• 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 applies to the spatial domain and relates to a gyroscopic actuator (10) with double guidance intended to equip a satellite comprising a main structure (11) connected to a platform (12) of the satellite, a ring, a cradle having a first end (19) and a second end (20), an inertia wheel (21) mounted on the cradle between the first and second ends (19, 20), the inertia wheel (21) being rotatable relative to the cradle around a first axis of rotation (22). According to the invention, it comprises a first bearing (23) positioned at the first end (19) of the cradle and a second bearing (24) positioned at the second end (20) of the cradle connecting the ring to the cradle, the first and second bearings (23, 24) being configured to rotate the cradle relative to the ring about a second axis of rotation (25) substantially perpendicular to the first axis of rotation (22), the ring is connected to the main structure (11), and the gyroscopic actuator (10) comprises at least one suspension element (13) adapted to limit micro-vibrations from the cradle and the flywheel (21) and at least one element of stop (14) adapted to limit a movement of the cradle and the inertia wheel (21) relative to the main structure (11).
    公开号:FR3041327A1
    申请号:FR1501932
    申请日:2015-09-18
    公开日:2017-03-24
    发明作者:Gilles Gans；Xavier Jeandot；Gilles Carte
    申请人:Centre National dEtudes Spatiales CNES；Thales SA；
    IPC主号:
    专利说明:

    GYROSCOPIC ACTUATOR WITH DOUBLE CARDAN GUIDANCE,
    The invention relates to a gyroscopic actuator with double guidance with suspension and abutment elements. The invention can be applied in the spatial field to control and modify the orientation of spacecraft such as satellites.
    A gyroscopic actuator, also known by the abbreviation CMG for its acronym "Control Momentum Gyroscope", has the main function of generating a gyroscopic torque by combining two movements. The constant speed rotation of an inertia wheel according to the axis of rotation of the wheel creates a kinetic moment. Then we impose a kinetic moment velocity in the axis perpendicular to the axis of rotation of the wheel. This axis is called the cardan axis, it is the axis of rotation that rotates the wheel on its transverse axis. This results in a gyroscopic torque of the order of several tens of Newton meters transmitted to the satellite platform. In other words, a gyroscopic actuator generates a gyroscopic torque by the combination of a kinetic moment created by the rotation of a constant speed rotating inertia wheel and the rotational speed of a cardan axis perpendicular to the axis of rotation. of the wheel. A major drawback is that these two rotations generate each of the microvibrations which are then transmitted to the platform and disturb the stability of the line of sight of the satellite observation instrument.
    This principle of operation is shown schematically in Figure 1. The main function of the gyroscopic actuator is achieved by the combination of the kinetic moment H of an inertia wheel and the speed of rotation of a gimbal. The resulting gyroscopic torque is the vector product of H and the rotation speed of the gimbal.
    In the prior art, there are different types of gyroscopic actuator for controlling the attitude of a spacecraft such as a satellite. A disadvantage of the actuators of the prior art comes from the fact that the inertia wheel is offset relative to the drive and guiding part of the gimbal. As a result, the guide portion, and in particular the bearing, takes up all of the bending stresses during the launch phase of the satellite on which the actuator is mounted. As the wheel is not stacked, to hold the important loads of the launch phase, it applies to this bearing some prestressing. However, this preload has the effect of reducing the life of the bearing and therefore of the actuator.
    Another disadvantage of known gyroscopic actuators of the prior art lies in their size which prevents them from keeping in a small volume.
    A further disadvantage of prior art gyroscopic actuators is due to the generation of micro-vibrations due to the rotation of the high-speed flywheel and the rotation of the gimbal. These micro-vibrations can propagate in the satellite platform and disrupt equipment such as for example shooting instruments. The invention aims to overcome all or part of the problems mentioned above by proposing a compact gyroscopic actuator having a specific architecture with a cardan guided by two guiding systems on either side of an inertia wheel and the implantation of suspension and stop elements for filtering at the source the micro-vibrations generated by the rotation of the flywheel and the rotation of the gimbal. For this purpose, the subject of the invention is a gyroscopic double-guide actuator intended to equip a satellite comprising: a main structure connected to a platform of the satellite, a ring, a cradle having a first end and a second end; an inertia wheel mounted on the cradle between the first and second ends, the inertia wheel being able to rotate with respect to the cradle about a first axis of rotation, characterized in that it comprises a first bearing positioned at the first end of the cradle and a second bearing positioned at the second end of the cradle connecting the ring to the cradle, the first and second bearings being configured to rotate the cradle relative to the ring about a second axis of the cradle; rotation substantially perpendicular to the first axis of rotation, and in that the ring is connected to the main structure.
    Advantageously, the gyroscopic actuator according to the invention comprises at least one suspension element capable of limiting microvibrations originating from the cradle and the flywheel.
    Advantageously, the gyroscopic actuator according to the invention further comprises at least one stop element able to limit a movement of the cradle and the inertia wheel relative to the main structure.
    According to one embodiment, the gyroscopic actuator according to the invention may comprise a motorization in the first end of the cradle for driving the cradle in rotation about the second axis of rotation.
    According to another embodiment, the gyroscopic actuator according to the invention may comprise a power transfer element and signals in the second end of the cradle for transferring power and signals between the flywheel and the platform.
    Advantageously, the cradle and the inertia wheel forming a subset having a center of gravity, the subassembly is configured to have its center of gravity on the second axis of rotation.
    Advantageously, the ring, the cradle and the flywheel forming a suspended assembly, the flywheel and the cradle constituting two components of a first block, the suspended assembly and the main structure constituting two components of a second block , the gyroscopic actuator and the platform constituting two components of a third block, the at least one suspension element is positioned between the two components of a block.
    Advantageously, the at least one abutment element is positioned between the two components of a block.
    Advantageously, the ring, the cradle and the flywheel forming a suspended assembly having a center of gravity, the at least one suspension element having an isobarycentre, the at least one suspension element is arranged so that the isobarycentre of the at least one suspension element substantially coincides with the center of gravity of the suspended assembly.
    Advantageously, the at least one abutment element having an isobarycentre, the at least one abutment element is arranged so that the isobarycentre of the at least one abutment element substantially coincides with the center of gravity of the suspended assembly. The invention also relates to a satellite comprising at least three gyroscopic actuators with double cardan guidance as described in this application and configured to manage the orientation of the satellite. The invention will be better understood and other advantages will appear on reading the detailed description of an embodiment given by way of example, a description illustrated by the attached drawing in which: FIG. 1, already commented, illustrates the principle of operation of a gyroscopic actuator, - Figure 2 shows the architecture of a gyroscopic actuator with double guidance according to the invention, - Figure 3 shows the cardan subassembly of the gyroscopic actuator with double guidance according to the invention. FIG. 4 shows the suspended assembly of the double-guide gyroscopic actuator according to the invention; FIG. 5 represents an exemplary configuration of the suspension modules and the stop modules of the gyroscopic actuator; double guidance according to the invention, - Figure 6 shows another example of configuration of the suspension elements and the stop elements of the gyro actuator According to the invention, FIG. 7 shows an embodiment of the main structure of the double-guide gyroscopic actuator according to the invention. FIG. 8 schematically represents a satellite comprising at least three gyroscopic actuators according to the invention. the invention.
    For the sake of clarity, the same elements will bear the same references in the different figures. The gyroscopic double gimbal actuator is designed for the positioning of agile satellites. The invention is based on two main points. First, the gyroscopic actuator has a specific architecture with a cardan guided by two bearings, or guide elements, on either side of an inertia wheel. Moreover, suspension and abutment elements are implanted to filter the micro-vibrations generated at the source by the rotation of the wheel and by the rotation of the cardan subassembly composed by the cradle and the flywheel. Indeed, a gyroscopic actuator generates a gyroscopic torque by the combination of a kinetic moment created by the rotation of an inertia wheel rotating at a constant speed and by the speed of rotation of a cardan axis perpendicular to the axis of rotation. of the wheel. These two rotations generate each of the micro-vibrations which are then transmitted to the satellite platform and disturb the stability of the line of sight of the observation instrument.
    During maneuvering and shooting phases by the scientific instruments on board the satellite, the gyroscopic actuators rotate the cardan shaft, the flywheel being rotated at a constant speed, to create a gyroscopic torque. According to the invention, the microvibrations generated by these two movements are attenuated by the implantation of several suspension elements to reduce the transmission of disturbances to the platform at best. The mobile assembly being suspended by the suspension elements and not stacked during launch, it is necessary to implement stop elements to limit the dynamic movements of the moving mass, that is to say the compound suspended assembly the cardan subassembly and the ring, during launch and transmit launch charges to the main structure with associated attenuation via these stop elements.
    FIG. 2 shows the architecture of a gyroscopic actuator 10 with double guidance according to the invention. The gyroscopic actuator 10 with double guidance is intended to equip a satellite. It comprises a main structure 11 connected to a platform 12 of the satellite, a ring 16, a cradle 18 having a first end 19 and a second end 20 and an inertia wheel 21 mounted on the cradle 18 between the first and second ends 19 , 20, the flywheel 21 being rotatable relative to the cradle 18 about a first axis of rotation 22. According to the invention, the gyroscopic actuator 10 comprises a first bearing 23 positioned at the first end 19 of the cradle 18 and a second bearing 24 positioned at the second end 20 of the cradle 18 connecting the ring 16 to the cradle 18, the first and second bearings 23, 24 being configured to make the cradle 18 rotatable relative to the ring 16 around a second axis of rotation substantially perpendicular to the first axis of rotation 22. According to the invention, the ring 16 is connected to the main structure 11.
    Advantageously, the gyroscopic actuator 10 comprises at least one suspension element 13 able to limit micro-vibrations resulting from the rotation of the cradle 18 and the flywheel 21.
    Advantageously, the gyroscopic actuator 10 according to the invention may further comprise at least one abutment element 14 able to limit a travel of the cradle 18 and the inertia wheel 21 with respect to the main structure 11.
    In this application, with regard to the ring 16, we will speak only of ring to facilitate understanding but the term ring is to be understood in the broad sense. The ring is to be understood as a perforated volume at its center. It may be a solid of revolution such as a torus or any other polyhedron pierced at its center, that is to say a polyhedron whose section may take various forms. The ring can also be a perforated polygon. The ring 16 is perforated so that the flywheel 21 is placed in the opening, the median plane of the ring 16 not necessarily coinciding with that of the flywheel 21.
    In this application, the ring 16 is shown in one piece. It is understood that it is not beyond the scope of the invention considering a ring composed of several sub-parts interconnected by known fastening means. It is the same for the cradle 18 and the main structure 11.
    The cradle 18 and the flywheel 21 form a subassembly called cardan subassembly 17. And the ring 16 and the cardan subassembly 17 form the suspended assembly 15.
    FIG. 3 shows the cardan subassembly 17 of the double guide gyroscopic actuator 10 according to the invention. As previously described, the cardan subassembly 17 is composed of the inertia wheel 21 mounted on the cradle 18, the cradle 18 is guided by two bearings 23, 24, also called guide elements, at these two ends 19, 20. The bearings 23, 24 may be any type of suitable bearings. For example, there may be mentioned plain bearings or preferably rolling bearings, such as, for example, ball bearings or roller bearings. According to the invention, the cardan subassembly 17 may comprise a motor 26 in the first 19 of the two ends of the cradle 18 intended to drive the cradle 18 in rotation about the second axis of rotation 25. The cardan subassembly 17 may comprise a power and signal transfer element 27 in the second 20 of both ends of the cradle 18 for transferring power and signals between the flywheel 21 and the platform. The signals coming from the flywheel 21 may for example be temperature, speed, position signals coming from different sensors present in the flywheel 21. The signal transfer can also take place from the platform to the wheel. , especially for the power for feeding the wheel. The power and signal transfer element 27 may be a contact collector or a contactless transformer. Advantageously, a contactless transformer will be preferred to the collector with contact because this component significantly improves the constraints related to the service life. Indeed, the collector with contact operates by friction between brushes and tracks for the transfer of power and signals. The friction limits the service life of the collector and disrupts the steering of the satellite when changing the direction of rotation of the gimbal. The gyroscopic actuator 10 may also include a position or speed sensor, for example in the first end 19 of the cradle 18. The sensor may be an optical encoder for controlling the position and speed of rotation of the cardan subassembly. 17.
    The second axis of rotation 25, that is to say the axis of rotation of the gimbal, can be inclined at an angle with respect to the interface plane between the main structure 11 and the platform 12 depending on the applications.
    The engine part is generally composed of a motor, a position and / or speed sensor and a main bearing. The ring 16 is a complex piece whose role is to ensure the necessary rigidity of the suspended assembly 15 while interfacing with the cardan subassembly 17 and the suspension elements 13 and stop 14. As previously explained , the ring 16 can have several forms, it is not necessarily circular, and with a section of several possible forms. This piece can be made in additive manufacturing from an optimized organic form.
    The cradle 18 can be made in additive manufacturing from an optimized organic form.
    The cardan subassembly 17 is guided with respect to a ring-shaped structure 16. This assembly, called the suspended assembly 15, is suspended by the suspension element or elements 13.
    FIG. 4 shows the suspended assembly 15 of the gyroscopic actuator 10 with double guidance according to the invention. The cardan subassembly 17, that is to say the ring 16, the cradle 18 and the flywheel 21, has a center of gravity Gc. The cardan subassembly 17 is configured to have its center of gravity on the second axis of rotation 25. This configuration can be obtained by construction, with a particular shape of the cradle 18 and / or the flywheel 21 and thanks to their positioning relative to each other.
    To have its center of gravity on the second axis of rotation 25, the cardan subassembly 17 may comprise at least one feeder 27 so as to position the center of gravity Gc of the cardan subassembly 17 on the second axis of rotation 25. The part rotated about the second axis of rotation 25, or cardan axis, composed essentially of the flywheel 21 and the cradle 18 is balanced in rotation by placing its center of gravity Gc on the axis of rotation 25. One or more balance weights, also called weights 27, are provided on the cradle 18 to adjust the position of the center of gravity Gc of the movable part, that is to say the cardan subassembly 17, on the axis of rotation 25. The number, the positioning, the shape of the balancing masses 27 may vary according to the configuration considered. In FIG. 4, they are positioned on one face of the cradle 18, nevertheless, they could also be positioned on another face of the cradle 18 or on the flywheel 21. The positioning of the center of gravity Gc of the cardan subassembly 17 on the axis of rotation 25 prevents the flywheel 21 from rotating during launching and limits the micro-vibrations generated by the rotation of the cardan sub-assembly 17. If these micro-vibrations are not limited, the performance is then degraded.
    FIG. 5 represents an exemplary configuration of the suspension elements 13 and the stop elements 14 of the double guide gyroscopic actuator 10 according to the invention. This example gives a configuration with four suspension elements 13 and four abutment elements 14 whose axes are positioned in the same plane, the axes pointing towards the center of gravity Gs of the suspended assembly 15. The invention is based on the fact that to use suspension elements 13 and abutment 14 to perform a micro-vibration filtering function generated by the rotation of the flywheel 21 and the drive of the gimbal during maneuvering phases and satellite shots by via suspension elements 13, as well as to perform a launch load-holding function thanks to the abutment elements 14.
    Depending on the mobile mass and the filter performance to be achieved, these elements 13, 14 can be multiplied around the mobile load to meet the desired need. In FIG. 5, the number of suspension elements 13 is equal to the number of abutment elements 14, but this is not necessarily the case. The number of suspension elements 13 may be different from the number of abutment elements 14.
    The suspension elements 13 and the abutment elements 14 are mounted between the set to isolate exported micro-vibration generator and the main structure 11 connected to the platform. It may be noted that the suspension elements 13 and the abutment elements 14 of the invention can be dimensioned specifically according to the use made of it, but also it is important to emphasize that they can be elements standard suspension and stop without the need to resize them regardless of the gyro actuator. Indeed, the modularity of these suspension elements 13 and stop elements 14 allows to choose the number of elements and arrange these elements depending on the performance to be achieved, the suspended mobile mass, efforts to launch.
    In this application, we distinguish between a suspension element 13 and a stop element 14. Nevertheless, the invention applies similarly to a common element which is both a suspension and abutment element. In other words, it is possible to apply the invention with an element having both the role of a suspension element and a stop element The suspension element 13 and the abutment element 14 are used for complementary way: indeed during the launch, the stop element 14 provides the holding function. Moving the moving load is limited and amortized. In other words, the movement of the moving load is controlled. When shooting, the suspension elements 13 filter the micro-vibrations generated by the suspended assembly 15 without contact at the stop element 14. The stiffness of the suspension elements 13 is lower than the stiffness of the elements abutment 14, typically a factor 10. At launch, the suspension element 13 follows the deformation of the abutment element 14.
    More specifically, a three-dimensional game is created around the abutment element 14. The suspension element 13 works and filters the microvibrations. The combined rotations of the flywheel 21 and the cradle 18 generate a gyroscopic torque to be transmitted to the platform. During the generation of the gyroscopic torque, the suspension element 13 is deformed until the stop element 14 takes over. The stop element 14 deforms when the game is caught and there is contact with the abutment element 14. The gyroscopic torque is then transmitted to the platform essentially by the abutment element 14.
    The suspension elements 13 can be placed in the same plane, the isobarycentre of all of these elements is advantageously coincident with, or substantially coincides with, the center of gravity of the suspended assembly 15. The axes of these elements can be placed in the same plane or not. Advantageously, one can choose to place the axes of these suspension elements 13 equidistant from the center of gravity of the suspended assembly 15 and point or not toward the center of gravity of the suspended assembly 15.
    The abutment elements 14 can also be placed in the same plane, the isobarycentre of all these elements is advantageously coincident with, or substantially coincides with, the center of gravity of the suspended assembly 15. The axes of these elements can be placed in the same plane or not and point or not towards the center of gravity of the suspended assembly 15.
    The planes containing the axes of the suspension elements 13 and the abutment elements 14 may or may not be merged. For example, one can choose to place the axes of the suspension elements 13 and the abutment elements 14 in the same plane and that this plane contains the center of gravity of the suspended assembly 15.
    The suspension elements 13 and the abutment members 14 can also be arranged as required with different angles to place the isobarycentre of the suspension elements 13 and / or abutment elements 14 at the center of gravity of the suspended assembly 15 .
    The stiffness of the suspension element 13 is lower than the stiffness of the abutment element 14, the aim being that the stiffness of the abutment element 14 ensures all the mechanical strength of the mobile part during launching. In the shooting mode, the suspension element 13 filters the micro-vibrations generated by the rotation of the wheel 21 and the rotation of the cradle 18, the abutment element 14 is not stressed: a functional game is present all around the stop.
    In general, the flywheel 21 and the cradle 18 constituting two components of a first block, the suspended assembly 15 and the main structure 11 constituting two components of a second block, the gyroscopic actuator 10 and the platform constituting two components of a third block, it can be said that the at least one suspension element 13 is positioned between the two components of a block. Similarly, the at least one abutment element 14 is positioned between the two components of a block. It is therefore possible to note the total modularity of the suspension elements 13 and the abutment elements 14 both as regards the number of each of the elements and the positioning of these elements. In other words, it is possible to position the suspension element or elements 13 and / or the abutment element or elements 14 between the flywheel 21 and the cradle 18 and / or between the suspended assembly 15 and the main structure 11 and or between the gyroscopic actuator 10 and the platform 12. For each of the configurations (between the flywheel 21 and the cradle 18, between the suspension assembly 15 and the main structure 11, between the gyroscopic actuator 10 and the platform 12), the suspension elements 13 and / or abutment 14 may be uniformly distributed or not between the two components of the corresponding block and the orientation of the suspension elements 13 may be the same for all the suspension elements, but may also differ. It is the same for the stop elements 14. In addition the suspension elements 13 can be oriented in the same way as the stop elements 14 but can also be oriented differently. The modularity of these elements is total.
    FIG. 6 represents another exemplary configuration of the suspension elements 13 and the stop elements 14 of the double guide gyroscopic actuator 10 according to the invention.
    The suspension elements 13 and abutment 14 can be distributed as desired both by their number and by their position on the ring 16. The suspended assembly 15 has a center of gravity Gs, the at least one suspension element 13 has a isobarycenter. And the at least one suspension element 13 is arranged so that the isobarycentre of the at least one suspension element 13 coincides substantially with the center of gravity Gs of the suspended assembly 15. Similarly, the at least one element stop 14 has an isobarycenter. The at least one abutment element 14 is arranged so that the isobarycentre of the at least one abutment element 14 substantially coincides with the center of gravity Gs of the suspended assembly 15.
    A preferred solution is to place the isobarycentre of all of the elements 13, 14 coincides with the center of gravity Gs of the suspended assembly 15.
    These suspension elements 13 and abutment 14 may be uniformly distributed or not around the moving assembly.
    The planes containing the suspension elements 13 and the abutment elements 14 may be merged or not.
    The suspension elements 13 and abutment 14 also limit the loads incurred by the equipment mounted on the suspended assembly 15. For example, the shock levels injected at the base of the CMG, that is to say between the main structure 11 and the platform 12, are filtered by the suspension elements 13 and abutment 14. This solution makes it possible to implement shock-sensitive elements on the suspended assembly 15, in particular the optical encoder and the flywheel 21.
    FIG. 7 represents an embodiment of the main structure 11 of the double guide gyroscopic actuator 10 according to the invention. The main structure 11 supporting the suspended assembly 15 can be made in additive manufacturing from an optimized organic form. This possibility makes it possible to obtain a main structure 11 of the desired shape, stiffness and holding with a considerable weight gain compared to a traditional main structure as represented in FIG. 2. For example, a main structure as represented in FIG. 2 weighs 9 kg while the main structure shown in Figure 7 weighs only 3 kg. The main structure 11 can take any desired shape, it is possible to choose the angle of inclination of the second axis of rotation 25. In Figure 2, this angle is about 30 °, but the possible adaptation the shape of the main structure 11 allows to have any angle of inclination.
    Thus, the invention proposes a gyroscopic actuator solution with two guides and a smaller motor, by integrating the suspensions into the actuator as close as possible to the micro-vibration generating components and by producing a completely suspended universal joint assembly. The ring allows to clear a lot of room to be able to place the elements of suspension and stop.
    The advantages of this solution are a reduction of microvibrations transmitted to the platform, with the possibility of placing a suspension system if necessary, the limitation of friction through the use of a contactless transformer to pass the power and signals of the wheel, which promotes the service life and increases the performance of the gyroscopic actuator because there is no dry friction torque from the collector. Another major advantage is the modularity of the suspension elements and the stop elements. The number of elements can be multiplied and it is possible to develop them to comply with the need based on the need for filtering, the suspended mass, the position of the center of gravity. A major advantage is the filtering of microvibrations generated at the source to avoid the amplification effect of these micro-vibrations. In addition, the stop elements make it possible to overcome an expensive stacking system. According to the invention, the moving load is not stacked thanks to the use of stop elements. Finally, the onboard equipment is protected by limiting the loads at launch by the abutment elements. The invention also relates to a satellite comprising at least three gyroscopic actuators as described above and configured to manage the orientation of the satellite. FIG. 8 schematically represents a satellite 100 comprising at least three gyroscopic actuators 10 according to the invention. Advantageously, the satellite 100 may comprise four or more gyroscopic actuators to provide redundancy in the event of a failure of one of the gyroscopic actuators.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    A gyroscopic actuator (10) with double guidance for equipping a satellite comprising: - a main structure (11) connected to a platform (12) of the satellite, - a ring (16), - a cradle (18) having a first end (19) and a second end (20), - an inertia wheel (21) mounted on the cradle (18) between the first and second ends (19, 20), the inertia wheel (21) being movable in rotation relative to the cradle (18) around a first axis of rotation (22), characterized in that it comprises a first bearing (23) positioned at the first end (19) of the cradle (18) and a second bearing (24) positioned at the second end (20) of the cradle (18) connecting the ring (16) to the cradle (18), the first and second bearings (23, 24) being configured to make the cradle (18) movable by rotation relative to the ring (16) about a second axis of rotation (25) substantially perpendicular to the first axis of rotation (22) , and in that the ring (16) is connected to the main structure (11).
    [2" id="c-fr-0002]
    2. Gyroscopic actuator (10) according to the preceding claim, characterized in that it comprises at least one suspension element (13) adapted to limit micro-vibrations from the cradle (18) and the flywheel (21). .
    [3" id="c-fr-0003]
    3. Gyroscopic actuator (10) according to any one of the preceding claims, characterized in that it further comprises at least one stop element (14) adapted to limit a movement of the cradle (18) and the flywheel (21) with respect to the main structure (11).
    [4" id="c-fr-0004]
    4. Gyroscopic actuator (10) according to any one of the preceding claims, characterized in that it comprises a motor in the first end (19) of the cradle (18) for driving the cradle (18) in rotation around the second rotation axis (25).
    [5" id="c-fr-0005]
    A gyro actuator (10) according to any one of the preceding claims, characterized in that it comprises a power and signal transfer element (27) in the second end (20) of the cradle (18) for transferring power and signals between the flywheel (21) and the platform (12).
    [6" id="c-fr-0006]
    A gyro actuator (10) as claimed in any one of the preceding claims, the cradle (18) and the inertia wheel (21) forming a subassembly (17) having a center of gravity, characterized in that the sub-assembly assembly (17) is configured to have its center of gravity on the second axis of rotation (25).
    [7" id="c-fr-0007]
    A gyro actuator (10) according to any one of claims 2 to 6 as dependent claims of claim 2, the ring (16), the cradle (18) and the flywheel (21) forming an assembly. suspended (15), the inertia wheel (21) and the cradle (18) constituting two components of a first block, the suspended assembly (15) and the main structure (11) constituting two components of a second block, the gyroscopic actuator (10) and the platform (12) constituting two components of a third block, characterized in that the at least one suspension element (13) is positioned between the two components of a block.
    [8" id="c-fr-0008]
    A gyro actuator (10) as claimed in any one of claims 3 to 7 as dependent claims of claim 3, the ring (16), the cradle (18) and the flywheel (21) forming an assembly. suspended (15), the inertia wheel (21) and the cradle (18) constituting two components of a first block, the suspended assembly (15) and the main structure (11) constituting two components of a second block, the gyroscopic actuator (10) and the platform (12) constituting two components of a third block, characterized in that the at least one abutment element (14) is positioned between the two components of a block.
    [9" id="c-fr-0009]
    The gyro actuator (10) according to any one of claims 2 to 8 as dependent claims of claim 2, the ring (16), the cradle (18) and the flywheel (21) forming an assembly. suspended (15) having a center of gravity, the at least one suspension element (13) having an isobarycenter, characterized in that the at least one suspension element (13) is arranged so that the isobarycenter from to at least one suspension element (13) substantially coincides with the center of gravity of the suspended assembly (15).
    [10" id="c-fr-0010]
    A gyro actuator (10) according to any one of claims 3 to 9 as dependent claims of claim 3, the ring (16), the cradle (18) and the flywheel (21) forming an assembly. suspension device (15) having a center of gravity, the at least one abutment element (14) having an isobarycenter, characterized in that the at least one abutment element (14) is arranged in such a way that the isobarycenter from least one abutment element (14) substantially coincides with the center of gravity of the suspended assembly (15).
    [11" id="c-fr-0011]
    11. Satellite (100) characterized in that it comprises at least three gyroscopic actuators (10) according to any one of the preceding claims configured to manage the orientation of the satellite.
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    同族专利:
    公开号 | 公开日
    US20170081050A1|2017-03-23|
    EP3144228A1|2017-03-22|
    FR3041327B1|2019-05-31|
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    法律状态:
    2016-08-26| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-24| PLSC| Publication of the preliminary search report|Effective date: 20170324 |
    2017-08-29| PLFP| Fee payment|Year of fee payment: 3 |
    2018-08-28| PLFP| Fee payment|Year of fee payment: 4 |
    2019-08-29| PLFP| Fee payment|Year of fee payment: 5 |
    2020-08-26| PLFP| Fee payment|Year of fee payment: 6 |
    2021-08-26| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1501932A|FR3041327B1|2015-09-18|2015-09-18|GYROSCOPIC ACTUATOR WITH DOUBLE CARDAN GUIDANCE, SUSPENSION ELEMENT AND STOPPER ELEMENT|
    FR1501932|2015-09-18|FR1501932A| FR3041327B1|2015-09-18|2015-09-18|GYROSCOPIC ACTUATOR WITH DOUBLE CARDAN GUIDANCE, SUSPENSION ELEMENT AND STOPPER ELEMENT|
    EP16188885.4A| EP3144228A1|2015-09-18|2016-09-15|Gyroscopic actuator with dual gimbal guidance, suspension member and abutment element|
    US15/267,737| US20170081050A1|2015-09-18|2016-09-16|Gyroscopic actuator with double gimbal guidance, suspension element and end-stop element|
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