A multi-directional damper suitable for large flexible solar wings and a method of operation thereof

Abstract

The application provides a multi-directional damper suitable for a large flexible solar wing and a working method thereof, and belongs to the technical field of space product structure and mechanism design. The problem that vibration suppression of the large flexible solar wing cannot meet the demand is solved. The multi-directional damper comprises a solar wing fixed section, a force transmission driving section, a damping section and a satellite fixed section which are sequentially connected, the solar wing fixed section comprises a solar wing connecting column, a universal ball seat, a fixed cover plate and a rectangular spring, the force transmission driving section comprises a force transmission driving section outer cylinder, a force transmission gear set, a transverse force transmission mechanism, a lead screw shaft and a longitudinal force transmission block, the damping section comprises a damping section outer cylinder, a magnetic steel, a ball nut and a damping copper ring, and the satellite fixed section comprises a satellite fixed section outer cylinder, a return spring and a spring seat. The multi-directional damper is mainly used for vibration suppression of the large flexible solar wing.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of space product structure and mechanism design, and particularly relates to a multi-directional damper suitable for a large-flexibility solar wing and a working method thereof. BACKGROUND

[0002] In recent years, with the increasing demand for satellite power, the area of the solar wing is also increasing, among which, the communication satellite and synthetic aperture radar satellite are particularly prominent, and the area of the solar wing is often several times or even dozens of times the area of the satellite cabin plate; at the same time, in order to reduce the difficulty of folding and unfolding, the large-size solar wing often adopts flexible materials, thus causing the large-flexibility attribute of this type of solar wing.

[0003] The in-orbit vibration of the large-flexibility solar wing has two characteristics: one is low-frequency and large-amplitude vibration, and the first few modes even reach 10 -2 Hz level; the other is that the vibration mode of the flexible vibration is mainly transverse swinging, and the vibration along the installation axis is less and basically in the high-frequency band. The flexible vibration acting on the satellite body will seriously interfere with the satellite attitude control, and the vibration characteristics determine that the traditional attitude controller based on the rigid model cannot effectively suppress this coupled vibration, and even may excite instability, such as inducing limit cycle oscillation. Therefore, it is necessary to take targeted suppression measures based on the large-flexibility vibration.

[0004] At present, the commonly used method for in-orbit vibration suppression is active vibration suppression control and passive vibration suppression control.

[0005] The active vibration suppression control actively suppresses and eliminates vibration through real-time monitoring and feedback adjustment, and the core is to detect the vibration signal by using a sensor, process and generate a control instruction by using a controller, and drive an actuator to apply a reaction force, so as to offset or weaken the vibration. However, the system thereof is complex, the cost is high, the weight is heavy, the environment is sensitive, the real-time requirement is high, and the algorithm is complex, thus greatly limiting the application range thereof.

[0006] The passive vibration suppression control suppresses vibration by changing the structure of the system or adding damping, and compared with the active vibration suppression control, the passive vibration suppression control has the advantages of low cost, high reliability, and easy implementation. In the field of aerospace, rubber pads, silicone pads, springs and other structures are often used to realize damping and vibration isolation effect, but they almost cannot suppress low-frequency vibration, and thus are not suitable for vibration suppression of large-flexibility solar wings. The damper applied in the field of civil engineering, such as the tuned damper and the high-performance viscous damper, can suppress low-frequency vibration, but the suppression direction thereof is often fixed, and a large damping stroke is required in the suppression direction, and thus the damper cannot be applied to the vibration suppression of the large-flexibility solar wing with multi-directional vibration mode and limited transverse damping stroke. SUMMARY

[0007] In view of the above, the present application aims to provide a multi-directional damper suitable for large flexible solar wings and a working method thereof to solve the problem that vibration suppression of large flexible solar wings cannot meet the requirements.

[0008] To achieve the above object, the present application adopts the following technical scheme: a multi-directional damper suitable for large flexible solar wings, which comprises a solar wing fixed section, a force transmission driving section, a damping section and a satellite fixed section connected in sequence, the solar wing fixed section comprises a solar wing connecting column, a universal ball seat, a fixed cover plate and a rectangular spring, the fixed cover plate and the rectangular spring are sleeved on the solar wing connecting column, one end of the rectangular spring is connected with the solar wing connecting column, and the other end is connected with the fixed cover plate, a universal ball is arranged at the end of the solar wing connecting column, the universal ball is connected with the universal ball seat, the force transmission driving section comprises a force transmission driving section outer cylinder, a force transmission gear set, a horizontal force transmission mechanism, a lead screw shaft and a longitudinal force transmission block, the fixed cover plate is connected with the force transmission driving section outer cylinder, the universal ball seat and the longitudinal force transmission block are arranged in the force transmission driving section outer cylinder, the number of the horizontal force transmission mechanisms is plural, the plural horizontal force transmission mechanisms are arranged in the circumferential direction of the force transmission driving section outer cylinder, the upper parts of the plural horizontal force transmission mechanisms are spliced into a cylindrical structure, the spliced cylindrical structure is located outside the solar wing connecting column, each horizontal force transmission mechanism is connected with the force transmission gear set below, the longitudinal force transmission block is provided with a rack, the rack is engaged with the force transmission gear set, the lead screw shaft is connected with the longitudinal force transmission block, the damping section comprises a damping section outer cylinder, a magnetic steel, a ball nut and a damping copper ring, the damping copper ring is rotatably connected in the damping section outer cylinder, the damping copper ring is provided with a magnetic steel on each of the upper and lower sides, the adjacent magnetic poles of the two magnetic steels are opposite, a spacer is arranged between the damping copper ring and the magnetic steel, the damping copper ring is provided with the ball nut, the lead screw shaft is connected with the ball nut in cooperation, the satellite fixed section comprises a satellite fixed section outer cylinder, a return spring and a spring seat, the satellite fixed section outer cylinder is provided with the return spring, the upper end of the return spring is connected with the spring seat, and the lead screw shaft passes through the damping section and abuts against the spring seat.

[0009] Furthermore, the universal ball seat is provided with rubber pads on the upper and lower sides, the upper part of the solar wing connecting column is a solar wing mounting surface, the lower part of the solar wing connecting column is connected with the universal ball through a connecting shaft, the universal ball seat is provided with a hemispherical arc surface, the universal ball is arranged in cooperation with the hemispherical arc surface, and the universal ball seat is of a split structure.

[0010] Further, the power transmission gear set comprises a plurality of gears, which are divided into a first gear, a second gear and a third gear, a gear frame is arranged on the power transmission driving section outer cylinder, the gear frame is divided into a first gear frame and a second gear frame, a third gear hole is formed on the power transmission driving section outer cylinder, the first gear is rotatably connected to the first gear frame, the first gear is connected to the transverse power transmission mechanism, the second gear and the third gear are coaxially rotatably connected to the second gear frame, the first gear is engaged with the second gear, and the third gear passes through the third gear hole and is engaged with the rack.

[0011] Further, the gear is connected to the gear frame through a rotating shaft, a small bearing is arranged between the rotating shaft and the gear frame, a circlip is arranged outside the small bearing, the rotating shaft is divided into a first rotating shaft and a second rotating shaft, the first gear is connected to the first gear frame through the first rotating shaft, and the second gear and the third gear are connected to the second gear frame through the second rotating shaft.

[0012] Further, the transverse power transmission mechanism comprises a transverse power transmission rod and a transverse power transmission cover, an installation surface is arranged on the upper end of the transverse power transmission rod, the transverse power transmission cover comprises an installation table and a transverse power transmission surface, the transverse power transmission surface is located outside the solar wing connecting column, the transverse power transmission surface is in a circular arc structure, an installation table is arranged outside the transverse power transmission surface, the installation table is connected to the installation surface, an embedding groove is formed in the lower part of the transverse power transmission rod, an embedding opening is arranged on the gear, the embedding groove is embedded with the embedding opening, a stop groove is formed in the gear and the transverse power transmission rod, a stop key and a circlip groove are arranged on the rotating shaft, the stop key is connected to the stop groove in a matched mode, and the circlip is installed on the circlip groove.

[0013] Further, a threaded groove is arranged on the lead screw shaft, the threaded groove is matched with balls in the ball nut, a fixing pin is arranged on the upper end of the lead screw shaft, a pin groove is arranged in the center of the longitudinal power transmission block, the fixing pin is inserted into the pin groove, and the lead screw shaft is connected to the longitudinal power transmission block through a bolt.

[0014] Further, the damping copper ring is connected to the damping section outer cylinder through a large bearing, and a partition plate is arranged on the upper end and the lower end of the damping section outer cylinder.

[0015] Further, the lower end of the satellite fixing section outer cylinder is a satellite installation surface, a lead screw blind hole is formed in the spring seat, and the lead screw shaft is inserted into the lead screw blind hole.

[0016] Further, the number of damping sections is multiple, and the multiple damping sections are connected in sequence.

[0017] The application further provides a working method of the multi-directional damper suitable for the large flexible solar wing, and specifically, the solar wing connecting column is directly or indirectly connected to the solar wing.

[0018] When the solar wing occurs lateral vibration, the solar wing swings, the solar wing connecting column pushes the lateral force transmission mechanism to rotate around the universal ball, the lateral force transmission mechanism drives the force transmission gear set to rotate, the force transmission gear set drives the longitudinal force transmission block to move downward through the meshing with the rack, and then drives the lead screw shaft to move linearly downward against the elastic force of the reset spring, in the process, since the ball nut is axially fixed, the damping copper ring rotates around the shaft under the lead screw shaft, the rotating damping copper ring moves between the two magnetic steels to cut the magnetic induction lines, thereby generating an eddy current resistance, forming a damping force to suppress the rotation of the damping copper ring, and suppressing the lateral vibration of the solar wing;

[0019] When the solar wing occurs axial vibration, the solar wing moves along the axial direction, the solar wing connecting column pushes the universal ball seat to move downward, the universal ball seat pushes the longitudinal force transmission block to move downward, and then drives the lead screw shaft to move linearly downward against the elastic force of the reset spring, in the process, since the ball nut is axially fixed, the damping copper ring rotates around the shaft under the lead screw shaft, the rotating damping copper ring moves between the two magnetic steels to cut the magnetic induction lines, thereby generating an eddy current resistance, forming a damping force to suppress the rotation of the damping copper ring, and suppressing the axial vibration of the solar wing;

[0020] When the solar wing occurs small-amplitude lateral vibration, the solar wing connecting column does not contact the lateral force transmission mechanism, at this time, the small-amplitude lateral vibration of the solar wing is suppressed by the elastic force of the rectangular spring after bending;

[0021] When the solar wing occurs small-amplitude longitudinal vibration, the stroke of the solar wing connecting column pushing the longitudinal force transmission block is insufficient to generate an eddy current resistance, at this time, the small-amplitude longitudinal vibration of the solar wing is suppressed by the elastic force of the rectangular spring after compression.

[0022] Compared with the prior art, the beneficial effects of the present application are:

[0023] (1) The multi-directional damper suitable for large flexible solar wings can realize lateral, longitudinal and combined vibration suppression effects, and can meet the vibration suppression needs of the solar wings in orbit, mainly with lateral swing, supplemented by longitudinal vibration, and combined with vibration mode.

[0024] (2) The multi-directional damper suitable for large flexible solar wings can suppress low-frequency large-amplitude vibration by means of eddy current damping, and is suitable for the vibration suppression needs of large flexible solar wings.

[0025] (3) The multi-directional damper suitable for large flexible solar wings realizes compact design in the lateral direction while meeting multi-directional damping, avoiding the installation burden caused by complex design in the lateral direction.

[0026] (4) The multi-directional damper suitable for large flexible solar wing of the present application changes the linear motion of the screw shaft into the rotary motion of the damping copper ring, changes the linear damping into rotary damping, and realizes the effect of shortening the damping demand stroke.

[0027] (5) The multi-directional damper suitable for large flexible solar wing of the present application is passive vibration suppression control, which has low cost, high reliability and easy implementation compared with active vibration suppression control.

[0028] (6) The multi-directional damper suitable for large flexible solar wing of the present application is a passive mechanism, which does not require any power supply or electrical signal requirement, and does not increase the additional energy or electrical interface burden of the whole satellite.

[0029] (7) The multi-directional damper suitable for large flexible solar wing of the present application avoids static friction in the damping process by the setting of the ball nut and bearing, reduces dynamic friction in the damping process, and realizes the suppression of flexible vibration through as much smooth and stable eddy current damping as possible, avoiding the vibration rigidity transmission caused by friction damping.

[0030] (8) The multi-directional damper suitable for large flexible solar wing of the present application has a wide vibration suppression frequency band, which can not only effectively suppress flexible vibration, but also suppress high-frequency vibration.

[0031] (9) The multi-directional damper suitable for large flexible solar wing of the present application can further adjust the damping and suppression frequency band range through various means.

[0032] (10) The multi-directional damper suitable for large flexible solar wing of the present application is composed of multiple independent parts, which can realize the effect of split synchronous assembly and general assembly, and has high assembly efficiency.

[0033] (11) The multi-directional damper suitable for large flexible solar wing of the present application is independent of each other, and can be designed / selected according to the specific requirements of the satellite, and the device has strong adaptability. BRIEF DESCRIPTION OF DRAWINGS

[0034] The accompanying drawings, which form a part of the present application, are used to provide further understanding of the present application, and the schematic embodiments of the present application and their descriptions are used to explain the present application, and do not constitute improper limitations on the present application. In the drawings:

[0035] Figure 1 The accompanying drawings, which form a part of the present application, are used to provide further understanding of the present application, and the schematic embodiments of the present application and their descriptions are used to explain the present application, and do not constitute improper limitations on the present application. In the drawings:

[0036] Figure 2 The accompanying drawings, which form a part of the present application, are used to provide further understanding of the present application, and the schematic embodiments of the present application and their descriptions are used to explain the present application, and do not constitute improper limitations on the present application. In the drawings:

[0037] Figure 3The sectional structure diagram of the solar wing fixed section of the present application is shown in the figure;

[0038] Figure 4 The structure diagram of the solar wing connecting column of the present application is shown in the figure;

[0039] Figure 5 The structure diagram of the universal ball seat of the present application is shown in the figure;

[0040] Figure 6 The structure diagram of the rectangular spring of the present application is shown in the figure;

[0041] Figure 7 The installation process diagram of the solar wing fixed section of the present application is shown in the figure Figure 1 ;

[0042] Figure 8 The installation process diagram of the solar wing fixed section of the present application is shown in the figure Figure 2 ;

[0043] Figure 9 The first motion form diagram of the solar wing fixed section of the present application is shown in the figure;

[0044] Figure 10 The second motion form diagram of the solar wing fixed section of the present application is shown in the figure;

[0045] Figure 11 The structure diagram of the force transmission driving section of the present application is shown in the figure;

[0046] Figure 12 The sectional structure diagram of the force transmission driving section of the present application is shown in the figure;

[0047] Figure 13 The outer tube structure diagram of the force transmission driving section of the present application is shown in the figure;

[0048] Figure 14 The first gear structure diagram of the present application is shown in the figure;

[0049] Figure 15 The transverse force transmission rod structure diagram of the present application is shown in the figure;

[0050] Figure 16 The transverse force transmission cover structure diagram of the present application is shown in the figure;

[0051] Figure 17 The lead screw shaft structure diagram of the present application is shown in the figure;

[0052] Figure 18 The longitudinal force transmission block structure diagram of the present application is shown in the figure;

[0053] Figure 19 The first rotating shaft structure diagram of the present application is shown in the figure;

[0054] Figure 20 A second rotating shaft structure according to the present application is shown in the figure;

[0055] Figure 21 A force transmission driving segment installation process according to the present application is shown in the figure Figure 1 ;

[0056] Figure 22 A force transmission driving segment installation process according to the present application is shown in the figure Figure 2 ;

[0057] Figure 23 A force transmission driving segment installation process according to the present application is shown in the figure Figure 3 ;

[0058] Figure 24 A force transmission driving segment movement form according to the present application is shown in the figure;

[0059] Figure 25 A damping segment cross-sectional structure according to the present application is shown in the figure;

[0060] Figure 26 A satellite fixing segment cross-sectional structure according to the present application is shown in the figure;

[0061] Figure 27 A multi-directional damper assembly structure cross-sectional view suitable for a large flexible solar wing according to the present application is shown in the figure;

[0062] Figure 28 A multi-directional damper installation structure overall view suitable for a large flexible solar wing according to the present application is shown in the figure;

[0063] Figure 29 A multi-directional damper installation structure partial view suitable for a large flexible solar wing according to the present application is shown in the figure;

[0064] Figure 30 A multi-directional damper X-directional flexible vibration suppression view suitable for a large flexible solar wing according to the present application is shown in the figure Figure 1 ;

[0065] Figure 31 A multi-directional damper X-directional flexible vibration suppression view suitable for a large flexible solar wing according to the present application is shown in the figure Figure 2 ;

[0066] Figure 32 A multi-directional damper transverse composite flexible vibration suppression view suitable for a large flexible solar wing according to the present application is shown in the figure;

[0067] Figure 33 A multi-directional damper Z-directional flexible vibration suppression view suitable for a large flexible solar wing according to the present application is shown in the figure.

[0068] In the figure:

[0069] 1-Solar fin fixing section, 2-Force transmission drive section, 3-Damping section, 4-Satellite fixing section, 5-Solar fin connecting column, 6-Universal ball seat, 7-Fixing cover plate, 8-Rectangular spring, 9-Rubber pad, 10-Solar fin mounting surface, 11-Connecting shaft, 12-Universal ball, 13-Hemispherical arc surface, 14-Mounting countersunk hole, 15-Force transmission drive section outer cylinder, 16-First gear, 17-Second gear, 18-Third gear, 19-Transverse force transmission rod, 20-Transverse force transmission cover, 21-Lead screw shaft, 22-Longitudinal force transmission block, 23-First rotating shaft, 24-Second rotating shaft, 25-Small bearing, 26-Snap ring, 27-First gear frame, 28-Second gear frame Gear carrier, 29-Third gear hole, 30-Stop groove, 31-Matching opening, 32-Matching groove, 33-Mounting surface, 34-Mounting platform, 35-Transverse force transmission surface, 36-Threaded groove, 37-Fixing pin, 38-Rack, 39-Pin groove, 40-Stop key, 41-Snap ring groove, 42-Damping section outer cylinder, 43-Magnet, 44-Large bearing, 45-Ball nut, 46-Damping copper ring, 47-Blocking plate, 48-Blocking cylinder, 49-Satellite fixing section outer cylinder, 50-Reset spring, 51-Spring seat, 52-Satellite mounting surface, 53-Blind hole of lead screw, 54-Solar wing, 55-Solar wing drive mechanism, 56-Satellite body. Detailed Implementation

[0070] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of the present invention can be combined with each other, and the described embodiments are only some embodiments of the present invention, not all embodiments.

[0071] See Figures 1-33 This implementation method is described as follows: Figure 1 As shown, a multi-directional damper suitable for a large flexible solar array includes a solar array fixed section 1, a force transmission drive section 2, a damping section 3, and a satellite fixed section 4 connected in sequence.

[0072] like Figure 2 and Figure 3 As shown, the solar wing fixing section 1 includes a solar wing connecting post 5, a universal ball seat 6, a fixing cover plate 7, and a rectangular spring 8. The fixing cover plate 7 and the rectangular spring 8 are both sleeved on the solar wing connecting post 5. One end of the rectangular spring 8 is connected to the solar wing connecting post 5, and the other end is connected to the fixing cover plate 7. A universal ball 12 is provided at the end of the solar wing connecting post 5, and the universal ball 12 is connected to the universal ball seat 6. Rubber pads 9 are provided on both the upper and lower sides of the universal ball seat 6. The solar wing connecting post 5 is as follows... Figure 4As shown, the upper part of the solar fin connecting post 5 is the solar fin mounting surface 10, and the lower part of the solar fin connecting post 5 is connected to the universal ball joint 12 via the connecting shaft 11. The universal ball joint 6 is as follows: Figure 5 As shown, the universal ball seat 6 has a hemispherical arc surface 13, and the universal ball 12 is configured to cooperate with the hemispherical arc surface 13. The universal ball seat 6 is a split structure, that is, two universal ball seats 6 are spliced ​​together, and the two hemispherical arc surfaces 13 cooperate with the universal ball 12. The rectangular spring 8 is as follows. Figure 6 As shown, the rectangular spring 8 has a rectangular cross-section and a countersunk hole 14. Its two ends can be fixed to the solar panel connecting post 5 and the fixing cover plate 7 respectively by countersunk screws.

[0073] The installation process of the solar panel fixing section 1 is as follows: Step 1, as... Figure 7 As shown, the rectangular spring 8, the fixing cover plate 7, and the two rubber pads 9 are fitted onto the connecting shaft 11 in the corresponding order. The second step is as follows... Figure 8 As shown, fasten the two universal ball seats 6 onto the universal ball 12 from both sides, and lock the two universal ball seats 6 with screws. Then, attach the rubber pads 9 on the upper and lower sides of the universal ball seats 6 to the surface of the universal ball seats 6. In the third step, use countersunk screws to fix the top of the rectangular spring 8 to the sun wing connecting post 5 and the bottom to the fixing cover plate 7.

[0074] In this embodiment, the fixed section 1 of the solar array has two motion states, one of which is longitudinal motion, such as... Figure 9 As shown, the assembly of the solar fin connecting column 5, the universal ball seat 6, and the rubber pad 9 overcomes the elastic force of the rectangular spring 8 during compression and undergoes displacement; the second is lateral swinging, such as... Figure 10 As shown, the solar wing connecting post 5, constrained by the universal ball 12 and the hemispherical arc surface 13, swings outward around the universal ball 12 as its center. Simultaneously, it overcomes the bending force of the rectangular spring 8, causing an angular deflection. This motion is an arbitrary lateral swing around the universal ball 12. Furthermore, because the rectangular spring 8 connecting the solar wing connecting post 5 and the fixed cover plate 7 has a relatively wide cross-section, the torsional resistance at both ends of the connection is large, making relative rotation around the axis between the solar wing connecting post 5 and the fixed cover plate 7 difficult.

[0075] like Figure 11 , Figure 12As shown, the power transmission driving section 2 comprises a power transmission driving section outer cylinder 15, a power transmission gear set, a transverse power transmission mechanism, a screw shaft 21 and a longitudinal power transmission block 22, the fixed cover plate 7 is connected with the power transmission driving section outer cylinder 15, the universal ball seat 6 and the longitudinal power transmission block 22 are both arranged in the power transmission driving section outer cylinder 15, the transverse power transmission mechanism is in plurality, the plurality of transverse power transmission mechanisms are arranged in the circumferential direction of the power transmission driving section outer cylinder 15, the upper parts of the plurality of transverse power transmission mechanisms are spliced into a cylindrical structure, the spliced cylindrical structure is located outside the solar wing connecting column 5, each transverse power transmission mechanism is connected with a power transmission gear set below, the longitudinal power transmission block 22 is provided with a rack 38, the rack 38 is engaged with the power transmission gear set, the screw shaft 21 is connected with the longitudinal power transmission block 22.

[0076] In the embodiment, the power transmission gear set comprises a plurality of gears, the plurality of gears are divided into a first gear 16, a second gear 17 and a third gear 18, the power transmission driving section outer cylinder 15 is provided with a gear frame, the gear frame is divided into a first gear frame 27 and a second gear frame 28, the power transmission driving section outer cylinder 15 is provided with a third gear gear hole 29, the first gear 16 is rotatably connected to the first gear frame 27, the first gear 16 is connected with the transverse power transmission mechanism, the second gear 17 and the third gear 18 are coaxially rotatably connected to the second gear frame 28, the first gear 16 is engaged with the second gear 17, the third gear 18 passes through the third gear gear hole 29 and is engaged with the rack 38.

[0077] In the embodiment, the gear is connected with the gear frame through a rotating shaft, a small bearing 25 is arranged between the rotating shaft and the gear frame, a circlip 26 is arranged outside the small bearing 25, the rotating shaft is divided into a first rotating shaft 23 and a second rotating shaft 24, the first gear 16 is connected with the first gear frame 27 through the first rotating shaft 23, the second gear 17 and the third gear 18 are connected with the second gear frame 28 through the second rotating shaft 24.

[0078] In the embodiment, the transverse power transmission mechanism comprises a transverse power transmission rod 19 and a transverse power transmission cover 20, the transverse power transmission rod 19 is provided with a mounting surface 33 at the upper end, the transverse power transmission cover 20 comprises a mounting table 34 and a transverse power transmission surface 35, the transverse power transmission surface 35 is located outside the solar wing connecting column 5, the transverse power transmission surface 35 is in a circular arc structure, the mounting table 34 is arranged outside the transverse power transmission surface 35, the mounting table 34 is connected with the mounting surface 33, the transverse power transmission rod 19 is provided with an embedded groove 32 at the lower part, the first gear 16 is provided with an embedded opening 31, the embedded groove 32 and the embedded opening 31 are embeddedly arranged, the gear and the transverse power transmission rod 19 are both provided with a stop groove 30, the rotating shaft is provided with a stop key 40 and a circlip groove 41, the stop key 40 is connected with the stop groove 30 in cooperation, and the circlip 26 is mounted on the circlip groove 41.

[0079] In this embodiment, the lead screw shaft 21 is provided with a threaded groove 36, which engages with the balls in the ball nut 45. A fixing pin 37 is provided at the upper end of the lead screw shaft 21, and a pin groove 39 is provided at the center of the longitudinal force transmission block 22. The fixing pin 37 is inserted into the pin groove 39, and the lead screw shaft 21 and the longitudinal force transmission block 22 are connected by bolts.

[0080] The specific description of the force transmission drive section 2 is as follows:

[0081] The force transmission drive section 2 includes a force transmission drive section outer cylinder 15, four first gears 16, four second gears 17, eight third gears 18, four transverse force transmission rods 19, four transverse force transmission covers 20, a lead screw shaft 21, a longitudinal force transmission block 22, four first rotating shafts 23, four second rotating shafts 24, sixteen small bearings 25, and thirty-two retaining rings 26.

[0082] Force transmission drive section outer cylinder 15 Figure 13 As shown, there are eight first gear holders 27 and eight second gear holders 28 on the circumference, which are used for the installation and fixing of the first gear 16 and the second gear 17, respectively. Next to the gear holder is a third gear hole 29, which is used for the third gear 18 to extend into the outer cylinder 15 of the power transmission drive section.

[0083] like Figure 14 As shown, the first gear 16 has a retaining groove 30 in its shaft hole to achieve rotational fixation with the first shaft 23. The second gear 17 and the third gear 18 also have retaining grooves 30. In order to ensure that the first gear 16 and the transverse force transmission rod 19 can be better engaged and connected, the first gear 16 also has a fitting port 31 to achieve engagement and fixation with the transverse force transmission rod 19.

[0084] like Figure 15 As shown, the pivot hole of the transverse force transmission rod 19 has a stop groove 30 to achieve rotational fixation with the first pivot 23. The transverse force transmission rod 19 has a fitting groove 32, which cooperates with the fitting opening 31. The transverse force transmission rod 19 has a mounting surface 33 for fixing the transverse force transmission cover 20.

[0085] like Figure 16 As shown, the transverse force transmission cover 20 has a mounting platform 34 for fixing the transverse force transmission rod 19, and a transverse force transmission surface 35. The transverse force transmission surface 35 is designed as a 1 / 4 arc surface, which can play a guiding role when subjected to transverse force. The four transverse force transmission surfaces 35 can be assembled into a complete cylinder.

[0086] like Figure 17As shown, the lead screw shaft 21 has a threaded groove 36 and a fixing pin 37. The threaded groove 36 engages with the balls in the ball nut 45, converting the linear motion of the lead screw shaft 21 into the rotational motion of the ball nut 45. The fixing pin 37 engages with the pin groove 39 of the longitudinal force transmission block 22, preventing the lead screw shaft 21 from rotating around its axis. The longitudinal force transmission block 22 has a connecting platform inside, with mounting holes on the connecting platform. The top of the lead screw shaft 21 has a threaded hole, through which a bolt passes and connects to the threaded hole, thus fixing the lead screw shaft 21 to the longitudinal force transmission block 22. Figure 18 As shown, the longitudinal force transmission block 22 has eight racks 38, with two racks 38 on each of its four sides. The lead screw shaft mounting hole of the longitudinal force transmission block 22 has a pin groove 39. (As shown...) Figure 19 As shown, the first rotating shaft 23 has two stop keys 40 and two snap ring grooves 41, as... Figure 20 As shown, the second rotating shaft 24 has four stop keys 40 and six snap ring grooves 41. The stop keys 40 cooperate with the stop grooves 30 to fix the gear rotation, and the snap ring grooves 41 are used for snapping the snap ring 26 to fix the gear and the small bearing 25 axially.

[0087] The installation process of the force transmission drive section 2 is as follows: First step, as... Figure 21 As shown, fix the transverse force transmission rod 19 to the transverse force transmission cover 20. The second step is as follows... Figure 22 As shown, the first gear 16 and the transverse force transmission rod 19 are fitted together, and then mounted on the first gear carrier 27 via the first rotating shaft 23 and the small bearing 25; the second gear 17 is meshed with the first gear 16, and then mounted on the second gear carrier 28 via the second rotating shaft 24 and the small bearing 25. The outer ring of the small bearing 25 is fixed to the inner hole of the gear carrier by adhesive bonding, and the inner ring of the small bearing 25 is fixed by the shaft shoulder and the retaining ring 26; in this way, the installation of all the first gears 16 and the second gears 17 is completed. The third step, as... Figure 23 As shown, the lead screw shaft 21 is fixed to the longitudinal force transmission block 22, and then inserted into the appropriate position inside the outer cylinder 15 of the force transmission drive section. The first gear 16 is rotated to make the transverse force transmission rod 19 vertical, so that the four transverse force transmission covers 20 are fastened into a complete cylinder. The third gear 18 is inserted into the outer cylinder 15 of the force transmission drive section and meshes with the rack 38. The snap ring 26 is then used to fix the third gear 18.

[0088] In this embodiment, the force transmission drive section 2 has one motion pattern, involving two driving methods, one of which is lateral swing drive, such as... Figure 24As shown, the lateral swing drive causes any lateral force transmission cover 20 to deflect the lateral force transmission rod 19, which in turn drives the first gear 16 to rotate. The first gear 16 drives the meshing second gear 17 to rotate, and the second gear 17 drives the third gear 18 to rotate via the second rotating shaft 24. The third gear 18 drives the combination of the longitudinal force transmission block 22 and the lead screw shaft 21 to perform longitudinal linear motion. At the same time, since all the third gears 18 mesh with the rack 38 of the longitudinal force transmission block 22, they will drive the other force transmission gear sets, lateral force transmission covers 20, and lateral force transmission rods 19 to move. That is, all lateral force transmission mechanisms exhibit the same motion trend, with only the difference between active and passive motion. The second type is longitudinal vibration drive, whose motion pattern is completely consistent with the lateral swing drive. The difference is that the longitudinal linear motion of the combination of the longitudinal force transmission block 22 and the lead screw shaft 21 is the active motion, while the motion of all force transmission gear sets and lateral force transmission mechanisms is the passive motion.

[0089] In this embodiment, the force transmission gear set converts the lateral oscillation into longitudinal linear motion through transmission, and the stroke can be amplified by multiple gears. That is, the small lateral oscillation is amplified into a long-stroke longitudinal linear motion, which will help the damper to dampen the vibration and avoid the vibration rigid transmission caused by poor damping effect of short stroke or excessive damping.

[0090] like Figure 25 As shown, the damping section 3 includes a damping section outer cylinder 42, magnets 43, ball nuts 45, and a damping copper ring 46. The damping copper ring 46 is rotatably connected inside the damping section outer cylinder 42. Magnets 43 are provided on both the upper and lower sides of the damping copper ring 46, and the adjacent magnetic poles of the two magnets 43 are opposite. A partition cylinder 48 is provided between the damping copper ring 46 and the magnets 43. A ball nut 45 is provided on the damping copper ring 46. The lead screw shaft 21 is connected to the ball nut 45. The damping copper ring 46 is connected to the damping section outer cylinder 42 through a large bearing 44. A partition plate 47 is provided at both the upper and lower ends of the damping section outer cylinder 42.

[0091] The installation process of damping section 3 is as follows: First, use countersunk screws to fix the ball nut 45 to the damping copper ring 46, and then glue the damping copper ring 46 to the inner ring of the large bearing 44. Second, insert a magnet 43, a partition cylinder 48, the large bearing 44, the assembly of the damping copper ring 46 and the ball nut 45, a partition cylinder 48, and a magnet 43 into the outer cylinder 42 of the damping section in sequence, and then place two partition plates 47 on the upper and lower sides of the assembly to complete the assembly.

[0092] In the embodiment, the material of the magnetic steel 43 is preferably neodymium iron boron. The magnetic steel has a large magnetic energy product, which can realize the miniaturization design of the damping section 3 and improve the damping effect. The magnetic steel has a wide use limit temperature range, which can avoid the demagnetization of the magnetic steel caused by high and low temperature environments in space. The two magnetic steels 43 in the damping section 3 are designed to have opposite adjacent magnetic poles. The ball screw nut 45 has balls, which can cooperate with the thread grooves 36 of the screw shaft 21 to convert the linear motion of the screw shaft 21 into the rotary motion of the ball screw nut 45. The material of the partition plate 47 and the partition cylinder 48 is preferably polyimide, which has an insulation effect under the premise of ensuring the mechanical strength, and can reduce the leakage of the eddy current of the damping section 3.

[0093] In the embodiment, after the completion of the assembly of the damper, the partition plate 47 and the partition cylinder 48 axially fix the combination of the magnetic steel 43, the large bearing 44, and the damping copper ring 46 and the ball screw nut 45, and simultaneously realize the fixation of the rotary direction of the magnetic steel 43 and the outer ring of the large bearing 44 through friction. Therefore, the damping section 3 has only one motion form, that is, the rotary motion of the ball screw nut 45 and the damping copper ring 46 around the shaft.

[0094] As shown in Figure 26 , the satellite fixing section 4 includes a satellite fixing section outer cylinder 49, a return spring 50, and a spring seat 51. The return spring 50 is arranged in the satellite fixing section outer cylinder 49, and the upper end of the return spring 50 is connected to the spring seat 51. The screw shaft 21 abuts against the spring seat 51 after passing through the damping section 3. The lower end of the satellite fixing section outer cylinder 49 is a satellite mounting surface 52 for mounting and fixing the satellite end. The spring seat 51 is provided with a screw blind hole 53, and the screw shaft 21 is inserted into the screw blind hole 53. The return spring 50 can be compressed through the spring seat 51, and the maximum compression stroke of the return spring 50 is greater than the maximum linear motion stroke of the screw shaft 21. In the embodiment, the satellite fixing section 4 has only one motion form, that is, the deformation of the return spring 50 and the axial linear motion of the spring seat 51.

[0095] The assembly process of the multi-directional damper suitable for the large flexible solar wing in the embodiment is shown in Figure 27 . After the installation of the solar wing fixing section 1, the force transmission driving section 2, the damping section 3, and the satellite fixing section 4 is completed, the four parts are sequentially connected end to end. The universal ball seat 6 of the solar wing fixing section 1 is sunk into the force transmission driving section outer cylinder 15. The screw shaft 21 passes through the cavity of the damping section 3, is screwed into the ball screw nut 45, and then is inserted into the screw blind hole 53 of the satellite fixing section 4. Finally, screws are used to fix the adjacent parts of the fixed cover plate 7, the force transmission driving section outer cylinder 15, the damping section outer cylinder 42, and the satellite fixing section outer cylinder 49, and the complete assembly of the damper is completed.

[0096] The application also provides a working method of the multidirectional damper suitable for the large flexible solar wing, which can play a passive vibration suppression control effect.

[0097] When the solar wing 54 occurs lateral vibration, the solar wing 54 swings, the solar wing connecting column 5 pushes the lateral force transmission mechanism to rotate around the universal ball 12, the lateral force transmission mechanism drives the force transmission gear set to rotate, the force transmission gear set drives the longitudinal force transmission block 22 to move downward through the meshing with the rack 38, and then drives the lead screw shaft 21 to move linearly downward against the elastic force of the return spring 50, in the process, since the ball nut 45 is axially fixed, the damping copper ring 46 rotates around the shaft under the driving of the lead screw shaft 21, the rotating damping copper ring 46 moves between the two magnetic steels 43 to cut the magnetic induction lines, so as to generate eddy current resistance, form damping force to suppress the rotation of the damping copper ring 46, and suppress the lateral vibration of the solar wing 54;

[0098] When the solar wing 54 occurs axial vibration, the solar wing 54 moves along the axial direction, the solar wing connecting column 5 pushes the universal ball seat 6 to move downward, the universal ball seat 6 pushes the longitudinal force transmission block 22 to move downward, and then drives the lead screw shaft 21 to move linearly downward against the elastic force of the return spring 50, in the process, since the ball nut 45 is axially fixed, the damping copper ring 46 rotates around the shaft under the driving of the lead screw shaft 21, the rotating damping copper ring 46 moves between the two magnetic steels 43 to cut the magnetic induction lines, so as to generate eddy current resistance, form damping force to suppress the rotation of the damping copper ring 46, and suppress the axial vibration of the solar wing 54;

[0099] When the solar wing 54 occurs small-amplitude lateral vibration, the solar wing connecting column 5 does not contact the lateral force transmission mechanism, at this time, the small-amplitude lateral vibration of the solar wing 54 is suppressed through the elastic force of the rectangular spring 8 after being bent;

[0100] When the solar wing 54 occurs small-amplitude longitudinal vibration, the stroke of the solar wing connecting column 5 pushing the longitudinal force transmission block 22 is insufficient to generate eddy current resistance, at this time, the small-amplitude longitudinal vibration of the solar wing 54 is suppressed through the elastic force of the rectangular spring 8 after being compressed.

[0101] The following will take the example of the multi-directional damper installed between the solar wing 54 and the solar wing driving mechanism 55, and the solar wing driving mechanism 55 installed on the satellite body 56 to describe the specific working mode as follows:

[0102] As shown in Figure 28 and Figure 29 , the solar wing connecting column 5 is connected with the solar wing 54, the satellite fixed section 4 is connected with the solar wing driving mechanism 55, and the solar wing driving mechanism 55 is installed on the satellite body 56. In this embodiment, the main vibration modes of the large flexible solar wing 54 include: X-direction swing perpendicular to the solar wing surface, Y-direction swing parallel to the solar wing surface, Z-direction vibration perpendicular to the installation axis, and a composite vibration mode composed of different vibration modes.

[0103] When the solar wing 54 occurs X-direction flexible vibration, as shown in Figure 30 , the solar wing 54 swings, and the transmission gear set of the transmission driving section 2 of the solar wing connecting column 5 is pushed to rotate to amplify the lateral swing into longitudinal motion, and then drive the lead screw shaft 21 to move linearly downward against the elastic force of the reset spring 50. Since the ball nut 45 of the damping section 3 is axially fixed, under the large stroke pushing of the lead screw shaft 21, the lower damping copper ring 46 is driven to rotate for multiple turns around the shaft. As shown in Figure 31 , the rotating damping copper ring 46 cuts the magnetic induction lines between the two magnetic steels 43, thereby generating eddy current resistance, which is embodied as damping force to suppress the rotation, and finally converts kinetic energy into heat energy to achieve the effect of suppressing the swing of the solar wing 54. In the reset process of the swing of the solar wing 54, similar to the above process, under the pushing force of the bottom reset spring 50, the lead screw shaft 21 moves linearly upward, pushes the damping copper ring 46 to rotate reversely, and also generates eddy current resistance to achieve the vibration suppression effect in the reset process.

[0104] When the solar wing 54 occurs Y-direction flexible vibration, the working mode of the damper is consistent with the above process of X-direction flexible vibration.

[0105] When the solar wing 54 occurs transverse composite flexible vibration, that is, the swing direction of the solar wing connecting column 5 has an angle difference with the X-direction and the Y-direction, as shown in Figure 32 , since the transverse transmission surface 35 of the transverse transmission cover 20 is a 1 / 4 circular arc surface, four transverse transmission covers 20 are spliced into a complete cylinder, and the vibration of the solar wing 54 generates a component force under the guidance of the arc surface and acts on two adjacent transverse transmission covers 20 and triggers the eddy current damping to suppress the vibration.

[0106] When the solar wing 54 occurs Z-direction flexible vibration, as shown in Figure 33As shown, the axial movement of the solar wing 54 pushes the gimbal seat 6 downward through the solar wing connecting column 5, which in turn pushes the longitudinal force block 22 downward, driving the screw shaft 21 to move linearly downward against the elastic force of the reset spring 50. The large stroke of the screw shaft 21 makes the damping copper ring 46 rotate around the shaft for multiple turns. Figure 31 As shown, the rotating damping copper ring 46 moves between the two magnetic steel 43 to cut the magnetic induction lines, thereby generating an eddy current resistance, which is a damping force that inhibits rotation, and finally converts kinetic energy into heat energy, achieving the effect of inhibiting the Z-directional flexible vibration of the solar wing. During the upward reset process of the solar wing 54, similar to the above process, the damper is pushed upward by the bottom reset spring 50, the screw shaft 21 moves linearly upward, pushing the damping copper ring 46 to rotate in the opposite direction, which also generates an eddy current resistance, achieving the effect of vibration suppression during the reset process.

[0107] When the solar wing 54 undergoes high-frequency transverse vibration, the solar wing connecting column 5 undergoes high-frequency small-amplitude oscillation and does not contact the transverse force block 20, so it does not suppress vibration through eddy current damping, but through the elastic force of the bent rectangular spring 8 to suppress vibration.

[0108] When the solar wing 54 undergoes high-frequency longitudinal vibration, the solar wing connecting column 5 does not cause large-stroke movement of the longitudinal force block 22, so it does not suppress vibration through eddy current damping, but through the elastic force of the compressed rectangular spring 8 and the two rubber pads 9 to suppress vibration.

[0109] When the solar wing 54 undergoes high-frequency transverse and longitudinal composite vibration, the vibration is suppressed through the bending and compression of the rectangular spring 8 and the compression of the two rubber pads 9.

[0110] In this embodiment, the application of the screw shaft 21, the ball nut 45, and the size bearing is to avoid static friction during motion transmission and reduce dynamic friction during motion transmission, so as to achieve flexible vibration suppression through smooth and stable eddy current damping as much as possible, and avoid vibration rigidity transmission caused by friction damping.

[0111] In this embodiment, the damper has the ability to suppress multi-directional vibration and a wide vibration suppression frequency band. On this basis, the damping and suppression frequency band range can be further adjusted through various means, including: one, changing the damping by changing the composition and specifications of the force transmission gear set to change the swing amplitude level; two, changing the specifications of the screw shaft 21 and the ball nut 45 to change the number of rotations of the damping copper ring 46 to achieve the effect of changing the damping; three, changing the size and magnetic properties of the magnetic steel 43 to change the damping; four, adding multiple damping sections 3 to the damper, which are connected in sequence to change the damping.

[0112] The detailed description of the application set forth above merely exemplifies the application. The detailed description set forth is not intended to be all-inclusive of the aspects of the application. A person having ordinary skill in the art can make modifications and variations to the application as described. It is contemplated that the application encompassed by the following claims can include these modifications and variations. The embodiments selected for the purposes of example are intended to illustrate the principles of the application and to enable others skilled in the art to best utilize the application.

Claims

1. A multi-directional damper suitable for use in a large flexible solar wing, characterized by: It includes the solar wing fixed section (1), the force transmission driving section (2), the damping section (3) and the satellite fixed section (4) connected in turn, the solar wing fixed section (1) includes the solar wing connecting column (5), the universal ball seat (6), the fixed cover plate (7) and the rectangular spring (8), the fixed cover plate (7) and the rectangular spring (8) are sleeved on the solar wing connecting column (5), one end of the rectangular spring (8) is connected with the solar wing connecting column (5), the other end is connected with the fixed cover plate (7), the end of the solar wing connecting column (5) is provided with the universal ball (12), the universal ball (12) is connected with the universal ball seat (6), the force transmission driving section (2) includes the force transmission driving section outer cylinder (15), the force transmission gear set, the transverse force transmission mechanism, the lead screw shaft (21) and the longitudinal force transmission block (22), the fixed cover plate (7) is connected with the force transmission driving section outer cylinder (15), the universal ball seat (6) and the longitudinal force transmission block (22) are arranged in the force transmission driving section outer cylinder (15), the number of the transverse force transmission mechanism is multiple, multiple transverse force transmission mechanisms are arranged along the circumference of the force transmission driving section outer cylinder (15), the upper portions of multiple transverse force transmission mechanisms are spliced into a cylindrical structure, the spliced cylindrical structure is located outside the solar wing connecting column (5), each transverse force transmission mechanism is connected with the force transmission gear set below, the longitudinal force transmission block (22) is provided with the rack (38), the rack (38) is engaged with the force transmission gear set, the lead screw shaft (21) is connected with the longitudinal force transmission block (22), the damping section (3) includes the damping section outer cylinder (42), the magnetic steel (43), the ball nut (45) and the damping copper ring (46), the damping copper ring (46) is rotatably connected in the damping section outer cylinder (42), the damping copper ring (46) is provided with the magnetic steel (43) on the upper side and the lower side, the adjacent magnetic poles of the two magnetic steels (43) are opposite, the damping copper ring (46) and the magnetic steel (43) are provided with the spacer (48), the damping copper ring (46) is provided with the ball nut (45), the lead screw shaft (21) is connected with the ball nut (45) in cooperation, the satellite fixed section (4) includes the satellite fixed section outer cylinder (49), the return spring (50) and the spring seat (51), the satellite fixed section outer cylinder (49) is provided with the return spring (50) inside, the upper end of the return spring (50) is connected with the spring seat (51), the lead screw shaft (21) passes through the damping section (3) and abuts against the spring seat (51).

2. A multi-directional damper suitable for use in a large flexible solar wing according to claim 1, characterized in that: The upper side and the lower side of the universal ball seat (6) are provided with the rubber pad (9), the upper portion of the solar wing connecting column (5) is the solar wing mounting surface (10), the lower portion of the solar wing connecting column (5) is connected with the universal ball (12) through the connecting shaft (11), the universal ball seat (6) is provided with the hemispherical arc surface (13), the universal ball (12) is arranged in cooperation with the hemispherical arc surface (13), the universal ball seat (6) is a split structure.

3. A multi-directional damper suitable for use in a large flexible solar wing according to claim 1, characterized in that: The power transmission gear set comprises a plurality of gears, which are divided into a first gear (16), a second gear (17) and a third gear (18), a gear frame is arranged on the power transmission driving section outer cylinder (15), the gear frame is divided into a first gear frame (27) and a second gear frame (28), a third gear gear hole (29) is formed on the power transmission driving section outer cylinder (15), the first gear (16) is rotatably connected to the first gear frame (27), the first gear (16) is connected to the transverse power transmission mechanism, the second gear (17) and the third gear (18) are coaxially rotatably connected to the second gear frame (28), the first gear (16) is engaged with the second gear (17), and the third gear (18) passes through the third gear gear hole (29) and is engaged with the rack (38).

4. A multi-directional damper suitable for use in a large flexible solar wing according to claim 3, characterized in that: The gear is connected to the gear frame through a rotating shaft, a small bearing (25) is arranged between the rotating shaft and the gear frame, a circlip (26) is arranged outside the small bearing (25), the rotating shaft is divided into a first rotating shaft (23) and a second rotating shaft (24), the first gear (16) is connected to the first gear frame (27) through the first rotating shaft (23), and the second gear (17) and the third gear (18) are connected to the second gear frame (28) through the second rotating shaft (24).

5. A multi-directional damper suitable for use in a large flexible solar wing according to claim 4, characterised in that: The transverse power transmission mechanism comprises a transverse power transmission rod (19) and a transverse power transmission cover (20), the upper end of the transverse power transmission rod (19) is provided with a mounting surface (33), the transverse power transmission cover (20) comprises a mounting table (34) and a transverse power transmission surface (35), the transverse power transmission surface (35) is located outside the solar wing connecting column (5), the transverse power transmission surface (35) has a circular arc structure, the mounting table (34) is arranged outside the transverse power transmission surface (35), the mounting table (34) is connected to the mounting surface (33), an embedding groove (32) is formed in the lower part of the transverse power transmission rod (19), an embedding opening (31) is arranged on the first gear (16), the embedding groove (32) and the embedding opening (31) are embeddedly arranged, a stop groove (30) is formed in the gear and the transverse power transmission rod (19), a stop key (40) and a circlip groove (41) are arranged on the rotating shaft, the stop key (40) is connected to the stop groove (30) in a matched mode, and the circlip (26) is mounted on the circlip groove (41).

6. A multi-directional damper suitable for use in a large flexible solar wing according to claim 1, characterized in that: A threaded groove (36) is arranged on the lead screw shaft (21), the threaded groove (36) is matched with balls in a ball nut (45), a fixed pin (37) is arranged at the upper end of the lead screw shaft (21), a pin groove (39) is arranged at the center of the longitudinal power transmission block (22), the fixed pin (37) is inserted into the pin groove (39), and the lead screw shaft (21) and the longitudinal power transmission block (22) are connected through bolts.

7. A multi-directional damper suitable for use in a large flexible solar wing according to claim 1, characterized in that: The damping copper ring (46) is connected to the damping section outer cylinder (42) through a large bearing (44), and a baffle (47) is arranged at each of the upper end and the lower end of the damping section outer cylinder (42).

8. A multi-directional damper suitable for use in a large flexible solar wing according to claim 1, characterized in that: The lower end of the satellite fixed section outer cylinder (49) is a satellite mounting surface (52), a screw blind hole (53) is formed in the spring seat (51), and the screw shaft (21) is inserted into the screw blind hole (53).

9. A multi-directional damper suitable for use in a large flexible solar array according to claim 1, characterized in that: The number of the damping sections (3) is multiple, and the multiple damping sections (3) are sequentially connected.

10. A method of operating a multi-directional damper suitable for use in a large flexible solar wing as claimed in claim 1, characterized by: The solar wing connecting column (5) is directly or indirectly connected with the solar wing (54); When the solar wing (54) occurs transverse vibration, the solar wing (54) swings, the solar wing connecting column (5) drives the transverse force transmission mechanism to rotate around the universal ball (12), the transverse force transmission mechanism drives the force transmission gear set to rotate, the force transmission gear set drives the longitudinal force transmission block (22) to move downward through the meshing with the rack (38), and then drives the screw shaft (21) to move linearly downward against the elastic force of the return spring (50), in the process, the damping copper ring (46) rotates around the shaft under the driving of the screw shaft (21) because the ball nut (45) is axially fixed, the rotating damping copper ring (46) moves between the two magnetic steels (43) to cut the magnetic induction lines, so that the eddy current resistance is generated, the damping force that inhibits the rotation of the damping copper ring (46) is formed, and the transverse vibration of the solar wing (54) is inhibited; When the solar wing (54) occurs axial vibration, the solar wing (54) moves along the axial direction, the solar wing connecting column (5) drives the universal ball seat (6) to move downward, the universal ball seat (6) drives the longitudinal force transmission block (22) to move downward, and then drives the screw shaft (21) to move linearly downward against the elastic force of the return spring (50), in the process, the damping copper ring (46) rotates around the shaft under the driving of the screw shaft (21) because the ball nut (45) is axially fixed, the rotating damping copper ring (46) moves between the two magnetic steels (43) to cut the magnetic induction lines, so that the eddy current resistance is generated, the damping force that inhibits the rotation of the damping copper ring (46) is formed, and the axial vibration of the solar wing (54) is inhibited; When the solar wing (54) occurs small-amplitude transverse vibration, the solar wing connecting column (5) does not contact the transverse force transmission mechanism, at this time, the small-amplitude transverse vibration of the solar wing (54) is inhibited through the elastic force of the rectangular spring (8) after being bent; When the solar wing (54) occurs small-amplitude longitudinal vibration, the stroke of the solar wing connecting column (5) driving the longitudinal force transmission block (22) is insufficient to generate the eddy current resistance, at this time, the small-amplitude longitudinal vibration of the solar wing (54) is inhibited through the elastic force of the rectangular spring (8) after being compressed. When the solar wing (54) occurs small-amplitude transverse vibration, the solar wing connecting column (5) does not contact the transverse force transmission mechanism, at this time, the small-amplitude transverse vibration of the solar wing (54) is inhibited through the elastic force of the rectangular spring (8) after being bent; When the solar wing (54) occurs small-amplitude longitudinal vibration, the stroke of the solar wing connecting column (5) driving the longitudinal force transmission block (22) is insufficient to generate the eddy current resistance, at this time, the small-amplitude longitudinal vibration of the solar wing (54) is inhibited through the elastic force of the rectangular spring (8) after being compressed.

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