A mechanism deployment verification system

Abstract

The application relates to a space antenna, in particular to a mechanism unfolding verification system, which solves the problem of how to eliminate the gravity interference as far as possible when the unfolding of the space antenna is verified on the ground. The horizontal guide rail is connected at the bottom of the top platform, the air floating bearing is sleeved on each horizontal guide rail, the throttle of the air floating bearing is provided with a throttle hole on the side of the horizontal guide rail, the throttle hole and the butt joint hole on the throttle are communicated through a cavity, the high-pressure gas pipeline is connected with the butt joint hole, the high-pressure gas in the high-pressure gas pipeline forms an air film between the throttle and the horizontal guide rail, the top of the space antenna is connected with the annular frame of the air floating bearing, the bottom of the space antenna is connected with the air floating foot, the air floating foot is provided with a plurality of air floating throttle holes at the bottom, the air floating foot is provided with an air inlet hole for connecting the high-pressure gas pipeline, the air inlet hole and the plurality of air floating throttle holes are communicated through an air cavity, the gravity interference is eliminated in the space antenna unfolding test through the cooperation of the air floating foot and the air floating bearing.

Description

Technical Field

[0001] This invention relates to space antennas, and more specifically to a mechanism deployment verification system. Background Technology

[0002] Space antennas are the main equipment used by on-orbit spacecraft to receive and transmit signals. To facilitate the launch of spacecraft, space antennas are usually designed with a folding structure. They are folded and stored inside the spacecraft during launch, and unfolded after the spacecraft enters its predetermined orbit to facilitate the reception and transmission of signals.

[0003] Since space antennas operate in outer space, a zero-gravity environment, their design and fabrication must simulate on-orbit deployment under zero gravity to verify their performance. However, zero-gravity deployment verification of space antennas is limited by cost, technology, and other factors, and can only be conducted on the ground. During ground verification, the space antenna is affected by gravity; the friction generated by gravity hinders the zero-gravity deployment verification, significantly impacting the verification results. Therefore, it is necessary to verify the deployment of space antennas while minimizing gravitational interference to ensure their normal deployment in outer space. Summary of the Invention

[0004] The purpose of this invention is to solve the problem of how to minimize gravity interference when conducting verification of space antenna deployment on the ground, and to provide a mechanism deployment verification system.

[0005] To achieve the above-mentioned objectives, the present invention provides the following technical solution: A mechanism deployment verification system for zero-gravity deployment verification of space antennas, characterized by including an unloading platform, a low-friction guide rail structure, and an air-floating unloading structure. The unloading platform includes a top platform and four supports located at the four corners of the bottom of the top platform; The low-friction guide rail structure includes multiple horizontal guide rails disposed below the top platform and multiple connectors for connecting the top platform and the horizontal guide rails. The extension direction of the horizontal guide rails is the same as the deployment direction of the space antenna. At least one air bearing is fitted on each horizontal guide rail. The air bearing includes an annular frame with an opening at the top and multiple throttles disposed on the inner wall of the annular frame. The opening is used to avoid connecting parts. There is a gap between the throttle and the horizontal guide rail. A throttle hole is provided on the throttle facing the horizontal guide rail. A docking hole is also provided on the throttle. The docking hole is used to connect with a high-pressure gas pipeline. The docking hole is connected to the throttle hole through a cavity disposed in the throttle. The high-pressure gas in the high-pressure gas pipeline passes through the docking hole, the cavity and the throttle hole in sequence and is blown toward the horizontal guide rail, forming an air film in the gap between the throttle and the horizontal guide rail. The two adjacent horizontal guide rails are located at different heights, which allows the two air bearings mounted on the adjacent horizontal guide rails to be staggered in height space; The air flotation unloading structure includes an air flotation platform located below the top platform and multiple air flotation feet located on the air flotation platform. Each air flotation foot corresponds to an air flotation bearing. Multiple air flotation throttling holes are provided at the bottom of the air flotation foot. An air inlet for connecting a high-pressure gas pipeline is provided on the air flotation foot, and the air inlet and multiple air flotation throttling holes are connected through an air cavity located inside the air flotation foot. The ring frame is used to connect to the top of the space antenna, and the air-bearing foot is used to connect to the bottom of the space antenna.

[0006] Furthermore, the top platform and the support are respectively composed of multiple rectangular grid units. Each rectangular grid unit includes multiple connecting rods and fixing components. The fixing components are set at the vertices of the rectangular grid unit. The fixing components are regular octahedrons, and each face is provided with threaded holes. Both ends of the connecting rods are provided with threaded sections. The connecting rods are connected to the fixing components through the cooperation of the threaded sections and the threaded holes. Two adjacent rectangular grid units share the fixing component located on the splicing surface of one of the rectangular grid units.

[0007] Furthermore, the connector includes a support beam and an adjustment assembly. The support beam is a standard aluminum profile and is connected to a fixing member located at the bottom of the top platform via a screw. The adjustment assembly includes an adjustment rod and a height adjustment mechanism. The top of the adjustment rod has a left-hand threaded section, and the bottom has a right-hand threaded section. The left-hand threaded section of the adjustment rod is used to engage with a T-nut in the slide groove of the support beam to connect the adjustment rod to the support beam. The height adjustment mechanism includes a base mounted on a horizontal guide rail and a horizontal plate mounted at the bottom of the adjustment rod. The horizontal plate is bolted to the base, and a threaded hole is provided in the horizontal plate. The right-hand threaded section of the adjustment rod is screwed into the threaded hole in the horizontal plate. The top opening of the ring frame is used to avoid the height adjustment mechanism.

[0008] Furthermore, the air-bearing foot includes a rectangular body and a connecting seat located at the center of the upper surface of the body. There are two air inlets symmetrically arranged on both sides of the body on the connecting seat. There are eight air-bearing throttling orifices, including four vertex throttling orifices and four edge throttling orifices. The four vertex throttling orifices are arranged in a rectangular distribution, and the four edge throttling orifices are located on the line connecting the centers of two adjacent vertex throttling orifices and at the midpoint of the corresponding line connecting the centers.

[0009] Furthermore, a pressure equalization groove is provided between the adjacent edge throttling orifice and the apex throttling orifice.

[0010] Furthermore, the space antenna and the air-floating foot are connected via a docking assembly, which includes an adapter plate, an adjustment plate, an adjustment screw, an adjustment nut, and a force sensor. The adjustment screw is connected to the top of the force sensor, and there are two adjustment nuts, both screwed onto the adjustment screw. The adjustment plate is sleeved on the adjustment screw and located between the two adjustment nuts. The adapter plate is located above the top of the adjustment screw, and the adapter plate and the adjustment plate are connected by bolts. The bottom of the space antenna is connected to the adapter plate. The force sensor has an S-shaped structure with a U-shaped groove at the top and bottom. The openings of the two U-shaped grooves face opposite directions. A threaded hole is formed vertically on the lower side wall of the lower U-shaped groove. A support rod is installed in the threaded hole. One end of the support rod is connected to the force sensor through the threaded hole, and the other end is connected to the connecting seat.

[0011] Furthermore, the air flotation platform is a rectangular structure formed by splicing multiple platform segments. Each platform segment has multiple leveling support seats at its bottom. The leveling support seat includes a base, a leveling screw, and a leveling nut. The top end of the leveling screw is connected to the bottom surface of the platform segment. The leveling screw is located in a through hole opened in the center of the base. The leveling nut is screwed onto the leveling screw, and the bottom surface of the leveling nut abuts against the top surface of the base.

[0012] Furthermore, the connecting seat has a through hole at its center and a receiving cavity at the bottom of the connecting seat corresponding to the position of the through hole. A hemispherical ball joint head is provided in the receiving cavity, and a groove adapted to the shape of the outer wall of the ball joint head is provided on the body. The ball joint head is located in the groove, and the other end of the support rod passes through the through hole and is connected to the ball joint head. An annular groove is provided at the top of the receiving cavity, and an anti-rotation rubber ring is provided inside the annular groove. The outer wall of the anti-rotation rubber ring abuts against the inner wall of the annular groove, and the inner wall abuts against the outer wall of the support rod.

[0013] Furthermore, the platform body is made of granite, the leveling support is made of stainless steel, and the air-floating feet are made of aluminum alloy.

[0014] Furthermore, the bottom of the ring frame is provided with a connecting ear, which is connected to the top of the space antenna.

[0015] Compared with the prior art, the beneficial effects of the present invention are: (1) The present invention provides a mechanism deployment verification system, wherein a horizontal guide rail is connected to the bottom of the top platform, and at least one air bearing is sleeved on each horizontal guide rail. The air bearing is provided with multiple throttles on the inner wall of the annular frame. The throttles are provided with throttle holes on the side facing the horizontal guide rail, and the throttle holes are connected to the docking holes provided on the throttles through the internal cavity of the throttles. The high-pressure gas pipeline is connected to the docking holes. The high-pressure gas in the high-pressure gas pipeline passes through the docking holes, the cavity and the throttle holes in sequence and is blown toward the horizontal guide rail, and forms an air film in the gap between the throttles and the horizontal guide rail. The top of the space antenna is connected to the annular frame of the air bearing. The bottom of the space antenna is connected to the air foot. The bottom of the air foot is provided with multiple air throttle holes. The air foot is provided with an air inlet for connecting the high-pressure gas pipeline, and the air inlet is connected to the multiple air throttle holes through the air passage. By cooperating with the air foot and the air bearing, gravity interference is eliminated in the space antenna deployment test.

[0016] (2) The top platform and support of the mechanism deployment verification system provided by the present invention are respectively spliced ​​from multiple rectangular grid units. Through the cooperation of connecting rods and fixing parts, they can be flexibly assembled, which improves flexibility.

[0017] (3) In the mechanism deployment verification system provided by the present invention, the support rod and the ball joint head form a ball joint connection, which can adapt to the platform split with different tilt angle changes, and will not generate additional torque on the space antenna, thus ensuring the verification effect.

[0018] (4) In the mechanism deployment verification system provided by the present invention, a pressure equalization groove is provided between the adjacent edge throttling holes and the vertex throttling holes. In this way, the high pressure zone of the air buoyancy foot is distributed on the periphery, and the air pressure distribution on the inner side is uniform, which has good load-bearing capacity and air film stiffness. Attached Figure Description

[0019] Figure 1 This is a three-dimensional structural diagram of the unloading platform in an embodiment of a mechanism deployment verification system of the present invention; Figure 2 This is a schematic diagram showing the connection between the connecting rod and the fixing member of the rectangular grid unit in an embodiment of the present invention; Figure 3 This is a simplified schematic diagram of the horizontal guide rail structure in an embodiment of the present invention; Figure 4 This is a schematic diagram showing the connection of the supporting beam, adjusting assembly, fixing member and horizontal guide rail in an embodiment of the present invention; Figure 5This is a schematic diagram showing the connection between the adjustment component, the horizontal guide rail, and the support beam in an embodiment of the present invention; Figure 6 This is a schematic diagram illustrating the fit between the air bearing and the horizontal guide rail in an embodiment of the present invention. Figure 7 This is a three-dimensional structural diagram of the air-floating foot in an embodiment of the present invention; Figure 8 This is a schematic diagram of the bottom structure of the air-floating foot in an embodiment of the present invention; Figure 9 This is a schematic diagram showing the connection between the air-floating foot and the docking assembly in an embodiment of the present invention; Figure 10 This is a schematic diagram showing the connection between the support rod and the ball joint in an embodiment of the present invention; Figure 11 This is a three-dimensional structural diagram of the air flotation platform in an embodiment of the present invention; Figure 12 This is a cross-sectional view of the leveling support base in an embodiment of the present invention.

[0020] The annotations in the attached figures are explained as follows: 1-Unloading platform, 101-Top platform, 102-Support, 103-Connecting rod, 104-Fixing component; 2-Horizontal guide rail, 3-Support beam, 4-Adjusting rod, 5-Base, 6-Horizontal plate, 7-Air bearing, 71-Ring frame, 72-Throttle, 721-Matching hole, 73-Connecting lug; 8-Air-floating platform, 81-Platform split; 9-Leveling support, 91-Base, 92-Leveling screw 93-Leveling nut; 10-Air float foot; 1001-Body body; 1002-Top throttling orifice; 1003-Side throttling orifice; 1004-Equalizing groove; 1005-Connecting seat; 1006-Air inlet; 11-Support rod; 12-Adapter plate; 13-Adjusting plate; 14-Adjusting screw; 15-Adjusting nut; 16-Force sensor; 161-U-groove; 17-Spherical hinge; 18-Anti-rotation rubber ring. Detailed Implementation

[0021] The present invention will be further described below with reference to the accompanying drawings and exemplary embodiments.

[0022] Reference Figures 1-12 The present invention provides a mechanism deployment verification system, comprising an unloading platform 1, a low-friction guide rail structure, and an air-float unloading structure. Uninstall platform 1 structure as follows Figure 1 As shown, the system includes a top platform 101 and four supports 102 located at the four corners of the bottom of the top platform 101. For ease of on-site assembly, the overall structure is a frame structure. The top platform 101 and the supports 102 are each composed of multiple rectangular grid units. Each rectangular grid unit includes multiple connecting rods 103 and fasteners 104. The connection diagram is shown below. Figure 2 As shown, the fastener 104 is a regular octahedron with threaded holes on each face. The fastener 104 is located at the vertex of each rectangular grid unit. Both ends of the connecting rod 103 are provided with threaded sections. The connecting rod 103 is connected to the fastener 104 through the engagement of the threaded holes and threaded sections. Two adjacent rectangular grid units share one of the fasteners 104 located on the splicing surface of the rectangular grid. This greatly improves the flexibility of the overall structure connection and allows for flexible assembly according to the space where the unloading platform 1 is located. Since the structural strength of the connecting rod 103 and the fastener 104 determines the structural strength of the entire unloading platform 1, both the connecting rod 103 and the fastener 104 in this embodiment are made of 304 stainless steel.

[0023] The low-friction guide rail structure includes multiple horizontal guide rails 2 set below the top platform 101 and connectors for connecting the top platform 101 and the horizontal guide rails 2. The extension direction of the horizontal guide rails 2 is the same as the deployment direction of the space antenna. The horizontal guide rails 2 are cylindrical guide rails of model SBR50SA, which have the advantages of low cost and strong load-bearing capacity.

[0024] The connector includes a support beam 3 and an adjustment assembly for adjusting the height of the horizontal guide rail 2. The support beam 3 is made of a standard 40×40 aluminum profile and is connected to a fixing member 104 located at the bottom of the top platform 101. The adjustment assembly includes an adjustment rod 4 and a height adjustment mechanism. The top of the adjustment rod 4 is provided with a left-hand threaded section, and the bottom is provided with a right-hand threaded section. A gripping section is provided between the left-hand threaded section and the right-hand threaded section. The adjustment rod 4 is connected to the support beam 3 by engaging a T-nut in the slide groove of the support beam 3 through the left-hand threaded section. The height adjustment mechanism includes a base 5 mounted on the horizontal guide rail 2 and a horizontal plate 6 mounted at the bottom of the adjusting rod 4. The horizontal plate 6 is bolted to the base 5. A threaded hole is provided on the horizontal plate 6, and the right-hand threaded section of the adjusting rod 4 is screwed into the threaded hole. Thus, when installing and adjusting the horizontal guide rail 2, the grip section can be rotated, which is convenient and quick. Furthermore, by adjusting the height adjustment mechanism, two adjacent horizontal guide rails 2 can be positioned at different heights, allowing the two air bearings 7 mounted on adjacent horizontal guide rails 2 to be staggered in height space, preventing interference between the two air bearings 7 during operation.

[0025] At least one air bearing 7 is provided on each horizontal guide rail 2. The schematic diagram of the cooperation between the air bearing 7 and the horizontal guide rail 2 is shown below. Figure 6As shown, the air bearing 7 includes an annular frame 71 with an opening at the top and three throttles 72 disposed on the inner wall of the annular frame 71. There is a gap between the throttles 72 and the horizontal guide rail 2. The opening at the top of the annular frame 71 is used to avoid the height adjustment mechanism, preventing the air bearing 7 from being blocked by the height adjustment structure when moving on the horizontal guide rail 2. A throttling orifice is provided on the side of the throttling device 72 facing the horizontal guide rail 2, and a docking hole 721 for connecting to a high-pressure gas pipeline is provided on the throttling device 72. The docking hole 721 and the throttling orifice are connected through a cavity provided in the throttling device 72. The high-pressure gas in the high-pressure gas pipeline passes through the docking hole 721, the cavity and the throttling orifice in sequence and is blown towards the horizontal guide rail 2, forming a gas film in the gap between the throttling device 72 and the horizontal guide rail 2. A connecting lug 73 for connecting the space antenna is provided at the bottom of the ring frame 71. When the top of the space antenna is connected to the connecting lug 73 and the bearing capacity of the air bearing 7 is balanced with the gravity load of the space antenna, the air bearing 7 will float in the equilibrium position. Since the air bearing 7 does not contact the horizontal guide rail 2, theoretically there is no friction, so it can move without friction under the action of external thrust. Furthermore, the air bearing 7 has the advantages of high motion accuracy, fast motion speed, low gas viscosity, and no significant heat generation after long-term operation, making it very suitable for zero-gravity deployment verification of the space antenna.

[0026] The space antenna has a large mass. Relying solely on the air bearing 7 to unload the space antenna's gravity will place high demands on the structural strength of the horizontal guide rail 2, the air bearing 7, and the connecting parts. This will undoubtedly increase the design difficulty and manufacturing cost of these components. Therefore, this invention also includes an air bearing unloading structure, which includes an air bearing platform 8 set at the bottom of the top platform 101 and multiple air bearing feet 10 set on the air bearing platform 8. Each air bearing foot 10 corresponds to an air bearing 7.

[0027] Because the air-bearing platform 8 needs to be adapted to the size of the deployed space antenna, it requires a large footprint. However, the surface precision and strength requirements of the air-bearing platform 8 are very high. If the air-bearing platform 8 were to be manufactured as a single unit, it would be very difficult. Therefore, in this embodiment, the entire air-bearing platform 8 is a rectangular structure formed by splicing together 12 platform segments 81. This divides the entire air-bearing platform 8 into 12 parts, and each platform segment 81 is manufactured separately, reducing the manufacturing difficulty. The length and width of each platform segment 81 are 3m × 2m, and the joints are filled with epoxy resin. The length and width of the spliced ​​air-bearing platform are 12m × 6m. After comprehensively considering various technical conditions, the platform segments 81 are made of granite, and each platform segment 81 is 300mm thick, which can achieve tests with a load of up to 10 tons, thus meeting most test requirements.

[0028] Because the entire air flotation platform 8 is composed of 12 platform segments 81, when they are assembled together, it is necessary to ensure the overall flatness so as not to affect the movement of the air flotation foot 10 on the surface of the air flotation platform 8. This requires setting an adjustment mechanism on each platform segment 81. In this embodiment, each platform segment 81 has 6 leveling support seats 9 at its bottom. The entire leveling support seat 9 is made of stainless steel, which has high strength and is not easily deformed after long-term use. The structure of the leveling support seat 9 is as follows: Figure 11 As shown, the system includes a base 91, a leveling screw 92, and a leveling nut 93. The top end of the leveling screw 92 is connected to the bottom surface of the platform body 81. The leveling screw 92 is located in a through hole opened in the center of the base. The leveling nut 93 is screwed onto the leveling screw 92, and the bottom surface of the leveling nut 93 abuts against the top surface of the base 91. Thus, when the leveling nut 93 is rotated, the leveling screw 92 will move in the vertical direction, thereby driving the platform body 81 to move in the vertical direction. Through the cooperation between the various leveling support seats 9, the leveling of the entire air flotation platform 8 can be achieved.

[0029] The air flotation foot 10 set on the air flotation platform 8 includes a rectangular body 1001 and a connecting seat 1005 set at the center of the upper surface of the body 1001. Two air inlets 1006 are symmetrically arranged on the body 1001 on both sides of the connecting seat 1005. Eight air-float throttling orifices are provided at the bottom of the main body 1001. The air-float throttling orifices include four vertex throttling orifices 1002 and four side throttling orifices 1003. The air inlet 1006 is connected to the vertex throttling orifices 1002 and the side throttling orifices 1003 through the air cavity inside the air-float foot 10. The four vertex throttling orifices 1002 are arranged in a rectangular distribution. The four side throttling orifices 1003 are located on the center line connecting two adjacent vertex throttling orifices 1002 and at the midpoint of the corresponding center line. A pressure equalization groove 1004 is provided between the adjacent side throttling orifices 1003 and the vertex throttling orifices 1002. The high pressure zone of the air-float foot 10 with this structure is distributed on the periphery, and the air pressure distribution on the inner side is uniform. It has good load-bearing capacity and air film stiffness. The entire air-float foot 10 is made of aluminum alloy material, which is lightweight and has high structural strength.

[0030] To connect with the bottom of the space antenna, the air-floating foot 10 is equipped with a docking assembly, which includes an adapter plate 12, an adjusting plate 13, an adjusting screw 14, an adjusting nut 15, and a force sensor 16. The adjusting screw 14 is connected to the top of the force sensor 16. There are two adjusting nuts 15, both screwed onto the adjusting screw 14. The adjusting plate 13 is fitted onto the adjusting screw 14 and located between the two adjusting nuts 15. The adapter plate 12 is located above the top of the adjusting screw 14. Four threaded holes are arranged in a rectangular pattern on the adapter plate 12. The bottom of the space antenna is connected to the adapter plate 12 through these four threaded holes. The adapter plate 12 and the adjusting plate 13 are connected by two bolts. When adjusting the height of the adapter plate 12, the height is adjusted by the adjusting nut 15 below the adjusting plate 13 and locked by the adjusting nut 15 above, avoiding the influence of thread backlash error on the height adjustment.

[0031] The force sensor 16 has an S-shaped structure, with a U-shaped groove 161 at the top and bottom. The openings of the two U-shaped grooves 161 face opposite directions. A threaded hole is provided on the lower side wall of the lower U-shaped groove 161 in the vertical direction. A support rod 11 is provided in the threaded hole. One end of the support rod 11 is connected to the force sensor 16 through the threaded hole, and the other end is connected to the connecting seat 1005.

[0032] Because achieving perfect flatness across all 12 platform components 81 is extremely difficult, in practice, it's sufficient that the flatness of each component 81 is within a reasonable range. This results in each component 81's surface not necessarily being perfectly level, potentially exhibiting a certain tilt angle, and the magnitude and direction of this tilt angle may differ. If the support rod 11 is rigidly connected to the connecting seat 1005, it could cause additional torque on the space antenna during the movement of the air-bearing foot 10, affecting the verification results. Therefore, a through hole is provided in the center of the connecting seat 1005. The bottom of the base 1005 has a receiving cavity corresponding to the through hole. A hemispherical ball joint head 17 is provided in the receiving cavity. A groove adapted to the shape of the outer wall of the ball joint head 17 is provided on the main body 1001. The ball joint head 17 is located in the groove. The other end of the support rod 11 passes through the through hole and is connected to the ball joint head 17. In this way, the support rod 11 and the ball joint head 17 form a ball joint connection. When passing through the platform split 81 with different tilt angles, the ball joint head 17 can rotate in the groove to adapt to the tilt angle change, while the support rod 11 always remains vertical and will not generate additional torque on the space antenna.

[0033] Because of the ball joint connection, the air-floating foot 10 may rotate around the support rod 11. Therefore, an annular groove is provided at the top of the receiving cavity, and an anti-rotation rubber ring 18 is provided in the annular groove. The outer wall of the anti-rotation rubber ring 18 abuts against the inner wall of the annular groove, and the inner wall abuts against the outer wall of the support rod 11. The friction between the anti-rotation rubber ring 18 and the inner wall of the annular groove will limit the rotation of the air-floating foot 10.

[0034] In use, the top of the space antenna is connected to the connecting lug 73 of the air bearing 7, and the bottom of the space antenna is connected to the adapter plate 12. Then, air is supplied to the air foot 10 and the air bearing 7 through the high-pressure gas pipeline, and the space antenna will be in a suspended state. The load-bearing force is monitored in real time by the force sensor 16. Then, a horizontal force is applied to the space antenna, so that it unfolds along the extension direction of the horizontal guide rail 2 under the condition of eliminating gravity interference, thus completing the zero-gravity unfolding verification of the space antenna.

[0035] The embodiments described above are merely illustrative of specific implementations of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made to the technical solutions of the present invention by those skilled in the art without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A mechanism deployment verification system for zero-gravity deployment verification of a space antenna, characterized in that: Includes an unloading platform (1), a low-friction guide rail structure, and an air-float unloading structure; The unloading platform (1) includes a top platform (101) and four supports (102) located at the four corners of the bottom of the top platform (101). The low-friction guide rail structure includes multiple horizontal guide rails (2) disposed below the top platform (101) and multiple connectors for connecting the top platform (101) and the horizontal guide rails (2). The extension direction of the horizontal guide rails (2) is the same as the deployment direction of the space antenna. At least one air bearing (7) is fitted on each horizontal guide rail (2). The air bearing (7) includes an annular frame (71) with an opening at the top and multiple throttles (72) set on the inner wall of the annular frame (71). The opening is used to avoid the connecting parts. There is a gap between the throttle (72) and the horizontal guide rail (2). A throttle hole is provided on the side of the throttle (72) facing the horizontal guide rail (2). A docking hole (721) is also provided on the throttle (72). The docking hole (721) is used to connect with the high-pressure gas pipeline. The docking hole (721) is connected to the throttle hole through the cavity set in the throttle (72). The high-pressure gas in the high-pressure gas pipeline passes through the docking hole (721), the cavity and the throttle hole in sequence and is blown toward the horizontal guide rail (2). An air film is formed in the gap between the throttle (72) and the horizontal guide rail (2). The two adjacent horizontal guide rails (2) are located at different heights, so that the two air bearings (7) sleeved on the adjacent horizontal guide rails (2) can be staggered in height space; The air flotation unloading structure includes an air flotation platform (8) set below the top platform (101) and multiple air flotation feet (10) set on the air flotation platform (8). Each air flotation foot (10) corresponds to an air flotation bearing (7). Multiple air flotation throttling holes are provided at the bottom of the air flotation foot (10). An air inlet (1006) for connecting a high-pressure gas pipeline is provided on the air flotation foot (10). The air inlet (1006) and the multiple air flotation throttling holes are connected through an air cavity set inside the air flotation foot (10). The ring frame (71) is used to connect to the top of the space antenna, and the air-bearing foot (10) is used to connect to the bottom of the space antenna.

2. The mechanism deployment verification system according to claim 1, characterized in that: The top platform (101) and the support (102) are respectively spliced ​​from multiple rectangular grid units. Each rectangular grid unit includes multiple connecting rods (103) and fixing parts (104). The fixing parts (104) are set on the vertices of the rectangular grid unit. The fixing parts (104) are regular octahedrons, and each face is provided with threaded holes. Both ends of the connecting rods (103) are provided with threaded sections. The connecting rods (103) are connected to the fixing parts (104) through the cooperation of the threaded sections and the threaded holes. When two adjacent rectangular grid units are spliced, they share the fixing parts (104) located on the splicing surface of one of the rectangular grid units.

3. The mechanism deployment verification system according to claim 2, characterized in that: The connector includes a support beam (3) and an adjustment assembly. The support beam (3) is a standard aluminum profile and is connected to a fastener (104) located at the bottom of the top platform (101). The adjustment assembly includes an adjustment rod (4) and a height adjustment mechanism. The top of the adjustment rod (4) is provided with a left-hand threaded section and the bottom is provided with a right-hand threaded section. The left-hand threaded section of the adjustment rod (4) is used to cooperate with the T-nut in the groove of the support beam (3) to connect the adjustment rod (4) to the support beam (3). The height adjustment mechanism includes a base (5) set on the horizontal guide rail (2) and a horizontal plate (6) set at the bottom of the adjustment rod (4). The horizontal plate (6) is connected to the base (5) by bolts. A threaded hole is opened in the horizontal plate (6). The right-hand threaded section of the adjustment rod (4) is screwed into the threaded hole on the horizontal plate (6). The top opening of the ring frame (71) is used to avoid the height adjustment mechanism.

4. The mechanism deployment verification system according to any one of claims 1-3, characterized in that: The air-floating foot (10) includes a rectangular body (1001) and a connecting seat (1005) located at the center of the upper surface of the body (1001). There are two air inlets (1006) symmetrically arranged on the body (1001) on both sides of the connecting seat (1005). There are eight air-floating throttling holes, including four vertex throttling holes (1002) and four side throttling holes (1003). The four vertex throttling holes (1002) are arranged in a rectangular distribution, and the four side throttling holes (1003) are located on the center line connecting two adjacent vertex throttling holes (1002) and at the midpoint of the corresponding center line.

5. The mechanism deployment verification system according to claim 4, characterized in that: A pressure equalization groove (1004) is provided between the adjacent edge throttling orifice (1003) and the apex throttling orifice (1002).

6. The mechanism deployment verification system according to claim 5, characterized in that: The space antenna is connected to the air-floating foot (10) via a docking assembly, which includes an adapter plate (12), an adjustment plate (13), an adjustment screw (14), an adjustment nut (15), and a force sensor (16). The adjustment screw (14) is connected to the top of the force sensor (16). There are two adjustment nuts (15), both of which are screwed onto the adjustment screw (14). The adjustment plate (13) is sleeved on the adjustment screw (14) and located between the two adjustment nuts (15). The adapter plate (12) is located above the top of the adjustment screw (14). The adapter plate (12) and the adjustment plate (13) are connected by bolts. The bottom of the space antenna is connected to the adapter plate (12). The force sensor (16) has an S-shaped structure with a U-shaped groove (161) at the top and bottom. The openings of the two U-shaped grooves (161) face opposite directions. A threaded hole is provided on the lower side wall of the lower U-shaped groove (161) in the vertical direction. A support rod (11) is provided in the threaded hole. One end of the support rod (11) is connected to the force sensor (16) through the threaded hole, and the other end is connected to the connecting seat (1005).

7. The mechanism deployment verification system according to claim 1, characterized in that: The air flotation platform (8) is a rectangular structure formed by splicing multiple platform segments (81). Each platform segment (81) has multiple leveling support seats (9) at its bottom. The leveling support seat (9) includes a base (91), a leveling screw (92), and a leveling nut (93). The top of the leveling screw (92) is connected to the bottom surface of the platform segment (81). The leveling screw (92) is located in a through hole opened in the center of the base (91). The leveling nut (93) is screwed on the leveling screw (92) and the bottom surface of the leveling nut (93) abuts against the top surface of the base (91).

8. The mechanism deployment verification system according to claim 6, characterized in that: The connecting seat (1005) has a through hole in the center and a receiving cavity is provided at the bottom of the connecting seat (1005) corresponding to the position of the through hole. A hemispherical ball joint head (17) is provided in the receiving cavity, and a groove adapted to the shape of the outer wall of the ball joint head (17) is provided on the body (1001). The ball joint head (17) is located in the groove, and the other end of the support rod (11) passes through the through hole and is connected to the ball joint head (17). An annular groove is provided at the top of the receiving cavity, and an anti-rotation rubber ring (18) is provided in the annular groove. The outer wall of the anti-rotation rubber ring (18) abuts against the inner wall of the annular groove, and the inner wall abuts against the outer wall of the support rod (11).

9. The mechanism deployment verification system according to claim 7, characterized in that: The platform body (81) is made of granite, the leveling support (9) is made of stainless steel, and the air-floating foot (10) is made of aluminum alloy.

10. The mechanism deployment verification system according to claim 7, characterized in that: The bottom of the ring frame (71) is provided with a connecting ear (73), which is connected to the top of the space antenna.

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