Offset rotary reflecting surface inter-satellite communication antenna

Abstract

A center shaft of a feed source and an X-axis stator of a base are coaxial and jointly fixed on an X-axis base, an X-axis drives an auxiliary reflector, a Y-axis and a main reflector to rotate jointly, the Y-axis drives the main reflector to rotate relative to the auxiliary reflector, microwave signals are emitted from the feed source and reflected to the main reflector through the auxiliary reflector with an included angle of 45 degrees, and the microwave signals are reflected to the main reflector through the auxiliary reflector with the included angle of 45 degrees. The first reflection microwave direction rotates along with the X axis, and the second reflection microwave direction rotates along with the Y axis; the microwave signal receiving process is opposite; when the antenna is launched, the antenna is folded, and the Y-axis driving shaft and the main reverse fixed assembly rotate reversely together, and are pressed on a satellite deck by a pressing point. A plurality of rotating joints and connecting waveguides of a two-dimensional mechanism are omitted, feed line loss is greatly reduced, efficiency is improved by more than 30% under the same caliber, weight is reduced by more than 40%, control over main and auxiliary reverse installation precision of the mechanism is greatly simplified, and the mechanical environment of a satellite launching section can be met.

Description

Technical Field

[0001] This utility model relates to the field of antenna technology, specifically to an inter-satellite communication antenna with a biased rotating reflector. Background Technology

[0002] Against the backdrop of the rapid development of the satellite industry, various inter-satellite communication needs are becoming more diversified, lightweight, miniaturized, and requiring higher bandwidth and communication efficiency. In order to meet the requirements of high gain, small size and light weight for inter-satellite communication of a certain network of satellites, the original configuration of the commonly used satellite-borne Ka-band feed sub-anti-main anti-reflection integrated fixed antenna + XY type mechanism cannot meet the small size layout and weight requirements of this small and medium-sized satellite.

[0003] To solve this problem, it is necessary to design a higher frequency inter-satellite communication antenna that is lightweight, small in size, has high installation accuracy, good mechanical adaptability, and high efficiency. Summary of the Invention

[0004] This invention addresses the problems of large size, heavy weight, low efficiency, and poor adaptability to spaceborne mechanical environments associated with existing antenna designs. It provides an offset rotating reflector inter-satellite communication antenna where the secondary reflector can rotate along the X-axis and the primary reflector can rotate along the Y-axis to control beam pointing. This invention eliminates the need for waveguide feeders through a new antenna configuration, reducing installation size requirements. It also solves the problems of high installation accuracy requirements and the need to meet the mechanical environment characteristics of the transmitting segment.

[0005] This utility model provides an offset rotating reflector inter-satellite communication antenna, including an X-axis assembly, a feed connected to the upper part of the X-axis assembly with its central axis coaxial with the stator of the X-axis assembly, a secondary reflector connected to the output axis of the X-axis assembly, a connecting rod connected to the secondary reflector, a main reflector, and a Y-axis output axis fixedly connected to the main reflector.

[0006] The X-axis assembly includes an X-axis base body, a first X-axis bracket and a second X-axis bracket vertically connected to both ends of the X-axis base body, an X-axis stator and an X-axis output shaft vertically connected to one end of the second X-axis bracket, a feed source vertically connected to the top of the first X-axis bracket with its central axis coaxial with the X-axis stator, and a secondary reflector shaft connected to the X-axis output shaft.

[0007] The angle between the secondary reflector and the feed axis is 45°, the mirror reflection direction is directly opposite the center of the primary reflector, and the beam direction coincides with the Y-axis output axis.

[0008] In the preferred embodiment of the biased rotating reflector inter-satellite communication antenna described in this invention, the X-axis output axis is perpendicular to the Y-axis output axis.

[0009] In a preferred embodiment of the offset rotating reflector inter-satellite communication antenna of the present invention, the X-axis base body, the first X-axis bracket, and the second X-axis bracket are all frame structures, and reinforcing ribs are provided between the X-axis base body and the first X-axis bracket, and between the X-axis base body and the second X-axis bracket.

[0010] The biased rotating reflector inter-satellite communication antenna of this utility model, as a preferred embodiment, further includes a pyrotechnic clamping point located on one side of the Y-axis output shaft and a clamping point connector connected to the side of the Y-axis output shaft. The pyrotechnic clamping point includes a protruding clamping rod and its bottom is connected to the satellite module. The clamping point connector is a hollow frame structure.

[0011] In a preferred embodiment of the biased rotating reflector inter-satellite communication antenna of this invention, the drive assembly of the main reflector and the Y-axis output axis is connected to the Y-axis frame, and the clamping point connector is connected to one side of the Y-axis frame.

[0012] The present invention discloses an inter-satellite communication antenna with a biased rotating reflector, wherein, as a preferred embodiment, the main reflector has a parabolic structure.

[0013] In the preferred embodiment of the biased rotating reflector inter-satellite communication antenna described in this invention, the main reflector center coincides with the axis of the Y-axis output axis.

[0014] In a preferred embodiment of the offset rotating reflector inter-satellite communication antenna described in this utility model, the angle between the main reflector mounting surface and the Y-axis output axis is 45° so that the direction of the reflected beam is 90° with the incident direction of the secondary reflector.

[0015] In a preferred embodiment of the biased rotating reflector inter-satellite communication antenna described in this invention, the rotation of the X-axis is driven by a drive assembly consisting of a motor and a reducer after being powered on.

[0016] In a preferred embodiment of the offset rotating reflector inter-satellite communication antenna described in this utility model, the rotation of the Y-axis output shaft is driven by a drive assembly consisting of a motor and a reducer after being powered on.

[0017] This utility model is applicable to microwave antennas with two-dimensional pointing function in various frequency bands, especially near-optical high-frequency bands.

[0018] This invention provides an inter-satellite communication antenna with a biased rotating reflector. Based on quasi-optical principles, it uses a rotating mechanism to drive the main and secondary reflectors to rotate in opposite directions, thereby achieving two-dimensional pointing functionality for a high-frequency microwave antenna and enabling inter-satellite communication. To meet high-precision pointing requirements, the antenna's feed center axis is coaxial with the base's X-axis stator and fixed together on the X-axis base. The X-axis drives the secondary reflector, Y-axis, and main reflector to rotate together. The Y-axis drives the main reflector to rotate relative to the secondary reflector. Microwave signals are emitted from the feed, reflected by the secondary reflector at a 45° angle to the main reflector, and then reflected by the main reflector's 45° parabolic surface towards another communication satellite antenna. The direction of the first reflected microwave rotates with the X-axis, and the direction of the second reflected microwave rotates with the Y-axis; the process of receiving microwave signals is the opposite. To adapt to the mechanical environment of the satellite transmission phase, the antenna is retracted, and the Y-axis drive shaft is fixedly assembled with the main reflector and rotated in opposite directions, secured to the satellite module with a clamping point. This antenna configuration eliminates the need for multiple rotating joints and connecting waveguides in a two-dimensional mechanism, significantly reducing feeder loss. It increases efficiency by more than 30% and reduces weight by more than 40% for the same aperture. It greatly simplifies the control of the main and auxiliary reverse installation accuracy, meets the mechanical environment requirements of satellite launch, and significantly reduces costs, making it widely applicable.

[0019] This utility model has the following advantages:

[0020] (1) The antenna involved in this utility model is a biased rotating reflector, which is different from traditional antennas. The central axis of the antenna feed is coaxial with the X-axis stator of the base. The antenna feed and the X-axis are fixed on the same base. The X-axis drives the sub-reflector, the Y-axis and the main reflector to rotate together. The Y-axis drives the main reflector to rotate relative to the sub-reflector. When transmitting microwave signals, the microwave signals are emitted from the feed and reflected by the sub-reflector at a 45° angle to the main reflector. Then, the main reflector is reflected by a 45° plane-like reflection to another satellite communication antenna. This utility model eliminates the rotating joint and waveguide feed line of the rotating shaft used in traditional antennas, making the structure very simple and saving about 40% of the weight.

[0021] (2) In this utility model, since the rotating joint and waveguide feed line are eliminated, the losses caused by the rotating joint and waveguide feed line of the original traditional antenna are also eliminated, and the overall antenna transmission efficiency is improved by 30%.

[0022] (3) This utility model integrates the mechanism X-axis with the feed source, which is more beneficial to the pointing accuracy guarantee compared with traditional antennas and other biased rotating antennas;

[0023] (4) Due to the structural design of this utility model, the X-axis is coaxial with the feed horn axis, the Y-axis is perpendicular to the X-axis, and the main and secondary reflectors are installed at 45 degrees, so that the direction of the reflected beam changes by 90° each time. The beam pointing is linearly equal to the rotation angle and rotation speed of the mechanism shaft. This is conducive to engineering implementation and tracking control. It can be used in the same way as other traditional solid surface antenna control methods, which can greatly simplify the control algorithm.

[0024] (5) This utility model has a clever configuration that allows the drive assembly and antenna to be fixedly installed and drive the rotating shaft in the opposite direction at the position of the output shaft. In the rocket launch section, the antenna can be retracted by using only one clamping point to clamp the drive assembly and the stator Y-axis frame near the center of mass of the antenna to achieve good mechanical adaptation conditions.

[0025] (6) The inter-satellite communication antenna with offset rotating reflector described in this utility model is the first of its kind in actual spaceborne system engineering applications and is the first of its kind in China. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of an inter-satellite communication antenna structure with a biased rotating reflector.

[0027] Figure 2 This is a schematic diagram of the compressed state of an inter-satellite communication antenna with a biased rotating reflector.

[0028] Figure label:

[0029] 1. X-axis assembly; 11. X-axis base body; 12. First X-axis bracket; 13. Second X-axis bracket; 14. X-axis stator; 15. X-axis output shaft; 2. Feed source; 3. Secondary reflector; 4. Connecting rod; 5. Main reflector; 6. Y-axis output shaft; 7. Beam; 8. Pyrotechnic clamping point; 9. Clamping point connector; 10. Y-axis frame. Detailed Implementation

[0030] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0031] Example 1

[0032] like Figure 1 As shown, an inter-satellite communication antenna with a biased rotating reflector includes an X-axis assembly 1, a feed 2 connected to the upper part of the X-axis assembly 1 and whose central axis is coaxial with the stator of the X-axis assembly 1, a secondary reflector 3 connected to the output axis of the X-axis assembly 1, a connecting rod 4, a main reflector 5 and a Y-axis output axis 6 fixedly connected to the secondary reflector 3 in sequence.

[0033] X-axis assembly 1 includes an X-axis base body 11, a first X-axis bracket 12 and a second X-axis bracket 13 vertically connected to both ends of the X-axis base body 11, an X-axis stator 14 vertically connected to one end of the second X-axis bracket 13, and an X-axis output shaft 15. The feed source 2 is vertically connected to the top of the first X-axis bracket 12 and its central axis is coaxial with the X-axis stator 14. The secondary reflector 3 is axially connected to the X-axis output shaft 15.

[0034] The angle between the axis of the secondary reflector 3 and the axis of the feed 2 is 45°, the direction of the mirror reflection is directly opposite the center of the main reflector 3, and the direction of the beam 7 coincides with the axis of the Y-axis output axis 6.

[0035] X-axis output axis 15 is perpendicular to Y-axis output axis 6;

[0036] The X-axis base body 11, the first X-axis bracket 12, and the second X-axis bracket 13 are all frame structures, and reinforcing ribs are provided between the X-axis base body 11 and the first X-axis bracket 12, and between the X-axis base body 11 and the second X-axis bracket 13.

[0037] In this embodiment, the central axis of the antenna feed 2 is coaxial with the X-axis stator 14 of the base and is fixed together on the X-axis base 11. The coaxiality of the feed 2 and the X-axis stator 14 is ensured by the X-axis base 22. The X-axis 15 drives the sub-reflector 3, the Y-axis 6, and the main reflector 5 to rotate together. The Y-axis 6 drive shaft is fixedly assembled with the main reflector 5, causing the main reflector 5 to rotate relative to the sub-reflector 3. When transmitting microwave signals, the microwave signal 7 is emitted from the feed, reflected by the sub-reflector 3 at a 45° angle to the main reflector 5, and then reflected by the main reflector 5 at a 45° plane-like angle to another satellite communication antenna. The direction of the first reflected microwave rotates with the X-axis 15, and the direction of the second reflected microwave rotates with the Y-axis 6; the process of receiving microwave signals is the opposite. During retraction, in order to adapt to the mechanical environment of the transmitting section, the Y-axis 6 drive shaft is fixedly assembled with the main reflector 5 and rotates in opposite directions and is pressed against the satellite compartment plate by a pyrotechnic clamping point 8.

[0038] The sub-reflector 3 is at a 45° angle to the axis of the feed source 2, and the mirror reflection direction is directly opposite the center of the main reflector 5. The beam direction 7 is designed to coincide with the Y-axis 6.

[0039] The main reflector 5 is a parabolic surface, specifically a truncated version of the parabolic surface. This offset parabolic surface avoids obstruction of the main surface by the secondary surface and by the feed and its support, thereby improving the paraxial sidelobe characteristics of the secondary radiation pattern and the input voltage VSWR characteristics of the feed, thus increasing the feed radiation efficiency and antenna gain. Furthermore, the center of the main reflector 5 coincides with the Y-axis 6, and the main reflector 5 is installed at a 45° angle to the Y-axis 6, ensuring that the reflected beam 7 forms a 90° angle with the incident direction of the secondary reflector.

[0040] The rotation of X-axis 15 and Y-axis 6 is driven by a drive assembly consisting of a motor and a reducer after being powered on. The specific rotation angle and speed are controlled by the relevant single unit inside the cabin.

[0041] like Figure 2 As shown, the auxiliary reflector 3, connecting rod 4, main reflector 5, X-axis rotor 15, Y-axis 6, etc. are pressed together by the clamping seat 9 in the launch section. After entering orbit, they are unlocked and deployed, and receive the whole satellite command to drive the X-axis 15 and Y-axis 6 to rotate for pointing, tracking and communication.

[0042] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. An inter-satellite communication antenna with a biased rotating reflector, characterized in that: It includes an X-axis assembly (1), a feed source (2) connected to the upper part of the X-axis assembly (1) and whose central axis is coaxial with the stator of the X-axis assembly (1), a secondary reflector (3) connected to the output shaft of the X-axis assembly (1), a connecting rod (4), a main reflector (5) connected to the secondary reflector (3) in sequence, and a Y-axis output shaft (6) fixedly connected to the main reflector (5); The X-axis assembly (1) includes an X-axis base body (11), a first X-axis bracket (12) and a second X-axis bracket (13) vertically connected to both ends of the X-axis base body (11), an X-axis stator (14) vertically connected to one end of the second X-axis bracket (13), and an X-axis output shaft (15). The feed source (2) is vertically connected to the top of the first X-axis bracket (12) and its central axis is coaxial with the X-axis stator (14). The secondary reflector (3) is axially connected to the X-axis output shaft (15). The sub-reflector (3) has an angle of 45° with the axis of the feed source (2), the mirror reflection direction is directly opposite the center of the main reflector (5), and the direction of the beam (7) coincides with the axis of the Y-axis output axis (6).

2. The biased rotating reflector inter-satellite communication antenna according to claim 1, characterized in that: The X-axis output axis (15) is perpendicular to the Y-axis output axis (6).

3. The biased rotating reflector inter-satellite communication antenna according to claim 1, characterized in that: The X-axis base body (11), the first X-axis bracket (12) and the second X-axis bracket (13) are all frame structures, and reinforcing ribs are provided between the X-axis base body (11) and the first X-axis bracket (12) and between the X-axis base body (11) and the second X-axis bracket (13).

4. The biased rotating reflector inter-satellite communication antenna according to claim 1, characterized in that: It also includes a pyrotechnic clamping point (8) located on one side of the Y-axis output shaft (6) and a clamping point connector (9) connected to the side of the Y-axis output shaft (6). The pyrotechnic clamping point (8) includes a protruding clamping rod and is connected to the bottom of the satellite compartment plate. The clamping point connector (9) is a hollow frame structure.

5. The biased rotating reflector inter-satellite communication antenna according to claim 4, characterized in that: The drive assembly of the main reverse (5) and the Y-axis output shaft (6) is connected to the Y-axis frame (10), and the clamping point connector (9) is connected to one side of the Y-axis frame (10).

6. The biased rotating reflector inter-satellite communication antenna according to claim 1, characterized in that: The main inverted surface (5) is a parabolic structure.

7. The biased rotating reflector inter-satellite communication antenna according to claim 1, characterized in that: The center of the main reflector (5) coincides with the axis of the Y-axis output shaft (6).

8. The biased rotating reflector inter-satellite communication antenna according to claim 6, characterized in that: The angle between the mounting surface of the main reflector (5) and the Y-axis output shaft (6) is 45° so that the direction of the reflected beam (7) is 90° with the incident direction of the secondary reflector (3).

9. The biased rotating reflector inter-satellite communication antenna according to claim 1, characterized in that: The rotation of the X-axis output shaft (15) is driven by a drive assembly consisting of a motor and a reducer after being powered on.

10. An inter-satellite communication antenna with a biased rotating reflector according to claim 1, characterized in that: The rotation of the Y-axis output shaft (6) is driven by a drive assembly consisting of a motor and a reducer after being powered on.

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