• 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 structure (10) comprising: • a support (16), • a tape measure (11, 12) fixed to the support (16), able to pass from a configuration wound around a Z axis to a deployed configuration. According to the invention, the deployable structure further comprises: an arm (15) movable in rotation relative to the support (16) around the Z axis, able to form a first contact with the tape measure (11, 12 ) to control the deployment of the tape measure (11, 12).
    公开号:FR3024228A1
    申请号:FR1401712
    申请日:2014-07-25
    公开日:2016-01-29
    发明作者:Yannick Baudasse；Stephane Vezain；Francois Guinot
    申请人:Thales SA；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a deployable structure with a tape measure for a flexible structure, windable and deployable. 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 antennas, solar generators, heat shields, baffles or telescopes. The space-deployable structures, such as solar generators for example, generally consist of rigid panels hinged together, these panels being, in the stored position, stacked one above the other. These structures have the advantage of having a controlled kinematics but have the disadvantage of a large surface mass and inertia. In addition, the rigid structures occupy, in the stored position, a large space under the cap of a launcher. Since the space allocated to the deployable structures, under the launcher cap, is limited, it is important to reduce the bulk of these deployable structures when in the stored position so as to optimize the deployed surface area. There are flexible flat deployable structures comprising a flexible fabric and tape measures (also known in the Anglo-Saxon literature as tape-spring) fixed on the same plane of the canvas. In the stored position, the fabric and the tape measures are wrapped around a mandrel. The deployment of the flexible flat structure is autonomously ensured by the spontaneous unwinding of the tape-meters when the mandrel is free to rotate.
    [0002] Indeed, the tape measures are known in the spatial field as being flexible tapes having a section in an arc whose radius of curvature is convex on a first face and concave on a second face, these tapes being able to pass of the wound state in the unrolled state essentially due to their own elastic energy. There are 30 different types of ribbon with their own properties. Monostable ribbons have a natural deployed position and require a hold in the stored position. Monostable tape measures therefore have a natural tendency to unfold to find themselves in their unrolled state. The deployment of monostable ribbons is often anarchic and uncontrolled.
    [0003] 3024228 2 Bistable tapes have two natural positions (stored position and extended position) and do not require holding in the stored position when the section is completely flattened. Their deployment is linear and controlled. However, in all cases, when the deployment is triggered, it may be violent and shock-producing, that is, the entire tape measure may have a tendency to recover right simultaneously, over its entire length. length, which poses a risk of damage to the surrounding elements or elements fixed on the tape measure such as a flexible membrane, an instrument, an antenna ... The conventional tape meters may thus present difficulties in terms of control of their deployment. In order to regulate the deployment speed of this type of structure, several methods can be used. There may be mentioned, for example, a regulation by an electric geared motor as described in the patent application FR12 / 03300 or a thermal regulation using hybrid tape meters as described in patents FR 0803986 and US 7856735. In addition, the tape measures do not have the same stiffness along the axis of stress. A force F applied on the convex face of the tape measure will have a tendency to bend the tape measure while the same force applied on the concave face will have no effect, which poses a problem of instability of the flexible structure in its unfolded state. To solve this problem of stability of the deployed state, it is then necessary to maintain the tape measure in the extended position by an additional holding device or to oversize the tape measure so that it remains stable under the orbital forces. whatever their application Thus, in stored configuration, the tape measure must be as compact as possible, that is to say have a winding radius as low as possible. This parameter is given by the physical characteristics of the ribbon, generally, the winding radius is substantially equal to that of their radius of curvature. In the case of a composite tape, it can be modified by changing the stack of folds and / or the direction of the fibers. In the deployed configuration, the best possible rigidity is sought, which means a larger and more closed section possible associated with embedding the end of the tape-meter as much as possible.
    [0004] The aim of the invention is to overcome all or some of the problems mentioned above by proposing a deployable structure for a flexible, rollable and deployable structure, having the advantage of being compact, easy to produce and having an optimization of the volume. the deployable structure when stored under the casing of a launcher, allowing control of deployment and a folding ability and allowing rigidity and stability of the structure when deployed.
    [0005] To this end, the subject of the invention is a deployable structure comprising: a support, a tape measure fixed to the support, capable of passing from a configuration wound around a Z axis to an expanded configuration, characterized in that it further comprises - an arm movable in rotation relative to the support about the Z axis, able to form a first contact with the tape measure so as to control the deployment of the tape measure.
    [0006] According to one embodiment, the tape measure having two ends, the tape measure is fixed between its two ends at an attachment point on the support, the arm is able to form a second contact with the tape measure so to control the deployment of the tape measure, a first end is able to deploy relative to the attachment point 25 along a first axis perpendicular to the Z axis in a first direction, a second end is able to unfold according to a second axis perpendicular to the Z axis in a second direction different from the first direction. Advantageously, both ends are able to deploy simultaneously. According to another embodiment, the deployable structure according to the invention may further comprise a mandrel and a shaft substantially parallel to the Z axis, the mandrel is fixed on the shaft and the tape measure is wound around the mandrel. .
    [0007] According to another embodiment, the arm carries two rollers, the rollers being in contact with the tape measure and the rollers are able to guide the tape measure.
    [0008] Advantageously, the rollers may be heating rollers, able to locally heat the tape measure. Advantageously, the deployable structure may further comprise a means of locking the degree of freedom in rotation around the Z axis of the arm. Advantageously, the locking means of the degree of freedom in rotation about the Z axis can be a fitting of a portion of tape measure in the shaft. According to another embodiment, the deployable structure according to the invention may comprise two secondary tape-meters each having two ends, a first end of one of the two secondary tape-meters is fixed at a distance from a first end of the meter. and a second end of the secondary tape measure is attached to one end of the arm. Advantageously, the secondary tape-meters may be flat blades.
    [0009] Advantageously, the structure may further comprise a deployable articulated mast fixed on a platform of a satellite via a rotation drive motor.
    [0010] The invention also relates to a satellite comprising at least one deployable structure. The invention will be better understood and other advantages will become apparent upon reading the detailed description of an exemplary embodiment, which is illustrated by the accompanying drawing, in which: FIGS. 1a, 1b and lc show three diagrams, in section in a plane perpendicular to the Z axis, of a deployable structure according to the invention, - Figures 2a, 2b and 2c show a deployable structure in a sectional view of the deployable structure according to 3a and 3b show a deployable structure according to a sectional view of the deployable structure according to the invention; FIG. 4a represents an isometric view of the deployable structure according to a first embodiment; FIG. 4b represents a sectional view of the deployable structure 10 according to a first embodiment; FIGS. 5a, 5b and 5c represent a deployable structure in a half-deployed position and in a position and a section of the deployable structure according to one embodiment, - Figure 6 shows a section of the deployable structure according to one embodiment, - Figure 7 shows a locking means of the tape measure in the deployed position. FIG. 8 is a semitransparent view of the locking means of the tape measure on the mandrel, FIG. 9 represents another means of stiffening the embedding of the tape measure, FIG. Automatic buckling of the secondary tape-meters; FIG. 11 shows schematically a satellite comprising at least one deployable structure according to the invention. For the sake of clarity, the same elements will bear the same references in the different figures.
    [0011] Figures 1a, 1b and 1c show three sectional diagrams in a plane perpendicular to a Z axis of the deployable structure 10 according to the invention. The deployable structure 10 comprises a support 16 and a tape measure 11 fixed to the support 16, able to pass from a configuration wound around a Z axis to a deployed configuration along an unfolded axis X. The structure 10 further comprises a arm 15 rotatable relative to the support 16 about the Z axis, able to form a first contact with the tape measure 11 so as to control the deployment of the tape measure 11. The first contact can be a contact punctual or longitudinal contact along an axis substantially parallel to the Z axis, along the entire width of the tape measure 11 or only a portion of the width of the tape measure 11. Indeed, without this contact, the tape measure could unfold uncontrollably along any axis. This contact can easily be replaced by at least one roller 20, carried by the arm 15. This roller 20 can have a degree of freedom in rotation about an axis parallel to the axis Z, 10 allowing it to be in rotation on the surface of the tape measure 11. The arm 15 makes it possible to control the deployment of the tape measure thanks to a more or less significant resistant torque depending on the type of regulation chosen (hybrid or electrical *). The contact is advantageously positioned close to the wound portion of the tape measure 11, in order to contribute to the maintenance of the tape measure 11 in its wound part. The deployable structure 10 according to the invention may further comprise a mandrel 13 and a shaft 14 substantially parallel to the axis Z. The mandrel 13 may be fixed on the shaft 14 and the tape measure 11 may be wound around the mandrel 13. The support 16 may be linked to the shaft 14. The presence of the mandrel 13 is not essential. Nevertheless, this configuration allows the tape measure 11 to be positioned and guided between the mandrel 13 and the roller 20. The tape measure 11 comprises two ends 81, 83. The tape measure 11 is fixed at its end 83, to the shaft 14 at the support 16. According to the invention, the tape measure 11 is fit to deploy in a direction parallel to an axis X, perpendicular to the axis Z. The winding of the tape measure is on a diameter corresponding to the diameter of the mandrel 13. Diagram 1c illustrates the deployable structure 10 in position 30 completely deployed. The tape measure 11 is integrally deployed along the X axis and always fixed at its end to the shaft 14. FIGS. 2a, 2b and 2c show three diagrams in section in a plane perpendicular to a Z axis of the deployable structure According to the invention. The deployable structure 10 comprises at least one tape measure 3024228 7 11 having an axis of deployment and folding substantially parallel to an unfolded axis X and a winding mandrel 13 carried by a shaft 14 along the axis Z perpendicular to the X axis. The tape measure 11 comprises two ends 81, 82. The tape measure 11 is fixed between its two ends 81, 82 to an attachment point at the support 16, (preferably in the center of the tape measure 11 ) on the shaft 14. The arm 15 is able to form a second contact with the tape measure 11 along an axis substantially parallel to the axis Z, so as to guide the tape measure 11 and control its deployment, a first end 81 is able to be deployed with respect to the point of attachment along a first unfolded axis X perpendicular to the Z axis in a first direction, a second end 82 is able to unfold along a second axis perpendicular to the axis Z in a second sense different from the first meaning. In some configurations, the second meaning can be opposed to the first sense.
    [0012] The tape measure 11 may be wound around the mandrel 13 physically connected to the shaft 14. The two ends 81, 82 are able to deploy relative to the attachment point 16 each in directions parallel to the X axis and diametrically opposite. Thus, the storage of both ends 81 and 82 of the tape measure 12 is achieved by winding in the same direction. This configuration makes it possible to obtain a winding of a tape measure over a diameter corresponding to the diameter of the mandrel 13. This configuration is therefore optimized for storage since it is not very bulky and allows an optimized unwinding since one simultaneously deploys or folds several lengths of ribbons. Moreover, the two ends 81, 82 are able to deploy simultaneously. Figure 2c illustrates the deployable structure 10 in a fully deployed position. The tape measure 11 is integrally deployed along the axis X and always fixed at its center on the interface 16. FIG. 3 shows two diagrams annotated respectively 3a and 3b, in section in a plane perpendicular to an axis Z, of the deployable structure 10 according to the invention. The stretchable ribbon structure 35 for a flexible, rollable and deployable structure comprises at least two ribbon meters 11 and 12 each having an axis of deployment and folding at any angle to the axis of rotation. X deployment of the first tape measure 11.
    [0013] Figure 4a shows the deployable structure 10 in isometric view and Figure 4b shows a sectional view of the deployable structure. The arm 15 is guided in rotation about the shaft 14 at the support 16. The arm 15 can form two substantially parallel contacts to the shaft 14 and can be symmetrical to each other with respect to the shaft 14, the arm being able to and control the deployment of the tape measure 11. In Figure 4b, the deployable structure 10 further comprises at least two rollers 20, 21 carried by the arm 15. The rollers 20, 21 are in contact with the meter. ribbon 11. The arm 15 has a degree of freedom in rotation around the axis Z. The rollers 20, 21 are able to guide the tape-meter 11. The two rollers 20, 21 make it possible in particular to ensure a correct and synchronized unwinding of the tape measure 11 around the mandrel 13 and also allow, if the arm 15 is motorized, to be able to fold the tape measure on the ground or in flight, for example when the flexible structure is mounted on a satellite. In addition, the rollers 20, 21 make it possible to limit the friction between the arm 15 and the tape measure 11. The invention can be applied to hybrid tape meters, consisting of a first driving structure (for example in fiber of carbon) which allows for the deployment of the tape measure, and a regulating portion (thermoelastic or material having a significantly lower processing temperature than that of the main tape) which promotes or limits the deployment as a function of temperature which it is applied to him. By using a natural phenomenon of viscosity change of a material by the temperature a good reliability and reproducibility of regulation of the deployment are guaranteed. It should be noted that in the case of the use of hybrid tape meters, the folding is impossible by the simple force of the tape measure because the tape measure is only motor in the direction of deployment. In order to allow a folding of the tape measure, it is necessary to add an electric gearmotor. Therefore, if one wishes a one-shot deployment, it is possible to have a regulation and / or hybrid or electric motorization. If multiple deployments of the tape measure are to be expected, the regulation and / or motorization will then be electrical.
    [0014] To regulate the deployment of the tape measure 11, in the case of the use of hybrid tape meters, it is possible to heat the mandrel 13. Advantageously, the rollers 20, 21 may be heating rollers. The heating rollers allow local heating at two points, at their respective anchors, the tape-meters, thus causing their deployment and also the rotation of the mandrel 13 which can thus heat the tape-measure section then brought into contact with the rollers 20, 21, as shown diagrammatically in FIG. 1b, the arrows indicating the rotation about the Z axis. The local heating by the heating rollers makes it possible to obtain a regulated deployment of the structure. In addition, since the heating is local, this configuration is energetically economical since it is not necessary to heat the entire tape measure and / or mandrel 13. This feature is particularly interesting for use on satellite.
    [0015] FIGS. 5a, 5b and 5c show a deployable structure 50 in the half-deployed position and in the deployed position as well as a section of the deployable structure 50 comprising two deployable structures 10 according to a first embodiment. The deployable structure 50 may comprise at least one flexible membrane 30. In FIGS. 5a, 5b, 5c, the deployable structures 10 according to the invention respectively comprise two tape-meters 41 and 42. The flexible membrane 30 may be intended to support elements to be deployed, for example solar cells, metallized cells for the reflection of radio waves, insulating elements for producing a thermal or optical screen, or any other device. The flexible membrane 30 is fixed on the tape measures 41, 42. The flexible membrane 30 may be stiffened by transverse slats themselves fixed to the tape measures, for example, by gluing, riveting, stapling or stitching. FIG. 5c shows a cross-section of the deployable structure 50 having two deployable structures 10 in a first embodiment, and a flexible membrane 30. In FIG. 5c, the mandrel 13 is fixed to the shaft 14. The arm 15 has a degree of freedom in rotation around the Z axis. This embodiment requires a rotating power supply system of the collector or spiral cable type to feed the heating rollers. It is more adapted to a heating chuck system 13 fixed with respect to the shaft 14 and not using a collector. It is also possible to consider another embodiment, as shown in FIG.
    [0016] It should be noted that the deployable structure 50 is shown with two tape measures. Nevertheless, it is possible to apply the invention to a deployable structure with more than two tape-meters, for example three or four, especially to thereby obtain a better support of the flexible membrane or in the case where the flexible membrane occupies a very important surface. FIG. 6 represents a section of the deployable structure 50 comprising two deployable structures 11, 12 according to a first embodiment. In Figure 6, the mandrel 13 is fixed to the shaft 14 and both 20 have a degree of freedom in rotation about the Z axis. The arm 15 is fixed. This embodiment does not require a rotating power supply system, collector type or spiral cable for powering the heating rollers. In this embodiment, there is no longer a need to compensate for the tape measure turns. Nevertheless, it is necessary to lock the rotation of each tape-measure at the end of deployment of the deployable structure 10. FIG. 7 represents a means of locking the degree of freedom in rotation around the Z axis of the measuring tape. deployed position. The locking means of the degree of freedom in rotation about the Z axis is a fitting of a portion of tape measure in the shaft 14. At the mandrel 13, the tape measure 11 can resume its initial position with a slightly concave shape of the face fixed to the mandrel 13 which then fits into the shaft 14. In other words, the tape measure 11 fits on the key-shaped shaft 14. The rotation along the Z axis of the tape measure is then locked. FIG. 8 illustrates, in an isometric semi-transparent view, the means 5 for locking the tape measure on the mandrel 13 with in detail the curvature of the tape measure which is flush with the level of the shaft 14. FIG. means of stiffening the embedding of the tape measure. This configuration is similar to that proposed in FIG. 8 with an arm 15 carrying the fixed rollers 20, 21 and a shaft 14, a mandrel 13 and tape measures 11 and 12 rotatable about the Z axis. Tape measure 11 and mandrel 13 each have two ends. The deployable structure 10 comprises two secondary tape meters 61, 62 each having two ends, a first end 71 of one of the two secondary tape-meters 61 is attached at a distance from a first end 81 of the tape measure 11. second end 72 of the secondary tape measure 61 is attached to one end 91 of the mandrel 13. Likewise, a first end 73 of the second secondary tape 62 62 is attached at a distance from a second end 82 of the tape measure 11. A second end 74 of the secondary tape measure 62 is attached to one end 92 of the mandrel 13. Each assembly consisting of a portion of a tape measure, a mandrel portion and a secondary tape measure forms in the deployed position a triangulated structure providing a excellent rigidity at 25 meter ribbon deployed. In FIG. 9, the arm 15 is shown in dashed lines, but it is obvious that it is connected to the heating rollers 20, 21 to allow a good guiding of the measuring tape and the deployment of the tape measure by local reheating. as explained above. Thus, the deployment of the tape measure can be regulated and controlled. The secondary tape-meters may be convex section tape-meters or flat blades.
    [0017] 3024228 12 A tape measure in deployed configuration offers good tensile strength but also compression (within a certain limit). It allows to be used alone as a "strut" as described above. On the other hand, it offers less storage capacity than a strip due to this more cumbersome installation. In order to save space in the stored position, and to facilitate winding, it may therefore be envisaged to use cables, flat blades or flexible strips to replace the tape measures. However, they work only in traction. They must therefore work 10 in pairs and be in opposition (as shown in FIG. 9) using the stiffness of the main measuring tape. Indeed, when applying a torque on the main tape measure, a flexible band retains the force, if applying a torque in the other direction, it is the opposite flexible band that acts. The secondary tape measures constitute a triangulation system on the tape measure 11. When it is desired to fold the flexible structure 30 into the configuration shown in FIG. 9, it is sufficient to flamish the secondary tape measure (s) for obtain the initial winding by applying a force to the center of the ribbon 61, normal to the axis of the latter.
    [0018] FIG. 10 shows a means 96 for automatic buckling of the secondary tape measures 61, 62. The buckling force can be obtained by means of a motor enabling the structure to be rewound. The motor is connected to a pulley 93 driving, via cables or web 94, the 25 tape measures 61, 62. When the pulley 93, via a stop 95, comes into contact with the mandrel 13, the motor drives the mandrel 13 to rewind the structure. FIG. 11 shows a satellite 100 comprising at least one deployable structure 50 equipped with a flexible membrane 30 and at least 2 deployable structures 10. The deployable structure 50 further comprises a deployable articulated mast 110 attached to a satellite platform 100 via, for example, a rotary drive motor. In FIG. 10, the flexible membrane 30 is fully deployed. The satellite 100 comprises a second flexible membrane 30. The two deployable structures 50 are positioned on either side of the satellite 100. The flexible structure 50 can be positioned in a T-shape relative to the satellite 100 (configuration shown in FIG. 2), that is to say that its longitudinal principal direction is perpendicular to the articulated mast 110. The flexible structure can also be positioned in the form of I (configuration shown in FIG. 1), with respect to the satellite 100, this is that is to say that its longitudinal main direction is in the extension of the articulated mast 110.
    [0019] Generally, in actual use, the deployable structure 50 is used for only one deployment. Nevertheless, new mission needs appear. Including the transfer or towing of satellite from a low orbit to a high orbit. During the docking, for the control of the transfer vehicle, the least possible inertia is required, that is to say that the presence of large deployable structures is not favorable. We must also avoid any interference with satellites that we seek to dock. As a result, it is preferable to wind up the deployable structures. When the satellite is hooked, we can deploy the structure again.
    [0020] The invention has a simplicity of assembly, with few parts to assemble. The progress of the measuring tape is well controlled. Indeed, the tape measure can be guided by the rollers 20, 21, and locally heated in the case where the rollers 20, 21 are heated, thus allowing 25 to regulate its deployment. Finally, the stacking can be autonomous because it is obtained by the bistability of the tape measure (hybrid or not) with its two stable positions (rolled up and deployed). However, the invention can also be applied with non-hybrid or non-bistable tape meters. In this case, the regulation of the deployment is done by geared motor (which retains the torque of the tape measure), replacing the torque (thermoplastic / heating rollers).
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Deployable structure (10) comprising: - a support (16), - a tape measure (11, 12) fixed to the support (16), able to pass from a configuration wound around a Z axis to an expanded configuration, Characterized in that it further comprises - an arm (15) movable in rotation relative to the support (16) about the Z axis, adapted to form a first contact with the tape measure (11, 12) of to control the deployment of the tape measure (11, 12). 10
    [0002]
    2. deployable structure (10) according to claim 1, the tape measure having two ends (81, 82, 83), characterized in that the tape measure (11, 12) is fixed between its two ends at a point of fixing on the support (16), in that the arm (15) is able to form a second contact with the measuring tape (11, 12) so as to control the deployment of the tape measure (11, 12), in that a first end is able to unfold with respect to the point of attachment along a first axis perpendicular to the Z axis in a first direction, and in that a second end is able to unfold according to a second axis perpendicular to the Z axis in a second direction different from the first direction.
    [0003]
    3. deployable structure (10) according to one of the preceding claims, characterized in that it further comprises a mandrel (13) 25 and a shaft (14) substantially parallel to the axis Z, in that the mandrel ( 13) is fixed on the shaft (14), and in that the tape measure (11, 12) is wound around the mandrel (13).
    [0004]
    4. Deployable structure (10) according to one of the preceding claims, characterized in that the arm (15) carries two rollers (20, 21), the rollers being in contact with the measuring tape (11) and in that that the rollers (20, 21) are able to guide the tape measure (11). 3024228 15
    [0005]
    5. Deployable structure (10) according to claim 4, characterized in that the rollers (20, 21) are heating rollers, and in that the rollers (20, 21) are able to locally heat the tape measure (11). ).
    [0006]
    6. deployable structure (10) according to one of claims 4 or 5, characterized in that it further comprises a locking means of the degree of freedom in rotation about the Z axis of the arm (15).
    [0007]
    7. Deployable structure (10) according to claim 6, characterized in that the means for locking the degree of freedom in rotation about the Z axis is a recess of a portion of tape measure (11) in the tree (14).
    [0008]
    8. Deployable structure (10) according to one of claims 6 or 7, the arm (15) having two ends (91, 92) and the mandrel (13) having two ends, characterized in that it comprises two meters -substrips (61, 62) each having two ends (71, 72, 73, 74), a first end (71, 73) of one of the two secondary tape-meters (61, 62) is attached at a distance from a first end (81, 83) of the tape measure (11) and that a second end (72, 74) of the secondary tape measure (61, 62) is attached to one end (91, 92) of mandrel (13).
    [0009]
    9. deployable structure (10) according to claim 8, characterized in that the secondary tape-meters (61, 62) are flat blades.
    [0010]
    10. deployable structure (10) according to one of the preceding claims, characterized in that it further comprises a hinged mast (110) deployable fixed on a platform of a satellite (100) via an engine rotating drive.
    [0011]
    11. Satellite (100) characterized in that it comprises at least one deployable structure (10) according to the preceding claim. 25 30
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    US10263316B2|2013-09-06|2019-04-16|MMA Design, LLC|Deployable reflectarray antenna structure|
    WO2016049476A1|2014-09-26|2016-03-31|Massachusetts Institute Of Technology|Methods and apparatus for deployable sparse-aperture telescopes|
    US9856039B2|2014-10-08|2018-01-02|Analytical Mechanics Associates, Inc.|Extendable solar array for a spacecraft system|
    US10189583B2|2015-05-13|2019-01-29|Analytical Mechanics Associates, Inc.|Deployable sheet material systems and methods|
    FR3048418B1|2016-03-02|2019-04-19|Thales|DEVICE FOR DEPLOYING AND POINTING|
    KR101872612B1|2016-11-10|2018-06-28|한국항공우주연구원|Spacecraft for space debris removal|
    US10326539B2|2017-04-12|2019-06-18|Rohde & Schwarz Gmbh & Co. Kg|Test system and test method|
    FR3098651A1|2019-07-11|2021-01-15|Thales|THREE-DIMENSIONAL DEPLOYMENT DEVICE|
    FR3110552A1|2020-05-20|2021-11-26|Thales|Vehicle in orbit with roll-up and deployable membrane for attitude and orbit control|
    法律状态:
    2015-06-29| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-29| PLSC| Publication of the preliminary search report|Effective date: 20160129 |
    2016-06-28| PLFP| Fee payment|Year of fee payment: 3 |
    2017-06-28| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-28| PLFP| Fee payment|Year of fee payment: 5 |
    2020-06-25| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1401712A|FR3024228B1|2014-07-25|2014-07-25|DEPLOYABLE STRUCTURE WITH METER-RIBBON|
    FR1401712|2014-07-25|FR1401712A| FR3024228B1|2014-07-25|2014-07-25|DEPLOYABLE STRUCTURE WITH METER-RIBBON|
    CA2897024A| CA2897024A1|2014-07-25|2015-07-10|Tape spring deployable structure|
    EP15177172.2A| EP2977323B1|2014-07-25|2015-07-16|Deployable structure with tape-spring|
    JP2015141879A| JP6669445B2|2014-07-25|2015-07-16|Tape spring deployable structure|
    ES15177172T| ES2799423T3|2014-07-25|2015-07-16|Roll-out frame with tape measure|
    US14/805,317| US9669949B2|2014-07-25|2015-07-21|Tape spring deployable structure|
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