A deployment mechanism for a multiple folded array deployable antenna and a satellite

Abstract

The application provides a deployment mechanism of a multi-fold array deployment antenna and a satellite, relates to the field of aerospace satellites, and the antenna unit comprises a plurality of first unit middle plates, a plurality of second unit middle plates, a plurality of unit upper plates and a plurality of unit lower plates; the plurality of first unit middle plates are sequentially arranged along the longitudinal direction, and the plurality of second unit middle plates are sequentially arranged along the longitudinal direction; the plurality of unit upper plates are sequentially arranged along the longitudinal direction and are connected through longitudinal hinge assemblies between adjacent unit upper plates; the plurality of unit lower plates are sequentially arranged along the longitudinal direction and are connected through longitudinal hinge assemblies between adjacent unit lower plates; a cross-plate driving assembly is arranged between adjacent first unit middle plates and adjacent second unit middle plates; a primary deployment driving assembly cooperates with a linkage part to drive longitudinal deployment; at least two secondary deployment driving assemblies are used to drive the unit upper plates and the unit lower plates to be horizontally flipped and deployed. The application has the effect that a large aperture can be obtained after the array antenna is opened.

Description

Technical Field

[0001] This application relates to the field of aerospace satellites, and in particular to a deployment mechanism for a multi-fold array deployment antenna and a satellite. Background Technology

[0002] To meet the demands for multi-functionality, multi-band, large capacity, high power, and high gain, space array antennas inevitably tend towards larger sizes. The deployability of the mechanism makes the design and application of large-aperture space antennas a reality. The design of deployable antenna mechanisms requires achieving a large fold-to-spread ratio, that is, a small volume when folded up in the transmitting state and a large aperture when unfolded.

[0003] In existing technologies, satellite array antennas are mainly deployed longitudinally; however, with the continuous upgrading and improvement of satellites, simply relying on longitudinal deployment results in a smaller aperture for the array antenna, making it difficult to meet current needs. Summary of the Invention

[0004] In order to minimize the space occupied by the antenna element in the folded state and maximize the aperture of the antenna element in the unfolded state, this application provides an unfolding mechanism for a multi-fold array unfolding antenna and a satellite.

[0005] To solve the above problems, the technical solution of this invention application is as follows: A deployment mechanism for a multi-fold array deployable antenna, characterized in that it includes, An antenna unit, the antenna unit comprising a plurality of first unit intermediate plates, a plurality of second unit intermediate plates, a plurality of unit upper plates and a plurality of unit lower plates; A plurality of first unit intermediate plates are arranged sequentially along the longitudinal direction. Adjacent first unit intermediate plates are connected by cross-plate driving components, and the rotation directions of adjacent cross-plate driving components are opposite. A plurality of second unit intermediate plates are arranged sequentially along the longitudinal direction and correspond one-to-one with the first unit intermediate plate in the transverse direction. Adjacent second unit intermediate plates are connected by a cross-plate driving assembly, and the rotation directions of adjacent cross-plate driving assemblies are opposite. The first unit intermediate plate and / or the second unit intermediate plate located at the head end are connected to the external planetary sidewall through a root hinge assembly. A fixing part is connected between the corresponding first unit intermediate plate and the second unit intermediate plate to fix their relative positions. Several unit upper plates are arranged sequentially along the longitudinal direction, and adjacent unit upper plates are connected by longitudinal hinge components; each unit upper plate corresponds to the first unit middle plate in the transverse direction, and is respectively connected to the side of the corresponding first unit middle plate away from the second unit middle plate by transverse hinge components. Several unit lower plates are arranged sequentially along the longitudinal direction, and adjacent unit lower plates are connected by a longitudinal hinge assembly; each unit lower plate corresponds to the second unit middle plate in the transverse direction, and is respectively connected to the side of the corresponding second unit middle plate away from the first unit middle plate by a transverse hinge assembly; The first-stage unfolding drive assembly has a fixed end connected to the side wall of the external star and a drive end connected to the root hinge assembly, which is used to drive the first unit middle plate and the second unit middle plate located at the head end to axially rotate and unfold. A plurality of linkage parts are respectively installed on the corresponding fixing parts. The input end of the linkage part located between the middle plate of the first unit and the second unit in the second horizontal row is connected to the driving end of the first unfolding drive assembly. In addition, in the two linkage parts arranged between odd-numbered horizontal rows and even-numbered horizontal rows along the direction away from the external celestial body, the output end of the linkage part closer to the external celestial body is connected to the input end of the linkage part farther from the external celestial body, so as to transmit the flipping driving force to each of the cross-plate drive assemblies and drive the middle plate of the first unit and the middle plate of the second unit to flip and unfold axially. At least two secondary unfolding drive components are provided, at least one of which is provided between the first unit middle plate and the unit upper plate, for driving the unit upper plate to flip and unfold laterally relative to the first unit middle plate, and at least one of which is provided between the second unit middle plate and the unit lower plate, for driving the unit lower plate to flip and unfold laterally relative to the second unit middle plate.

[0006] The deployment mechanism of the multi-fold array deployment antenna of the present invention includes a first fixed hinge, a first rotating hinge, a first drive source, a main linkage wheel, and a locking part. One end of the first fixed hinge is fixed to the first drive source body, and the other end of the first fixed hinge is fixed to the fixed end of the root hinge assembly connected to the external celestial body; the first rotating hinge is fixed to the output shaft of the first drive source, and the other end of the first rotating hinge is fixed to the fixed part; and the main linkage wheel is fixed to the output shaft of the first drive source; the locking part is disposed between the first fixed hinge and the first rotating hinge for fixing; the locking part includes a locking rod, a locking block, a locking groove, and a locking torsion spring; the locking rod is rotatably connected to the first rotating hinge, the locking block is fixed to the first fixed hinge, and the locking groove is opened on the first fixed hinge; the locking torsion spring is disposed between the first fixed hinge and the locking rod, and the locking rod slides on the locking block and locks into the locking groove to achieve locking; The fixing part consists of a first fixing plate and a second fixing plate arranged longitudinally between the corresponding middle plates of the first and second units. The linkage part consists of a first driven wheel and a second driven wheel respectively disposed on the first fixing plate and the second fixing plate. Along the direction away from the external celestial body, the second driven wheels of the fixing parts in odd-numbered rows are all connected to the first driven wheels of the next odd-numbered rows of fixing parts by rope transmission, and the second driven wheels of the fixing parts in even-numbered rows are all connected to the first driven wheels of the next even-numbered rows of fixing parts by rope transmission. Among them, the first driven wheels located in the second row are connected to the main linkage wheel by rope transmission.

[0007] The deployment mechanism of the multi-fold array deployment antenna of the present invention includes a secondary deployment driving component comprising a second driving source, a second fixed hinge, and a second rotating hinge. One end of the second fixed hinge is fixed to the second drive source body, and the other end of the second fixed hinge is fixed to the first unit middle plate or the second unit middle plate; one end of the second rotating hinge is fixed to the output shaft of the second drive source, and the other end of the second rotating hinge is fixed to the associated unit upper plate or the unit lower plate.

[0008] The deployment mechanism of the multi-fold array deployment antenna of the present invention includes a secondary deployment driving component, which further includes a locking part, the locking part including a locking ring, a locking rod, a positioning groove, and a locking torsion spring; The locking ring is fixed to the output shaft of the second drive source / the second rotating hinge, the locking groove is formed on the locking ring, the locking rod is rotatably connected to the second fixed hinge, and the locking torsion spring is disposed between the second fixed hinge and the locking rod; the locking rod slides on the outer wall of the locking ring and is engaged in the locking groove.

[0009] The deployment mechanism of the multi-fold array deployable antenna of the present invention includes a root hinge assembly comprising a connecting plate, a mounting plate, at least one third fixed hinge, at least one third rotating hinge, and a limiting part. The third fixed hinge is fixed to the connecting plate, and the connecting plate is fixed to the external celestial body; the third rotating hinge is fixed to the mounting plate, and the mounting plate is fixedly connected to the first unit intermediate plate and / or the second unit intermediate plate at the head end; the end of the third fixed hinge away from the connecting plate is rotatably connected to the end of the third rotating hinge away from the mounting plate. The limiting part is disposed between the third fixed hinge and the third rotating hinge.

[0010] The deployment mechanism of the multi-fold array deployment antenna of the present invention includes a limiting part comprising a limiting block, a limiting groove, a limiting rod, and a limiting torsion spring; The limiting block is fixed to the third rotating hinge, and the limiting groove is formed on the limiting block; the limiting rod is rotatably connected to the third fixed hinge, the limiting torsion spring is disposed between the third fixed hinge and the limiting rod, and the limiting rod slides on the outer wall of the limiting block and is engaged in the limiting groove.

[0011] The deployment mechanism of the multi-fold array deployment antenna of the present invention includes a cross-plate driving assembly comprising a first connecting rod, a second connecting rod, a first female hinge, a second female hinge, a driving spring, and a limiting part; The first end of the first connecting rod and the first end of the second connecting rod are rotatably connected. The two torsion arms of the driving spring are fixedly connected to the first connecting rod and the second connecting rod and driven to move closer to each other. The first female hinge is rotatably connected to the second end of the first connecting rod, and the second female hinge is rotatably connected to the second end of the second connecting rod. Both the first female hinge and the second female hinge are fixed to the adjacent first unit middle plate / second unit middle plate. The restricted portion includes an arc-shaped plate, a groove, a rotating rocker arm, and two rotating torsion springs; the arc-shaped plate is fixed to the second end of the first connecting rod and the second end of the second connecting rod, and the groove is formed on the first connecting rod and the second connecting rod; the rotating rocker arm is rotatably connected to the first female hinge and the second female hinge respectively, and the rotating torsion springs are respectively disposed between the first female hinge / second female hinge and the rotating rocker arm; and the rotating rocker arm slides on the arc-shaped surface of the arc-shaped plate and is engaged in the groove; The restricted part also includes a locking hook and a locking rod respectively disposed on the first connecting rod and the second connecting rod, wherein the locking hook and the locking rod are engaged with each other when fully extended in the longitudinal direction.

[0012] The deployment mechanism of the multi-fold array deployment antenna of the present invention includes a third connecting rod, a fourth connecting rod, a third female hinge plate, and a fourth female hinge plate in both the transverse hinge assembly and the longitudinal hinge assembly. The first end of the third link and the first end of the fourth link are rotatably connected. The third female hinge plate is fixed to the second end of the third link, and the fourth female hinge plate is fixed to the second end of the fourth link. The third female hinge plate and the fourth female hinge plate in the transverse hinge assembly are respectively connected to the adjacent upper plate of the unit and the middle plate of the first unit / the adjacent lower plate of the unit and the middle plate of the second unit. The third female hinge plate and the fourth female hinge plate in the longitudinal hinge assembly are respectively connected to the adjacent upper plate of the unit / the adjacent lower plate of the unit.

[0013] The deployment mechanism of the multi-fold array deployment antenna of the present invention includes a positioning part for both the transverse hinge assembly and the longitudinal hinge assembly. The positioning part includes a positioning plate, a positioning groove, a positioning rod, and a positioning torsion spring. The positioning plate is fixed to the third connecting rod, and the positioning groove is formed on the positioning plate. The positioning rod is rotatably connected to the fourth connecting rod, and the positioning torsion spring is disposed between the fourth connecting rod and the positioning rod. The fourth connecting rod slides on the positioning plate and is engaged in the positioning groove.

[0014] A satellite includes a deployment mechanism for the aforementioned multi-fold array deployable antenna.

[0015] Because of the above technical solutions, this invention application has the following advantages and positive effects compared with the prior art: 1. Through the combined action of the cross-plate drive assembly, the lateral hinge assembly, the longitudinal hinge assembly, the primary deployment drive assembly, and the secondary deployment drive assembly, the antenna unit is able to be folded and retracted as much as possible in the retracted state; in the fully deployed state, the antenna unit can obtain a large deployment area; the antenna unit is first fully deployed in the longitudinal direction, and then the upper plate and the lower plate of the unit are deployed in the lateral direction, thereby expanding the aperture after deployment.

[0016] Second, the antenna deployment is powered by the first drive source on the primary deployment drive assembly and the second drive source on the secondary deployment drive assembly. The deployment speed and acceleration are controllable, which reduces the disturbance and impact on the spacecraft's attitude during the antenna deployment process.

[0017] Third, the locking part, limiting part, restricted part, and positioning part ensure that the antenna unit can achieve self-locking after it is fully deployed, thereby improving the rigidity and conformity accuracy of the antenna front. Attached Figure Description

[0018] Figure 1 A schematic diagram of the overall structure of the deployment mechanism of the multi-fold array deployment antenna in this application embodiment. Figure 2 A schematic diagram of the deployment process of the multi-fold array deployment antenna in this application embodiment. Figure 3 A schematic diagram of the primary deployment drive assembly of the multi-fold array deployment antenna in this application embodiment. Figure 4 A schematic diagram of the latching structure of the deployment mechanism of the multi-fold array deployment antenna in this application embodiment. Figure 5 A schematic diagram of the linkage structure of the deployment mechanism of the multi-fold array deployment antenna in this application embodiment. Figure 6 A schematic diagram of the secondary deployment drive component of the deployment mechanism of the multi-fold array deployment antenna in this application embodiment. Figure 7 A schematic diagram of the locking part structure of the deployment mechanism of the multi-fold array deployment antenna in this application embodiment. Figure 8 A schematic diagram of the root hinge assembly of the deployment mechanism of the multi-fold array deployment antenna in this application embodiment. Figure 9 A schematic diagram of the cross-plate assembly structure of the deployment mechanism for the multi-fold array deployment antenna in this application embodiment. Figure 10 A schematic diagram of the longitudinal hinge assembly of the deployment mechanism of the multi-fold array deployment antenna in this application embodiment. Figure 11 A schematic diagram of the positioning part structure of the deployment mechanism of the multi-fold array deployment antenna in this application embodiment. Explanation of reference numerals in the attached drawings: 1. First unit intermediate plate; 2. Second unit intermediate plate; 3. Unit upper plate; 4. Unit lower plate; 5. Cross-plate drive assembly; 6. Root hinge assembly; 7. Fixing part; 8. Longitudinal hinge assembly; 9. Transverse hinge assembly; 10. Primary deployment drive assembly; 11. Linkage part; 12. Secondary deployment drive assembly; 13. First fixed hinge; 14. First rotating hinge; 15. First drive source; 16. Main linkage wheel; 17. First fixed plate; 18. Second fixed plate; 19. First driven wheel; 20. Second driven wheel; 21. Second drive source; 22. Second fixed hinge; 23. Second rotating hinge; 24. Locking ring; 25. Locking rod; 26. Locking groove; 27. Connecting plate; 28. 1. Mounting plate; 29. ​​Third fixed hinge; 30. Third rotating hinge; 31. Limiting part; 32. Limiting block; 33. Limiting groove; 34. Limiting rod; 35. First connecting rod; 36. Second connecting rod; 37. First female hinge; 38. Second female hinge; 39. Drive spring; 40. Arc plate; 41. Groove; 42. Rotating swing arm; 43. Third connecting rod; 44. Fourth connecting rod; 45. Third female hinge plate; 46. Fourth female hinge plate; 47. Positioning plate; 48. Positioning groove; 49. Positioning rod; 50. Locking hook; 51. Locking rod; 52. Locking rod; 53. Locking groove; 54. Locking block; 55. Locking torsion spring; 56. Locking torsion spring; 57. Limiting torsion spring; 58. Rotating torsion spring; 59. Positioning torsion spring. Detailed Implementation

[0019] The deployment mechanism of a multi-fold array deployment antenna according to this application will be further described in detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of this application will become clearer from the following description and claims.

[0020] Example 1: See Figure 1 and Figure 2This embodiment provides a deployment mechanism for a multi-fold array deployable antenna, including an antenna unit, a cross-plate driving assembly 5, a root hinge assembly 6, a longitudinal hinge assembly 8, a transverse hinge assembly 9, a primary deployment driving assembly 10, and a secondary deployment driving assembly 12. The antenna element can be a helical antenna, including several first unit intermediate plates 1, several second unit intermediate plates 2, several unit upper plates 3 and several unit lower plates 4; A plurality of first unit intermediate plates 1 are arranged sequentially along the longitudinal direction, and adjacent first unit intermediate plates 1 are connected by a cross-plate driving assembly 5, and the rotation directions of adjacent cross-plate driving assemblies 5 are opposite; a plurality of second unit intermediate plates 2 are arranged sequentially along the longitudinal direction and correspond one-to-one with the first unit intermediate plates 1 in the transverse direction, and adjacent second unit intermediate plates 2 are connected by a cross-plate driving assembly 5, and the rotation directions of adjacent cross-plate driving assemblies 5 are opposite; wherein, the first unit intermediate plate 1 and / or the second unit intermediate plate 2 located at the head end are connected to the outer planetary sidewall through a root hinge assembly 6, and a fixing part 7 is connected between the corresponding first unit intermediate plate 1 and the second unit intermediate plate 2 to fix their relative positions.

[0021] Several unit upper plates 3 are arranged sequentially along the longitudinal direction, and adjacent unit upper plates 3 are connected by longitudinal hinge components 8; the unit upper plates 3 correspond one-to-one with the first unit middle plate 1 in the transverse direction, and are respectively connected to the side of the corresponding first unit middle plate 1 away from the second unit middle plate 2 by transverse hinge components 9; several unit lower plates 4 are arranged sequentially along the longitudinal direction, and adjacent unit lower plates 4 are connected by longitudinal hinge components 8; the unit lower plates 4 correspond one-to-one with the second unit middle plate 2 in the transverse direction, and are respectively connected to the side of the corresponding second unit middle plate 2 away from the first unit middle plate 1 by transverse hinge components 9.

[0022] The fixed end of the primary deployment drive assembly 10 is connected to the side wall of the external celestial body, and the drive end is connected to the root hinge assembly 6. It is used to drive the first unit intermediate plate 1 and the second unit intermediate plate 2 located at the head end to rotate and unfold axially. Several linkage parts 11 are respectively installed on the corresponding fixed parts 7. The input end of the linkage part 11 located between the first unit intermediate plate 1 and the second unit in the second horizontal row is connected to the drive end of the primary deployment drive assembly 10. In addition, in the two linkage parts 11 arranged between odd-numbered horizontal rows and even-numbered horizontal rows along the direction away from the external celestial body, the output end of the linkage part 11 closer to the external celestial body is connected to the input end of the linkage part 11 farther away from the external celestial body. It is used to transmit the rotation driving force to each span plate drive assembly 5 to drive the first unit intermediate plate 1 and the second unit intermediate plate 2 to rotate and unfold axially. At least two secondary unfolding drive components 12 are provided, wherein at least one secondary unfolding drive component 12 is provided between the first unit middle plate 1 and the unit upper plate 3 for driving the unit upper plate 3 to flip and unfold laterally relative to the first unit middle plate 1, and at least one secondary unfolding drive component 12 is provided between the second unit middle plate 2 and the unit lower plate 4 for driving the unit lower plate 4 to flip and unfold laterally relative to the second unit middle plate 2.

[0023] Further configuration: the number of the first unit middle plate 1, the second unit middle plate 2, the unit upper plate 3, and the unit lower plate 4 are all four. The overall working process is as follows: the first deployment drive assembly 10 and several linkage parts 11 cooperate to realize the longitudinal deployment of the antenna unit plate. During the longitudinal deployment, the cross-plate drive assembly 5 and the longitudinal hinge assembly 8 cause the relative rotation of adjacent first unit middle plates, adjacent second unit middle plates, adjacent unit upper plates 3, and adjacent unit lower plates 4, from an inverted W shape until they are fully opened in the longitudinal direction. Then, the second deployment drive assembly 12 realizes the lateral deployment of the unit upper plate 3 and unit lower plate 4, and transmits the driving force of the second deployment drive assembly 12 to each unit upper plate 3 or each unit lower plate 4 through the lateral hinge assembly 9 and the longitudinal hinge assembly 8 until they are fully deployed in the lateral direction, forming a 4×4 deployable antenna unit.

[0024] The horizontal row counting is defined as counting from the direction closest to the external star to the direction furthest away from the external star when all antenna elements are fully deployed; further, odd-numbered horizontal rows are the first and third horizontal rows, and even-numbered horizontal rows are the second and fourth horizontal rows.

[0025] The specific structure of the deployment mechanism of the multi-fold array deployment antenna in this embodiment will be further explained below: See Figure 1 , Figure 3 , Figure 4 and Figure 5 In this embodiment, the one-time deployment drive assembly 10 includes a first fixed hinge 13, a first rotating hinge 14, a first drive source 15, a main linkage wheel 16, and a snap-fit ​​part. One end of the first fixed hinge 13 is fixed to the body of the first drive source 15, and the other end of the first fixed hinge 13 is fixed to the fixed end of the root hinge assembly 6 connected to the external celestial body; the first rotating hinge 14 is fixed to the output shaft of the first drive source 15, and the other end of the first rotating hinge 14 is fixed to the fixing part 7; and the main linkage wheel 16 is fixed to the output shaft of the first drive source; the fixing part 7 consists of a first fixing plate 17 and a second fixing plate 18 arranged longitudinally between the corresponding first unit intermediate plate 1 and second unit intermediate plate 2, and the linkage part 1... 1. The first driven wheel 19 and the second driven wheel 20 are respectively set on the first fixed plate 17 and the second fixed plate 18. Along the direction away from the external celestial body, the second driven wheel 20 of the odd-numbered horizontal fixed part 7 is connected to the first driven wheel 19 of the next odd-numbered horizontal fixed part 7 by rope transmission, and the second driven wheel 20 of the even-numbered horizontal fixed part 7 is connected to the first driven wheel 19 of the next even-numbered horizontal fixed part 7 by rope transmission; wherein, the first driven wheel 19 located in the second row is connected to the main drive wheel 16 by rope transmission.

[0026] A locking part is disposed between the first fixed hinge 13 and the first rotating hinge 14 for fixing; specifically, the locking part includes a locking rod 52, a locking block 54, and a locking groove 53; the locking rod 52 is fixed to the first rotating hinge 14, so that the first rotating hinge 14 can drive the locking rod 52 to move during rotation; the locking block 54 is fixed to the first fixed hinge 13, and the locking groove 53 is opened on the locking block 54. When the first rotating hinge 14 and the second fixed hinge 22 rotate to a preset position, the locking rod 52 is locked in the locking groove 53, so that the first deployment drive assembly 10 is more stable after deployment; of course, in order to keep the locking rod 52 in the locking groove 53, a locking torsion spring 55 can be provided between the locking rod 52 and the first rotating hinge 14. The locking torsion spring 55 is always in a rebound state, so that the locking rod 52 is pressed against the inner wall of the locking groove 53.

[0027] Further configuration: the number of single-expansion drive components 10 is one, and one end of the first rotating hinge 14 is fixed to the first fixed plate 17 between the first unit middle plate 1 of the first end (first horizontal row) and the second unit middle plate 2 of the first end (first horizontal row), so that the single-expansion drive components 10 are more stable in force transmission; the first drive source 15 is a motor. The one-time unfolding drive component 10 may be equipped with a micro switch to monitor whether it is fully opened and realize information feedback; its main working process is: when the lever 52 is engaged in the slot 53, the lever 52 can push the switch component on the micro switch, so that the micro switch is triggered and realizes information feedback.

[0028] Its working process is as follows: An existing technology (currently known as a clamping release device) is installed on the external celestial body to fix the folded antenna unit to the side wall of the external celestial body. When the antenna unit needs to be unfolded, the clamping release device is released using a pyrotechnic unlocking method. The output shaft of the first drive source 15 rotates, driving the first rotating hinge 14 to rotate. At this time, the associated root hinge assembly 6 will also rotate, driving the first unit middle plate 1 and the second unit middle plate 2 of the first horizontal row to move. During the rotation of the output shaft of the first drive source 15, it will drive the main linkage wheel 16 to rotate. The main linkage wheel 16 drives the first driven wheel 19 between the first unit middle plate 1 and the second unit middle plate 2 of the second horizontal row via a rope. The second driven wheel 20 between the first horizontal unit intermediate plate 1 and the first horizontal unit intermediate plate 2 is connected to the first driven wheel 19 between the third horizontal unit intermediate plate 1 and the third horizontal unit intermediate plate 2 via a rope drive. The second driven wheel 20 between the second horizontal unit intermediate plate 1 and the second horizontal unit intermediate plate 2 is connected to the first driven wheel 19 between the fourth horizontal unit intermediate plate 1 and the fourth horizontal unit intermediate plate 2. Since the first driven wheel 19 and the second driven wheel 20 are fixed to the corresponding fixing part 7, the friction generated by the rope during the movement will drive the movement of the adjacent first unit intermediate plate 1 and the adjacent second unit intermediate plate 2, ultimately realizing the opening of the antenna unit in the longitudinal direction.

[0029] See Figure 1 , Figure 6 and Figure 7 In this embodiment, the secondary deployment drive assembly 12 includes a second drive source 21, a second fixed hinge 22, and a second rotating hinge 23. One end of the second fixed hinge 22 is fixed to the body of the second drive source 21, and the other end of the second fixed hinge 22 is fixed to the middle plate 1 of the first unit or the middle plate 2 of the second unit; one end of the second rotating hinge 23 is fixed to the output shaft of the second drive source 21, and the other end of the second rotating hinge 23 is fixed to the associated upper plate 3 of the unit or the lower plate 4 of the unit; a micro switch may be provided on the secondary unfolding drive assembly 12 to monitor whether it is fully opened and realize information feedback.

[0030] Further configuration: the number of secondary deployment drive components 12 is two, with one secondary deployment drive component 12 located between the upper plate 3 of the second horizontal row unit and the middle plate 1 of the first unit in the second horizontal row, and the other secondary deployment drive component 12 located between the lower plate 4 of the second horizontal row unit and the middle plate 2 of the second unit in the second horizontal row. The main implementation process is as follows: when the antenna unit is fully deployed in the longitudinal direction, the second drive source 21 is activated, and the output shaft drives the second rotating hinge 23 to rotate. One of the second rotating hinges 23 drives the upper plate 3 of the second horizontal row unit to rotate. During the rotation of the upper plate 3 of the second horizontal row unit, the force is transmitted due to the mutual connection of the longitudinal hinge component 8 and the transverse hinge component 9, driving the other upper plates 3 of the unit to move. The other second rotating hinge 23 drives the lower plate 4 of the second horizontal row unit to rotate. During the rotation of the lower plate 4 of the second horizontal row unit, the force is transmitted due to the mutual connection of the longitudinal hinge component 8 and the transverse hinge component 9, driving the other lower plates 4 of the unit to move.

[0031] See Figure 1 , Figure 6 and Figure 7 In this embodiment, the secondary deployment drive assembly 12 also includes a locking part, which includes a locking ring 24, a locking rod 25, a locking groove 26, and a locking torsion spring 56. The locking ring 24 is fixed to the output shaft / second rotating hinge 23 of the second drive source 21, the locking groove 26 is opened on the locking ring 24, and the locking rod 25 is rotatably connected to the second fixed hinge 22. The locking torsion spring 56 is disposed between the second fixed hinge 22 and the locking rod 25, and the locking rod 25 slides on the outer wall of the locking ring 24 and is engaged in the locking groove 26.

[0032] In a further configuration, the locking ring 24 and the second fixed hinge 22 are integrated. That is, when the second fixed hinge 22 rotates synchronously with the output shaft of the second drive source 21, the locking ring 24 also rotates simultaneously. The locking rod 25 slides on the outer wall of the locking ring 24. When the upper plate 3 and the lower plate 4 of the unit are fully extended in the lateral direction, the locking groove 26 moves to the preset position, and the locking rod 25 slides from the connected outer wall into the locking groove 26, thus achieving locking. Of course, in order to ensure that the locking rod 25 is always located in the locking groove 26, a locking torsion spring 56 can be provided between the locking rod 25 and the second fixed hinge 22. By keeping the locking torsion spring 56 in a rebound state, the locking rod 25 is pressed against the inner wall of the locking groove 26.

[0033] Similarly, to facilitate observation of the secondary deployment drive assembly 12, a micro switch can be provided on the secondary deployment drive assembly 12.

[0034] See Figure 1 and Figure 8In this embodiment, the root hinge assembly 6 includes a connecting plate 27, a mounting plate 28, at least one third fixed hinge member 29, at least one third rotating hinge member 30, and a limiting part 31; the third fixed hinge member 29 is fixed to the connecting plate 27, and the connecting plate 27 is fixed to the external celestial body; the third rotating hinge member 30 is fixed to the mounting plate 28, and the mounting plate 28 is fixedly connected to the first unit intermediate plate 1 and / or the second unit intermediate plate 2 at the head end; the end of the third fixed hinge member 29 away from the connecting plate 27 is rotatably connected to the end of the third rotating hinge member 30 away from the mounting plate 28; the limiting part 31 is disposed between the third fixed hinge member 29 and the third rotating hinge member 30.

[0035] Further configuration includes two third fixed hinge members 29 and two third rotating hinge members 30; the connecting plate 27 can be fixed to the external star by bolts or other means, and each end of the connecting plate 27 is fixed with a corresponding third fixed hinge member 29. One end of one third rotating hinge member 30 is connected to the third fixed hinge member 29, and the other end is connected to the first unit intermediate plate 1. A torsion spring can be set between the third rotating hinge member 30 and the third fixed hinge member 29, and the two work together under the rebound force of the torsion spring and the driving force of the first driving source 15; one end of the other third rotating hinge member 30 is connected to the other third fixed hinge member 29, and the other end is fixed to the second unit intermediate plate 2. A torsion spring can be set between the third rotating hinge member 30 and the third fixed hinge member 29; thus, the first deployment drive assembly 10 is located between the two third fixed hinge members 29, and the first fixed hinge member 13 is fixed to the connecting plate 27; making the connection between the root hinge assembly 6 and the antenna unit more stable, and the placement of the first deployment drive assembly 10 more reasonable.

[0036] As a further feature, a microswitch can be installed on the root hinge assembly 6 to monitor whether it is fully open and to provide feedback.

[0037] See Figure 1 and Figure 8 In this embodiment, the limiting part 31 includes a limiting block 32, a limiting groove 33, a limiting rod 34, and a limiting torsion spring 57; the limiting block 32 is fixed on the third rotating hinge member 30, and the limiting groove 33 is opened on the limiting block 32; the limiting rod 34 is fixed on the third fixed hinge member 29, and the limiting torsion spring 57 is disposed between the third rotating hinge member 30 and the limiting rod 34, and the limiting rod 34 slides on the limiting block 32 and is engaged in the limiting groove 33.

[0038] Furthermore, the limiting block 32 and the third rotating hinge 30 are integrally formed. Thus, when the third rotating hinge 30 moves, the limiting block 32 also rotates synchronously. The side wall of the limiting block 32 is arc-shaped, allowing the limiting rod 34 to slide on the side wall of the limiting block 32. When the limiting rod 34 slides into the limiting groove 33, the root hinge assembly 6 and the first-time deployment drive assembly 10 are locked. Of course, in order to ensure that the limiting rod 34 is always located in the limiting groove 33, a limiting torsion spring 57 can be provided between the limiting rod 34 and the third fixed hinge 29. By keeping the limiting torsion spring 57 in a rebound state, the limiting rod 34 is pressed against the inner wall of the limiting groove 33.

[0039] See Figure 1 and Figure 9 In this embodiment, the cross-plate drive assembly 5 includes a first connecting rod 35, a second connecting rod 36, a first female hinge 37, a second female hinge 38, a drive spring 39, and a restricted part; The first end of the first link 35 and the first end of the second link 36 are rotatably connected. The two torsion arms of the drive spring 39 are fixedly connected to the first link 35 and the second link 36 and are driven to move closer to each other. The first female hinge 37 is rotatably connected to the second end of the first link 35, and the second female hinge 38 is rotatably connected to the second end of the second link 36. The first female hinge 37 and the second female hinge are both fixed to the adjacent first unit intermediate plate 1 / second unit intermediate plate 2. The restricted portion includes two arc-shaped plates 40, two grooves 41, two rotating rocker arms 42, and two rotating torsion springs 58. The arc-shaped plates 40 are fixed to the second end of the first connecting rod 35 and the second end of the second connecting rod 36. The grooves 41 are formed on the first connecting rod 35 and the second connecting rod 36. The rotating rocker arms 42 are rotatably connected to the first female hinge 37 and the second female hinge 38, respectively. The rotating torsion springs 58 are respectively disposed between the first female hinge 37 / the second female hinge 38 and the rotating rocker arms 42, and the rotating rocker arms 42 slide on the arc-shaped plates 40 and are engaged in the grooves 41. The restricted portion also includes a locking hook 50 and a locking rod 51 respectively disposed on the first connecting rod 35 and the second connecting rod 36. The locking hook 50 and the locking rod 51 are engaged with each other when fully extended longitudinally.

[0040] Furthermore, two cross-plate drive assemblies 5 are provided between the adjacent first unit intermediate plate 1 and the adjacent second unit intermediate plate 2, which are far apart from each other. This design makes the rotation process more stable.

[0041] Furthermore, to ensure that the rotating rocker arm 42 is always located within the groove 41, a rotating torsion spring 58 can be provided between the rotating rocker arm 42 and the first female hinge 37 / second female hinge 38. By ensuring that the rotating torsion spring 58 is always in a rebound state, the rotating rocker arm 42 is pressed against the inner wall of the groove 41. Additionally, a micro switch can be provided on the cross-plate drive assembly 5 to monitor whether it is fully open and to provide information feedback.

[0042] See Figure 1 , Figure 10 and Figure 11 In this embodiment, both the transverse hinge assembly 9 and the longitudinal hinge assembly 8 include a third connecting rod 43, a fourth connecting rod 44, a third female hinge plate 45, and a fourth female hinge plate 46. The first end of the third connecting rod 43 and the first end of the fourth connecting rod 44 are rotatably connected. The third female hinge plate 45 is fixed to the second end of the third connecting rod 43, and the fourth female hinge plate 46 is fixed to the second end of the fourth connecting rod 44. The third female hinge plate 45 and the fourth female hinge plate 46 in the transverse hinge assembly 9 are respectively connected to the adjacent unit upper plate 3 and the first unit middle plate 1 / the adjacent unit lower plate 4 and the second unit middle plate 2. The third female hinge plate 45 and the fourth female hinge plate 46 in the longitudinal hinge assembly 8 are respectively connected to the adjacent unit upper plate 3 / the adjacent unit lower plate 4.

[0043] Further configuration includes two mutually distant lateral hinge components 9 between adjacent first unit intermediate plate 1 and unit upper plate 3, and between adjacent second unit intermediate plate 2 and unit lower plate 4. Similarly, two mutually distant longitudinal connecting components are provided between adjacent first unit intermediate plates 1 and adjacent second unit intermediate plates 2. A torsion spring can be provided between the third link 43 and the fourth link 44. Under the rebound action of the torsion spring, the driving force of the first driving source 15 and the second driving source 21 can be reduced on the one hand, and the antenna unit can be more flexible in rotation on the other hand.

[0044] In this embodiment, both the transverse hinge assembly 9 and the longitudinal hinge assembly 8 include a positioning part, which includes a positioning plate 47, a positioning groove 48, a positioning rod 49, and a positioning torsion spring 59. The positioning plate 47 is fixed to the third connecting rod 43, and the positioning groove 48 is formed on the positioning plate 47. The positioning rod 49 is rotatably connected to the fourth connecting rod 44, and the positioning torsion spring 59 is disposed between the fourth connecting rod 44 and the positioning rod 49. The fourth connecting rod 44 slides on the positioning plate 47 and is engaged in the positioning groove 48.

[0045] Further configuration: the third link 43 located in the transverse hinge assembly 9 is fixed to the intermediate plate 2 of the second unit, and the third link 43 located in the longitudinal hinge assembly 8 is fixed to the intermediate plate 1 of the first unit; the positioning plate 47 is integrally formed on the third link 43, and the fourth link 44 will drive the positioning rod 49 to slide on the side wall of the positioning plate 47 during rotation until the positioning rod 49 is engaged in the positioning groove 48 to achieve self-locking.

[0046] In a further configuration, to ensure that the positioning rod 49 is always located within the positioning groove 48, a positioning torsion spring 59 can be provided between the positioning rod 49 and the fourth connecting rod 44. The positioning torsion spring 59 is always in a rebound state, pressing the positioning rod 49 against the inner wall of the positioning groove 48. Microswitches can be provided on the third female hinge plate 45 and the fourth female hinge plate 46 to monitor whether the transverse hinge assembly 9 and the longitudinal hinge assembly 8 have achieved self-locking.

[0047] In summary, the deployment mechanism of the multi-fold array deployment antenna in this embodiment will be described below. First step: The antenna unit is first deployed longitudinally. The first drive source 15 of the first deployment drive assembly 10 is activated. After the output shaft rotates, it will drive the first rotating hinge 14 to rotate. At the same time, the third rotating hinge 30 of the root hinge assembly 6 will rotate, driving the unit upper plate 3, unit lower plate 4, first unit middle plate 1, and second unit middle plate 2 of the first horizontal row (head end) to be deployed longitudinally. Then, through the sequential connection of the first deployment drive assembly 10 and several linkage parts 11, the other unit upper plate 3, unit lower plate 4, first unit middle plate 1, and second unit middle plate 2 are deployed longitudinally through friction, forming an inverted W shape. When fully deployed, the first unit middle plate 1 and the second unit middle plate 2 are located on the same plane, forming a 2 (column) × 4 (row) pattern, and are self-locked by the limiting part in the cross plate drive assembly 5 and the positioning part in the longitudinal hinge assembly 8. Step 2: The antenna unit is then horizontally expanded. The second drive source 21 of the secondary expansion drive assembly 12 is activated. After the output shaft rotates, it will drive the second rotating hinge 23 to move simultaneously. The second rotating hinge 23 drives the upper plate 3 and the lower plate 4 of the unit to expand horizontally. And it achieves self-locking through the positioning part in the horizontal hinge assembly 9, finally forming a 4 (column) × 4 (row) pattern. Therefore, this implementation has the advantages of good deployment synchronization, small folding volume, simple structure and low impact force, and can lock the antenna unit after two-dimensional deployment, which can meet the high precision requirements of the antenna.

[0048] Example 2: A satellite includes a deployment mechanism for a multi-fold array deployable antenna. The deployment mechanism includes an antenna element, a cross-plate drive assembly 5, a root hinge assembly 6, a longitudinal hinge assembly 8, a transverse hinge assembly 9, a primary deployment drive assembly 10, and a secondary deployment drive assembly 12. The antenna unit includes several first unit intermediate plates 1, several second unit intermediate plates 2, several unit upper plates 3, and several unit lower plates 4; A plurality of first unit intermediate plates 1 are arranged sequentially along the longitudinal direction, and adjacent first unit intermediate plates 1 are connected by a cross-plate driving assembly 5, and the rotation directions of adjacent cross-plate driving assemblies 5 are opposite; a plurality of second unit intermediate plates 2 are arranged sequentially along the longitudinal direction and correspond one-to-one with the first unit intermediate plates 1 in the transverse direction, and adjacent second unit intermediate plates 2 are connected by a cross-plate driving assembly 5, and the rotation directions of adjacent cross-plate driving assemblies 5 are opposite; wherein, the first unit intermediate plate 1 and / or the second unit intermediate plate 2 located at the head end are connected to the outer planetary sidewall through a root hinge assembly 6, and a fixing part 7 is connected between the corresponding first unit intermediate plate 1 and the second unit intermediate plate 2 to fix their relative positions.

[0049] Several unit upper plates 3 are arranged sequentially along the longitudinal direction, and adjacent unit upper plates 3 are connected by longitudinal hinge components 8; the unit upper plates 3 correspond one-to-one with the first unit middle plate 1 in the transverse direction, and are respectively connected to the side of the corresponding first unit middle plate 1 away from the second unit middle plate 2 by transverse hinge components 9; several unit lower plates 4 are arranged sequentially along the longitudinal direction, and adjacent unit lower plates 4 are connected by longitudinal hinge components 8; the unit lower plates 4 correspond one-to-one with the second unit middle plate 2 in the transverse direction, and are respectively connected to the side of the corresponding second unit middle plate 2 away from the first unit middle plate 1 by transverse hinge components 9.

[0050] The fixed end of the primary deployment drive assembly 10 is connected to the side wall of the external celestial body, and the drive end is connected to the root hinge assembly 6. It is used to drive the first unit intermediate plate 1 and the second unit intermediate plate 2 located at the head end to rotate and unfold axially. Several linkage parts 11 are respectively installed on the corresponding fixed parts 7. The input end of the linkage part 11 located in the second horizontal row of the first unit intermediate plate 1 and the second unit intermediate plate is connected to the drive end of the primary deployment drive assembly 10. In addition, in the two linkage parts 11 arranged between odd-numbered horizontal rows and even-numbered horizontal rows along the direction away from the external celestial body, the output end of the linkage part 11 closer to the external celestial body is connected to the input end of the linkage part 11 farther away from the external celestial body. It is used to transmit the rotation driving force to each span plate drive assembly 5 to drive the first unit intermediate plate 1 and the second unit intermediate plate 2 to rotate and unfold axially.

[0051] At least two secondary unfolding drive components 12 are provided, at least one secondary unfolding drive component 12 is provided between the first unit middle plate 1 and the unit upper plate 3, for driving the unit upper plate 3 to flip and unfold laterally relative to the first unit middle plate 1, and at least one secondary unfolding drive component 12 is provided between the second unit middle plate 2 and the unit lower plate 4, for driving the unit lower plate 4 to flip and unfold laterally relative to the second unit middle plate 2.

[0052] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings; however, the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, if these changes fall within the scope of the claims of the present invention and their equivalents, they shall still fall within the protection scope of the present invention.

Claims

1. A deployment mechanism for a multi-fold array deployable antenna, characterized in that, include, An antenna unit, the antenna unit comprising a plurality of first unit intermediate plates, a plurality of second unit intermediate plates, a plurality of unit upper plates and a plurality of unit lower plates; A plurality of first unit intermediate plates are arranged sequentially along the longitudinal direction. Adjacent first unit intermediate plates are connected by a cross-plate driving assembly, and the rotation directions of adjacent cross-plate driving assemblies are opposite. The cross-plate driving assembly includes a first connecting rod, a second connecting rod, a first female hinge, a second female hinge, a driving spring, and a limiting part. The first end of the first connecting rod and the first end of the second connecting rod are rotatably connected. The two torsion arms of the driving spring are fixedly connected to the first connecting rod and the second connecting rod and driven to move closer to each other. The first female hinge is rotatably connected to the second end of the first connecting rod, and the second female hinge is rotatably connected to the second end of the second connecting rod. Both the first female hinge and the second female hinge are fixed to the adjacent first unit intermediate plate / second unit intermediate plate. A plurality of second unit intermediate plates are arranged sequentially along the longitudinal direction and correspond one-to-one with the first unit intermediate plates in the transverse direction. Adjacent second unit intermediate plates are connected by a cross-plate driving assembly, and the rotation directions of adjacent cross-plate driving assemblies are opposite. The first unit intermediate plate and / or the second unit intermediate plate located at the head end are connected to the external planetary sidewall through a root hinge assembly. A fixing part is connected between the corresponding first unit intermediate plate and the second unit intermediate plate to fix their relative positions. The fixing part consists of a first fixing plate and a second fixing plate arranged longitudinally between the corresponding first unit intermediate plate and the second unit intermediate plate. Several unit upper plates are arranged sequentially along the longitudinal direction, and adjacent unit upper plates are connected by a longitudinal hinge assembly; each unit upper plate corresponds to the first unit middle plate in the transverse direction, and is respectively connected to the side of the corresponding first unit middle plate away from the second unit middle plate by a transverse hinge assembly. Several unit lower plates are arranged sequentially along the longitudinal direction, and adjacent unit lower plates are connected by a longitudinal hinge assembly; each unit lower plate corresponds to the second unit middle plate in the transverse direction, and is respectively connected to the side of the corresponding second unit middle plate away from the first unit middle plate by a transverse hinge assembly; A primary deployment drive assembly, with its fixed end connected to the sidewall of an external celestial body and its driving end connected to the root hinge assembly, is used to drive the first unit intermediate plate and the second unit intermediate plate located at the head end to axially rotate and unfold. The primary deployment drive assembly includes a first fixed hinge, a first rotating hinge, a first drive source, and a main linkage wheel. One end of the first fixed hinge is fixed to the body of the first drive source, and the other end is fixed to the fixed end of the root hinge assembly connected to the external celestial body. The first rotating hinge is fixed to the output shaft of the first drive source, and the other end is fixed to the fixed part. Furthermore, the main linkage wheel is fixed to the output shaft of the first drive source. A plurality of linkage parts are respectively installed on the corresponding fixed parts. The linkage parts are a first driven wheel and a second driven wheel respectively set on the first fixed plate and the second fixed plate. The input end of the linkage part located on the first unit middle plate and the second unit middle plate in the second horizontal row is connected to the driving end of the first unfolding drive assembly. In addition, in the two linkage parts arranged between odd-numbered horizontal rows and between even-numbered horizontal rows along the direction away from the external celestial body, the output end of the linkage part closer to the external celestial body is connected to the input end of the linkage part farther from the external celestial body. The first driven wheel located in the second row is connected to the main linkage wheel through a rope to transmit the flipping driving force to each of the cross-plate drive assemblies, driving the first unit middle plate and the second unit middle plate to flip and unfold axially. At least two secondary unfolding drive components are provided, at least one of which is provided between the first unit middle plate and the unit upper plate, for driving the unit upper plate to flip and unfold laterally relative to the first unit middle plate, and at least one of which is provided between the second unit middle plate and the unit lower plate, for driving the unit lower plate to flip and unfold laterally relative to the second unit middle plate.

2. The deployment mechanism of the multi-fold array deployment antenna according to claim 1, characterized in that: The primary deployment drive assembly includes a snap-fit ​​part; The locking part is disposed between the first fixed hinge and the first rotating hinge for fixing; the locking part includes a locking rod, a locking block, a locking groove, and a locking torsion spring; the locking rod is rotatably connected to the first rotating hinge, the locking block is fixed to the first fixed hinge, and the locking groove is formed on the first fixed hinge; the locking torsion spring is disposed between the first fixed hinge and the locking rod, and the locking rod slides on the locking block and engages with the locking groove to achieve locking; Along the direction away from external celestial bodies, the second driven wheels of the odd-numbered horizontal rows of the fixed parts are all connected to the first driven wheels of the next odd-numbered horizontal rows of the fixed parts via rope transmission, and the second driven wheels of the even-numbered horizontal rows of the fixed parts are all connected to the first driven wheels of the next even-numbered horizontal rows of the fixed parts via rope transmission.

3. The deployment mechanism of the multi-fold array deployment antenna according to claim 1, characterized in that: The secondary deployment drive assembly includes a second drive source, a second fixed hinge, and a second rotating hinge; One end of the second fixed hinge is fixed to the second drive source body, and the other end of the second fixed hinge is fixed to the first unit middle plate or the second unit middle plate; one end of the second rotating hinge is fixed to the output shaft of the second drive source, and the other end of the second rotating hinge is fixed to the associated unit upper plate or the unit lower plate.

4. The deployment mechanism of the multi-fold array deployment antenna according to claim 3, characterized in that: The secondary deployment drive assembly also includes a locking part, which includes a locking ring, a locking rod, a locking groove, and a locking torsion spring. The locking ring is fixed to the output shaft of the second drive source / the second rotating hinge, the locking groove is formed on the locking ring, the locking rod is rotatably connected to the second fixed hinge, and the locking torsion spring is disposed between the second fixed hinge and the locking rod; the locking rod slides on the outer wall of the locking ring and is engaged in the locking groove.

5. The deployment mechanism of the multi-fold array deployment antenna according to claim 1, characterized in that: The root hinge assembly includes a connecting plate, a mounting plate, at least one third fixed hinge member, at least one third rotating hinge member, and a limiting part; The third fixed hinge is fixed to the connecting plate, and the connecting plate is fixed to the external celestial body; the third rotating hinge is fixed to the mounting plate, and the mounting plate is fixedly connected to the first unit intermediate plate and / or the second unit intermediate plate at the head end; the end of the third fixed hinge away from the connecting plate is rotatably connected to the end of the third rotating hinge away from the mounting plate. The limiting part is disposed between the third fixed hinge and the third rotating hinge.

6. The deployment mechanism of the multi-fold array deployment antenna according to claim 5, characterized in that: The limiting part includes a limiting block, a limiting groove, a limiting rod, and a limiting torsion spring; The limiting block is fixed to the third rotating hinge, and the limiting groove is formed on the limiting block; the limiting rod is rotatably connected to the third fixed hinge, the limiting torsion spring is disposed between the third fixed hinge and the limiting rod, and the limiting rod slides on the outer wall of the limiting block and is engaged in the limiting groove.

7. The deployment mechanism of the multi-fold array deployment antenna according to claim 1, characterized in that: The restricted portion includes two arc-shaped plates, two grooves, two rotating rocker arms, and two rotating torsion springs; the arc-shaped plates are fixed to the second end of the first connecting rod and the second end of the second connecting rod, and the grooves are formed on the first connecting rod and the second connecting rod; the rotating rocker arms are rotatably connected to the first female hinge and the second female hinge respectively, and the rotating torsion springs are respectively disposed between the first female hinge / second female hinge and the rotating rocker arms; and the rotating rocker arms slide on the arc-shaped surface of the arc-shaped plates and are engaged in the grooves; The restricted part also includes a locking hook and a locking rod respectively disposed on the first connecting rod and the second connecting rod, wherein the locking hook and the locking rod are engaged with each other when fully extended in the longitudinal direction.

8. The deployment mechanism of the multi-fold array deployment antenna according to claim 1, characterized in that: Both the transverse hinge assembly and the longitudinal hinge assembly include a third link, a fourth link, a third female hinge plate, and a fourth female hinge plate. The first end of the third link and the first end of the fourth link are rotatably connected. The third female hinge plate is fixed to the second end of the third link, and the fourth female hinge plate is fixed to the second end of the fourth link. The third female hinge plate and the fourth female hinge plate in the transverse hinge assembly are respectively connected to the adjacent upper plate of the unit and the middle plate of the first unit / the adjacent lower plate of the unit and the middle plate of the second unit. The third female hinge plate and the fourth female hinge plate in the longitudinal hinge assembly are respectively connected to the adjacent upper plate of the unit / the adjacent lower plate of the unit.

9. The deployment mechanism of the multi-fold array deployment antenna according to claim 8, characterized in that: Both the transverse hinge assembly and the longitudinal hinge assembly include a positioning part, which includes a positioning plate, a positioning groove, a positioning rod, and a positioning torsion spring. The positioning plate is fixed to the third connecting rod, and the positioning groove is formed on the positioning plate. The positioning rod is rotatably connected to the fourth connecting rod, and the positioning torsion spring is disposed between the fourth connecting rod and the positioning rod. The fourth connecting rod slides on the positioning plate and is engaged in the positioning groove.

10. A satellite, characterized in that: The deployment mechanism includes the multi-fold array deployment antenna as described in any one of claims 1 to 9.

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