High-frequency-band and high-integration satellite-borne transmitting surface antenna

Abstract

The invention discloses a high-frequency-band and high-integration satellite-borne transmitting surface antenna, which belongs to the field of antennae, and comprises a supporting seat, a pitching pointing base is fixed on the side surface of the supporting seat, a horizontal pointing base is arranged on one side of the pitching pointing base, and a variable speed motor I is arranged on the side surface of the pitching pointing base; an output shaft of the first variable-speed motor penetrates through the side face of the pitching pointing base, the output shaft of the first variable-speed motor penetrates through the horizontal pointing base and is fixedly connected with the horizontal pointing base, a cabin plate is arranged on the side, close to the supporting base, of the horizontal pointing base, and a reflecting surface assembly is arranged on the cabin plate. A second variable-speed motor is arranged on the horizontal pointing base, an output shaft of the second variable-speed motor penetrates through the horizontal pointing base to be fixedly connected with the cabin plate, and a locking and releasing mechanism used for locking and releasing the reflecting surface assembly is arranged on the supporting base. The method has the effect of improving the assembly efficiency.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of antennas, in particular to a high-frequency high-integration satellite-borne transmitting surface antenna. BACKGROUND

[0002] In the field of satellite-borne antennas, a conventional double-axis pointing mechanism generally adopts a separated design of an independent unfolding arm and a plurality of locking mechanisms, leading to high structural complexity, large weight redundancy and difficulty in simultaneously meeting the coverage of inter-satellite and earth-satellite communication. In addition, the assembly error of a main reflecting surface and a main reflecting support and a vice reflecting surface and a vice reflecting support will significantly increase the pointing angle between the electrical axis and the mechanical axis of the antenna, and the conventional scheme needs to rely on high-precision machining and complex assembly process to reduce the angle between the two, thereby reducing the assembly and production efficiency of the antenna. SUMMARY

[0003] In order to improve the low antenna assembly efficiency, the application provides a high-frequency high-integration satellite-borne transmitting surface antenna.

[0004] The high-frequency high-integration satellite-borne transmitting surface antenna provided by the application adopts the following technical scheme: A high-frequency high-integration satellite-borne transmitting surface antenna, comprising a support seat, a side surface of the support seat being fixed with an elevation pointing base, one side of the elevation pointing base being provided with a horizontal pointing base, a side surface of the elevation pointing base being provided with a variable speed motor one, an output shaft of the variable speed motor one penetrating through the side surface of the elevation pointing base, the output shaft of the variable speed motor one penetrating through the horizontal pointing base, the output shaft of the variable speed motor one being fixedly connected with the horizontal pointing base, one side of the horizontal pointing base close to the support seat being provided with a cabin plate, the cabin plate being provided with a reflecting surface assembly, the horizontal pointing base being provided with a variable speed motor two, an output shaft of the variable speed motor two penetrating through the horizontal pointing base and being fixedly connected with the cabin plate, the support seat being provided with a locking and releasing mechanism for locking and releasing the reflecting surface assembly.

[0005] By adopting the above technical scheme, the elevation and horizontal double-axis pointing mechanism form is adopted, the reflecting surface assembly is locked by the locking and releasing mechanism, then the assembly error is eliminated and the pointing precision is improved by the integrated design of the reflecting surface assembly structure, so as to improve the assembly efficiency, and the communication coverage of earth-satellite and inter-satellite can be met by the simultaneous operation of the two groups of pointing mechanisms.

[0006] Preferably, the reflecting surface assembly comprises a main reflecting surface arranged on the cabin plate and a feed source assembly arranged in the main reflecting surface, a support base is arranged on the feed source assembly, and a vice reflecting surface is arranged at the top end of the support base.

[0007] By adopting the above technical solution, the feed assembly, support base and sub-reflector are designed as an integrated structure. The pointing deviation caused by processing error is a fixed error. The error related to power supply can be compensated by control software after testing. The mechanical processing error can be compensated by assembly and debugging. The residual after compensation is calculated as a random error, thereby eliminating assembly error, improving antenna pointing accuracy, reducing assembly difficulty and improving assembly efficiency.

[0008] Preferably, the bottom surface of the bracket base has a through hole, and the bracket base is sleeved on the outer peripheral surface of the feed component through the through hole, and the inner wall of the through hole is threadedly connected to the outer peripheral surface of the feed component.

[0009] By adopting the above technical solution, the bracket base and the feed assembly are connected by threads, which makes it easy to install the sub-reflector on the feed assembly.

[0010] Preferably, the locking and releasing mechanism includes two shape memory alloy expansion joints disposed on the top surface of the support base. Two fixing holes are provided on the top surface of the compartment plate away from the horizontally pointing base. The two fixing holes correspond to the two shape memory alloy expansion joints, and the expansion rods at the top of the shape memory alloy expansion joints are inserted into the fixing holes.

[0011] By adopting the above technical solution, the antenna is fixed and locked to the cabin plate by two shape memory alloy expansion joints during the transmission phase. After entering the orbit, the shape memory alloy expansion joints are powered, the slotted bolts are broken, and the antenna separates from the locking point under the action of the fracture impact force and the separation spring. The horizontally pointing base drives the antenna to unfold.

[0012] Preferably, a rotating joint 1 is provided below the cabin plate, the rotating joint 1 is coaxially arranged with the output shaft of the variable speed motor 2, and connecting plates are fixed on both sides of the rotating joint 1. The top surface of the connecting plate is fixed to the bottom surface of the cabin plate by bolts. Waveguide components 1 are rotatably connected to both ends of the rotating joint 1. A mounting plate is fixed on the side of the horizontally pointing base. A rotating joint 2 is provided on the side of the mounting plate away from the support base. The rotating joint 2 is coaxially arranged with the variable speed motor. The ends of the two waveguide components 1 away from the rotating joint 1 are respectively rotatably installed at both ends of the rotating joint 2.

[0013] By adopting the above technical solution, a waveguide component is set between the first rotating joint and the second rotating joint, so that the waveguide component transmits the signal received by the antenna.

[0014] Preferably, waveguide components 2 are rotatably mounted at both ends of the rotary joint 2, and a three-way tool is fixed to the side of the pitch-pointing base. The ends of the two waveguide components 2 away from the rotary joint 2 are connected to the three-way tool.

[0015] By adopting the above technical solution, the antenna signal received by waveguide component one is transmitted to waveguide line two, thereby enabling waveguide line two to transmit the signal to the tripod.

[0016] Preferably, a positioning plate with two openings on its top surface is fixed to the side of the horizontally pointing base. Two waveguide components pass through the two openings on the positioning plate, and a limiting plate is clamped on each of the two waveguide components. The limiting plate and the positioning plate are fixedly connected by bolts.

[0017] By adopting the above technical solution, two waveguide components pass through the positioning plate, and then the limiting plate is clamped on the two waveguide components. Then, the positioning plate and the limiting plate are fixedly connected by bolts, thereby fixing the waveguide component and improving the stability of the waveguide component.

[0018] Preferably, a positioning plate II with two openings on the side is fixed to the side of the pitch pointing base, and two waveguide components II pass through the two openings respectively. A limiting plate II is clamped on the two waveguide components II, and the limiting plate II is fixedly connected to the positioning plate II by bolts.

[0019] By adopting the above technical solution, two waveguide components 2 pass through positioning plate 2, then phase plate 2 is clamped on the two waveguide components 2, and then limiting plate 2 and positioning plate 2 are fixedly connected by bolts, thereby fixing the waveguide component 2 with positioning plate 2 and limiting plate 2, thereby improving the stability of waveguide component 2.

[0020] Preferably, a connector assembly is provided on the side of the pitch-pointing base.

[0021] By adopting the above technical solution, a connector assembly is set on the side of the pitch-pointing base, which facilitates the connection of circuits and the transmission and exchange of data signals between devices.

[0022] In summary, this application includes at least one of the following beneficial technical effects: 1. It adopts a dual-axis pointing mechanism with pitch and horizontal axes. The high fundamental frequency is locked to the reflector assembly through a locking and releasing mechanism. Then, the integrated design of the reflector assembly structure eliminates assembly errors and improves pointing accuracy, thereby improving assembly efficiency. The simultaneous operation of the two pointing mechanisms can meet the communication coverage between the satellite and the ground and between satellites. 2. The feed assembly, support base, and sub-reflector are designed as an integrated structure. The pointing deviation caused by processing errors is a fixed error. Feed-related errors can be compensated by control software after testing. Mechanical processing errors can be compensated by assembly and debugging. The residual after compensation is calculated as a random error, thereby eliminating assembly errors, improving antenna pointing accuracy, reducing assembly difficulty, and improving assembly efficiency. 3. During the launch phase, the antenna is fixed and locked to the cabin plate by two shape memory alloy expansion joints. After entering the rail, the shape memory alloy expansion joints are powered, the slotted bolts are broken, and the antenna separates from the locking point under the action of the fracture impact force and the separation spring. The horizontally pointing base drives the antenna to unfold. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of the high-frequency, highly integrated spaceborne transmitting surface antenna according to an embodiment of this application.

[0024] Figure 2 This is a schematic diagram of the structure of the cabin in an embodiment of this application.

[0025] Figure 3 This is a schematic diagram of the structure of the emitting surface assembly in an embodiment of this application.

[0026] Figure 4 This is a schematic diagram of the structure of a rotary joint in an embodiment of this application.

[0027] Figure 5 yes Figure 1 Enlarged diagram of point A in the middle.

[0028] Figure 6 This is a schematic diagram of the connector assembly in an embodiment of this application.

[0029] Reference numerals: 1. Support base; 11. Pitch pointing base; 12. Horizontal pointing base; 13. Variable speed motor one; 2. Cabin plate; 21. Variable speed motor two; 22. Shape memory alloy expansion joint; 23. Fixing hole; 24. Emitting surface assembly; 241. Main reflector; 242. Feed assembly; 243. Support base; 244. Through hole; 245. Secondary reflector; 3. Rotary joint one; 31. Connecting plate; 32. Waveguide component one; 33. Mounting plate; 34. Rotary joint two; 35. Positioning plate one; 36. Limiting plate one; 4. Tri-tool; 41. Connector assembly; 42. Waveguide component two; 43. Positioning plate two; 44. Limiting plate two. Detailed Implementation

[0030] The following is in conjunction with the appendix Figures 1-6 This application will be described in further detail.

[0031] This application discloses a high-frequency, highly integrated spaceborne transmitting surface antenna.

[0032] Reference Figure 1 A high-frequency, highly integrated spaceborne transmitting antenna includes a support base 1. An elevation pointing base 11 is fixed to the side of the support base 1. A horizontal pointing base 12 is provided on one side of the elevation pointing base 11. A variable speed motor 13 is fixed to the side of the elevation pointing base 11 away from the horizontal pointing base 12. The output shaft of the variable speed motor 13 passes through the side of the elevation pointing base 11 and is rotatably connected to the elevation pointing base 11. The horizontal pointing base 12 is sleeved and fixed on the outer circumferential surface of the output shaft of the variable speed motor 13.

[0033] Reference Figure 1 , Figure 2 and Figure 3 A compartment plate 2 is provided on the side of the horizontal pointing base 12 near the support base 1. A launching surface assembly 24 is fixed on the top surface of the compartment plate 2. Two shape memory alloy expansion joints 22 are fixed on the top surface of the support base 1. Two fixing holes 23 are opened on the top surface of the compartment plate 2 near the support base 1. The two fixing holes 23 correspond to the two shape memory alloy expansion joints 22. The slotted bolts on the shape memory alloy expansion joints 22 are inserted into the fixing holes 23. A variable speed motor 21 is fixed on the side of the horizontal pointing base 12 away from the support base 1. The output shaft of the variable speed motor 21 passes through the horizontal pointing base 12 and is rotatably connected to the horizontal pointing base 12. The compartment plate 2 is sleeved and fixed on the outer circumferential surface of the output shaft of the variable speed motor 21. The emitting surface assembly 24 includes a main reflector 241 fixed to the top surface of the cabin plate 2. A feed assembly 242 is fixed inside the main reflector 241. A support base 243 is provided on the feed assembly 242. A through hole 244 is opened on the top surface of the support base 243. The support base 243 is sleeved on the outer peripheral surface of the feed assembly 242 through the through hole 244. The support base 243 is threadedly connected to the feed assembly 242. A secondary reflector 245 is fixed at the top of the support base 243.

[0034] Reference Figure 1 and Figure 4 A rotating joint 3 is located below the cabin plate 2. The rotating joint 3 is coaxially mounted with the output shaft of the variable speed motor 21. Connecting plates 31, which are L-shaped plates, are bolted to both sides of the rotating joint 3. The top of the connecting plates 31 is bolted to the bottom surface of the cabin plate 2. Waveguide components 32 are rotatably mounted at both ends of the rotating joint 3. A mounting plate 33 is fixed to the side of the horizontally pointing base 12 away from the pitch pointing base 11. A rotating joint 34 is bolted to the side of the mounting plate 33 away from the support base 1. The rotating joint 34 is coaxially mounted with the output shaft of the variable speed motor 13. The ends of the two waveguide components 32 away from the rotating joint 3 are rotatably mounted at both ends of the rotating joint 34.

[0035] ReferenceFigure 1 , Figure 5 and Figure 6 A positioning plate 35 with two openings on its top surface is fixed to the side of the pitch pointing base 11 near the horizontal pointing base 12. Two waveguide components 32 pass through the two openings on the positioning plate 35, and limiting plates 36 are clamped onto the two waveguide components 32. The limiting plates 36 are fixedly connected to the positioning plate 35 by bolts. A tripod 4 is fixed to the side of the pitch pointing base 11, and a connector assembly 41 is fixed to the side of the pitch pointing base 11 away from the tripod 4.

[0036] Reference Figure 1 and Figure 4 Both ends of the rotary joint 34 are rotatably mounted with waveguide components 42. The end of the waveguide component 42 away from the rotary joint 34 is fixedly connected to the tripod 4. A positioning plate 43 with two openings on its top surface is fixed to the side of the pitch-pointing base 11. The two waveguide components 42 pass through the two openings on the positioning plate 43 respectively. Each waveguide component 42 is fitted with a limiting plate 44, which is fixedly connected to the positioning plate 43 by bolts.

[0037] The implementation principle of a high-frequency, highly integrated spaceborne transmitting antenna according to an embodiment of this application is as follows: During the transmission phase, the antenna is locked by two shape memory alloy expansion joints 22, keeping the antenna in a folded and locked state. After the antenna enters the rail, power is supplied to the shape memory alloy expansion joints 22, the slotted bolts are disconnected, and then the first variable speed motor 13 is started. The output shaft of the first variable speed motor 13 drives the horizontally pointing base 12 to rotate, which in turn drives the second variable speed motor 21 to rotate. The second variable speed motor 21 drives the cabin plate 2 to rotate, and the cabin plate 2 drives the transmitting surface assembly 24 to rotate, thus rotating the main reflector... The reflector 241 is deployed, and then the variable speed motor 21 is activated. The output shaft of the variable speed motor 21 drives the cabin plate 2 to rotate, which in turn drives the main reflector 241 to rotate. This causes the variable speed motor 13 to drive the horizontal pointing base 12 to rotate, and the variable speed motor 21 to drive the main reflector 241 to rotate. This ensures that during inter-satellite communication, the beam pointing elevation angle range is not less than -90° to 90°, and the horizontal angle range is not less than -9° to 1°. During satellite-to-ground communication, the beam pointing range is not less than a cone angle of 63.5°, which can meet the communication coverage requirements for inter-satellite and satellite-to-ground communication under various conditions. Furthermore, through the integrated sub-reflector 245 and the support base 243 structure, the pointing deviation caused by processing errors is made into a fixed error. Feed-related errors can be compensated by control software after testing, and mechanical processing errors can be compensated by assembly and debugging. The residual after compensation is calculated as a random error, thereby eliminating assembly errors, improving antenna pointing accuracy, reducing assembly difficulty, and thus improving assembly efficiency.

[0038] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A high-frequency, highly integrated spaceborne transmitting antenna, characterized in that: Includes a support base (1), a pitch pointing base (11) fixed to the side of the support base (1), a horizontal pointing base (12) provided on one side of the pitch pointing base (11), a variable speed motor (13) provided on the side of the pitch pointing base (11), the output shaft of the variable speed motor (13) passing through the side of the pitch pointing base (11), the output shaft of the variable speed motor (13) passing through the horizontal pointing base (12), and the output shaft of the variable speed motor (13) being connected to... The horizontal pointing base (12) is fixedly connected. A compartment plate (2) is provided on the side of the horizontal pointing base (12) near the support base (1). A reflective surface assembly is provided on the compartment plate (2). A variable speed motor (21) is provided on the horizontal pointing base (12). The output shaft of the variable speed motor (21) passes through the horizontal pointing base (12) and is fixedly connected to the compartment plate (2). A locking and releasing mechanism for locking and releasing the reflective surface assembly is provided on the support base (1).

2. The high-frequency, highly integrated spaceborne transmitting antenna according to claim 1, characterized in that: The reflector assembly includes a main reflector (241) disposed on the cabin plate (2) and a feed assembly (242) disposed within the main reflector (241). A support base (243) is disposed on the feed assembly (242), and a secondary reflector (245) is disposed at the top of the support base (243).

3. The high-frequency, highly integrated spaceborne transmitting antenna according to claim 2, characterized in that: The bottom surface of the support base (243) is provided with a through hole (244). The support base (243) is sleeved on the outer peripheral surface of the feed assembly (242) through the through hole (244). The inner wall of the through hole (244) is threadedly connected to the outer peripheral surface of the feed assembly (242).

4. The high-frequency, highly integrated spaceborne transmitting antenna according to claim 1, characterized in that: The locking and releasing mechanism includes two shape memory alloy expansion joints (22) disposed on the top surface of the support base (1). Two fixing holes (23) are opened at the end of the top surface of the compartment plate (2) away from the horizontal pointing base (12). The two fixing holes (23) correspond to the two shape memory alloy expansion joints (22). The expansion rod at the top of the shape memory alloy expansion joint (22) is inserted into the fixing hole (23).

5. The high-frequency, highly integrated spaceborne transmitting antenna according to claim 1, characterized in that: A rotating joint (3) is provided below the cabin plate (2). The rotating joint (3) is coaxially arranged with the output shaft of the variable speed motor (21). A connecting plate (31) is fixed on both sides of the rotating joint (3). The top surface of the connecting plate (31) is fixed to the bottom surface of the cabin plate (2) by bolts. Waveguide component (32) is rotatably connected to both ends of the rotating joint (3). A mounting plate (33) is fixed on the side of the horizontally pointing base (12). A rotating joint (34) is provided on the side of the mounting plate (33) away from the support base (1). The rotating joint (34) is coaxially arranged with the variable speed motor (13). The ends of the two waveguide components (32) away from the rotating joint (3) are rotatably installed on both ends of the rotating joint (34).

6. The high-frequency, highly integrated spaceborne transmitting antenna according to claim 5, characterized in that: Waveguide component 2 (42) is rotatably mounted at both ends of the second rotating joint (34). A three-way tool (4) is fixed on the side of the pitch pointing base (11). The ends of the two waveguide components 2 (42) away from the second rotating joint (34) are connected to the three-way tool (4).

7. A high-frequency, highly integrated spaceborne transmitting antenna according to claim 5, characterized in that: The side of the horizontal pointing base (12) is fixed with a positioning plate (35) with two openings on the top surface. The two waveguide components (32) pass through the two openings on the positioning plate (35) respectively. The two waveguide components (32) are fitted with a limiting plate (36). The limiting plate (36) and the positioning plate (35) are fixedly connected by bolts.

8. A high-frequency, highly integrated spaceborne transmitting antenna according to claim 6, characterized in that: The pitch pointing base (11) has a positioning plate (43) with two openings on its side. Two waveguide components (42) pass through the two openings respectively. A limiting plate (44) is clamped on the two waveguide components (42). The limiting plate (44) is fixedly connected to the positioning plate (43) by bolts.

9. A high-frequency, highly integrated spaceborne transmitting antenna according to claim 1, characterized in that: A connector assembly (41) is provided on the side of the pitch pointing base (11).

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