Off-set feed type double-antenna combined structure configuration with common reference of auxiliary reflector and feed source

Abstract

The invention provides an offset-feed-type double-antenna combined structure configuration with co-reference of an auxiliary reflector and feed sources. The offset-feed-type double-antenna combined structure configuration comprises two main reflecting surfaces, two auxiliary reflecting surfaces, two sets of feed sources, an antenna tower, a base and a waveguide assembly, the two main reflecting surfaces and the antenna tower are arranged on the base in an L shape, the two auxiliary reflecting surfaces, the two sets of feed sources and the waveguide assembly are compactly installed on the antenna tower, and the main reflecting surfaces, the auxiliary reflecting surfaces and the feed sources keep a specified angle direction to achieve antenna ground detection. Factors of limited outer envelope, compact space, weight reduction and the like of a satellite to the ground and double antennas are comprehensively considered, the layout is compact, and installation constraints of various satellite surfaces can be fully adapted; the auxiliary reflecting surface and the feed source share one set of antenna tower, so that the weight and envelope of the system are greatly reduced, the common-reference installation precision is high, and the directional performance of the antenna is ensured; the antenna tower is of a closed structure, provides abundant installation interfaces and good heat dissipation capability for the feed source and the waveguide assembly, and is higher in adaptability.

Description

Technical Field

[0001] This invention belongs to the field of satellite overall design technology, specifically, it relates to an offset-fed dual-antenna combination structure with a common reference for the sub-reflector and the feed source. Background Technology

[0002] With the development of Earth remote sensing technology in fields such as meteorology, environment, and exploration, the demands for satellite missions and functions are increasing, and satellites often need to carry multiple large-sized payloads with different functions and types. However, due to constraints such as limited space for satellite external layout and the large number and types of payloads carried by satellites, the requirements for the configuration and envelope of satellite payloads are becoming increasingly stringent.

[0003] Currently, there are various types of large-size reflector antennas carried on satellites, including prime-fed and offset-fed types. A single satellite typically carries multiple large-size antennas, each belonging to different subsystems and development units. Each antenna is designed independently, placing demands on various resources such as the satellite's weight, space, thermal control, and accuracy. This results in redundancy and waste of resources, preventing the optimization of the overall satellite design and the maximization of resource utilization. Therefore, the integrated and optimized design of multiple large-size antennas is essential.

[0004] A search of existing technologies revealed numerous patents related to satellite configurations, most of which focused on satellite configurations carrying a specific payload. Patents specifically addressing satellite payload antenna configurations are scarce, particularly those related to dual-antenna configurations. The following section lists only a few patents related to satellite configurations with reflector antennas.

[0005] Chinese invention patent CN105501471A, entitled "Satellite Configuration for Mounting a Large Deployable Antenna with Dual Reflectors," provides a satellite configuration for mounting a large deployable antenna with dual reflectors. By ensuring the relative positional relationship between the feed array, main reflector, and sub-reflector during on-orbit flight, and under the constraints of satisfying the launch vehicle fairing envelope and the correct deployment of the large deployable antenna, a truss-structured payload bay is designed with reasonable layout and placement. The main force transmission path design is optimized, ensuring a compact and rational structural space for the large deployable antenna in its folded state, while simultaneously meeting the deployment path requirements. The dual reflector antenna involved in this invention is a large deployable mesh structure antenna that can be folded into a smaller size to adapt to the transmission envelope during transmission. In contrast, the dual reflector antenna involved in this invention is an offset-fed solid-surface antenna with a size of 1.25m, which does not require folding or folding. The two configurations are fundamentally different.

[0006] Chinese invention patent CN107482305A, entitled "Method for Configuration of Remote Sensing Satellite Relay Antenna Adapted to Dual-Looking Operation," provides a method for configuring a remote sensing satellite relay antenna adapted to dual-looking operation. The method includes the following steps: Step 1, the relay antenna is folded to the side of the satellite during transmission and unfolds towards the satellite surface after entering orbit; Step 2, after unfolding, the hinge at the root of the relay antenna locks the unfolding arm at a certain angle to the OXZ plane of the satellite. This invention involves a single relay antenna configuration and uses an unfolding arm for folding and unfolding, while this invention relates to a dual-emitting-surface antenna configuration, where the antenna does not require unfolding and folding. The two configurations are fundamentally different.

[0007] Chinese invention patent CN111891388B, entitled "Compact Satellite Configuration Applicable to Multi-Band Detection Payloads," provides a compact satellite configuration suitable for multi-band detection payloads. The configuration includes a satellite body, a dual-wing solar cell assembly, a relay antenna, a multi-band detection payload antenna assembly, a communication payload assembly, a data transmission antenna assembly, a telemetry and control antenna, and a thruster. The left and right wing solar cell arrays of the dual-wing solar cell assembly are respectively mounted on the left and right sides of the satellite body. The relay antenna and the multi-band detection payload antenna assembly are respectively mounted on the back and front of the satellite body. The communication payload assembly and the thruster are both mounted on the satellite body. The left and right data transmission antennas of the data transmission antenna assembly are respectively mounted on the left and right sides of the satellite body. The telemetry and control antenna is mounted on the front and / or back of the satellite body. This invention is a satellite configuration for multi-band detection payloads, incorporating small-sized antennas across multiple frequency bands. In contrast, this invention relates to a large-sized dual-antenna combination configuration with a shared reference for the sub-reflector and feed. The two are fundamentally different in their applicable objects and configurations.

[0008] Chinese invention patent CN109927938B, entitled "Geostationary Orbit Solid Aperture Microwave Sounding Satellite Configuration," relates to a geostationary orbit solid aperture microwave sounding satellite configuration in the field of satellite overall technology. The configuration includes a satellite platform, a microwave sounder, a microwave sounder quasi-optical system, a locking / releasing device, solar panels, a data transmission antenna, and a light-blocking mechanism. The primary and secondary reflective surfaces of the microwave sounder are pressed against the satellite platform; after separation from the launch vehicle, the primary and secondary reflective surfaces are unlocked and deployed into position. The microwave sounder quasi-optical system is installed and embedded in the satellite platform via a micro-deformation frame. The solar panels are mounted on the heat dissipation surface of the satellite platform. The data transmission antenna is mounted on the top of the satellite platform via a bracket. The satellite platform and the microwave sounder are inclined, meaning there is an angle between the Earth observation axis and the satellite's Z-axis (i.e., +Z ground). After on-orbit positioning, the over-constraint connection between the microwave sounder and the satellite platform is unlocked, and the light-blocking mechanism is deployed. This invention is aimed at satellite configurations equipped with a single microwave detector antenna, while this invention relates to a large-size dual-antenna combination configuration with a common reference for the sub-reflector and feed. The two have fundamentally different applications and configurations.

[0009] Chinese invention patent CN110329542B, entitled "Satellite Configuration Applicable to Cooperative Control of Ultra-Large Flexible Satellites," provides a satellite configuration suitable for cooperative control of ultra-large flexible satellites in the field of aerospace satellites. The configuration includes: a satellite body, a flexible antenna, a cooperative control mechanism, and a solar array. The satellite body comprises a sealed cabin consisting of a base plate, a middle plate, a top plate, a partition plate, and side plates. The flexible antenna includes antenna elements, an antenna folding and unfolding mechanism, a piezoelectric stack actuator, and an antenna mounting base, with the piezoelectric stack actuator connected to the antenna elements. The cooperative control mechanism includes a body-end stator and a confined-space two-dimensional rotor, which are respectively mounted on the base plate and the antenna mounting base. The solar array includes a connecting frame, a battery array substrate, and a solar cell array. The solar cells are arrayed and mounted on the battery array substrate, which is disposed on the connecting frame, which is connected to the side plates. This invention is aimed at satellite configurations equipped with a single large-size mesh flexible antenna, while the present invention relates to a large-size dual-antenna combination configuration with a common reference for the sub-reflector and the feed. The two have fundamentally different applications and configurations.

[0010] The Chinese invention patent with publication number CN107658570A, entitled "A Deployable High-Precision Solid Surface Reflector Antenna," focuses on solving the problem of on-orbit deployment of a single, large-aperture solid surface reflector antenna. Its structure is complex, relying on numerous fan-shaped panels, hinges, tension springs, and support rods to work together to achieve folding and deployment. This results in a heavy system, high reliability risk, and the surface accuracy after deployment is affected by the splicing of multiple panels and the gaps between hinges, making it difficult to guarantee.

[0011] To meet the integration requirements of multiple payloads, large size, and high precision, there is an urgent need for an innovative antenna combination structure to solve the problem of compact and high-precision common reference installation of multiple large-size antennas in a limited space. Summary of the Invention

[0012] To address the shortcomings of existing technologies, the purpose of this invention is to provide a dual-antenna configuration with a common reference for both the secondary reflector and the feed source.

[0013] The offset-fed dual-antenna combination structure configuration with a common reference for the secondary reflector and the feed source provided by the present invention includes: a first main reflector 1, a second main reflector 2, a first secondary reflector 3, a second secondary reflector 4, a first feed source 5, a second feed source 6, an antenna tower 7, a base 8, and a waveguide assembly 9. The first main reflector 1, the second main reflector 2, and the antenna tower 7 are arranged in an L-shape on the base 8; The first sub-reflector 3, the second sub-reflector 4, the first feed 5, the second feed 6, and the waveguide assembly 9 are compactly mounted on the antenna tower 7; The first primary reflector 1, the second primary reflector 2, the first secondary reflector 3, the second secondary reflector 4, the first feed source 5, and the second feed source 6 maintain a specified angular orientation relative to each other to enable the antenna to detect the ground.

[0014] Preferably, the first main reflector 1 and the second main reflector 2 are mounted on the base 8 through a pressing and releasing mechanism and a two-dimensional rotation mechanism. They are in a compressed state during launch and are unlocked and released after launch into orbit.

[0015] Preferably, after the first main reflective surface 1 and the second main reflective surface 2 are unlocked and released, they can rotate in two directions through a two-dimensional rotating mechanism, with a rotation angle range of ±6.5°.

[0016] Preferably, the first main reflector 1, the second main reflector 2, and the antenna tower 7 are arranged in an L-shape on the base 8 and positioned by pin holes to ensure the installation accuracy between the three.

[0017] Preferably, the first sub-reflector 3 and the second sub-reflector 4 are suspended upside down below the mounting plate on the top of the antenna tower 7, and the first sub-reflector 3 and the second sub-reflector 4 are positioned by pin holes to ensure the installation accuracy between the first sub-reflector 3 and the second sub-reflector 4 and the antenna tower 7.

[0018] Preferably, the first feed 5 and the second feed 6 are obliquely nested inside the antenna tower 7 by a bracket, and the feed bracket is positioned by pin holes to ensure the installation accuracy between the first feed 5, the second feed 6 and the antenna tower 7.

[0019] Preferably, the first feed 5 and the second feed 6 support the reception and transmission of electromagnetic waves in the C, Ku, K, Ka and EHF bands. The rear ends of the first feed 5 and the second feed 6 are connected to the transmitter through waveguide components 9 arranged inside the antenna tower 7 to reduce link attenuation. Antenna tower 7 provides sufficient installation space and provides first feed 5 and second feed 6 to support the reception and transmission of electromagnetic waves in multiple frequency bands. First feed 5 and second feed 6 can be connected to the transmitter in the form of waveguide, optical fiber, or radio frequency coaxial cable.

[0020] Preferably, the first primary reflector 1, the second primary reflector 2, the first secondary reflector 3, the second secondary reflector 4, the first feed 5, and the second feed 6 are all equipped with optical precision prisms, and the optical precision measurement results can be used for on-orbit calibration of antenna pointing.

[0021] Preferably, the antenna tower 7 is assembled from 8 honeycomb sandwich panels, which supports quick assembly and disassembly, facilitating the portable installation of feed back-end equipment and waveguide components 9 inside the antenna tower 7. The honeycomb sandwich panels provide a closed space, providing a thermal control environment for the products inside the antenna tower 7.

[0022] Preferably, the outer surfaces of the antenna tower 7 and the base 8 have abundant envelope space, which can be used for the layout of other payloads and antenna products on the satellite.

[0023] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention comprehensively considers factors such as the limited outer envelope of the satellite to the ground and the dual antennas, compact space, and weight reduction. The two sets of main and secondary reflectors and the feed source are arranged in an L-shape, which is compact and can fully adapt to the installation constraints of various satellite surfaces. 2. The sub-reflector and feed share a single antenna tower, which greatly reduces the system weight and envelope, and the common reference installation has high accuracy, ensuring the antenna pointing performance; 3. The antenna tower has a closed structure, providing abundant installation interfaces and good heat dissipation capabilities for the feed and waveguide components, making it more adaptable; 4. The common reference mounting design simultaneously satisfies the requirements of minimizing the combined envelope of the dual antennas and ensuring high stability of their positional accuracy. Attached Figure Description

[0024] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the configuration of a bias-fed dual-antenna combination structure with a common reference for the sub-reflector and the feed source according to the present invention; Figure 2 This is a schematic diagram of the antenna tower structure configuration of the present invention; Figure 3This is a schematic diagram of the compact layout of the feed, sub-reflector, and waveguide components inside the antenna tower of the present invention.

[0025] The diagram shows: Detailed Implementation

[0026] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0027] A dual-antenna configuration with a shared reference for the secondary reflector and feed includes: a first main reflector 1, a second main reflector 2, a first secondary reflector 3, a second secondary reflector 4, a first feed 5, a second feed 6, an antenna tower 7, a base 8, and a waveguide assembly 9. The first main reflector 1 and the second main reflector 2 are antenna reflectors with a diameter of 1.25m. This size parameter can be adaptively adjusted according to satellite mission requirements, and based on the lateral envelope constraint of the launch vehicle fairing, the size does not exceed 1.9m. The first main reflector 1, the second main reflector 2, and the antenna tower 7 are arranged in an L-shape on the base 8. The first secondary reflector 3, the second secondary reflector 4, the first feed 5, the second feed 6, and the waveguide assembly 9 are compactly mounted on the antenna tower 7. The first main reflector 1, the second main reflector 2, the first secondary reflector 3, the second secondary reflector 4, the first feed 5, and the second feed 6 maintain a specified angular orientation relative to each other to achieve ground detection.

[0028] The first primary reflector 1 and the second primary reflector 2 are mounted on the base 8 via a clamping and releasing mechanism and a two-dimensional rotation mechanism. During launch, they are in a clamped and retracted state, and after launch into orbit, they are unlocked and released at a small angle. After unlocking and releasing, the first primary reflector 1 and the second primary reflector 2 can rotate in two directions via the two-dimensional rotation mechanism, with a rotation angle range of ±6.5°.

[0029] The first main reflector 1, the second main reflector 2, and the antenna tower 7 are arranged in an L-shape on the base 8 and are positioned by pin holes to ensure the installation accuracy between the three. The first secondary reflector 3 and the second secondary reflector 4 are suspended upside down below the top mounting plate of the antenna tower 7 and are positioned by pin holes to ensure the installation accuracy between the first secondary reflector 3, the second secondary reflector 4 and the antenna tower 7. The first feed 5 and the second feed 6 are obliquely nested inside the antenna tower 7 by brackets and are positioned by pin holes to ensure the installation accuracy between the first feed 5, the second feed 6 and the antenna tower 7.

[0030] The first feed 5 and the second feed 6 support the reception and transmission of electromagnetic waves in multiple frequency bands such as C, Ku, K, Ka, and EHF. The back end of the first feed 5 and the second feed 6 is connected to the transmitter through the waveguide assembly 9 arranged inside the antenna tower 7 to reduce link attenuation.

[0031] The first primary reflector 1, the second primary reflector 2, the first secondary reflector 3, the second secondary reflector 4, the first feed 5, and the second feed 6 are all equipped with optical precision prisms. The results of the optical precision measurements can be used for on-orbit calibration of the antenna pointing.

[0032] The antenna tower 7 is assembled from 8 honeycomb sandwich panels, which support quick assembly and disassembly. This facilitates the portable installation of feed back-end equipment, waveguide components 9, and other components inside the antenna tower 7. The honeycomb sandwich panels provide a closed space, which provides a better thermal control environment for the products inside the antenna tower 7. The outer surfaces of the antenna tower 7 and the base 8 have abundant envelope space, which can be used for the layout of other payloads and antenna products on the satellite.

[0033] The dual-antenna combination structure configuration in this invention has the following overall configuration: Figure 1 As shown, the antenna tower configuration is as follows: Figure 2 As shown, the first sub-reflector 3, the second sub-reflector 4, the first feed 5, the second feed 6, and the waveguide assembly 9 inside the antenna tower are compactly arranged as follows: Figure 3 As shown.

[0034] like Figure 1 As shown, the first main reflector 1 and the second main reflector 2 are mounted on the base 8 through a pressing and releasing mechanism and a two-dimensional rotation mechanism. They are in a compressed state during launch and are unlocked and released at a small angle after launch into orbit.

[0035] Furthermore, when the first main reflective surface 1 and the second main reflective surface 2 are closed and pressed together, they are at 0°. After the track is unlocked, they need to be unfolded to 16° to the zero position.

[0036] The first main reflective surface 1 and the second main reflective surface 2 are mounted on the base 8 through a pressing release mechanism and a two-dimensional rotation mechanism. After the first main reflective surface 1 and the second main reflective surface 2 are unlocked and released, they can be rotated in two directions through the two-dimensional rotation mechanism.

[0037] Furthermore, after the first primary reflector 1 and the second primary reflector 2 are unlocked upon entering the orbit, they can rotate in two dimensions within a range of ±6.5° in two directions, based on the zero position.

[0038] The first main reflector 1, the second main reflector 2, and the antenna tower 7 are arranged in an L-shape on the base 8 and are positioned by pin holes to ensure the installation accuracy between the three.

[0039] Furthermore, the L-shaped envelope formed by the first main reflector 1, the second main reflector 2, and the antenna tower 7 has a size of 1700mm × 1700mm, and the installation position accuracy of the three is ±0.1mm.

[0040] The first reflector 3 and the second reflector 4 are suspended upside down below the mounting plate on the top of the antenna tower 7. The first reflector 3 and the second reflector 4 are positioned by pin holes to ensure the installation accuracy between the first reflector 3, the second reflector 4 and the antenna tower 7.

[0041] Furthermore, the positional accuracy between the first sub-reflector 3, the second sub-reflector 4, and the antenna tower 7 is ±0.1mm.

[0042] The first feed 5 and the second feed 6 are nested obliquely inside the antenna tower 7 via brackets. The feed brackets are positioned by pin holes to ensure the installation accuracy between the first feed 5, the second feed 6 and the antenna tower 7.

[0043] Furthermore, the positional accuracy between the first feed 5, the second feed 6, and the antenna tower 7 is ±0.1mm.

[0044] The first feed 5 and the second feed 6 support the reception and transmission of electromagnetic waves in multiple frequency bands such as C, Ku, K, Ka, and EHF. The back end of the first feed 5 and the second feed 6 is connected to the transmitter through the waveguide assembly 9 arranged inside the antenna tower 7 to reduce link attenuation.

[0045] Furthermore, the antenna tower 7 provides sufficient installation space to support the reception and transmission of electromagnetic waves in multiple frequency bands, including but not limited to C, Ku, K, Ka, EHF, etc. The feed and transmitter support various forms of connection such as waveguide, optical fiber, and radio frequency coaxial cable.

[0046] The first primary reflector 1, the second primary reflector 2, the first secondary reflector 3, the second secondary reflector 4, the first feed 5, and the second feed 6 are all equipped with optical precision prisms. The results of the optical precision measurements can be used for on-orbit calibration of the antenna pointing.

[0047] Furthermore, the optical precision measurement index between the first primary reflector 1, the second primary reflector 2, the first secondary reflector 3, the second secondary reflector 4, the first feed source 5, and the second feed source 6 is ≤15′.

[0048] like Figure 2 , Figure 3 As shown, the antenna tower 7 is assembled from 8 honeycomb sandwich panels, which supports quick assembly and disassembly, facilitating the portable installation of feed back-end equipment, waveguide components 9, etc. inside the antenna tower 7. The honeycomb sandwich panels provide a closed space, providing a better thermal control environment for the products inside the antenna tower 7.

[0049] The outer surfaces of the antenna tower 7 and the base 8 have ample envelope space, which can be used for the layout of other payloads and antenna products on the satellite.

[0050] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0051] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A configuration of a dual antenna combination structure of a parasitic and a feed source co-reference, characterized by, Comprise: The first main reflecting surface (1), the second main reflecting surface (2), the first sub-reflector (3), the second sub-reflector (4), the first feed source (5), the second feed source (6), the antenna tower (7), the base (8), the waveguide assembly (9); The first main reflecting surface (1), the second main reflecting surface (2) and the antenna tower (7) are arranged in L shape on the base (8); The first sub-reflector (3), the second sub-reflector (4), the first feed source (5), the second feed source (6) and the waveguide assembly (9) are compactly installed on the antenna tower (7); The first main reflecting surface (1), the second main reflecting surface (2), the first sub-reflector (3), the second sub-reflector (4) and the first feed source (5), the second feed source (6) keep a specified angle direction with each other to realize the antenna detection on the ground.

2. The parasitically fed dual antenna combination configuration of claim 1, wherein, The first main reflecting surface (1), the second main reflecting surface (2) are installed on the base (8) through the compression release mechanism and the two-dimensional rotating mechanism, and are in the state of folding and compression during launching, and are unlocked and released after launching into orbit.

3. The parasitic and feed source co-reference parasitic-fed dual antenna combination configuration of claim 2, wherein, After the first main reflecting surface (1), the second main reflecting surface (2) are unlocked and released, they can be rotated in two directions through the two-dimensional rotating mechanism, and the rotation angle range is ±6.5°.

4. The parasitically fed dual antenna combination configuration of claim 1, wherein, The first main reflecting surface (1), the second main reflecting surface (2) and the antenna tower (7) are arranged in L shape on the base (8), and are positioned through pin holes, so as to ensure the installation precision among them.

5. The parasitically fed dual antenna combination configuration of claim 1, wherein, The first sub-reflector (3) and the second sub-reflector (4) are hung below the top mounting plate of the antenna tower (7), and are positioned through pin holes, so as to ensure the installation precision between the first sub-reflector (3), the second sub-reflector (4) and the antenna tower (7).

6. The parasitically fed dual antenna combination configuration of claim 1, wherein, The first feed source (5) and the second feed source (6) are obliquely nested inside the antenna tower (7) through a support, and the support is positioned through pin holes, so as to ensure the installation precision between the first feed source (5), the second feed source (6) and the antenna tower (7).

7. The parasitically fed dual antenna combination configuration of claim 1, wherein, The first feed source (5) and the second feed source (6) support the receiving and transmitting functions of C, Ku, K, Ka and EHF frequency band electromagnetic waves, and the back end of the first feed source (5) and the second feed source (6) is connected with a transmitter through the waveguide assembly (9) arranged inside the antenna tower (7), so as to reduce the link attenuation. The antenna tower (7) is used for sufficient installation space, provides the first feed source (5) and the second feed source (6) support the receiving and transmitting functions of multiple frequency band electromagnetic waves, and the first feed source (5) and the second feed source (6) support the connection in the form of waveguide, optical fiber and radio frequency coaxial cable with the transmitter.

8. The parasitically fed dual antenna combination configuration of claim 1, wherein, The first main reflecting surface (1), the second main reflecting surface (2), the first sub-reflector (3), the second sub-reflector (4), the first feed source (5) and the second feed source (6) are all installed with optical precision measuring prisms, and through the optical precision measurement results, they can be used for on-orbit calibration of antenna pointing.

9. The parasitically fed dual antenna combination configuration of claim 1, wherein, The antenna tower (7) is assembled by 8 honeycomb sandwich panels, supports quick disassembly and assembly, facilitates portable installation of the feed source rear-end equipment and the waveguide assembly (9) inside the antenna tower (7), and the honeycomb sandwich panel provides a closed space to provide a thermal control environment for the products inside the antenna tower (7).

10. The parasitically fed dual antenna combination configuration of claim 1, wherein, The antenna tower (7) and the base (8) have rich envelope space on the outer surface, which can be used for the layout of other loads and antenna products on the satellite.

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