• 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 invention relates to an autonomously deployable deployable mast having at least one elementary structural block (10) having a longitudinal deployment axis X, the elementary structural block comprising two platforms respectively lower (13) and upper (12) parallel to a plane YZ orthogonal to the axis X and N stages stacked one above the other parallel to the axis X, where N is greater than 1 and where i is between 1 and N-1. Each stage (Ei) comprises at least six flexible longitudinal linking arms (11) articulated by tape-meters, which in the deployed position are in planes parallel to the X axis and are inclined with respect to the X axis, the N stages being fixed between them two by two through connecting platforms (15) parallel to the YZ plane; two contiguous lower and upper stages (Ei, Ei + 1) are angularly offset relative to one another by a rotation about the deployment axis X.
    公开号:FR3025498A1
    申请号:FR1401992
    申请日:2014-09-05
    公开日:2016-03-11
    发明作者:Yannick Baudasse；Stephane Vezain；Robin Lacroix；Francois Guinot
    申请人:Thales SA；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a deployable mast with autonomous spontaneous deployment and a satellite comprising at least one such mast. 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 sensors or antennas or instruments with long focal lengths such as telescopes for example. A deployable mast for connecting two spacecraft spaced a distance of several meters is generally composed of a plurality of mast segments stacked one above the other, articulated between them and whose deployment is motorized. Each mast segment is generally composed of several rigid beams articulated by hinges and locked by bolts. This type of mast has the disadvantage of requiring the use of an engine for deployment and presents a significant mass problem and reliability of the joints. In addition, the beams being rigid, the mast occupies, 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 the mast when it is in the stored position, so as to optimize the surface in the deployed position. Thus, the mast must have a ratio of the deployed length / stacked volume as high as possible while ensuring a low mass, stability and rigidity of the mast in the deployed position sufficiently high to be compatible space applications.
    [0002] The object of the invention is to provide a deployable mast not having the disadvantages of existing deployable masts, having the advantage of being compact, lightweight, simple to perform, having an optimization of the mast volume when stored under a launcher cap, enabling reliable long-orbit deployment and control of deployment without the use of an engine and allowing rigidity and stability of the mast when deployed.
    [0003] For this, the invention relates to a deployable self-expanding mast having at least one elementary structural block having a longitudinal deployment axis X, the elementary structural block having two platforms respectively lower and upper 5 parallel to a plane YZ orthogonal to the axis X and N stages stacked one above the other parallel to the longitudinal deployment axis X, where N is greater than 1 and where i is between 1 and N-1. Each stage comprises at least six flexible longitudinal link arms articulated by tape measures, which in the deployed position are in planes parallel to the X axis and are inclined on the X axis; the N stages are fixed together in pairs by means of connecting platforms parallel to the YZ plane, two contiguous lower and upper stages being angularly offset relative to one another by a rotation about the axis of Deployment X. According to a characteristic of the invention, two adjacent lower and upper contiguous stages are fixed to each other by a connecting platform common to the two adjacent stages. Preferably, each upper, lower and connecting platform comprises fixing lugs grouped in regularly distributed pairs, each fixing lug being dedicated to the attachment of an end 20 of a connecting arm. According to another characteristic of the invention, the fixing lugs are oriented towards the outside of the mast and for each pair of fastening lugs, the connecting arms in the folded configuration are oriented at an angle of between 0 ° and 45 °. in the YZ plane, tangentially to the platform. Each linking arm advantageously has folding zones (= zones articulated by meter-ribbons) and non-folding zones with an arcuate section, such that the arc of the non-folding zones 30 is longer than the folding areas. The folding zones are typically located towards both ends of the link arm and at an intermediate zone, and the arcuate sections of the zones towards the ends can be reversed (diametrically opposite) with respect to the section of the intermediate zone.
    [0004] At least three pairs of fasteners are distributed around the lower and upper platforms, at least six pairs of fasteners are distributed around each connecting platform. When the platforms are triangular the pairs of brackets are generally distributed at the vertices of the triangles but this is not essential. All the connecting arms are advantageously identical and of the same length. The deployable mast may have several identical structural blocks stacked one above the other. It preferably comprises means for regulating the speed of deployment of the mast, which comprise, for example, a motorized main pulley fixed to the lower platform, and non-motorized secondary pulleys capable of being driven by the main pulley by means of at least a cable or ribbon. The secondary pulleys can be attached to the upper platform and each connecting platform with the same cable or ribbon connecting secondary pulleys of the different platforms to the main pulley.
    [0005] According to an alternative, the secondary pulleys are fixed to the lower platform, the main pulley is stepped and comprises as many stages as secondary pulleys, and the speed control means comprise as many cables or ribbons as secondary pulleys, respectively attached to the upper platform and each link platform. In another alternative, the secondary pulleys are attached to the lower platform, the main pulley is stepped and has as many stages as secondary pulleys, and the speed control means comprises as many cables or ribbons as secondary pulleys. , respectively attached to the upper platform only. A deployment lock-release device is advantageously positioned on each link platform to allow after the deployment of said platform, the release of the contiguous platform which is greater.
    [0006] The ends of connecting arms in the form of tape-meters have a profile varying according to the deployed or folded position of the connecting arms; according to a feature of the invention, the locking-release device comprises locking-releasing means according to said profile.
    [0007] The subject of the invention is also a satellite characterized in that it comprises at least one deployable mast with autonomous spontaneous deployment as described above.
    [0008] Other characteristics and advantages of the invention will appear on reading the detailed description which follows, given by way of nonlimiting example and with reference to the appended drawings, in which: FIG. 1 schematically represents an example of a mast according to FIG. In the six-stage invention, in the deployed position, FIG. 2 schematically represents in perspective an example of a mast according to the invention with three stages being deployed, FIGS. 3 schematically represent an example of a mast according to the invention in stored position. 3 are a perspective view (FIG 3a) and seen from above (FIG 3b), FIGS. 4 are diagrammatic perspective views of examples of connecting arms equipped with tape meters according to the invention, with a continuous section (FIG. and 4b), and with evolutive sections shown in folded and unfolded configurations (Figs 4c and 4d), Figs 5 schematically seen in cross section a first example of regulation of the deployment speed of a mast according to the invention with four stages, in stored configuration (FIG. 5a) and being deployed (FIG 5b), for a synchronized deployment of the different stages of the mast, FIG 6 shows schematically in section a second example of means for regulating the speed of the deployment of a mast according to FIG. four-stage invention, being deployed, for a synchronized deployment of the various stages of the mast, FIG. 7 is a diagrammatic sectional view of an example of means for regulating the speed of deployment of a mast 35 according to the invention, four-stage, in stored configuration (FIG 7a), in progress 3025498 5 deployment (FIG 7b and 7c) and deployed (FIG.7d), for a sequential deployment of the various stages of the mast. From one figure to another, the same elements are identified by the same references.
    [0009] In the rest of the description, the terms "lower", "upper", "lower", "high" are used with reference to the orientation of the figures described. Since the device can be positioned in other orientations, the directional terminology is illustrative and not limiting.
    [0010] FIG. 1 illustrates an example of a deployable mast according to the invention, in the deployed position along a longitudinal deployment axis X, the mast comprising a multi-stage elementary structural block. An elementary structural block 10 is at least made up of a lower platform 13, an upper platform 12, one or more connecting platforms 15 and N stages E1,..., Ei, Ei + 1,. .., EN, where N is an integer greater than one and i is between 1 and N-1 inclusive, stacked one above the other parallel to the longitudinal deployment axis X and fixed rigidly between them two to two. Two contiguous stages E 1 and E 1 + 1 can be attached to each other via a connecting platform 15 common to the two adjacent stages. The two lower platforms 13 and upper 12 and the connecting platforms 15 are parallel to a YZ plane orthogonal to the X axis; they are rigid and have a symmetrical shape preferably around the X axis such as for example a disk or ring shape, or may have a polygonal (triangular for example as shown in the figures) or circular peripheral contour. One stage of the elementary structural block 10 comprises at least six connecting arms equipped with tape-strips 11 which are deployed in planes parallel to the axis X, and whose ends are respectively attached to an upper platform 12 or a lower platform 13 or a connecting platform 15. The tape measures are all identical, all have the same length and the same shape. Each connecting arm equipped with a tape measure has a lower end fixed rigidly to a platform of a lower stage E 1 and an upper end fixed rigidly to a platform of an upper stage E 1 + 1 adjacent to the lower stage. Ei. For this purpose, each upper and lower platform and each connecting platform comprises fixing lugs 14 distributed on its periphery, each fixing lug being dedicated to the attachment of an end of a connecting arm equipped with tape measure.
    [0011] It is possible to increase the length of the mast by stacking several elementary structural blocks one above the other. The Applicant has described in the patent application EP 14160636.8 a deployable mast self-deployment spontaneous 10 having platforms interconnected by at least three meters ribbons. In the deployed position, the tape meters are parallel to the axis X of the mast and in the stacked position they are folded in two in the direction of the length radially inwardly of the mast or outwardly. This structure, however, offers some stability problems during deployment: the ribbons 15 can unfold in a non-synchronized and unregulated manner because of the position and orientation of the ribbons. When deployed, the orientation of the ribbons does not make it possible to oppose resistance to torsion. According to the invention, in the deployed position the link arms articulated by tape-meters are in planes parallel to the X direction of deployment, but as shown in FIG. 2 they do not deploy parallel to the axis X of the mast; deployed they are inclined relative to X as can be seen in Figure 1. This inclination allows the connecting arms equipped with measuring tape to take the loads and moments applied to the platforms in the form of effort along their axis of 25 deployment (that is to say according to their own neutral fiber) which is more favorable in terms of load recovery. Between two contiguous platforms and when they are deployed, they form in pairs figures resembling Vs and / or inverted Vs, the tip of the V being able to be more or less pointed according to the spacing of the fastening tabs of the ends of the arms. binding. The smaller this spacing is, the more direct the force passage is, which makes it possible to balance the thrust between the connecting arms equipped with tape measures and thus to increase the rigidity. In the stacked (or stored) configuration shown in FIGS. 3a and 3b, the link arms equipped with ribbons are not folded radially; they are folded in half lengthwise outwardly and each folded ribbon typically forms with one of the two platforms to which it is attached, an angle of between 0 ° and 45 °, which provides greater stability deployment and is less cumbersome. The angle α is defined by the direction of a connecting arm bent with respect to the tangent to a circle passing in a plane YZ by the anchoring zones of the fastening tabs. This angle a is typically determined as a function of the length of the mast, its volume in stored configuration and the desired rigidity. The tape measures are known in the spatial field as flexible ribbons or strips having a convex first face 114, a concave second face 115 and having an arcuate section of radius of curvature R, as shown for example on Figures 4a and 4b. Tape meters have a natural tendency to extend longitudinally autonomously, mainly due to their own elastic energy without the use of an engine.
    [0012] In the context of the invention, it is possible to use connecting arms equipped with commercial tape measures with a constant cross section along the entire length of the tape measure. As shown in FIGS. 4c and 4d, with the link arm in folded and deployed configuration for each case, it is also possible to use ribbon meters which have an evolutionary section along their length in order to optimize performance; typically the need for arcuate section is essential to the right folds. Each connecting arm has fold zones 112 articulated by tape-meters, which are situated towards the two ends 111 and in an intermediate zone, and non-folding zones 113. According to one embodiment of the invention, the 25 non-folding zones 113 have an arcuate section longer than the arc of the folding zones 112 as shown in FIG. 4d, and which can be maximum then forming a complete circle which then define tubular zones as shown in FIG. 4c : This favors the buckling behavior. In addition, the arcuate sections of the end fold zones 111 can be inverted with respect to the section of the intermediate fold zone as shown in FIG. 4c, whereby a same deployment force is obtained on all the folded areas. When the arcuate sections are identical for all the folding zones, different deployment forces are obtained according to the folded zones. In example 3025498 8 of Figure 4d, the link arm comprises a tape measure over its entire length. The tape measures can be oriented so as to have their concave face facing the outside of the mast, but it is also possible to orient them in the opposite direction so that they have their concave face oriented towards the inside of the mast. . Referring to FIG. 1, each stage comprises at least six connecting arms 11 equipped with stretching ribbon strips in planes parallel to the longitudinal deployment axis X and inclined relative to the X axis, the six connecting arms 11 equipped with tape-meters 11 having two opposite ends respectively fixed on the connecting platforms 15 or on the upper platform 12 or on the lower platform 13. To ensure the attachment of the ends of the arms 15 connection 11 of two contiguous stages Ei, Ei + 1, the number of fastening tabs 14 of each connecting platform 15 is twice as large as the number of link arms 11 of a stage Ei of the elementary structural block 10. Thus , in the case where each stage Ei of the elementary structural block comprises six connecting arms 11, each connecting platform 15 comprises twelve fastening tabs grouped into six pairs of preferably regular distributed around the platform: three pairs on which are respectively fixed six link arms 11 of the lower stage Ei and three pairs on which are respectively fixed six link arms 11 of the upper contiguous stage Ei + 1. Preferably, these six pairs are themselves grouped into three quadruplets 141 of fastening lugs which can be seen in FIG. 3b. A stage comprising eight link arms will have twice four pairs of attachment tabs, preferably grouped into four quadruplets, etc. The attachment tabs 14 are oriented so that they extend outwardly of the structural block elementary 10 and thus to the outside of the mast. They are integral with each link platform and are typically mounted on the outer periphery of each platform. These fixing lugs can be directly attached to the platform. The fastening lugs 14 integral with each connecting platform 15 may be located in the plane YZ of the corresponding connecting platform 30 or may be inclined relative to the plane YZ of this platform, the inclination being oriented in opposite directions. for the connecting arms of the upper stage Ei + 1 relative to the lower stage Ei. The fastening tabs of the connecting arms of the lower stage Ei may be inclined upwards of the mast while the fixing lugs of the connecting arms of the upper stage Ei + 1 may be inclined towards the bottom of the mast, so as to create a longitudinal overlap zone 17 between two contiguous stages E 1 and E 1 + 1, which has the advantage of increasing the rigidity of the mast and of improving the compactness of the elementary structural block 10 when it is folded into stored position 10. Two consecutive connecting platforms 15, therefore belonging to the same stage Ei, and comprise fastening lugs oriented in opposite directions with respect to the YZ plane of the two connecting platforms. According to one alternative, the fastening lugs 14 of a quadruplet are attached to the platform by means of an anchoring zone, for example with 5 branches distributed in a star, one in the extension of the periphery of the platform, the others dedicated to the four fixing lugs as can be seen in Figure 3b, with two branches dedicated to the fixing of the tape-meters of the lower floor Ei, and the other two branches dedicated to fixing the tape-meters of the upper stage Ei + 1.
    [0013] The ends of the link arms 11 of each stage Ei may be fixed by means of flanges mounted on the fastening lugs 14 of the connecting platforms 15 or on the attachment lugs 14 of the upper or lower platforms 12 or 13, or may be fixed by riveting, screwing or gluing. In the case where the mast comprises several elementary structural blocks 10, the lower platforms 13 and upper 12 located at the base and at the top of each elementary structural block 10 provide the connection between the connecting arms 11 of two consecutive elementary structural blocks. Preferably, for the mast to be balanced, the fastening lugs 14 and the connecting arms 11 equipped with tape-meters 11 which are fixed thereto are regularly spaced around the longitudinal deployment axis X and for each connecting platform the angles separating two quadruplets of fastening lugs may have identical values. Two contiguous stages are angularly offset relative to each other by a rotation about the deployment axis X so as to interconnect the connecting arms equipped with tape meters of a lower stage Ei between the connecting arms equipped with tape meters of an upper contiguous stage Ei + 1, and interposing the fixing tabs of a lower stage Ei between the brackets of an upper contiguous stage Ei + 1 and for which two consecutive platforms 5, the connecting arms equipped with tape-meters form inverted Vs and / or Vs figures. When an elementary structural block 10 is folded back into the stored position, it is in a compact state and all the upper, lower, and connecting platforms 15 separating the different stages of the elementary structural block are stacked one above the other. others as shown in the views of Figures 3a and 3b where we can see the connecting arms equipped with folded tape meters to the outside of the mast. In FIG. 1, the elementary structural block 10 comprises six stages with six link arms equipped with tape meters per stage, ie a total of 36 link arms regularly distributed over the circumference of an annular ring consisting of a stack of all the upper, lower and connecting platforms of the elementary structural block in the stacked state. In the compact state, the connecting arms 11 are folded in two over themselves in the direction of their length, the folding being effected towards the outside of the mast with the fastening tabs extending outwards from the mast. mast as shown in Figures 3a and 3b. Two consecutive connecting platforms 15, therefore belonging to the same stage Ei, comprise anchoring zones whose spacing is determined so as to ensure maximum elastic folding of the connecting arms equipped with tape-meters. This spacing is identical for each pair of anchoring zones. The link arms 11 equipped with tape measures are made of a material compatible with a spatial environment and may be made of a metallic material or a composite material such as, for example, carbon fibers embedded in an epoxy resin or in a cyanate resin. Composite materials are preferred because they have a much lower coefficient of expansion than metal materials. The upper and lower platforms and the connecting platforms are preferably made of carbon.
    [0014] 302 54 98 11 The mast has no hinge itself, no hinges, no pivot, and no deployment motor. In the stored position, all the link arms 11 equipped with tape measures 11 of all the elementary structural stages Ei store elastic energy due to the constraints which hold them in the folded position in two. The maintenance of the connecting arms 11 equipped with tape-meters in the folded position is provided by a stacking system maintaining the various platforms in stored configuration. The deployment of the mast is initiated by the release of the stacking system. The deployment is then carried out passively 10 by relaxation of stresses on the tape-meters during their unfolding and the release of the elastic energy stored by the tape-meters. To ensure that the deployment is not too violent, speed control means are preferably used to control the deployment of the mast. For example, the speed of the unfolding of the tape meters can be controlled by a progressive unfolding of a cable run by a motor. These means for regulating the speed of deployment are advantageously distributed in at least three identical speed control devices; they include three in our example distributed on the periphery of the platforms. These speed regulation means are described with reference to FIGS. 5, 6 and 7, in which two speed control devices 16a and 16b can be seen in section. Each speed control device 16a or 16b typically comprises: a single motorized main pulley 160 fixed to the lower platform and common to all the braking devices 16a, 16b, 25 and non-motorized secondary pulleys 161a, 161b capable of being driven by the main pulley 160 by means of at least one connecting cable 162a, 162b. The cable can be replaced by a ribbon, that is to say a flat-section band. It is also possible to simultaneously wind on the same pulley stage several cables or bands as shown in FIGS. 5a and 5b. The main pulley may have several grooves for driving several cables. Synchronous deployment speed control means are distinguished, with all the stages being synchronously deployed and sequentially deployed speed regulating means, the first stage then deploying before the second unfolding before the third, and so on. . According to a first embodiment, an example of which is shown in FIGS. 5a and 5b, a synchronized deployment means speed control device 16a or 16b which comprises one or two secondary pulleys 161a, 161b fixed to the upper platform 12 and to each linkage platform 15; the same cable or ribbon 162a, 162b connects the secondary pulleys of different platforms to the main pulley 160. According to another configuration described in connection with FIG. 6, a synchronized deployment means 16a or 16b of speed control device comprises: secondary pulleys 161a, 161b fixed to the lower platform 13, and respectively dedicated to the upper platform 12 and to each connecting platform 15, 15 - connecting cables 162a, 162b or ribbons respectively connecting the main pulley 160 to said platform or link, via the corresponding secondary pulley. This main pulley is stepped and the diameters of the different pulley stages are calculated to allow a uniform deployment of the different stages. In the case of a 4-stage configuration, the upper platform having to travel a distance 4 times greater than that of the 1st stage, the diameters of the main staged pulley 160 must therefore comprise the corresponding difference. According to another embodiment, an example of which is shown in FIGS. 7a to 7d, a sequential deployment means of speed control device 16a or 16b comprises: a single secondary pulley 161a, 161b attached to the lower platform 13, the same cable or tape 162a, 162b connecting the main pulley 160 to the upper platform 12 via this secondary pulley, and a locking / release device of the connecting platforms 15 and upper 12. This locking / release device shown in FIGS. 7a and 7b in FIG. zoom, comprises for each stage Ei a hook 163a, 163b connected to the upper platform 12 or to the upper connecting platform 15 of this stage Ei (except possibly the upper link platform of the stage 3025498 13 E1, the deployment of this first stage being controlled by the release of the stacking system holding the structure in stored configuration during the launch phase, and maintained then, then speed-regulated by the main pulley according to whether it is stopped as symbolized by an X 5 in Figures 7a and 7d, or in operation as symbolized by a rounded arrow in Figures 7b and 7c). The other end of the hook is intended to be hooked during locking to the lower link platform of this stage Ei in the following manner. This other end has a "U" shape in the YZ plane of this lower platform, the branches of the "U" 10 engaging in notches provided for this purpose in the upper end 111 of the link arm 11 (this end is in the form of a tape measure) itself attached to this lower platform. When this lower platform is in the stored position, this end 111 is flattened and the branches of the "U" are engaged in the tape measure thus blocking its deployment: the lower platform is then hooked to its upper platform by the hook. The deployment of the connecting arm equipped with tape measures the deformation of these ends which resume their curvilinear shape (rest position). As soon as this end 111 curves towards the inside of the "U" thanks to its elastic energy, the 20 branches of the "U" are released from the notches: the hook no longer blocks the deployment of the tape measure. The hooks are thus released sequentially sequentially and so that the connecting platforms 15 and the upper platform 12 corresponding. This locking-release device can also be installed on the mast independently of the other elements (pulleys, cables, etc.) of the speed regulation means. For space applications, the mast can be used for example to move a device or an antenna from the body of a satellite. In this case, the lower platform 13 of the lower stage of the mast is fixed on the body of the satellite and the apparatus to be removed is fixed to the upper platform 12 of the upper stage of the mast. Although the invention has been described in connection with particular embodiments, it is obvious that it is in no way limited thereto and that it includes all the technical equivalents of the means described and their combinations if those are within the scope of the invention. 5
    权利要求:
    Claims (18)
    [0001]
    REVENDICATIONS1. Autonomous self-expanding deployable mast comprising at least one elementary structural block (10) having a longitudinal deployment axis X, the elementary structural block comprising two platforms respectively lower (13) and upper (12) parallel to a YZ plane orthogonal to the X and N stages (E1, ..., Ei, Ei + 1, ..., EN) stacked one above the other parallel to the longitudinal deployment axis X, where N is greater than 1 and where i is between 1 and N-1, characterized in that each stage (Ei) comprises at least six flexible longitudinal linkage arms (11) articulated by tape-meters, which in the deployed position are in planes parallel to the axis X and are inclined with respect to the X axis, the N stages being fixed together in pairs by connecting platforms (15) parallel to the YZ plane and in that two contiguous lower and upper stages (Ei, Ei + 1) are angularly shifted one by relative to each other by rotating around the X deployment axis.
    [0002]
    2. deployable mast according to the preceding claim, characterized in that two contiguous stages (Ei, Ei + 1) respectively lower and upper, are fixed together by a connecting platform (15) common to the two adjacent floors (Ei, Ei + 1).
    [0003]
    3. deployable mast according to one of the preceding claims, characterized in that each upper platform (12), lower (13) and connecting (15) comprises fastening lugs (14) grouped in regularly distributed pairs, each leg of fixing being dedicated to the attachment of an end (111) of a connecting arm.
    [0004]
    4. deployable mast according to one of the preceding claims, characterized in that the fastening lugs (14) are oriented towards the outside of the mast and in that for each pair of fastening lugs, the connecting arms in folded configuration are oriented at an angle between 0 ° and 45 ° in the YZ plane, tangentially to the platform.
    [0005]
    5. Deployable mast according to one of the preceding claims, characterized in that each tape measure (11) has folding zones (112) arcuate section and non-folding areas (113) arcuate section. in that the arc of the non-folding zones is longer than that of the folding zones. 10
    [0006]
    6. deployable mast according to the preceding claim, characterized in that the folding zones (112) are located at the two ends (111) of the connecting arm and in an intermediate zone, and in that the arcuate sections of the zones at the ends are diametrically opposite to the section of the intermediate zone.
    [0007]
    7. Deployable mast according to claim 5, characterized in that the folding zones (112) at both ends (111) and in an intermediate zone have an arcuate section, and in that the sections of the zones of non-folding (113) have a tubular section.
    [0008]
    8. deployable mast according to one of the preceding claims, characterized in that each connecting platform (15) comprises at least six pairs of fastening lugs (14). 25
    [0009]
    9. deployable mast according to one of the preceding claims, characterized in that all the connecting arms (11) are identical.
    [0010]
    10. Deployable mast according to one of the preceding claims, characterized in that it comprises several identical structural blocks (10) stacked one above the other.
    [0011]
    11. Deployable mast according to one of the preceding claims, characterized in that it comprises means for regulating the speed of deployment of the mast. 3025498 17
    [0012]
    12. Deployable mast according to the preceding claim, characterized in that the speed control means comprise a motorized main pulley (160) attached to the lower platform (13), and non-motorized secondary pulleys (161a, 161b) adapted to driven by the main pulley (160) by means of at least one cable (162a, 162b) or ribbon.
    [0013]
    13. Deployable mast according to the preceding claim, characterized in that at least one secondary pulley (161a, 161b) is fixed to the upper platform (12) and to each connecting platform (15) and in that one cable (162a, 162b) or ribbon connects secondary pulleys of the different platforms to the main pulley (160).
    [0014]
    14. Deployable mast according to claim 12, characterized in that the secondary pulleys (161a, 161b) are fixed to the lower platform (13), the main pulley (160) has as many stages as secondary pulleys and in that that the speed regulation means comprise as many cables (162a, 162b) or ribbons as secondary pulleys, respectively fixed to the upper platform (12) and each connection platform (15).
    [0015]
    15. Deployable mast according to claim 12, characterized in that in that the secondary pulleys (161a, 161b) are fixed to the lower platform (13), the main pulley (160) has as many stages as secondary pulleys. and in that the speed regulating means comprise as many cables (162a, 162b) or ribbons as there are stages of the main pulley (160) and / or movable platforms (15) and upper (12), the cables or ribbons being attached to the upper platform (12). 30
    [0016]
    16. Deployable mast according to one of the preceding claims, characterized in that a deployment lock-release device (111, 114, 163a, 163b) is positioned on each connecting platform (15) to allow after the deployment of Said platform, the release of the contiguous platform which is superior to it. 3025498 18
    [0017]
    17. deployable mast according to the preceding claim, characterized in that the ends (111) of connecting arm in the form of tape-meters have a profile varying according to the deployed or folded position of the link arms, and in that the device locking-release means comprises locking-releasing means according to said profile.
    [0018]
    18. Satellite characterized in that it comprises at least one deployable mast 10 autonomous spontaneous deployment, according to one of the preceding claims.
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    EP3301328B1|2020-11-04|Force-shunting device and mechanical actuator comprising such a device
    FR2655720A1|1991-06-14|WING GALBEE DEPLOYABLE FOR FLYING ENGINE.
    WO2021009072A1|2021-01-21|Foldable/deployable structure comprising a deployable mast
    同族专利:
    公开号 | 公开日
    JP6623004B2|2019-12-18|
    ES2628484T3|2017-08-03|
    US20160068281A1|2016-03-10|
    JP2016056947A|2016-04-21|
    EP2993131B1|2017-03-29|
    FR3025498B1|2017-12-08|
    CA2902034A1|2016-03-05|
    US9764857B2|2017-09-19|
    EP2993131A1|2016-03-09|
    引用文献:
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    US6374565B1|1999-11-09|2002-04-23|Foster-Miller, Inc.|Foldable member|
    EP1676776A1|2004-12-28|2006-07-05|Alcatel|Device for supporting elements of a spacecraft equipment with flexible deployable blades|
    EP2143641A1|2008-07-11|2010-01-13|Thales|Tape measure with thermal unrolling and unrolling structure comprising such a tape measure|
    US1360131A|1916-03-28|1920-11-23|Axel N Miller|Scaffold|
    US1511679A|1922-06-23|1924-10-14|Schwarz Carl|Extension tower|
    US2697845A|1951-06-18|1954-12-28|Paul E Broner|Link structure|
    US3593481A|1969-03-19|1971-07-20|Tom T Mikulin|Extensible structure|
    EP0408826B1|1989-07-19|1994-09-14|Japan Aircraft Mfg. Co., Ltd|Extendable mast|
    US5184444A|1991-08-09|1993-02-09|Aec-Able Engineering Co., Inc.|Survivable deployable/retractable mast|
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    US7617639B1|2006-08-08|2009-11-17|The United States Of America As Represented By The Secretary Of The Air Force|Tape-spring deployable boom|
    US20080283670A1|2006-12-13|2008-11-20|Thomas Jeffrey Harvey|K-truss deployable boom system|
    EP2272761A1|2009-06-18|2011-01-12|Astrium Limited|Extendable structure|
    US8683755B1|2010-01-21|2014-04-01|Deployable Space Systems, Inc.|Directionally controlled elastically deployable roll-out solar array|
    FR2974348B1|2011-04-21|2014-01-24|Thales Sa|DEVICE FOR PROTECTING AN OPTICAL INSTRUMENT OF A SATELLITE|
    FR3003846B1|2013-03-29|2017-01-27|Thales Sa|DEPLOYABLE MAT WITH DEPLOYMENT OF SPONTANEOUS AUTONOMOUS AND SATELLITE COMPRISING AT LEAST ONE SUCH MATT|US10263316B2|2013-09-06|2019-04-16|MMA Design, LLC|Deployable reflectarray antenna structure|
    US9856039B2|2014-10-08|2018-01-02|Analytical Mechanics Associates, Inc.|Extendable solar array for a spacecraft system|
    US10119292B1|2015-07-02|2018-11-06|M.M.A. Design, LLC|Deployable boom and deployable boom with solar blanket|
    US10435182B1|2016-09-12|2019-10-08|Space Systems/Loral, Llc|Articulation techniques for a spacecraft solar array|
    GB2555657A|2016-11-08|2018-05-09|Oxford Space Systems|Deployable mast structure|
    FR3087426A1|2018-10-18|2020-04-24|Thales|DEPLOYABLE TAPE MEASUREMENT WITH NON-CONSTANT SECTION|
    CN110979742B|2019-11-29|2021-12-07|北京卫星制造厂有限公司|High-expansion-ratio unfolding mechanism suitable for space environment|
    法律状态:
    2015-08-25| PLFP| Fee payment|Year of fee payment: 2 |
    2016-03-11| PLSC| Publication of the preliminary search report|Effective date: 20160311 |
    2016-08-26| PLFP| Fee payment|Year of fee payment: 3 |
    2017-08-29| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1401992A|FR3025498B1|2014-09-05|2014-09-05|DEPLOYABLE MAT WITH AUTONOMOUS SPONTANEOUS AND SATELLITE DEPLOYMENT COMPRISING AT LEAST ONE SUCH MAT|FR1401992A| FR3025498B1|2014-09-05|2014-09-05|DEPLOYABLE MAT WITH AUTONOMOUS SPONTANEOUS AND SATELLITE DEPLOYMENT COMPRISING AT LEAST ONE SUCH MAT|
    EP15182588.2A| EP2993131B1|2014-09-05|2015-08-26|Deployable mast with autonomous spontaneous deployment and satellite comprising at least one such mast|
    ES15182588.2T| ES2628484T3|2014-09-05|2015-08-26|Folding mast of autonomous and satellite spontaneous deployment that includes at least said mast|
    CA2902034A| CA2902034A1|2014-09-05|2015-08-28|Deployable mast with spontaneous autonomous deployment, and satellite comprising at least one mast of this type|
    JP2015170065A| JP6623004B2|2014-09-05|2015-08-31|Deployable mast with spontaneous autonomous deployment and satellite with at least one mast of this kind|
    US14/846,242| US9764857B2|2014-09-05|2015-09-04|Deployable mast with spontaneous autonomous deployment, and satellite|
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