High-integration satellite-borne reflector antenna

Abstract

The utility model discloses a high-integration satellite-borne reflector antenna, which comprises a base, a locking and releasing mechanism, a waveguide assembly, a reflector assembly, a connector assembly, a group of rotary joints and a group of pointing mechanisms, the locking and releasing mechanism further comprises a cabin plate mounting surface and an antenna mounting surface, the base and the cabin plate mounting surface of the locking and releasing mechanism are arranged on a satellite cabin plate or an antenna mounting bracket, and the antenna mounting surface is arranged on the back of the reflecting surface assembly; according to the scheme, through the design of the integrated double-shaft mechanism and the unfolding arm, the structure is simplified, and the weight is reduced; through a single-point locking system, the number of locking and releasing devices is reduced, and the unlocking reliability is improved; through the integrated auxiliary reflecting surface and support structure, the assembly error is eliminated, the pointing precision is improved, and the assembly efficiency is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of satellite-borne antennas, and in particular to a highly integrated satellite-borne reflector antenna. Background Art

[0002] In the field of satellite-borne antennas, traditional dual-axis pointing mechanisms generally adopt a separate design with independent deployment arms and multiple locking mechanisms, resulting in high structural complexity and significant weight redundancy. For example, Chinese patent CN117374556A, "A Flat Two-Dimensional Pointing Deployable Dual-Axis Antenna with a Rigid Thermal Control Cover," uses a four-locking point design. While this meets structural rigidity requirements, the large number of locking and release mechanisms (four) results in a weight increase of over 400g. Furthermore, assembly errors between the secondary reflector and the secondary reflector bracket significantly increase the pointing angle between the antenna's electrical and mechanical axes. Traditional solutions rely on high-precision machining and complex assembly processes to reduce this angle, thereby reducing antenna assembly and production efficiency and hindering the high-volume, low-cost production of low-Earth orbit constellation antennas in the commercial aerospace sector. Utility Model Content

[0003] In response to the above technical problems, the utility model provides a highly integrated satellite-borne reflector antenna, which is suitable for satellite communication systems with strict requirements on light weight, high-precision pointing and high reliability.

[0004] The utility model is realized by adopting the following technical solutions:

[0005] A highly integrated satellite-borne reflector antenna comprises a base, a locking and releasing mechanism, a waveguide assembly, a reflector assembly, a connector assembly, a set of rotating joints, and a set of pointing mechanisms. The locking and releasing mechanism also includes a cabin mounting surface and an antenna mounting surface. The cabin mounting surfaces of the base and the locking and releasing mechanism are arranged on the satellite cabin or the antenna mounting bracket, and the antenna mounting surface is arranged on the back of the reflector assembly.

[0006] Specifically, the pointing mechanism is an XY type dual-axis pointing mechanism, including a Y-axis pointing mechanism and an X-axis pointing mechanism. The Y-axis pointing mechanism is connected to the base, and the reflective surface assembly is mounted on the X-axis pointing mechanism, and the antenna mounting surface on the back of the reflective surface assembly is fixed.

[0007] Specifically, the Y-axis pointing mechanism integrates the mechanical rotation and deployment actions of the antenna and is provided with a rotation unit for driving;

[0008] Among them, the Y-axis pointing mechanism and the X-axis pointing mechanism are connected through the locking and releasing device cabin panel locking point and the antenna locking point to maintain the folded and locked state; after entering orbit, the locking and releasing device is disconnected by the integrated electronic control, the Y-axis pointing mechanism rotates to the predetermined angle, and the antenna is unfolded; then the Y-axis pointing mechanism and the X-axis pointing mechanism receive the rotation command and start working.

[0009] Specifically, the rotating unit includes a motor, a harmonic reducer and a rotary transformer.

[0010] Specifically, the rotation joint includes a Y-axis rotation joint and an X-axis rotation joint.

[0011] Specifically, the locking and releasing mechanism is locked with a single point on the back of the reflector assembly, and the locking point is located on the back of the antenna reflector assembly and the X-axis pointing mechanism structure; the locking and releasing mechanism also includes a memory alloy expander, a slotted bolt and a separation spring;

[0012] Among them, the antenna is locked by a single locking and releasing device during the launch phase. After entering orbit, the memory alloy expander is powered, the slotted bolts are disconnected, and the antenna is separated from the locking point under the action of the breaking impact force and the separation spring, and the rotating mechanism drives the antenna to unfold.

[0013] Specifically, the reflector assembly includes a main reflector, a sub-reflector assembly and a feed assembly. The sub-reflector assembly includes a sub-reflector, a sub-reflector bracket and a bracket base. The sub-reflector bracket adopts a four-support arm form and is integrated with the sub-reflector and the bracket base.

[0014] The beneficial effects of the present invention are as follows: the present invention proposes a highly integrated satellite-borne reflector antenna, which simplifies the structure and reduces the weight through an integrated dual-axis mechanism and deployment arm design; reduces the number of locking and releasing devices and improves the unlocking reliability through a single-point locking system; eliminates assembly errors, improves pointing accuracy, and improves assembly efficiency through an integrated sub-reflector and bracket structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0016] Figure 1 This is a schematic diagram of the overall structure of the antenna in the embodiment of the present utility model in the unfolded state;

[0017] Figure 2 A three-dimensional diagram of a single-point locking and releasing device in an embodiment of the present utility model;

[0018] Figure 3 This is a schematic diagram of the integrated secondary reflector and bracket structure in an embodiment of the present utility model;

[0019] Figure 4This is a schematic diagram of a locked state of the overall structure of a QV feeding antenna in an embodiment of the present utility model;

[0020] Among them, 1-base, 2-locking and releasing mechanism, 3-waveguide assembly, 4-Y-axis pointing mechanism, 5-Y-axis rotation joint, 6-X-axis pointing mechanism, 7-X-axis rotation joint, 8-reflecting surface assembly, 9-connector assembly;

[0021] 201-cabin mounting surface, 202-antenna mounting surface, 203-cabin locking point, 204-antenna locking point;

[0022] 801-main reflector, 802-secondary reflector assembly, 803-feed assembly. DETAILED DESCRIPTION

[0023] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0024] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0025] The following is combined with Figures 1 to 4 , some embodiments of the present invention are described in detail. In the absence of conflict, the following embodiments and features in the embodiments can be combined with each other.

[0026] This utility model proposes a highly integrated satellite-borne reflector antenna, such as Figure 1 As shown, the antenna comprises a base 1, a locking and release mechanism 2, a waveguide assembly 3, a Y-axis pointing mechanism 4, a Y-axis rotation joint 5, an X-axis pointing mechanism 6, an X-axis rotation joint 7, a reflector assembly 8, and a connector assembly 9. The base 1 and the locking and release mechanism panel mounting surface 201 are located on the satellite panel or antenna mounting bracket; the Y-axis pointing mechanism 4 is connected to the base 1; the reflector assembly 8 is mounted on the X-axis pointing mechanism 6; and the locking and release mechanism antenna mounting surface 202 is located on the back of the reflector assembly 8 and fixed to the X-axis pointing mechanism 6.

[0027] In a preferred embodiment, the antenna utilizes an XY dual-axis pointing mechanism, with the Y-axis pointing mechanism also serving as the satellite antenna's deployment arm, integrating the antenna's mechanical rotation and deployment. The pointing mechanism is driven by a rotation unit comprised of a motor, a harmonic reducer, and a resolver. During satellite launch, the Y-axis pointing mechanism and the X-axis pointing mechanism are connected via the locking and releasing mechanism's cabin locking point 203 and the antenna locking point 204, maintaining a folded and locked state. Upon orbital entry, the locking and releasing mechanism is disconnected by integrated electronic control, allowing the Y-axis pointing mechanism to rotate to a predetermined angle and deploy the antenna. Subsequently, the Y-axis and X-axis pointing mechanisms receive rotation commands and begin operation.

[0028] This design can save the antenna from a set of pointing mechanisms including a rotating unit and a deployment arm. Taking a certain QV-band satellite-borne reflector antenna as an example, this design can reduce the weight of the entire device by 1000~1200g.

[0029] In a preferred embodiment, the antenna adopts a single-point locking design on the back of the reflector assembly, such as Figure 2 As shown, a single locking and release mechanism achieves high-frequency locking of the reflector and pointing mechanism. The core component of the locking and release mechanism is a memory alloy expander. The antenna is locked during launch using a single locking and release mechanism. After orbital entry, the memory alloy expander is powered, disconnecting the slotted bolts. The antenna then separates from the locking point due to the breaking force and the release spring, allowing the rotating mechanism to deploy the antenna.

[0030] Compared with the multi-locking mechanism solution, each reduction in a locking release mechanism can reduce the weight of the entire antenna by more than 150g, while also reducing the risk of unlocking failure.

[0031] like Figure 3 As shown, the antenna reflector assembly 8 consists of a main reflector 801, a sub-reflector assembly 802, and a feed assembly 803. In the present invention, the antenna sub-reflector assembly adopts an integrated design and processing solution, integrating the sub-reflector, sub-reflector bracket, and bracket base structures of a traditional antenna. This reduces component weight by removing non-load-bearing materials. Furthermore, by eliminating the assembly relationship between the back surface of the sub-reflector and the sub-reflector bracket, the non-electrical performance structure of the sub-reflector is simplified, reducing the overall size and height of the antenna.

[0032] Taking a QV band antenna as an example, this design reduces the sub-reflector assembly's weight by over 80g and its profile height by over 10mm. Furthermore, through integrated processing, assembly errors within the antenna's sub-reflector assembly are eliminated, reducing the angle between the antenna's electrical and mechanical axes by over 0.02°, thereby improving antenna pointing accuracy.

[0033] The present invention will be further described below in conjunction with the embodiments.

[0034] Taking a QV frequency band feed antenna as an example, the antenna adopts the following design scheme.

[0035] The antenna adopts XY dual-axis pointing mechanism, such as Figure 4 As shown, the antenna base and locking and release mechanism are mounted on the satellite antenna mounting bracket. The Y-axis pointing mechanism is fixed to the base, providing the antenna locking and deployment functions and 0-240° rotation. The X-axis pointing mechanism connects the antenna reflector assembly and the Y-axis pointing mechanism, providing -60° to +60° rotation. The antenna uses a dual-path BJ400 waveguide for signal transmission and reception. The X-axis and Y-axis rotating joints, combined with the two rotating mechanisms, provide electrical connections within the antenna's rotation range. The antenna reflector assembly uses a forward-fed dual reflector configuration, with a main reflector diameter of 400mm and an operating frequency range of 37.5 to 50 GHz.

[0036] The antenna adopts a single locking and releasing mechanism scheme, in which the locking point is located on the back of the antenna reflector assembly and the X-axis pointing mechanism structure. When the Y-axis pointing unit is folded, it plays the role of Y-axis compression and X-axis fixing. Figure 4 The antenna's locking and release mechanism weighs approximately 150g, which is 450-600g lighter than similar antennas with three or four locking and release mechanisms, and reduces the risk of unlocking failure.

[0037] The antenna's sub-reflector assembly features a four-arm sub-reflector bracket integrated with the sub-reflector and bracket base. This eliminates the traditional connection structure between the sub-reflector, bracket, and base, reducing assembly weight. The sub-reflector assembly is machined using a five-axis machine tool, weighing only 82g. This design increases the sub-reflector assembly's local first-order mode to 320Hz, improving the antenna's mechanical adaptability.

[0038] Based on the above design, the performance test results of a QV feed antenna are as follows: the QV band antenna weighs approximately 4.5 kg, a 27.8% reduction compared to the traditional solution's 6.3 kg. The antenna's Y-axis rotation range is ≥240°, and its X-axis rotation range is ≥120°. The antenna's gain at 37.5 GHz is ≥40 dBi, the sidelobe level is ≤-15 dB, and the angle between the antenna's electrical and mechanical axes is ≤0.03°.

[0039] For the sake of simplicity, the aforementioned embodiments are described as a series of actions. However, those skilled in the art should be aware that this application is not limited by the order of the actions described, because according to this application, some steps can be performed in other orders or simultaneously. Secondly, those skilled in the art should also be aware that the embodiments described in this specification are preferred embodiments, and the actions involved are not necessarily required by this application.

[0040] The above embodiments describe the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Without departing from the spirit and scope of the present invention, modifications and variations made by those skilled in the art without departing from the spirit and scope of the present invention should be within the scope of protection of the appended claims.

Claims

1. A highly integrated satellite-borne reflector antenna, characterized in that: The invention comprises a base (1), a locking and releasing mechanism (2), a waveguide assembly (3), a reflecting surface assembly (8), a connector assembly (9), a set of rotating joints and a set of pointing mechanisms; the locking and releasing mechanism (2) further comprises a cabin panel mounting surface (201) and an antenna mounting surface (202); the cabin panel mounting surface (201) of the base (1) and the locking and releasing mechanism (2) is arranged on a satellite cabin panel or an antenna mounting bracket, and the antenna mounting surface (202) is arranged on the back of the reflecting surface assembly (8).

2. The highly integrated satellite-borne reflector antenna according to claim 1, characterized in that: The pointing mechanism is an XY type dual-axis pointing mechanism, comprising a Y-axis pointing mechanism (4) and an X-axis pointing mechanism (6), wherein the Y-axis pointing mechanism (4) is connected to the base (1), and the reflecting surface assembly (8) is mounted on the X-axis pointing mechanism (6), and the antenna mounting surface (202) on the back of the reflecting surface assembly (8) is fixed.

3. The highly integrated satellite-borne reflector antenna according to claim 2, characterized in that: The Y-axis pointing mechanism (4) integrates the mechanical rotation and deployment actions of the antenna and is provided with a rotation unit for driving.

4. The highly integrated satellite-borne reflector antenna according to claim 3, characterized in that: The rotating unit includes a motor, a harmonic reducer and a rotary transformer.

5. The highly integrated satellite-borne reflector antenna according to claim 2, characterized in that: The rotary joint comprises a Y-axis rotary joint (5) and an X-axis rotary joint (7).

6. The highly integrated satellite-borne reflector antenna according to claim 1, characterized in that: The locking and releasing mechanism (2) is locked with the back of the reflecting surface assembly (8) at a single point, and the locking point is located on the back of the reflecting surface assembly (8) and the X-axis pointing mechanism (6) structure; the locking and releasing mechanism (2) also includes a memory alloy expander, a slotted bolt and a separation spring.

7. The highly integrated satellite-borne reflector antenna according to claim 1, characterized in that: The reflector assembly (8) comprises a main reflector (801), a sub-reflector assembly (802) and a feed assembly (803); the sub-reflector assembly (802) comprises a sub-reflector, a sub-reflector bracket and a bracket base; the sub-reflector bracket adopts a four-support arm form and is designed as an integrated whole with the sub-reflector and the bracket base.

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