Deployable truss of satellite antenna

Abstract

A satellite antenna deployable truss disclosed by the present invention comprises a load-bearing truss, a plurality of stay bar devices are arranged on the load-bearing truss, each stay bar device comprises a lifting module, a floating connection structure and a fine adjustment support module, each fine adjustment support module comprises a mounting rack, a swing connection piece and a locking support assembly, and the mounting rack is mounted on a floating seat of the floating connection structure. The locking supporting assembly comprises a ball stud, a base assembly and a top cover, the ball stud is mounted in the mounting groove, the top cover can be rotationally switched between an unlocking state and a locking state relative to the base assembly, a plurality of locking rods are arranged on the base assembly in a sliding mode, and a guide structure is arranged between the top cover and the locking rods; when the top cover is rotationally switched between the unlocking state and the locking state relative to the base assembly, the lock rods get close to or get away from one another through the guide structures. The satellite antenna is convenient to disassemble and assemble on the bearing truss, the ball head bolt is firmly locked and is not easy to shake, and the stress concentration in the placing process of the satellite antenna is effectively avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite antenna processing and assembly, and in particular to a deployable truss for a satellite antenna. Background Art

[0002] The existing Chinese patent with announcement number CN101635390B discloses a final assembly mold of a truss-type spatial structure, whose structure is as follows: a plurality of brackets are fixed on a base, and a fine-tuning mechanism is installed on the top of each of the brackets; the fine-tuning mechanism is composed of: a fixed plate, fixed to the top of the bracket; an adjustment plate, placed above the fixed plate, and fixed to the fixed plate eccentrically as a whole, and at the same time, the adjustment plate is fixed to the disc seat placed above it eccentrically as a whole for horizontal adjustment; a lifting rod, the lower end of which is fixed to the center position of the disc seat for vertical adjustment; a ball head support, the bottom of which is a sphere and the top of which is a cylindrical support rod, the ball at the bottom of which is connected to the ball socket at the upper end of the lifting rod through a tightening cover, so that the ball head support swings with the ball socket as the center.

[0003] However, the above-mentioned satellite antenna truss assembly mold has the following disadvantages: usually, after the factory processes and assembles the satellite antenna, it needs to send the satellite antenna assembled on the truss mold to the testing center for testing. After the testing, the satellite antenna is sent back to the factory and placed on the truss mold. At the same time, multiple brackets are used to support and position the satellite antenna. When the satellite antenna is put back on the truss mold, the above-mentioned brackets lack a positioning structure between the ball head support and the satellite antenna, so the position of the satellite antenna placed on the truss mold will deviate from the assembly position during the original processing, resulting in a reduction in the overall support of the truss mold for the satellite antenna and deformation of the satellite antenna.

[0004] To this end, the existing technology has proposed an improvement plan, namely, installing several flower keys 81 on the curved surface of the bottom of the satellite antenna, and setting an interface 82 at the outer end of the flower key 81, wherein a threaded hole is opened in the middle of the interface 82, and at the same time, a bolt positioning structure is set at the top of the bracket corresponding to the ball head support. When the satellite antenna is first assembled to the truss mold, the ball head support thread can be tightened to the corresponding interface 82. During inspection, it is only necessary to separate the ball head support from the bracket, and the satellite antenna with the ball head support can be sent for inspection. After the inspection is completed and transported back to the company, the multiple ball head supports at the bottom of the satellite antenna are fixed again in the corresponding bolt positioning structure on the bracket, so as to realize the positioning of the entire satellite antenna. This raises a problem. What kind of bolt positioning structure should be set on the support rod device on the truss mold so that the ball head support can be quickly disassembled or assembled, which has become a problem that needs to be solved urgently. Summary of the Invention

[0005] The purpose of the present invention is to provide a deployable truss for a satellite antenna, which has the advantages that the satellite antenna can be easily disassembled and assembled on the load-bearing truss, the ball head bolts are firmly locked and not easy to shake, and stress concentration can be effectively avoided during the placement of the satellite antenna.

[0006] The above technical objectives of the present invention are achieved through the following technical solutions: a deployable truss for a satellite antenna, comprising a load-bearing truss, wherein the load-bearing truss is provided with a plurality of strut devices for supporting the satellite antenna, wherein the strut devices include a lifting module and a fine-tuning support module, wherein the fine-tuning support module is floatingly mounted on the output end of the lifting module via a floating connection structure; The floating connection structure includes a floating seat, and the fine-tuning support module includes a mounting frame, a swing connection member, and a locking support assembly. The mounting frame is mounted on the floating seat, and the locking support assembly is rotatably mounted on the mounting frame via the swing connection member. The locking support assembly includes a ball stud, a base assembly and a top cover. The base assembly is provided with an installation groove corresponding to the ball stud, and the top cover is provided with an avoidance hole corresponding to the ball stud. The ball head of the ball stud passes through the avoidance hole and is installed in the installation groove. The top cover can be rotated and switched between an unlocked state and a locked state relative to the base assembly. A plurality of locking rods are slidably provided on the base assembly, and a guide structure is provided between the top cover and the locking rods. When the top cover is rotated and switched between an unlocked state and a locked state relative to the base assembly, the plurality of locking rods approach each other through the guide structure and lock the ball stud, or, the plurality of locking rods move away from each other through the guide structure and release the ball stud.

[0007] By adopting the above technical solution, before the initial positioning of the satellite antenna, the ball head bolt is first unlocked and separated from the support rod device, and then the ball head bolt thread is locked on the interface at the bottom of the satellite antenna. Thereafter, according to the different position heights of the bottom surface of the satellite antenna, the lifting module of the support rod device at the corresponding position is adaptively raised and lowered to find the optimal support height of the fine-tuning support module and the satellite antenna. Since the curvature of the bottom surface of each satellite antenna is different, the locking support components at different positions drive the swing connector to adaptively rotate to the corresponding angle relative to the mounting frame, ensuring that each support component can fit tightly with the curved surface of the bottom surface of the satellite antenna. Then, the top cover is screwed on, and the top cover drives multiple locking rods to lock each other on the outside of the ball head bolt through the guide structure, so as to realize the locking positioning of the ball head bolt on the base assembly, thereby effectively preventing the satellite antenna from shaking relative to the load-bearing truss. When the assembled and calibrated satellite antenna needs to be sent to the inspection center for inspection, The top cover can be screwed in the opposite direction, and the guide structure can be used to drive multiple locking rods away from each other and release the ball studs. After that, the satellite antenna with the ball studs can be sent to the inspection center to inspect the accuracy of its inner concave surface. After the inspection, the satellite antenna is sent back to the company, and the multiple ball studs at the bottom of the satellite antenna are aligned with the corresponding strut devices on the load-bearing truss, so that the ball studs are inserted into the mounting slots on the corresponding base components, and the ball studs are re-tightened by screwing the top cover. In this way, even after multiple transportations, the satellite antenna can be accurately placed back to the predetermined position on the load-bearing truss. The present invention uses a floating connection structure to achieve elastic support for the satellite antenna, which can effectively prevent stress concentration when the satellite antenna contacts the strut device. The satellite antenna is easy to disassemble and assemble on the load-bearing truss, the ball studs are firmly locked and not easy to shake, and stress concentration is effectively avoided during the placement of the satellite antenna.

[0008] The present invention is further configured as follows: the load-bearing truss includes a middle load-bearing area and side load-bearing areas located on both sides of the middle load-bearing area; a plurality of the strut devices are arranged in the middle load-bearing area and the side load-bearing area along the length direction of the satellite antenna; and the strut devices in the side load-bearing areas are provided with an extension portion between the lifting module and the fine-tuning support module.

[0009] By adopting the above technical solution, since the height of the two sides of the satellite antenna is usually higher than the middle area, in order to realize that the load-bearing truss can effectively support the side load-bearing areas on both sides, the present invention provides an extension part between the lifting module and the fine-tuning support module of the support rod device of the side load-bearing area. Through the dual height-increasing effect of the lifting module and the extension part, the present invention is used to realize effective support of both sides of the satellite antenna.

[0010] The present invention is further configured as follows: the guide structure includes a guide column and a spiral guide groove, the guide column is arranged on the locking rod, the spiral guide groove is opened at the bottom of the top cover, the guide column and the spiral guide groove are guided and cooperated, the top cover includes a proximal end close to the position of the ball stud and a distal end away from the position of the ball stud, and the curvature radius of the spiral guide groove gradually decreases from the distal end to the proximal end.

[0011] By adopting the above technical solution, when the top cover rotates relative to the base assembly, the guide column slides in the spiral guide groove, driving the locking rod to slide in a direction toward a predetermined track on the base assembly, thereby achieving the mutual approach or distance of multiple locking rods.

[0012] The present invention is further configured as follows: a plurality of linear track grooves communicating with the mounting grooves are opened in a radial direction on the upper surface of the base assembly, and the locking rod is slidably arranged in the corresponding linear track grooves.

[0013] By adopting the above technical solution, multiple linear track grooves are radially opened on the upper surface of the base assembly. Driven by the guide structure, multiple locking rods slide relatively close to or away from their respective linear track grooves on the base assembly to clamp or release the ball head bolt.

[0014] The present invention is further configured as follows: the base assembly includes a bottom plate and a base plate fixed on the bottom plate; an annular groove is provided on the side wall of the base plate; an annular extension is provided downwardly on the edge of the top cover; a mounting hole is provided on the annular extension corresponding to the annular groove; a guide block is installed in the mounting hole; the end of the guide block extends out of the mounting hole and slides with the annular groove guide.

[0015] By adopting the above technical solution, the top cover can be rotatably connected to the base plate and cooperate with it to prevent it from falling off. At the same time, the rotation cooperation of the guide block in the annular groove can effectively prevent the top cover from jumping when rotating relative to the base plate.

[0016] The present invention is further configured as follows: a mounting seat is fixedly provided on the base assembly, an elastic positioning structure is provided between the mounting seat and the top cover, the elastic positioning structure includes an elastic member, a resisting bead and a locking hole, a mounting cylinder with an opening facing the top cover is provided on the mounting seat, the mounting cylinder has a receiving groove, the elastic member and the resisting bead are arranged in the receiving groove, the locking hole is opened on the side wall of the top cover corresponding to the resisting bead, and the elastic member has a movement tendency to push the resisting bead to elastically press against the locking hole.

[0017] By adopting the above technical solution, when the top cover is rotated to a locked state or an unlocked state relative to the base assembly and is in place, the elastic member pushes the beads into the corresponding lock holes on the side walls of the top cover and emits a "tick-tick" indicator sound to prompt that the top cover has been rotated into place. At the same time, the tightening effect of the beads and the lock holes can effectively prevent the top cover from accidentally rotating relative to the base assembly.

[0018] The present invention is further configured as follows: the mounting frame has a mounting position, one end of the swing connection member is rotatably connected to the mounting position via a rotating shaft, the outer wall of the swing connection member is provided with an angle scale centered on the rotating shaft, and the mounting frame is provided with a pointer mark for indicating the value of the angle scale.

[0019] By adopting the above technical solution, the rotation angle of the swing connection member relative to the installation position can be indicated in real time, so that the operator can clearly understand the swing angle of the swing connection member from the outside.

[0020] The present invention is further configured as follows: a force sensor is connected between the mounting bracket and the floating seat.

[0021] By adopting the above technical solution, the compressive stress of the satellite antenna on the support rod device can be monitored in real time using a force sensor. When the compressive stress fluctuates greatly, the situation can be checked and adjusted in time to prevent local stress concentration in the satellite antenna from causing damage to the internal structure.

[0022] The present invention is further configured as follows: the lifting module includes a lifting drive member and a lifting seat assembly, the lifting drive member is configured as an oil cylinder or an air cylinder, the lifting seat assembly is fixedly mounted on the end of the piston rod of the oil cylinder or the air cylinder, a fixed seat is fixedly mounted on the lifting drive member, a plurality of optical axes are parallelly mounted on the bottom of the lifting seat assembly, a plurality of first linear bearings are mounted on the fixed seat, and the optical axis guides are inserted into the corresponding first linear bearings.

[0023] By adopting the above technical solution and utilizing the guiding function of the optical axis and the first linear bearing, the consistency of the lifting and lowering adjustment direction of the lifting seat assembly is improved.

[0024] The present invention is further configured as follows: the floating connection structure includes a guide shaft, a spring and a second linear bearing, the second linear bearing is fixedly mounted on the floating seat, the guide shaft is fixedly mounted on the lifting seat assembly, the guide shaft is guided through the second linear bearing, the spring is sleeved on the guide shaft, and one end of the spring elastically abuts against the floating seat, and the other end of the spring elastically abuts against the lifting seat assembly.

[0025] By adopting the above technical solution, the compressive stress generated by the satellite antenna acts on the support plate to press the spring down to contract and accumulate elastic potential energy. The guide cooperation between the guide shaft and the second linear bearing can improve the consistency of the vertical movement of the support plate. At the same time, it can ensure that the deformation direction of the spring is always along the axial direction of the guide shaft, preventing the spring from bending during elastic deformation, resulting in cooperation failure, thereby extending the service life of the equipment and the operational stability.

[0026] In summary, the present invention has the following beneficial effects: The invention adopts a plurality of strut devices arranged on the load-bearing truss, the strut device includes a lifting module and a fine-tuning support module, the fine-tuning support module is floated and installed on the output end of the lifting module through a floating connection structure, the fine-tuning support module includes a mounting frame, a swing connection and a locking support assembly, the mounting frame is installed on the floating seat of the floating connection structure, the locking support assembly includes a ball stud, a base assembly and a top cover, wherein the top cover can rotate relative to the base assembly, the base assembly is provided with a mounting groove, the ball head of the ball stud passes through the avoidance hole of the top cover and is installed in the mounting groove, a plurality of linear track grooves connected to the mounting groove are provided on the base assembly in a radial direction, a locking rod is provided in each linear track groove, a guide column is provided on the side of the locking rod away from the mounting groove, and the top cover A spiral track groove is provided at the bottom corresponding to the guide column, and the curvature radius of the spiral guide groove gradually decreases from the distal end to the proximal end. The spiral track groove cooperates with the guide column to drive the locking rod to approach or move away from each other in the straight track groove, thereby realizing the locking or release of the ball head bolt by the locking rod. Even after multiple transportations, the satellite antenna can finally be accurately placed back to the predetermined position on the load-bearing truss. The present invention realizes elastic support for the satellite antenna through a floating connection structure, which can effectively prevent stress concentration when the satellite antenna contacts the support rod device. The satellite antenna is easy to disassemble and assemble on the load-bearing truss, the ball head bolt is firmly locked and not easy to shake, and stress concentration is effectively avoided during the placement of the satellite antenna. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is the overall structural diagram of the present invention.

[0028] Figure 2 It is a front view of the satellite antenna of the present invention when placed on the load-bearing truss.

[0029] Figure 3 It is a cross-sectional view of the spline keypad at the bottom of the satellite antenna of the present invention in a state of being threadedly connected to a ball stud via an interface, wherein the ball stud is locked by a locking rod.

[0030] Figure 4 It is a structural diagram of the support rod device located in the middle load-bearing area of the present invention.

[0031] Figure 5It is a schematic diagram of the installation of the fine-tuning support module of the present invention on the lifting seat assembly.

[0032] Figure 6 This invention Figure 5 A partial view from another perspective.

[0033] Figure 7 This invention Figure 6 sectional view of .

[0034] Figure 8 It is a structural diagram of the support rod device located in the side load-bearing area of the present invention.

[0035] Figure 9 It is a structural diagram of the locking support assembly of the present invention.

[0036] Figure 10 This invention Figure 9 Longitudinal cross-sectional view.

[0037] Figure 11 This invention Figure 9 Exploded diagram.

[0038] Figure 12 This invention Figure 9 Exploded image from another perspective.

[0039] In the figure: 1. load-bearing truss; 11. middle load-bearing area; 12. side load-bearing area; 2. support rod device; 21. extension part; 3. lifting module; 31. lifting drive member; 311. fixed seat; 3111. first linear bearing; 32. lifting seat assembly; 3201. lifting plate; 3202. first adjustment plate; 3203. second adjustment plate; 321. stud; 322. locking nut; 33. optical axis; 4. floating connection structure; 41. floating seat; 411. through hole; 42. guide shaft; 43. spring; 44. second linear bearing; 5. fine-tuning support module; 51. mounting frame; 510. pointer mark; 511. mounting position; 512. arc groove; 513. locking bolt; 52. swing connection; 521. rotating shaft; 522. angle scale; 523. threaded hole; 53. locking support assembly; 531. Ball stud; 5311, ball head; 5312, screw; 532, base assembly; 5321, bottom plate; 5322, base plate; 53220, mounting groove; 53221, annular groove; 53222, linear track groove; 5323, support seat; 53231, positioning groove; 53232, positioning rib; 53233, support slope; 533, top cover; 5330, avoidance hole; 5331 , spiral guide groove; 5332, annular extension; 53321, mounting hole; 53322, guide block; 534, locking hole; 535, mounting seat; 5351, mounting tube; 53511, accommodating groove; 5352, elastic member; 5353, bead; 6, locking rod; 61, guide column; 62, guide slope; 7, force sensor; 8, satellite antenna; 80, curved surface; 81, flower keyboard; 82, interface. DETAILED DESCRIPTION

[0040] The present invention will be further described below with reference to the accompanying drawings.

[0041] A satellite antenna deployable truss, such as Figures 1-12As shown, it includes a load-bearing truss 1, characterized in that: the load-bearing truss 1 is provided with a plurality of strut devices 2 for supporting satellite antennas 8, the strut device 2 includes a lifting module 3 and a fine-tuning support module 5, and the fine-tuning support module 5 is floatingly mounted on the output end of the lifting module 3 through a floating connection structure 4; the floating connection structure 4 includes a floating seat 41, and the fine-tuning support module 5 includes a mounting frame 51, a swing connection member 52 and a locking support assembly 53, the mounting frame 51 is mounted on the floating seat 41, and the locking support assembly 53 is rotatably mounted on the mounting frame 51 through the swing connection member 52. The locking support assembly 53 includes a ball stud 531, a base assembly 532 and a top cover 533. The base assembly 532 is provided with a mounting groove 53220 corresponding to the ball stud 531, and the top cover 533 is provided with an avoidance hole 5330 corresponding to the ball stud 531. The ball head 5311 of the ball stud 531 passes through the avoidance hole 5330 and is installed in the mounting groove 53220. The top cover 533 can be rotated relative to the base assembly 532 between the unlocked state and the locked state. A plurality of locking rods 6 are slidingly provided on the base assembly 532. The top cover 533 and the locking rod 6 A guide structure is provided between them. When the top cover 533 rotates relative to the base assembly 532 to switch between the unlocked state and the locked state, the multiple locking rods 6 approach each other through the guide structure and lock the ball stud 531, or the multiple locking rods 6 move away from each other through the guide structure and release the ball stud 531; the ball stud 531 in this embodiment is a commonly used model on the market, including a screw portion 5312 and a ball head 5311, the ball head 5311 extends into the mounting groove 53220, and when the top cover 533 rotates relative to the base assembly 532 to the locked state, the multiple locking rods 6 move closer to each other through the guide structure and lock the ball stud 531, or, the multiple locking rods 6 move away from each other through the guide structure and release the ball stud 531; 6 is pressed against the outer wall of the screw part 5312. At this time, the locking rod 6 and the ball head 5311 cooperate to prevent disengagement, so that the ball head bolt 531 locked by multiple locking rods 6 can firmly connect the support rod and the satellite antenna 8, preventing the ball head bolt 531 from being separated from the base assembly 532; and a guiding slope 62 is provided at one end of the locking rod 6 close to the ball head bolt 531, and the ball head 5311 is guided by the guiding slope 62 to be inserted into the installation groove 53220. The addition of the guiding slope 62 is conducive to improving the installation efficiency of the ball head bolt 531 in the base assembly 532.

[0042] like Figure 1-Figure 3 and Figures 9-12As shown, the load-bearing truss 1 includes a middle load-bearing area 11 and side load-bearing areas 12 located on both sides of the middle load-bearing area 11. A plurality of strut devices 2 are arranged in the middle load-bearing area 11 and the side load-bearing area 12 along the length direction of the satellite antenna 8, and the strut devices 2 of the side load-bearing area 12 are provided with an extension portion 21 between the lifting module 3 and the fine-tuning support module 5. Since the heights of the satellite antenna 8 on both sides are usually higher than those on the middle area, in order to enable the load-bearing truss 1 to effectively support the side load-bearing areas 12 on both sides, the present invention provides an extension portion 21 between the lifting module 3 and the fine-tuning support module 5 for the strut devices 2 of the side load-bearing area 12. Through the dual height-increasing effect of the lifting module 3 and the extension portion 21, the present invention can effectively support both sides of the satellite antenna 8; the guide structure includes a guide column 61 and a spiral guide groove 5331. The guide column 61 is provided on the locking rod 6, and the spiral guide groove 5331 is opened at the bottom of the top cover 533. The guide column 61 and the spiral guide groove 5331 are connected. The guide groove 5331 is guided and matched, and the top cover 533 includes a proximal end close to the position of the ball stud 531 and a distal end away from the position of the ball stud 531. The curvature radius of the spiral guide groove 5331 gradually decreases from the distal end to the proximal end. When the top cover 533 rotates relative to the base assembly 532, the guide column 61 guides and slides in the spiral guide groove 5331, driving the locking rod 6 to slide in a predetermined direction on the base assembly 532, thereby realizing that multiple locking rods 6 are close to or away from each other; A plurality of linear track grooves 53222 connected to the mounting groove 53220 are provided on the upper surface of the component 532 in a radial direction. The locking rod 6 is slidably arranged in the corresponding linear track groove 53222, so that the plurality of linear track grooves 53222 are radially provided on the upper surface of the base component 532. Driven by the guide structure, the plurality of locking rods 6 slide relatively close to or away from each other along their respective linear track grooves 53222 on the base component 532 to clamp or release the ball head bolt 531.

[0043] like Figure 3-Figure 12As shown, the base assembly 532 includes a bottom plate 5321, a base plate 5322 fixed on the bottom plate 5321, a side wall of the base plate 5322 is provided with an annular groove 53221, an edge of the top cover 533 is provided with an annular extension 5332 facing downward, an installation hole 53321 is provided on the annular extension 5332 corresponding to the annular groove 53221, a guide block 53322 is installed in the installation hole 53321, and the end of the guide block 53322 extends out of the installation hole 53321 and is aligned with the annular groove 5322. 1 guide sliding fit, so that the top cover 533 can be rotatably connected to the base plate 5322 and cooperate with it to prevent it from falling off. At the same time, the rotation fit of the guide block 53322 in the annular groove 53221 can effectively prevent the top cover 533 from jumping when rotating relative to the base plate 5322. In this embodiment, the base assembly 532 also includes a support seat 5323, which is fixedly connected to the bottom plate 5321 and is located at the bottom of the mounting groove 53220. The support seat 5323 corresponds to the ball head 5311 is provided with a positioning groove 53231, and a plurality of positioning ribs 53232 are provided in the positioning groove 53231. The ball head 5311 extends into the positioning groove 53231 and cooperates with the positioning ribs 53232 for positioning support. The plurality of positioning ribs 53232 can effectively support the ball head 5311 of the ball stud 531, thereby improving the support of the base assembly 532 for the ball stud 531; the positioning rib 53232 is provided with a supporting inclined surface 53233 corresponding to the ball head 5311, and the plurality of positioning ribs 532 The support inclined surface 53233 of the support base 53233 is positioned and matched with the outer wall of the ball head 5311. The multiple support inclined surfaces 53233 cooperate to form a profile for positioning the ball head 5311, so that the ball head 5311 can be accurately installed in the predetermined position of the support base 5323. At the same time, the ball head 5311 can rotate on the profile formed by the multiple support inclined surfaces 53233, which is conducive to adjusting the depth of the threaded connection of the ball stud 531 on the outer wall of the satellite antenna 8, thereby improving the assembly accuracy and convenience of the ball stud 531.The base assembly 532 is fixed with a mounting seat 535, and an elastic positioning structure is provided between the mounting seat 535 and the top cover 533. The elastic positioning structure includes an elastic member 5352, a bead 5353 and a lock hole 534. The mounting seat 535 is provided with a mounting cylinder 5351 with an opening toward the top cover 533. The mounting cylinder 5351 has a receiving groove 53511. The elastic member 5352 and the bead 5353 are arranged in the receiving groove 53511. The lock hole 534 is opened on the side wall of the top cover 533 corresponding to the bead 5353. The elastic member 5352 has a tendency to push the bead 5353 to elastically press against the locking hole 534. When the top cover 533 is rotated relative to the base assembly 532 to the locked or unlocked state and in place, the elastic member 5352 pushes the bead 5353 into the corresponding locking hole 534 on the side wall of the top cover 533 and emits a "tick-tick" sound to indicate that the top cover 533 has been rotated into place. At the same time, the pressing action of the bead 5353 and the locking hole 534 can effectively prevent the top cover 533 from accidentally rotating relative to the base assembly 532.

[0044] The mounting frame 51 has a mounting position 511, one end of the swing connector 52 is rotatably connected to the mounting position 511 via a rotating shaft 521, an outer wall of the swing connector 52 is provided with an angle scale 522 centered on the rotating shaft 521, and a pointer mark 510 is provided on the mounting frame 51 to indicate the value of the angle scale 522, which can indicate the rotation angle of the swing connector 52 relative to the mounting position 511 in real time, so that the operator can clearly understand the swing angle of the swing connector 52 from the outside; a force sensor 7 is connected between the mounting frame 51 and the floating seat 41, and the force sensor 7 can be used to The compressive stress of the satellite antenna 8 on the strut device 2 is monitored in real time. When the compressive stress fluctuates greatly, the situation can be checked and adjusted in time to prevent the satellite antenna 8 from being damaged due to local stress concentration and internal structure damage. In some other embodiments, an arc groove 512 can be opened on the mounting frame 51 with the rotating shaft 521 as the rotation center, and a threaded hole 523 can be opened on the side wall of the swing connection 52. The locking bolt 513 passes through the arc groove 512 and is threadedly locked in the corresponding threaded hole 523 to achieve locking positioning between the swing connection 52 and the mounting frame 51.

[0045] like Figures 1-8As shown, the lifting module 3 includes a lifting drive member 31 and a lifting seat assembly 32. The lifting drive member 31 is configured as an oil cylinder or an air cylinder. The lifting seat assembly 32 is fixed to the end of the piston rod of the oil cylinder or the air cylinder. A fixed seat 311 is fixed on the lifting drive member 31. A plurality of optical axes 33 are provided in parallel at the bottom of the lifting seat assembly 32. A plurality of first linear bearings 3111 are provided on the fixed seat 311. The optical axes 33 are guided through the corresponding first linear bearings 3111. The guiding effect of the optical axes 33 and the first linear bearings 3111 is utilized to improve the consistency of the lifting and lowering adjustment direction of the lifting seat assembly 32. The floating connection structure 4 includes a guide shaft 42, a spring 43 and a second linear bearing 44. The second linear bearing 4 4 is fixed on the floating seat 41, and the guide shaft 42 is fixed on the lifting seat assembly 32. The guide shaft 42 is guided through the second linear bearing 44. The spring 43 is sleeved on the guide shaft 42, and one end of the spring 43 elastically presses against the floating seat 41, and the other end of the spring 43 elastically presses against the lifting seat assembly 32. The compressive stress generated by the satellite antenna 8 acts on the support plate to press the spring 43 downward to contract and accumulate elastic potential energy. The guide cooperation between the guide shaft 42 and the second linear bearing 44 can improve the consistency of the vertical movement of the support plate, and at the same time ensure that the deformation direction of the spring 43 is always along the axial direction of the guide shaft 42, preventing the spring 43 from bending and deforming during elastic deformation, resulting in cooperation failure, thereby playing a role. The effect of extending the service life of the equipment and the operation stability is achieved; a stud 321 is fixed on the lifting seat assembly 32, and a through hole 411 is opened on the floating seat 41 corresponding to the stud 321. One end of the stud 321 is passed through the outside of the through hole 411 and is locked by a locking nut 322. The floating seat 41 cooperates with the stud 321 to prevent it from falling off through the locking nut 322. When the satellite antenna 8 is separated from the supporting device, the locking effect of the locking nut 322 and the stud 321 can effectively prevent the spring 43 from pushing the floating seat 41 upward and separating it from the stud 321. In addition, the locking nut 322 can also limit the floating distance between the floating seat 41 and the lifting seat assembly 32; in this embodiment, the lifting seat assembly 32 includes A lifting plate 3201, a first adjustment plate 3202 slidingly arranged on the lifting plate 3201, a second adjustment plate 3203 slidingly arranged on the first adjustment plate 3202, and a first bolt locking structure is provided between the first adjustment plate 3202 and the lifting plate 3201, the first bolt locking structure is used to adjust the relative position of the first adjustment plate 3202 relative to the lifting plate 3201 along the first direction, a second bolt locking structure is provided between the second adjustment plate 3203 and the first adjustment plate 3202, the second bolt locking structure is used to adjust the relative position of the second adjustment plate 3203 relative to the first adjustment plate 3202 along the second direction, wherein the extension direction of the first direction is perpendicular to the extension direction of the second direction.

[0046] The basic working principle of the present invention is as follows: a plurality of strut devices 2 are arranged on a load-bearing truss 1, the strut device 2 includes a lifting module 3 and a fine-tuning support module 5, the fine-tuning support module 5 is floatingly mounted on the output end of the lifting module 3 through a floating connection structure 4, the fine-tuning support module 5 includes a mounting frame 51, a swing connection 52 and a locking support assembly 53, the mounting frame 51 is mounted on a floating seat 41 of the floating connection structure 4, the locking support assembly 53 includes a ball stud 531, a base assembly 532 and a top cover 533, wherein the top cover 533 can rotate relative to the base assembly 532, the base assembly 532 is provided with a mounting groove 53220, the ball head 5311 of the ball stud 531 passes through the avoidance hole 5330 of the top cover 533 and is mounted in the mounting groove 53 220, a plurality of linear track grooves 53222 connected to the mounting groove 53220 are opened on the base assembly 532 in the radial direction, and a locking rod 6 is provided in each linear track groove 53222. A guide column 61 is provided on the side of the locking rod 6 away from the mounting groove 53220. A spiral track groove is opened at the bottom of the top cover 533 corresponding to the guide column 61. The curvature radius of the spiral guide groove 5331 gradually decreases from the distal end to the proximal end. The spiral track groove and the guide column 61 guide and cooperate to drive the locking rod 6 to move closer to or away from each other in the linear track groove 53222. Before the initial positioning of the satellite antenna 8, the ball stud 531 is first unlocked and separated from the support rod device 2, and then the ball stud 531 is threadedly locked on the interface 82 at the bottom of the satellite antenna 8. The bottom surface of the satellite antenna 8 has different heights. The lifting module 3 of the support rod device 2 at the corresponding position is adaptively lifted and lowered to find the optimal support height of the fine-tuning support module 5 and the satellite antenna 8. Since the curvature of the bottom surface of each satellite antenna 8 is different, the locking support components 53 at different positions drive the swing connection 52 to adaptively rotate to the corresponding angle relative to the mounting frame 51, ensuring that each support component can fit tightly with the curved surface 80 of the bottom surface of the satellite antenna 8. Then, the top cover 533 is screwed on. The top cover 533 drives multiple locking rods 6 to lock each other outside the ball stud 531 through the guide structure, realizing the locking positioning of the ball stud 531 on the base component 532, thereby effectively preventing the satellite antenna 8 from shaking relative to the load-bearing truss 1. When it is needed When the assembled and calibrated satellite antenna 8 is sent to the inspection center for inspection, the top cover 533 can be screwed in the opposite direction, and the guide structure can be used to drive the multiple locking rods 6 away from each other and release the ball studs 531. Then, the satellite antenna 8 with the ball studs 531 can be sent to the inspection center to inspect the accuracy of its inner concave surface. After the inspection, the satellite antenna 8 is sent back to the company, and the multiple ball studs 531 at the bottom of the satellite antenna 8 are aligned with the corresponding support rod devices 2 on the load-bearing truss 1, so that the ball studs 531 are inserted into the mounting grooves 53220 on the corresponding base components 532, and the ball studs are re-tightened by screwing the top cover 533. In this way, even after multiple transportations, the satellite antenna 8 can be accurately placed back to the predetermined position on the load-bearing truss 1.The present invention uses the floating connection structure 4 to elastically support the satellite antenna 8, effectively preventing stress concentration from occurring when the satellite antenna 8 contacts the support rod device 2. This facilitates assembly and disassembly of the satellite antenna from the load-bearing truss, securely locks the ball studs, and effectively prevents stress concentration from occurring during placement of the satellite antenna.

[0047] The above description is only a preferred embodiment of the present invention. Therefore, any equivalent changes or modifications made according to the structure, characteristics and principles described in the scope of the patent application of the present invention are included in the scope of the patent application of the present invention.

Claims

1. A satellite antenna deployable truss, comprising a load-bearing truss (1), characterized in that: The load-bearing truss (1) is provided with a plurality of support rod devices (2) for supporting satellite antennas (8), the support rod devices (2) comprising a lifting module (3) and a fine-tuning support module (5), the fine-tuning support module (5) being floatingly mounted on the output end of the lifting module (3) via a floating connection structure (4); The floating connection structure (4) includes a floating seat (41), the fine-tuning support module (5) includes a mounting frame (51), a swing connection member (52) and a locking support assembly (53), the mounting frame (51) is mounted on the floating seat (41), and the locking support assembly (53) is rotatably mounted on the mounting frame (51) via the swing connection member (52); The locking support assembly (53) includes a ball stud (531), a base assembly (532) and a top cover (533), wherein the base assembly (532) is provided with a mounting groove (53220) corresponding to the ball stud (531), and the top cover (533) is provided with a relief hole (5330) corresponding to the ball stud (531), and the ball head (5312) of the ball stud (531) passes through the relief hole (5330) and is installed in the mounting groove (53220), and the top cover (533) can be relatively fixed to the base assembly ( 532) is rotated and switched between an unlocked state and a locked state, a plurality of locking rods (6) are slidably provided on the base assembly (532), and a guide structure is provided between the top cover (533) and the locking rods (6). When the top cover (533) is rotated and switched between an unlocked state and a locked state relative to the base assembly (532), the plurality of locking rods (6) approach each other through the guide structure and lock the ball stud (531), or the plurality of locking rods (6) move away from each other through the guide structure and release the ball stud (531).

2. The deployable satellite antenna truss according to claim 1, characterized in that: The load-bearing truss (1) includes a middle load-bearing area (11) and side load-bearing areas (12) located on both sides of the middle load-bearing area (11); a plurality of the strut devices (2) are arranged in the middle load-bearing area (11) and the side load-bearing areas (12) along the length direction of the satellite antenna (8); and the strut devices (2) in the side load-bearing areas (12) are provided with an extension portion (21) between the lifting module (3) and the fine-tuning support module (5).

3. The deployable satellite antenna truss according to claim 1, characterized in that: The guide structure includes a guide column (61) and a spiral guide groove (5331), wherein the guide column (61) is provided on the locking rod (6), and the spiral guide groove (5331) is opened at the bottom of the top cover (533), and the guide column (61) and the spiral guide groove (5331) are guided and matched, and the top cover (533) includes a proximal end close to the position of the ball stud (531) and a distal end away from the position of the ball stud (531), and the curvature radius of the spiral guide groove (5331) gradually decreases from the distal end to the proximal end.

4. The deployable satellite antenna truss according to claim 1, characterized in that: The upper surface of the base assembly (532) is provided with a plurality of linear track grooves (53222) connected to the mounting groove (53220) in a radial direction, and the locking rod (6) is slidably arranged in the corresponding linear track grooves (53222).

5. The deployable satellite antenna truss according to claim 1, characterized in that: The base assembly (532) includes a bottom plate (5321) and a base plate (5322) fixed on the bottom plate (5321); a side wall of the base plate (5322) is provided with an annular groove (53221); an annular extension portion (5332) is provided on the edge of the top cover (533); a mounting hole (53321) is provided on the annular extension portion (5332) corresponding to the annular groove (53221); a guide block (53322) is installed in the mounting hole (53321); an end of the guide block (53322) extends out of the mounting hole (53321) and is slidingly matched with the annular groove (53221).

6. The deployable satellite antenna truss according to claim 1, characterized in that: A mounting seat (535) is fixedly provided on the base assembly (532), and an elastic positioning structure is provided between the mounting seat (535) and the top cover (533), and the elastic positioning structure includes an elastic member (5352), a bead (5353) and a locking hole (534). The mounting seat (535) is provided with a mounting tube (5351) with an opening toward the top cover (533), and the mounting tube (5351) has a receiving groove (53511). The elastic member (5352) and the bead (5353) are arranged in the receiving groove (53511), and the locking hole (534) is opened on the side wall of the top cover (533) corresponding to the bead (5353), and the elastic member (5352) has a movement tendency to push the bead (5353) to elastically press against the locking hole (534).

7. The deployable satellite antenna truss according to claim 1, characterized in that: The mounting frame (51) has a mounting position (511), one end of the swing connection member (52) is rotatably connected to the mounting position (511) via a rotating shaft (521), an outer wall of the swing connection member (52) is provided with an angle scale (522) centered on the rotating shaft (521), and a pointer mark (510) for indicating the value of the angle scale (522) is provided on the mounting frame (51).

8. The deployable satellite antenna truss according to claim 1, characterized in that: A force sensor (7) is connected between the mounting frame (51) and the floating seat (41).

9. The deployable satellite antenna truss according to claim 1, characterized in that: The lifting module (3) comprises a lifting drive member (31) and a lifting seat assembly (32); the lifting drive member (31) is configured as an oil cylinder or an air cylinder; the lifting seat assembly (32) is fixed to the end of a piston rod of the oil cylinder or the air cylinder; a fixed seat (311) is fixed to the lifting drive member (31); a plurality of optical axes (33) are parallel to the bottom of the lifting seat assembly (32); a plurality of first linear bearings (3111) are provided on the fixed seat (311); and the optical axes (33) are guided and passed through corresponding first linear bearings (3111).

10. The deployable satellite antenna truss according to claim 9, characterized in that: The floating connection structure (4) includes a guide shaft (42), a spring (43) and a second linear bearing (44), wherein the second linear bearing (44) is fixed on the floating seat (41), the guide shaft (42) is fixed on the lifting seat assembly (32), the guide shaft (42) is guided through the second linear bearing (44), the spring (43) is sleeved on the guide shaft (42), and one end of the spring (43) elastically presses against the floating seat (41), and the other end of the spring (43) elastically presses against the lifting seat assembly (32).

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