Satellite antenna test deployment and unloading structure

Abstract

The satellite antenna test unfolding and unloading structure provided by the utility model, including unloading rod body, rotating unloading unit and flexible docking unit, rotating unloading unit and flexible docking unit are movably arranged at both ends of unloading rod body, and all adopt modular installation, through unloading rod body, rotating unloading unit and flexible docking unit, the force direction that satellite antenna unloads is always perpendicular to ground in the process of satellite antenna unfolding, facilitating subsequent unloading stress analysis, facilitating the realization of load force unloading, safe and reliable, the operation process is high in stability, simultaneously, can effectively avoid the interference condition with the process of satellite antenna unfolding, facilitate satellite antenna test, be favorable to improving satellite antenna test efficiency and debugging efficiency.

Description

Technical Field

[0001] This utility model belongs to the field of satellite antenna deployment testing. Specifically, this utility model relates to a satellite antenna testing deployment and unloading structure. Background Technology

[0002] Aerospace, as one of the most challenging and far-reaching high-tech fields in the world today, is an important manifestation of a nation's comprehensive strength and status as a major power. In addition to the various aerospace missions required for my country's own economic and social development, my country has also expanded international cooperation in recent years, leading to an increasing demand for aerospace satellite testing missions. According to domestic satellite antenna testing requirements, both ground-based and space-orbit antennas must undergo electrical signal performance testing before successful delivery to the customer. During antenna electrical performance testing, shell-shaped antennas require a process from a retracted state to an extended state, necessitating an deployment and unloading device to unload the load. Traditional deployment and unloading devices use a two-force straight rod structure with large gantry inertia, which is difficult to control and results in poor antenna deployment positioning accuracy, failing to meet the ease of use requirements during antenna testing. Unloading relies on oblique control of the gantry displacement to control the antenna deployment amount, which is cumbersome, results in long periods of ineffective working time, and is detrimental to antenna testing. It also requires highly skilled operators; carelessness can easily lead to interference between the unloading device and the antenna, affecting product safety and hindering the testing process.

[0003] To address the aforementioned issues, application number 2013106426094 discloses a support device for satellite antenna deployment, comprising a support beam and a simulation plate. The support beam is a rectangular frame structure, with the simulation plate positioned near the rear end of the frame. The width of the simulation plate is greater than the width of the support beam, while the length of the simulation plate is less than the length of the support beam. Multiple lifting lugs are also provided on the support beam. A first, second, and third horizontal plate are sequentially positioned at the front end of the support beam. Three antenna connecting plates (upper, middle, and lower) are positioned on the three horizontal plates, and three support rod assemblies (upper, middle, and lower) are positioned on the three antenna connecting plates. The length of the upper support rod assembly is greater than the length of the middle support rod assembly, and the length of the middle support rod assembly is greater than the length of the lower support rod assembly. However, this method fails to solve the aforementioned problems.

[0004] Therefore, in order to improve or solve at least one of the above problems, a satellite antenna testing, deployment, and unloading structure is provided that facilitates unloading of load forces, is safe and reliable, has high operational stability, can effectively avoid interference with the satellite antenna deployment process, facilitates satellite antenna testing, and is conducive to improving satellite antenna testing and debugging efficiency. Summary of the Invention

[0005] This utility model is designed to solve the aforementioned problems. Its purpose is to provide a satellite antenna testing, deployment, and unloading structure that facilitates load unloading, is safe and reliable, has high operational stability, effectively avoids interference with the satellite antenna deployment process, is convenient for satellite antenna testing, and improves satellite antenna testing and debugging efficiency. To achieve the above objectives, the technical solution adopted by this utility model is as follows: This utility model provides a satellite antenna test deployment and unloading structure, which includes an unloading rod body, a rotating unloading unit, and a flexible docking unit, wherein the rotating unloading unit and the flexible docking unit are movably disposed at both ends of the unloading rod body.

[0006] The satellite antenna test deployment and unloading structure provided by this utility model may also have the following features: the unloading rod body includes an intermediate rod, a first connecting rod and a second connecting rod, one end of the first connecting rod is connected to one end of the intermediate rod, one end of the second connecting rod is connected to the other end of the intermediate rod, and the unloading rod body is C-shaped.

[0007] The satellite antenna test deployment and unloading structure provided by this utility model may also have the following features: the end of the first connecting rod away from the middle rod is provided with a first connecting flange, and the first connecting flange is provided with a first connecting hole; the end of the second connecting rod away from the middle rod is provided with a second connecting flange, and the second connecting flange is provided with a second connecting hole.

[0008] The satellite antenna test deployment and unloading structure provided by this utility model may also have the following feature: the end of the first connecting rod away from the intermediate rod is movably connected to the rotary unloading unit. The rotary unloading unit includes a first rotating seat and a second rotating seat movably connected to the first rotating seat. The first rotating seat includes a first rotating plate, a first support plate, and a rotating shaft. The rotating shaft is disposed on the first rotating plate, and the first support plate is disposed on the first rotating plate. The first support plate is provided with a first bolt hole. The second rotating seat includes a second rotating plate and a second support plate. The second support plate is disposed on the second rotating plate, and the second rotating plate is provided with a rotating shaft hole adapted to the rotating shaft. The second support plate is provided with a second bolt hole.

[0009] The satellite antenna test deployment and unloading structure provided by this utility model may also have the following features: a first bolt is inserted into the first bolt hole; and a second bolt is inserted into the second bolt hole.

[0010] The satellite antenna test deployment and unloading structure provided by this utility model may also have the following features: a first ball bearing is provided in the first connecting hole, and a first bolt passes through the first ball bearing; a bearing groove is provided on the second rotating plate, a second ball bearing is provided in the bearing groove, the second ball bearing is sleeved on the rotating shaft, and a clamping nut is screwed on the end of the rotating shaft.

[0011] The satellite antenna test deployment and unloading structure provided by this utility model may also have the following features: the flexible docking unit includes a movable joint and a docking component. The movable joint includes a joint body, a first hinge plate and a second hinge plate. The first hinge plate is disposed on one side of the joint body and has a first hinge hole. The second hinge plate is disposed on the other side of the joint body and has a second hinge hole.

[0012] The satellite antenna test deployment and unloading structure provided by this utility model may also have the following features: the docking component includes a docking plate, a docking pin, and a connecting protrusion. The docking pin is located on one side of the docking plate, and the connecting protrusion is located on the other side of the docking plate. The connecting protrusion is movably connected to the second hinge plate. The technical advantages of this utility model are as follows: The satellite antenna test deployment and unloading structure provided by this utility model includes an unloading rod body, a rotating unloading unit, and a flexible docking unit. The rotating unloading unit and the flexible docking unit are movably installed at both ends of the unloading rod body and are modularly installed. Through the unloading rod body, the rotating unloading unit, and the flexible docking unit, the direction of the force on the satellite antenna during unloading can always be perpendicular to the ground during the deployment process. This facilitates subsequent unloading force analysis, facilitates the unloading of load forces, is safe and reliable, and has high operational stability. At the same time, it can effectively avoid interference with the satellite antenna deployment process, facilitates satellite antenna testing, and helps improve the efficiency of satellite antenna testing and debugging. Attached Figure Description

[0013] This manual includes the following figures, which illustrate the following: Figure 1 This is a schematic diagram of the satellite antenna test deployment and unloading structure in an embodiment of this utility model; Figure 2 This is an exploded view of the satellite antenna test deployment and unloading structure in an embodiment of this utility model; Figure 3 yes Figure 1 Sectional view of section AA; Figure 4 This is a schematic diagram of the flexible docking unit in an embodiment of this utility model.

[0014] The components in the diagram are labeled as follows: unloading rod body-10, intermediate rod-11, first connecting rod-12, first connecting flange-121, first connecting hole-122, second connecting rod-13, second connecting flange-131, second connecting hole-132, rotating unloading unit-20, first rotating seat-21, first rotating plate-211, first support plate-212, rotating shaft-213, first bolt hole-214, second rotating seat-22, second rotating plate-221, second support plate-222, and rotating shaft. Shaft hole-223, second bolt hole-224, bearing groove-225, first bolt-23, second bolt-24, first ball bearing-25, second ball bearing-26, clamping nut-27, flexible docking unit-30, movable joint-31, joint body-311, first hinge plate-312, second hinge plate-313, first hinge hole-314, second hinge hole-315, docking part-32, docking plate-321, docking pin-322, connecting flange-323. Detailed Implementation

[0015] The specific embodiments of the present invention will be further described in detail below with reference to the accompanying drawings, in order to help those skilled in the art to have a more complete, accurate and in-depth understanding of the inventive concept and technical solution of the present invention, and to facilitate its implementation.

[0016] Figure 1 This is a schematic diagram of the satellite antenna test deployment and unloading structure in an embodiment of this utility model; Figure 2 This is an exploded view of the satellite antenna test deployment and unloading structure in an embodiment of this utility model.

[0017] like Figure 1 and Figure 2 As shown, the satellite antenna test deployment and unloading structure provided by this utility model includes an unloading rod body 10, a rotating unloading unit 20, and a flexible docking unit 30. The rotating unloading unit 20 and the flexible docking unit 30 are movably disposed at both ends of the unloading rod body 10 and are modularly installed. Through the unloading rod body 10, the rotating unloading unit 20, and the flexible docking unit 30, the direction of the force acting on the satellite antenna during unloading can always be perpendicular to the ground during the deployment process. This facilitates subsequent unloading force analysis, enables easy unloading of load forces, ensures safety and reliability, and provides high stability during operation. At the same time, it can effectively avoid interference with the satellite antenna deployment process, facilitates satellite antenna testing, and helps improve the efficiency of satellite antenna testing and debugging.

[0018] like Figure 1 and Figure 2As shown, the unloading rod body 10 includes an intermediate rod 11, a first connecting rod 12, and a second connecting rod 13. One end of the first connecting rod 12 is connected to one end of the intermediate rod 11, and one end of the second connecting rod 13 is connected to the other end of the intermediate rod 11, making the unloading rod body 10 "C" shaped. During the deployment of the satellite antenna to the target location, the unloading rod body 10 can avoid the satellite antenna and related equipment, preventing motion interference and ensuring the safety of the satellite antenna product. During the deployment of the satellite antenna, the gantry crane only needs to unload in a vertical state, making the operation convenient and quick.

[0019] like Figure 1 and Figure 2 As shown, the first connecting rod 12 has a first connecting flange 121 at the end away from the intermediate rod 11, and a first connecting hole 122 on the first connecting flange 121. The first connecting flange 121 and the first connecting hole 122 are used to connect with the rotary unloading unit 20. The second connecting rod 13 has a second connecting flange 131 at the end away from the intermediate rod 11, and a second connecting hole 132 on the second connecting flange 131. The second connecting flange 131 and the second connecting hole 132 are used to connect with the flexible docking unit 30, which facilitates the modular connection between the rotary unloading unit 20 and the flexible docking unit 30 and the unloading rod body 10, and facilitates the installation and maintenance of the rotary unloading unit 20 and the flexible docking unit 30.

[0020] Figure 3 yes Figure 1 A sectional view of section AA in the middle.

[0021] like Figure 3 As shown, the end of the first connecting rod 12 away from the intermediate rod 11 is movably connected to the rotary unloading unit 20. The rotary unloading unit 20 includes a first rotating seat 21 and a second rotating seat 22 movably connected to the first rotating seat 21. The first rotating seat 21 includes a first rotating plate 211, a first support plate 212, and a rotating shaft 213. The rotating shaft 213 is disposed on the first rotating plate 211, and the first support plate 212 is disposed on the first rotating plate 211. The first support plate 212 is provided with a first bolt hole 214. The two first support plates 211... The two rotating bases 22 are arranged parallel to each other. The second rotating base 22 includes a second rotating plate 221 and a second support plate 222. The second support plate 222 is disposed on the second rotating plate 221. The second rotating plate 221 is provided with a rotating shaft hole 223 adapted to the rotating shaft 213. The second support plate 222 is provided with a second bolt hole 224. The two second support plates 222 are arranged parallel to each other, so that the first rotating base 21 and the first rotating base 21 can rotate flexibly, so that the direction of the force on the satellite antenna when unloading is always perpendicular to the ground.

[0022] A first bolt 23 is inserted into the first bolt hole 214. The first bolt 23 is used to connect the unloading rod body 10 and the rotary unloading unit 20. A second bolt 24 is inserted into the second bolt hole 224. The second bolt 24 is used to connect the rotary unloading unit 20 and the satellite antenna.

[0023] A first ball bearing 25 is provided in the first connecting hole 122, and a first bolt 23 passes through the first ball bearing 25, the first connecting hole 122, and the first bolt hole 214, so that the unloading rod body 10 and the rotating unloading unit 20 can rotate relative to each other, so that the direction of the force on the antenna during unloading is always perpendicular to the ground; a bearing groove 225 is provided on the second rotating plate 221, and a second ball bearing 26 is provided in the bearing groove 225. The outer ring of the second ball bearing 26 is connected to the bearing groove 225 by an interference fit. The second ball bearing 26 is sleeved on the rotating shaft 213, and a clamping nut 27 is screwed on the end of the rotating shaft 213. The clamping nut 27 is used to clamp the second ball bearing 26, so that the first rotating seat 21 and the first rotating seat 21 can rotate relative to each other, which can realize the conversion of the force direction, so that the direction of the force on the antenna during unloading is always perpendicular to the ground. This makes the satellite antenna test deployment and unloading structure provided by this utility model flexible in operation and compact in structure. Meanwhile, the first ball bearing 25 and the second ball bearing 26 are located in the rotating part, which reduces the running resistance and makes the operation more flexible. This improves the flexibility and operational stability of the antenna during electrical testing, shortens the electrical testing time of the antenna, and improves the efficiency of the test work.

[0024] Figure 4 This is a schematic diagram of the flexible docking unit in an embodiment of this utility model.

[0025] like Figure 4 As shown, the flexible docking unit 30 includes a movable joint 31 and a docking component 32. The movable joint 31 includes a joint body 311, a first hinge plate 312, and a second hinge plate 313. The first hinge plate 312 is disposed on one side of the joint body 311, and the two first hinge plates 312 are arranged parallel to each other. The second hinge plate 313 is disposed on the other side of the joint body 311, and the two second hinge plates 313 are arranged parallel to each other. The first hinge plate 312 and the second hinge plate 313 are parallel to each other. The first hinge plate 312 is provided with a first hinge hole 314, which is used for the flexible docking unit 30 to be movably connected to the unloading rod body 10. Bolts and nuts are inserted into the first hinge hole 314 and the second connecting hole 132. The second hinge plate 313 is provided with a second hinge hole 315, which is used for the movable connection between the movable joint 31 and the docking component 32.

[0026] The docking component 32 includes a docking plate 321, a docking pin 322, and a connecting protrusion 323. The docking pin 322 is located on the side of the docking plate 321 away from the movable joint 31, and the connecting protrusion 323 is located on the other side of the docking plate 321 near the movable joint 31. The connecting protrusion 323 is movably connected to the second hinge plate 313. By bolts passing through the second hinge hole 315 and the connecting protrusion 323, a rotatable connection between the movable joint 31 and the docking component 32 is achieved. This allows the flexible docking unit 30 to maintain a perpendicular position to the ground during antenna unloading by changing its own attitude, thus facilitating subsequent unloading force analysis.

[0027] The satellite antenna test deployment and unloading structure provided by this utility model includes an unloading rod body 10, a rotating unloading unit 20, and a flexible docking unit 30. The rotating unloading unit 20 and the flexible docking unit 30 are movably disposed at both ends of the unloading rod body 10 and are modularly installed. Through the unloading rod body 10, the rotating unloading unit 20, and the flexible docking unit 30, the direction of the force on the satellite antenna during unloading is always perpendicular to the ground during the deployment process. This facilitates subsequent unloading force analysis, enables easy unloading of load forces, ensures safety and reliability, and provides high stability during operation. At the same time, it effectively avoids interference with the satellite antenna deployment process, facilitates satellite antenna testing, and helps improve the efficiency of satellite antenna testing and debugging.

[0028] The present invention has been described above by way of example with reference to the accompanying drawings. Obviously, the specific implementation of the present invention is not limited to the above-described manner. Any non-substantial improvements made using the inventive concept and technical solution of the present invention; or the direct application of the inventive concept and technical solution to other situations without modification, are all within the protection scope of the present invention.

Claims

1. A satellite antenna test deployment and unloading structure, characterized in that, It includes an unloading rod body (10), a rotating unloading unit (20), and a flexible docking unit (30), wherein the rotating unloading unit (20) and the flexible docking unit (30) are movably disposed at both ends of the unloading rod body (10).

2. The satellite antenna test deployment and unloading structure according to claim 1, characterized in that, The unloading rod body (10) includes an intermediate rod (11), a first connecting rod (12) and a second connecting rod (13). One end of the first connecting rod (12) is connected to one end of the intermediate rod (11), and one end of the second connecting rod (13) is connected to the other end of the intermediate rod (11). The unloading rod body (10) is C-shaped.

3. The satellite antenna test deployment and unloading structure according to claim 2, characterized in that, The first connecting rod (12) has a first connecting flange (121) at one end away from the intermediate rod (11), and a first connecting hole (122) is provided on the first connecting flange (121); the second connecting rod (13) has a second connecting flange (131) at one end away from the intermediate rod (11), and a second connecting hole (132) is provided on the second connecting flange (131).

4. The satellite antenna test deployment and unloading structure according to claim 3, characterized in that, The end of the first connecting rod (12) away from the intermediate rod (11) is movably connected to the rotary unloading unit (20). The rotary unloading unit (20) includes a first rotating seat (21) and a second rotating seat (22) movably connected to the first rotating seat (21). The first rotating seat (21) includes a first rotating plate (211), a first support plate (212), and a rotating shaft (213). The rotating shaft (213) is disposed on the first rotating plate (211), and the first support plate (212) is disposed on the first rotating plate (211). The first support plate (212) is provided with a first bolt hole (214). The second rotating seat (22) includes a second rotating plate (221) and a second support plate (222). The second support plate (222) is disposed on the second rotating plate (221). The second rotating plate (221) is provided with a rotating shaft hole (223) adapted to the rotating shaft (213), and the second support plate (222) is provided with a second bolt hole (224).

5. The satellite antenna test deployment and unloading structure according to claim 4, characterized in that, A first bolt (23) is inserted into the first bolt hole (214); a second bolt (24) is inserted into the second bolt hole (224).

6. The satellite antenna test deployment and unloading structure according to claim 5, characterized in that, The first connecting hole (122) is provided with a first ball bearing (25), and the first bolt (23) passes through the first ball bearing (25); the second rotating plate (221) is provided with a bearing groove (225), and the bearing groove (225) is provided with a second ball bearing (26), the second ball bearing (26) is sleeved on the rotating shaft (213), and the end of the rotating shaft (213) is screwed with a clamping nut (27).

7. The satellite antenna test deployment and unloading structure according to claim 6, characterized in that, The flexible docking unit (30) includes a movable joint (31) and a docking component (32). The movable joint (31) includes a joint body (311), a first hinge plate (312) and a second hinge plate (313). The first hinge plate (312) is disposed on one side of the joint body (311) and has a first hinge hole (314). The second hinge plate (313) is disposed on the other side of the joint body (311) and has a second hinge hole (315).

8. The satellite antenna test deployment and unloading structure according to claim 7, characterized in that, The docking component (32) includes a docking plate (321), a docking pin (322), and a connecting protrusion (323). The docking pin (322) is disposed on one side of the docking plate (321), and the connecting protrusion (323) is disposed on the other side of the docking plate (321). The connecting protrusion (323) is movably connected to the second hinge plate (313).

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