis 11, in particular but not exclusively orthogonal to the general direction of deployment 12. The folding of the panels 2 around the folding axis 11 can be carried out in two directions of rotation. In a first direction of rotation around a folding axis 11 between two adjacent panels, the concave faces 9 of the two adjacent panels are pressed against each other and are designated as internal faces 21 (relative to the connection 7 flexible considered) while the convex faces 8 are turned outwards and are therefore designated as external faces 22. Symmetrically, in a second direction of rotation around the folding axis 11, opposite to the first direction of rotation, the faces convex 8 of two adjacent panels are pressed against each other and thus become the internal faces 21 (always with respect to the flexible connection 7 considered) while the concave faces 9 become the external faces 22.
    Thus, if the structure 1 comprises at least three panels 2 folded in accordion, as shown in FIG. 3, any panel comprising a flexible connection 7a and 7b at each of its ends has a face (for example the convex face 8) which is both an external face 22a with respect to the flexible connection 7a and an internal face 21b with respect to the flexible connection 7b. Similarly, the opposite face of this panel (here the concave face 9) is simultaneously an internal face 21a with respect to the flexible connection 7a and an external face 22b with respect to the flexible connection 7b.
    The flexible connection 7 consists of a plurality of links whose ends are respectively fixed to each panel 2, on either side of their adjoining edge 10.
    The flexible connection 7 comprises in particular at least one link, called the traction link 4, shown in FIG. 2A in the folded position of the panels 2 to the left of the drawing and in the deployed position of the panels to the right of the drawing. Note that in the drawings of FIGS. 2A to 2C, the space between the internal faces 21 of the panels 2 in the folded position and between the edges 10 of the panels in the deployed position has been exaggerated for a better understanding of the drawing.
    The traction link 4 consists of a strip of flexible material in flexion and not extensible in traction, such as for example a metallic strip or a strip of composite material comprising a fabric of mineral or synthetic fibers, for example metallic fibers (whiskers ), glass fibers, carbon fibers, aramid fibers, etc. embedded in a resin matrix, preferably a flexible resin or any other material meeting the requirements for flexibility and deformation of the flexible bond to be obtained, for example a resin based on silicones, natural or synthetic rubber, elastomers, especially fluoropolymers, etc. The traction link 4 comprises two attachment tabs 42 respectively fixed on the internal faces of two adjacent panels, the attachment tabs being connected together by a flexible part 41 forming the articulation between the panels. The position of the tabs 42 for attachment and the length of the flexible part 41 are such that in the deployed position, the two adjacent panels are held edge to edge. In particular, the fastening tabs 42 can be fixed respectively, for example by gluing, to the edge 10 of each of the two panels, the flexible part 41 between the two fastening tabs being of a length just sufficient to allow the rotation of the two panels around an axis of rotation substantially coincident with the angle formed by the edge 10 and the internal face 21 of the two panels, with the necessary play necessary for this rotation.
    In a particular embodiment, the traction link 4 can be constituted by a same bundle of fibers forming the internal face 21 of the two panels and extending continuously between the two panels. Thus, the attachment tabs 42 form an integral part of the surface of the internal face 21 of the two panels, the flexible part 41 being protected from coating with resin when the panels are produced so as to retain its flexibility.
    Preferably, the traction link 4 is placed in an area where the elastic deformation force generated between the two adjacent panels by their flattening in the folded position is minimal. Indeed, when the means which hold the two panels pressed against one another are released, the internal faces 21 of these panels tend to move away from one another as a function of the position of the curvature Signs. For example, if the internal faces of the panels are the concave faces 9, the internal faces tend to deviate more in the middle of the facing edges of the adjacent panels than at their ends. Conversely, if the internal faces are convex faces 8, the elastic deformation force is minimal in the middle of the edge of the panels. Consequently, by placing the traction link 4 in an area where the elastic deformation force is minimal, the tearing force exerted on the attachment tabs 42 is also minimal, which contributes to the reliability of the fixing the fastening tabs 42 on the internal face 21 of the panels.
    The flexible connection 7 also comprises at least one link, called the compression link 5, shown in FIG. 2B in the folded position of the panels 2 to the left of the drawing and in the deployed position of the panels to the right of the drawing. Like the traction link 4, the compression link 5 consists of a strip of flexible material in bending and not extensible in traction, for example in the same materials, and comprises two attachment tabs 52 connected by a flexible part 51.
    Unlike the traction link 4, the attachment tabs 52 are fixed on the external faces 22 of two adjacent panels 2. The flexible part 51 has a length corresponding to twice the thickness of a panel 2, so that in the folded position, the flexible part 51 maintains the internal faces 21 of the two adjacent panels pressed against one another . Thus, when two adjacent non-planar adjacent panels are folded against each other connected by a compression link 5, the flexible part 51 is under tension under the effect of the elastic deformation force of the two panels. Thanks to this tension of the flexible part 51, when the two panels are no longer held pressed against one another, a tensile force is exerted on the external faces 22 of the two panels 2, resulting, in combination with the traction link 4, by a torque aimed at deploying the two panels. This tension of the flexible part 51 of the compression link 5 is maintained substantially throughout the time that an elastic deformation of the curvature of the panels remains. When the panels 2 are deployed, they are held edge to edge by the traction link 4 and the compression link 5 forms a loop at its flexible part 51. It should be noted that advantageously, the attachment tabs 52 of the link compression 5 are only subjected to a force while the panels are folded and this force results in a shear stress on the joint between the fastening tabs and the panel, which makes assembly by gluing particularly advantageous.
    Therefore, in order to maximize the torque exerted by each compression link 5, it is preferable to place them in a chosen area to generate a non-zero, and in particular maximum, elastic deformation force between the panels in the folded position. . Thus, the compression links will preferably be placed in the middle of the edges opposite the adjacent panels when they are folded up concave face against concave face and vice versa at the end of the edges of the panels when they are folded up convex face against convex face. .
    As seen above, the flexible connection 7 comprises at least one traction link 4 which keeps the panels 2 edge to edge in the deployed position and at least one compression link 5 which exerts a deployment torque on the panels 2 when they do not are no longer held flat against each other.
    The connection 7 further comprises at least one third link, said alignment link 6, formed of at least two juxtaposed bands 6a and 6b fixed respectively and alternately between the external face 22 and the internal face 21 of two adjacent panels. Such an alignment link 6 is shown in FIG. 2C and comprises a first strip 6a of flexible material in flexion and not extensible in traction, for example made of the same materials as the traction links 4 or compression links 5. The first strip 6a has two attachment tabs 62a separated by a flexible part 61a. One of the fastening tabs 62a is fixed on the internal face 21 of a first panel 2 while the other fastening tab 62a is fixed on the external face 22 of a second panel adjacent to the first. The alignment link 6 comprises a second strip 6b, juxtaposed with the first strip 6a, and also comprises two attachment tabs 62b separated by a flexible part 61b. The second strip 6b is also fixed alternately between the external face 22 of the first panel 2 and the internal face 21 of the second panel adjacent to the first. The flexible parts 61a and 61b therefore cross opposite the edge of the two facing panels. These two flexible parts are not fixed to the panels, which allows the panels to rotate one opposite the other. However, thanks to the juxtaposition of the two strips 6a and 6b, any lateral movement of the panels relative to each other is greatly limited. Therefore thanks to the alignment link 6, the panels are held laterally one opposite the other along their edges.
    In a preferred embodiment of the deployable structure 1, the panels 2 are connected two by two by flexible connections 7. Each of these flexible links 7 comprises at least three groups of links, each group of links comprising at least one traction link 4 or a compression link 5 associated with at least one alignment link 6. The groups of links are preferably placed in the middle and at the ends of the edges 10 facing the panels. Thus, as shown in Figure 1, the two panels 2 shown in solid lines are connected by their edges 10 opposite by a flexible connection 7. This flexible connection 7 and adapted to allow the folding of the two panels so that their concave faces 9 are internal faces 21 for the flexible connection considered. A first group of links comprises two compression links 5 fixed on the convex face 8 of the panels 2 (which is the external face 22 of these panels), these compression links being located on either side of the longitudinal median axis panels and two alignment links 6 placed on either side of the compression links 5. This first group of links is completed by two other groups of links each comprising a traction link 4 placed at the lateral ends of the edge 10 of the panels 2. Inside the traction links 4, towards the middle of the edges 10, each group is completed by at least one alignment link 6 (not shown in FIG. 1 for reasons of clarity of the drawing). Of course, depending on the width of the panels 2, it can be envisaged to place more than three groups of links, at regular intervals along the edge 10 of the panels. Likewise, each group of links can consist of traction links 4 and compression links 5 associated with each other, for example the traction link can be placed on the internal faces of the panels, just below a link of compression 5.
    The flexible connection 7 may extend over the entire width of the panel or only over a fraction thereof. In particular, when the deployment forces or the forces applied to the structure are low (for example for satellites in micro gravity) and we want to minimize the mass added by the links, the ratio between the width of the flexible link and the width of the panels can be from 1 to 30. On the other hand, in the presence of greater efforts, it is preferable that the links forming the flexible connection extend over the entire width of the panel.
    Preferably, for large forces, the flexible connection covers 100% of the width of the panel with at least 25% occupied by traction links 4, 25% by compression links 5, the latter being able to overlap the traction links , and 50% by alignment links. The thickness of the links also depends on the forces they must resist and the materials in which they are made and generally varies between 0.1 and 1 times the thickness of the panel.
    In a variant of the deployable structure 1, it is possible that the deployment axes 3 between the panels 2 are not substantially parallel to the general direction of deployment 12. As shown in FIG. 4, the panels 2 can have a triangular shape or even trapezoidal with a folding axis 11 not perpendicular to the general direction of deployment 12. In this example, the deployment axes 3 have an alternately positive and negative angle around the general direction of deployment 12, so that a once deployed, the structure 1 has a generally rectilinear direction parallel to the general direction of deployment 12.
    It is also possible to design structures 1 which can be deployed in a non-rectilinear direction of deployment as shown for example in FIG. 5. In this example, panels 2 of triangular shape are articulated relative to each other by connections 7 flexible arranged to allow deployment of the panels in a substantially circular deployment direction. Such an arrangement thus makes it possible to produce structures suitable for forming, for example, satellite dishes.
    Of course, this description is given by way of illustrative example only and the person skilled in the art can make numerous modifications to it without departing from the scope of the invention, such as for example designing deployable structures of various shapes, for example in T shape, cube shape etc.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1 / - Deployable structure (1) for spontaneous deployment, comprising at least two adjacent panels (2) hinged together, adapted to deploy along a deployment axis (3), each panel having:
    a non-planar surface at rest, delimited by an edge (10) not rectilinear at rest, inscribed in a plane orthogonal to the deployment axis, parallel to an adjoining edge of the adjacent panel, each edge admitting at all points a common tangent plane on the surface of the two adjacent panels, a flexible connection (7) connecting the adjoining edges of said panels, said structure being adapted to be able to be placed:
    in a folded position in which the panels are folded over each other so as to have facing main faces, called internal faces (21), the panels being held flat by compression and elastic deformation of their curvature, and in a deployed position in which the panels are aligned edge to edge on their adjoining edges and extend in line with each other, said flexible connection comprising at least one first link, called traction link (4), suitable for connecting, in folded position, at at least one point the internal faces of two adjacent panels, and to maintain said panels edge to edge in the deployed position, characterized in that the flexible connection comprises at least one second link, called compression link (5), of a length suitable for, in the folded position, to be pressed against main faces, called external faces (22), opposite the internal faces of two adjacent panels, said compression link being adapted to remain under tension as long as an elastic deformation of the curvature of the panels remains.
    [2" id="c-fr-0002]
    2 / - Structure according to claim 1, characterized in that the adjacent panels (2) have a non-planar adjusted surface whose generatrices are parallel to each other and parallel to the deployment axis (3)
    [3" id="c-fr-0003]
    3 / - Structure according to any one of claims 1 or
    2, characterized in that at least one - in particular each - compression link (5) is placed in a zone chosen to generate a non-zero elastic deformation force - in particular maximum - of the panels in the folded position.
    [4" id="c-fr-0004]
    4 / - Structure according to any one of claims 1 to
    3, characterized in that each traction link (4) is placed in an area where the elastic deformation force generated between two adjacent panels by their flattening in the folded position is minimal.
    [5" id="c-fr-0005]
    5 / - Structure according to any one of claims 1 to
    4, characterized in that the flexible link (7) further comprises at least one third link, said alignment link (6), comprising at least two flexible bands (6a, 6b) flexible non-extensible juxtaposed fixed respectively and alternately between the external face (22) and the internal face (21) of two adjacent panels (2).
    [6" id="c-fr-0006]
    6 / - Structure according to any one of claims 1 to
    5, characterized in that the links comprise at least one strip of flexible material in flexion and not extensible in traction fixed on the corresponding faces of the panels.
    [7" id="c-fr-0007]
    7 / - Structure according to claim 6, characterized in that the flexible non-extensible bands are metal bands.
    [8" id="c-fr-0008]
    8 / - Structure according to claim 6, characterized in that the flexible non-extensible bands are made of mineral fiber fabric coated with flexible resin.
    [9" id="c-fr-0009]
    9 / - Structure according to any one of claims 6 to
    8, characterized in that at least a portion of the non-extensible flexible strips are formed by an extension of the corresponding faces of the panels.
    [10" id="c-fr-0010]
    10 / - Structure according to any one of claims 5 to
    9, characterized in that two adjacent panels (2) are connected by at least three groups of links (4, 5, 6) placed in the middle and at the ends of the edges (10) opposite said panels, each group of links comprising at at least one traction link (4) or a compression link (5) associated with at least one alignment link (6).
    1/2
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    同族专利:
    公开号 | 公开日
    FR3059304B1|2019-05-17|
    EP3326920A1|2018-05-30|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3386128A|1966-09-26|1968-06-04|Ryan Aeronautical Co|Self-actuating, self-locking hinge|
    EP0360694A1|1988-09-22|1990-03-28|AEROSPATIALE Société Nationale Industrielle|Articulated panel automatically locked in a deployed position, in particular for a satellite solar generator|
    US7354033B1|2006-08-01|2008-04-08|The United States Of America As Represented By The Secretary Of The Air Force|Tape-spring deployable hinge|
    EP3925894A1|2018-06-26|2021-12-22|Airbus Defence and Space SAS|A flexible radiative fin for a spacecraft|
    RU200445U1|2020-07-03|2020-10-26|Федеральное государственное бюджетное образовательное учреждение высшего образования "Рязанский государственный радиотехнический университет имени В.Ф. Уткина"|BINARY SPACE WITH A RECONFIGURABLE ANTENNA COMBINED WITH A SOLAR BATTERY DEPLOYABLE MULTIVECTOR MATRIX ROCKET ENGINES|
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    法律状态:
    2018-02-28| PLFP| Fee payment|Year of fee payment: 2 |
    2018-06-01| PLSC| Publication of the preliminary search report|Effective date: 20180601 |
    2019-11-29| PLFP| Fee payment|Year of fee payment: 4 |
    2020-11-30| PLFP| Fee payment|Year of fee payment: 5 |
    2021-11-30| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1661572|2016-11-28|
    FR1661572A|FR3059304B1|2016-11-28|2016-11-28|DEPLOYABLE STRUCTURE WITH SPONTANEOUS DEPLOYMENT|FR1661572A| FR3059304B1|2016-11-28|2016-11-28|DEPLOYABLE STRUCTURE WITH SPONTANEOUS DEPLOYMENT|
    EP17203917.4A| EP3326920A1|2016-11-28|2017-11-27|Deployable structure with spontaneous deployment|
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