Satellite-borne four-arm helical antenna and design method thereof

Abstract

The application provides a spaceborne four-arm helical antenna and a design method thereof, and belongs to the technical field of spaceborne antennas. The antenna comprises a platform cooperative compensation structure, the platform cooperative compensation structure comprises a base boundary isolation wall, a local parasitic conductor sheet and a top offset loading sheet; the base boundary isolation wall is formed by extending downward from the local edge of the mounting base, the lower part of the base boundary isolation wall is open, and the height of the base boundary isolation wall is less than a preset height threshold; the local parasitic conductor sheet is arranged at the edge of the mounting base, the local parasitic conductor sheet is located at the corresponding azimuth of the damaged airspace of the antenna, and the local parasitic conductor sheet and the mounting base are insulated from each other; and the top offset loading sheet is arranged at the lower end of the four-arm helical radiator and deviates from the main shaft position of the antenna and is located at the corresponding azimuth of the damaged airspace of the antenna. The spaceborne four-arm helical antenna and the design method thereof can improve the working performance of the spaceborne four-arm helical antenna.

Description

Technical Field

[0001] This application belongs to the field of spaceborne antenna technology, and more specifically, relates to a spaceborne four-arm helical antenna and its design method. Background Technology

[0002] Quad-arm helical antennas possess advantages such as excellent circular polarization characteristics, compact structure, low profile, and easy integration, and are widely used in satellite telemetry, tracking, command and control, navigation enhancement, satellite-to-ground communication, and inter-satellite links. When such antennas are directly mounted on the satellite's metal hull, electromagnetic coupling, electromagnetic wave blockage, and surface current crosstalk occur between the satellite's metal structure and the antenna. This causes problems such as pattern distortion in the antenna's local spatial domain, deterioration of axial ratio, decrease in circular polarization purity, and degradation of performance in key coverage areas, affecting the antenna's operating performance and the communication quality of the onboard link.

[0003] Therefore, it is urgent to improve the structure of existing spaceborne quad-arm helical antennas to enhance their performance. Summary of the Invention

[0004] The purpose of this application is to provide a spaceborne quad-helical antenna and its design method to solve the problems in the prior art where the satellite metal structure causes pattern distortion, axial ratio deterioration, circular polarization purity reduction and key coverage area performance degradation in the local airspace of the antenna, thereby improving the working performance of the spaceborne quad-helical antenna.

[0005] In a first aspect, this application provides a spaceborne quad-helical antenna. The overall structure of the antenna includes a mounting base, a quad-helical radiator, and a feeding structure. The mounting base is used to mount the quad-helical radiator and the feeding structure on the mounting surface of a satellite. The antenna also includes a platform cooperative compensation structure, which is parasitic on the overall structure and includes a base boundary isolation wall, a local parasitic conductor sheet, and a top bias loading sheet. The base boundary isolation wall is formed by extending downward from a local edge of the mounting base, and the lower part of the base boundary isolation wall is open. The height of the base boundary isolation wall is less than a preset height threshold. The local parasitic conductor piece is disposed on the edge of the mounting base, and the local parasitic conductor piece is located in the orientation corresponding to the damaged airspace of the antenna. The local parasitic conductor piece is insulated from the mounting base. The damaged airspace of the antenna is obtained by co-simulating the antenna and the satellite installation scenario. The top bias loading plate is located at the lower end of the four-armed helical radiator, offset from the main axis of the antenna, and in the orientation corresponding to the damaged airspace of the antenna.

[0006] In a second aspect of this application, the overall structure of the antenna includes a mounting base, a four-armed helical radiator, and a feeding structure. The mounting base is used to mount the four-armed helical radiator and the feeding structure on a satellite mounting surface. A platform cooperative compensation structure is parasitic on the overall structure. The method includes: Construct a satellite installation scenario and determine the satellite platform boundary conditions; The corresponding operating frequency band is determined based on the preset task requirements. The overall structure of the spaceborne four-arm helical antenna is constructed based on the satellite platform boundary conditions and the operating frequency band. A platform collaborative compensation structure is constructed based on the overall structure described above; The construction steps of the platform collaborative compensation structure include: The local edge of the mounting base is extended downward to form a base boundary isolation wall, and the lower part of the base boundary isolation wall is open, and the height of the base boundary isolation wall is less than a preset height threshold. A local parasitic conductor patch is provided at the edge of the mounting base, and the local parasitic conductor patch is located at the position corresponding to the damaged airspace of the antenna. The local parasitic conductor patch is insulated from the mounting base. The damaged airspace of the antenna is obtained by co-simulating the antenna and the satellite installation scenario. A top bias loading plate is provided at the lower end of the four-armed helical radiator. The top bias loading plate is offset from the main axis of the antenna and is located in the orientation corresponding to the damaged airspace of the antenna.

[0007] The beneficial effects of the spaceborne quad-arm helical antenna and its design method provided in this application are as follows: In this embodiment, a platform collaborative compensation structure consisting of "base boundary isolation wall + local parasitic conductor sheet + top bias loading sheet" is constructed around the antenna body and mounting base. This forms a layered compensation mechanism of "base boundary constraint - local parasitic guidance - top bias adjustment", thereby achieving comprehensive control over platform coupling current diffusion, redistribution of damaged airspace radiation energy, and circular polarization stability. This can effectively improve the problems of antenna pattern distortion, axial ratio deterioration, and circular polarization purity reduction caused by electromagnetic coupling of the satellite platform, and significantly improve the working performance of the spaceborne quad-helical antenna. Furthermore, this embodiment breaks through the existing technical concept of separating antenna design from the impact of satellite platform installation. It integrates the four-armed helical radiator, feeding structure, mounting base, and platform collaborative compensation structure into the same design process, taking into account the impact of adjacent structures on the satellite platform, thereby forming a collaborative design scheme oriented towards real satellite installation scenarios, which can make the design scheme more in line with the requirements of satellite installation. Attached Figure Description

[0008] To more clearly illustrate the technical solutions in the embodiments of this application, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0009] Figure 1 This is a schematic diagram of the installation of a spaceborne quad-arm helical antenna in a typical small satellite installation scenario, as provided in an embodiment of this application. Figure 2 This is a schematic diagram of the overall structure of the platform collaborative compensation structure provided in an embodiment of this application; Figure 3 This is a top-down layout diagram of a platform collaborative compensation structure provided in an embodiment of this application; Figure 4 A side view of a platform collaborative compensation structure provided in an embodiment of this application; Figure 5 A schematic flowchart illustrating the design method of a spaceborne quad-arm helical antenna provided in an embodiment of this application; In the picture: 1-Metal cabin, 2-Solar fin, 3-Mounting bracket, 31-Mounting base, 4-Four-arm spiral radiator, 5-Base boundary isolation wall, 6-Local parasitic conductor sheet, 7-Top offset loading sheet. Detailed Implementation

[0010] In the following description, specific details such as particular system architectures and techniques are set forth for illustrative purposes and not for limitation, in order to provide a thorough understanding of the embodiments of this application. However, those skilled in the art will understand that this application may also be implemented in other embodiments without these specific details. In other instances, detailed descriptions of well-known systems, apparatuses, circuits, and methods have been omitted so as not to obscure the description of this application with unnecessary detail.

[0011] To make the objectives, technical solutions, and advantages of this application clearer, the following description will be provided in conjunction with the accompanying drawings and specific embodiments.

[0012] Please refer to Figure 1 , Figure 1 This is a schematic diagram of the installation of a spaceborne quad-helical antenna in a typical small satellite installation scenario according to an embodiment of this application. The metal cabin 1 provides a mounting surface for the mounting bracket 3. The quad-helical radiators 4 and the feeding structure are both mounted on the metal cabin 1 via the mounting bracket 3. The bottom of the mounting bracket 3 is provided with a mounting base 31. The quad-helical radiators 4 are located on the lower side of the mounting base 31. Solar panels 2 are deployed on both sides of the satellite cabin. The surface of the solar panels 2 is covered with grid-like solar cells for on-orbit power generation.

[0013] Based on this, in order to solve the coupling, scattering, and shading problems caused by the boundaries of the metal cabin 1, mounting bracket 3, and solar array 2 in the above satellite installation scenario, this embodiment also includes a platform cooperative compensation structure. Please refer to [reference needed]. Figures 2-4 The platform's collaborative compensation structure specifically comprises three parts: a base boundary isolation wall 5, a local parasitic conductor sheet 6, and a top bias loading sheet 7. The specific structures of these three parts are as follows: The base boundary isolation wall 5 is formed by extending downward from a local edge of the mounting base 31, and the lower part of the base boundary isolation wall 5 is open. The height of the base boundary isolation wall 5 is less than a preset height threshold. The local parasitic conductor 6 is disposed at the edge of the mounting base 31 and is located in the orientation corresponding to the damaged airspace of the antenna. The local parasitic conductor 6 is insulated from the mounting base 31. The damaged airspace of the antenna is obtained by co-simulating the antenna and satellite installation scenario. The top bias loading plate 7 is located at the lower end of the four-armed helical radiator 4, offset from the main axis of the antenna, and in the direction corresponding to the damaged airspace of the antenna.

[0014] In this embodiment, the direction in which the partial edge of the mounting base 31 extends downward is... Figure 2 In the z-direction, the base boundary isolation wall 5 extends downward from the edge of the mounting base 31, forming a low-profile perimeter structure integrally with the mounting base 31. Its overall distribution is locally or circumferentially along the outer edge of the mounting base 31, but its height is significantly lower than the height of the four-armed helical radiator 4. Simultaneously, the base boundary isolation wall 5 opens downward, not forming a multi-layered nested cavity, nor covering the outermost layer of the four-armed helical radiator 4. The preset height threshold can be 0.04λ. L Preferably, the height of the shallow-edge isolation wall is 0.01λ. L ~0.04λ L The wall thickness is 0.005λ. L ~0.02λ L The distance between the outer edge of the four-armed spiral radiator 4 and the outer edge of the spiral radiator 4 ( Figure 3 d1) in the equation is 0.01λ. L ~0.06λ L , where λ L This indicates the wavelength corresponding to the lowest operating frequency of the antenna.

[0015] The base boundary isolation wall 5 can create a low-profile local boundary constraint region at the edge of the mounting surface, so that the surface coupling current generated by the satellite metal cabin 1 and the mounting surface excitation is preferentially attenuated near the mounting base 31, rather than diffused to a larger area of ​​the mounting surface, thereby reducing the direct disturbance of the platform edge and adjacent metal structure to the four-armed helical radiator 4.

[0016] Furthermore, electromagnetic simulation software such as Field Computations Involving Bodies of Arbitrary Shape (FEKO) or High Frequency Structure Simulator (HFSS) can be used to perform co-simulation of the antenna and satellite installation scenario, obtaining the airspace significantly affected by the satellite platform, i.e., the damaged airspace. A local parasitic conductor sheet 6 is then installed at the location corresponding to the damaged airspace. This local parasitic conductor sheet 6 is arranged along the outer edge of the mounting base 31 and is a non-closed, non-fully encircling local parasitic metal conductor, only covering the azimuth range corresponding to the damaged airspace, without forming a complete closed loop. Simultaneously, the local parasitic conductor sheet 6 can be insulated from the mounting base 31, or it can be supported by a local dielectric to maintain a predetermined gap with the mounting base 31, thus forming a locally controlled parasitic current. Preferably, the width of the local parasitic conductor sheet 6 is 0.01λ. L ~0.05λ L The distance between the outer edge of the four-armed spiral radiator 4 and ( Figure 3 d2) is 0.01λ L ~0.08λ L .

[0017] By setting up a local parasitic conductor sheet 6 structure, directional compensation can be performed towards the damaged space, so that problems such as pattern collapse, gain reduction or polarization degradation in that direction can be locally corrected, rather than uniformly redistributing the radiated energy of the entire space.

[0018] Furthermore, a top bias loading plate 7 is disposed at the lower end of the four-armed helical radiator 4, offset from the central axis. The top bias loading plate 7 is a localized metal loading unit located near the lower end of the radiator, employing a short-sectioned conductor. One end of the top bias loading plate 7 is connected to the helical arm segment of the four-armed helical radiator, while the other end is suspended or maintains a predetermined coupling gap with a nearby conductor, thus forming a biased localized loading path. The top bias loading plate 7 does not form a complete cap-shaped ring structure around the central axis, nor does it include a combination of a vertical ring and a horizontal ring. Instead, it is located at a localized bias position on one side of the damaged space, used to adjust the current concentration area and phase distribution near the lower end of the radiator. Preferably, the length of the top bias stub loading plate is 0.03λ. H ~0.08λ H The width is 0.01λ H ~0.04λ H The height difference from the reference surface at the lower end of the antenna ( Figure 2 h) is 0 to 0.03λ. H , λ HThis indicates the wavelength corresponding to the antenna's highest operating frequency. This structure allows for localized correction of axial ratio characteristics, circular polarization purity, and pattern stability—all susceptible to platform influences in satellite-mounted configurations—without significantly increasing the overall antenna height.

[0019] Therefore, this embodiment constructs a platform collaborative compensation structure of "base boundary isolation wall + local parasitic conductor sheet + top bias loading sheet" around the antenna body and mounting base 31, forming a hierarchical compensation mechanism of "base boundary constraint - local parasitic guidance - top bias adjustment", thereby realizing comprehensive control over platform coupling current diffusion, redistribution of damaged airspace radiation energy and circular polarization stability. It can effectively improve the problems of antenna pattern distortion, axial ratio deterioration and circular polarization purity reduction caused by electromagnetic coupling of satellite platform, and significantly improve the working performance of spaceborne quad-arm helical antenna.

[0020] In one embodiment of this application, the base boundary isolation wall 5 adopts a rounded rectangular frame. Compared with a right-angle frame, the rounded transition can avoid current concentration and edge diffraction at the right angle, reduce the spread of the coupled current on the satellite platform surface to a wider range, weaken the electromagnetic coupling interference of the metal cabin 1 to the antenna, and thus suppress pattern distortion. At the same time, the rounded structure can reduce electromagnetic scattering and secondary radiation caused by the right-angle frame, reduce the disturbance to the main lobe and side lobes of the antenna, reduce beam distortion and side lobe level rise, and improve the pattern performance of the key coverage area. In addition, the smooth rounded transition can avoid abrupt changes in local field strength, reduce asymmetric disturbance to the circular polarization field of the antenna, maintain axial ratio stability, and avoid a decrease in circular polarization purity.

[0021] In one embodiment of this application, the local parasitic conductor patch 6 is an annular segment, and the center of the local parasitic conductor patch 6 coincides with the main axis of the antenna. In practical use, the center of the local parasitic conductor patch 6 and the main axis of the antenna can be approximately coincident. Specifically, a first error range can be set to no more than 0.05λ. L The second error range is set to be no more than 5% of the diameter of the mounting base. Based on this, the radial deviation between the geometric center of the local parasitic conductor sheet 6 and the main axis of the antenna satisfies either the first error range or the second error range, with the smaller error range between the first and second error ranges being used as the standard.

[0022] In one embodiment of this application, to ensure the effective electrical length of the locally parasitic conductor sheet 6 and to provide sufficient electromagnetic guidance and current suppression capabilities, the central angle of the annular segment cannot be too small; simultaneously, to ensure directional compensation only for the locally damaged spatial region and to avoid causing additional electromagnetic interference to the normal radiation region, the central angle of the annular segment cannot be too large. Therefore, the final central angle of the annular segment ( Figure 3 θ is set to 30°~120°.

[0023] Corresponding to the spaceborne four-arm helical antenna in the above embodiment, Figure 5 This is a schematic flowchart illustrating a design method for a spaceborne quad-helical antenna according to an embodiment of this application. The method can be executed by an electronic device and includes: S101: Construct a satellite installation scenario and determine the satellite platform boundary conditions.

[0024] In this embodiment, a typical mounting surface (e.g., the mounting reference surface of the satellite's side panel external flange) can be selected as the design object based on the actual installation requirements of the satellite surface. A simplified platform model is established, consisting of the satellite's metal body, mounting surface, body edge, mounting bracket, solar panel boundary, and adjacent metal structure. The specific position of the antenna on this mounting surface is then determined. This step provides boundary conditions for the collaborative design of the antenna and satellite platform, allowing the antenna design to be directly oriented towards real or typical satellite installation scenarios, rather than an ideal free-space environment, making the design scheme more closely aligned with the requirements of satellite installation.

[0025] S102: Determine the corresponding operating frequency band based on the preset task requirements.

[0026] In this embodiment, the operating frequency band of the spaceborne antenna is not determined solely by the "spaceborne" attribute, but rather by the specific mission. Different spaceborne missions (including telemetry, tracking, command and control, navigation enhancement, data transmission, or satellite-to-ground links) can correspond to different frequency bands such as VHF / UHF, L, S, X, Ku, and Ka. A single satellite platform often needs to handle multiple missions, including telemetry, tracking, command and control, navigation enhancement, and satellite-to-ground links. Using multiple single-frequency antennas to achieve this would not only increase the surface area occupied and structural weight of the satellite, but also increase the platform coupling complexity and the overall satellite integration difficulty under multiple antenna coexistence.

[0027] Therefore, this embodiment selects two working frequency bands from the satellite mission frequency bands such as VHF / UHF, L, S, X, Ku, and Ka, based on the specific mission requirements undertaken by the satellite platform, such as telemetry, tracking and command, navigation enhancement, data transmission, or satellite-to-ground link. The antenna is designed based on the two working frequency bands, which allows the same antenna to meet the needs of multiple services.

[0028] It should be noted that there is no strict execution order between steps S101 and S102. Step S101 can be executed before or after step S102.

[0029] S103: The overall structure of the spaceborne quad-helical antenna is constructed based on the satellite platform boundary conditions and operating frequency band; the overall structure includes the mounting base, the quad-helical radiator, and the feeding structure.

[0030] In this embodiment, based on the satellite platform boundary conditions and operating frequency band determined in steps S101 and S102, the overall structure of the spaceborne quad-helical antenna can be constructed. The overall structure includes a mounting base, a quad-helical radiator, and a feeding structure. The quad-helical radiator serves as the main radiating part of the antenna, used to achieve electromagnetic radiation in the corresponding operating frequency band. The feeding structure is arranged around the quad-helical radiator to achieve energy input, power distribution, and circular polarization excitation in the corresponding operating frequency band, ensuring that the quad-helical radiator has the corresponding radiation excitation capability in the corresponding operating frequency band. The mounting base is used to realize the mechanical connection between the antenna and the satellite platform.

[0031] S104: Construct a platform collaborative compensation structure based on the overall structure.

[0032] In this embodiment, based on the overall structure consisting of a four-armed helical radiator, a feeding structure, and a mounting base, an integration location for a platform collaborative compensation structure is reserved around the antenna body and the mounting base. The platform collaborative compensation structure can be constructed at this integration location, enabling the platform collaborative compensation structure to form a unified collaborative working whole with the antenna body and the satellite platform.

[0033] The steps involved in constructing the platform's collaborative compensation structure include: The local edge of the mounting base is extended downward to form a base boundary isolation wall, and the lower part of the base boundary isolation wall has an opening, and the height of the base boundary isolation wall is less than a preset height threshold. A local parasitic conductor patch is placed at the edge of the mounting base, and the local parasitic conductor patch is located in the orientation corresponding to the damaged airspace of the antenna. The local parasitic conductor patch is insulated from the mounting base. The damaged airspace of the antenna is obtained by co-simulating the antenna and satellite installation scenario. A top bias loading plate is installed at the lower end of the four-armed helical radiator. The top bias loading plate is offset from the main axis of the antenna and is located in the azimuth corresponding to the damaged airspace of the antenna.

[0034] In this embodiment, the base boundary isolation wall can construct a low-profile local boundary constraint region at the edge of the mounting surface, so that the surface coupling current generated by the satellite metal cabin and the mounting surface excitation is preferentially attenuated near the mounting base, rather than diffused to a larger area of ​​the mounting surface, thereby reducing the direct disturbance of the platform edge and adjacent metal structure to the four-armed helical radiator.

[0035] Meanwhile, through the local parasitic conductor sheet structure, directional compensation can be performed on the damaged space, so that the problems of pattern collapse, gain reduction or polarization degradation in that direction can be locally corrected, rather than uniformly redistributing the radiation energy of the entire space.

[0036] Furthermore, by setting a top offset loading plate, the axial ratio characteristics, circular polarization purity, and top pattern stability that are susceptible to platform influences during satellite mounting can be locally corrected without significantly increasing the overall height of the antenna.

[0037] Therefore, the aforementioned platform collaborative compensation structure of "base boundary isolation wall + local parasitic conductor sheet + top bias loading sheet" can form a hierarchical compensation mechanism of "base boundary constraint - local parasitic guidance - top bias adjustment", thereby realizing comprehensive control over platform coupling current diffusion, redistribution of damaged airspace radiation energy and circular polarization stability. This effectively improves the problems of antenna pattern distortion, axial ratio deterioration and circular polarization purity reduction caused by electromagnetic coupling of the satellite platform, and significantly enhances the radiation performance of key coverage airspace.

[0038] Furthermore, in the existing technology, most quad-arm spiral antennas are designed under relatively ideal free space conditions, lacking synchronous consideration for specific spaceborne installation scenarios. This can easily lead to deviations in the antenna's radiation pattern, axial ratio, and polarization performance under actual satellite installation conditions, making it difficult to meet the expected airspace coverage requirements.

[0039] This embodiment breaks through the existing technical concept of treating antenna design and satellite platform installation effects separately. It integrates the four-armed helical radiator, feeding structure, mounting base, and platform collaborative compensation structure into the same design process, taking into account the influence of adjacent structures on the satellite platform, thereby forming a collaborative design scheme oriented towards real satellite installation scenarios, which can make the design scheme more in line with the requirements of satellite installation.

[0040] In one embodiment of this application, the satellite platform boundary conditions include the available range of the mounting surface, the distance to the cabin edge, the support boundary, the solar panel boundary, and the relative orientation of the adjacent metal structure; The operating frequency band includes a first operating frequency band and a second operating frequency band, and the frequency of the first operating frequency band is greater than the frequency of the second operating frequency band. Before constructing a platform-based collaborative compensation structure based on the overall structure, the design methods for spaceborne four-arm helical antennas also included: The lateral deployment method of the four-armed spiral radiators is determined based on the available range of the mounting surface and the distance to the edge of the cabin. Adjust the power supply lead-out direction and local coupling branch layout of the power supply structure according to the relative directions of the support boundary, the solar panel boundary and the adjacent metal structure. Adjust the parameters of multiple radiators of the four-armed spiral radiator to achieve impedance matching in the first and second operating frequency bands; Adjust multiple feeding parameters of the feeding structure to form four equal-amplitude, sequentially phase-shifted circular polarization excitations in both the first and second operating frequency bands.

[0041] In this embodiment, before constructing the platform's collaborative compensation structure based on the overall structure, the collaborative design of the four-armed helical radiator and the feed structure can be carried out in conjunction with the satellite platform's boundary conditions. First, the lateral layout of the four-armed helical radiator is limited according to the available range of the mounting surface and the distance to the cabin edge, which can avoid structural interference and edge electromagnetic disturbances. At the same time, by combining the relative directions of the support boundary, the solar panel boundary, and the adjacent metal structure, the feed lead-out direction and the arrangement of local coupling branches can be optimized, which can weaken the electromagnetic coupling interference caused by the platform's metal body.

[0042] Furthermore, by adjusting the parameters of multiple radiators in the four-armed spiral radiator, impedance matching in both frequency bands (the first and second operating frequency bands) can be achieved, ensuring that the antenna can transmit and receive signals normally in both operating frequency bands.

[0043] For example, the adjustment process of multiple radiator parameters of a four-armed helical radiator may include: Determine the range of values ​​for each radiator parameter; For each radiator parameter, multiple candidate values ​​are selected from the range of values ​​of the radiator parameter based on a preset step size, and these are used as the candidate set for the radiator parameter. Based on the candidate sets of multiple radiator parameters, all possible combinations of values ​​for the multiple radiator parameters are determined, resulting in multiple sets of radiator parameter combinations. The radiator parameters are iterated based on multiple combinations of radiator parameters until the first preset condition is met. Each iteration of the radiator parameters includes the following steps: Select one radiator parameter combination from the multiple radiator parameter combinations that have never been used as the current radiator parameter combination; Based on the current combination of radiator parameters, a collaborative simulation of the antenna and satellite installation scenario is performed to extract impedance characteristic data of the first operating frequency band and the second operating frequency band. The impedance characteristic data of the first operating frequency band is compared with the preset impedance matching threshold, and the impedance characteristic data of the second operating frequency band is compared with the preset impedance matching threshold. The first preset condition is: the comparison results show that impedance matching is achieved in both the first and second operating frequency bands.

[0044] In this embodiment, the parameters of multiple radiators of the four-armed spiral radiator can be iteratively optimized using co-simulation until impedance matching is achieved in the first and second operating frequency bands. The first operating frequency band has a higher frequency and can be referred to as the high-frequency band, while the second operating frequency band has a lower frequency and can be referred to as the low-frequency band. The high-frequency band is mainly formed by the radiating arms of the four-armed spiral radiator to form the main resonant channel, while the low-frequency band forms a secondary resonant channel through additional coupling arms.

[0045] Impedance characteristic data can be obtained using return loss S11. If the return loss S11 of the first operating frequency band is less than a preset impedance matching threshold, and the return loss S11 of the second operating frequency band is less than a preset impedance matching threshold, then impedance matching is determined for the first and second operating frequency bands. The preset impedance matching threshold can be -10dB, meaning the antenna's reflected power is no more than 10% of the total input power.

[0046] Multiple radiator parameters may include parameters such as radiating arm length, additional coupling arm length, pitch, and arm spacing. This embodiment mainly targets the small satellite installation scenario. The first operating frequency band is the X-band, and the second operating frequency band is the S-band. Due to limited surface space on the small satellite, the antenna design must also consider low profile, miniaturization, and lightweight requirements. Therefore, the value ranges for each of the multiple radiator parameters are set as follows: radiating arm length is 0.95λ. L ~1.9λ L The length of the additional coupling arm is 0.59λ. L ~1.17λ L The pitch is 0.32λ. L ~0.64λ L The arm spacing is 0.25λ. L ~0.50λ L .

[0047] Based on this, for each radiator parameter, multiple candidate values ​​can be selected from the range of values ​​of that radiator parameter based on a preset step size, forming a candidate set for that radiator parameter. Then, multiple iterations of optimization are performed based on the candidate sets of each radiator parameter to ultimately achieve impedance matching of the four-arm helical antenna in dual-band operation. The preferred step size for single adjustment of the radiating arm length, pitch, and arm spacing is 2% to 5% of the initial reference size, and the preferred step size for single adjustment of the length of the additional coupling arm is 0.005λ. L ~0.01λ L .

[0048] Furthermore, by adjusting multiple feeding parameters of the feeding structure, four equal-amplitude excitation signals with a 90° phase difference can be output in both the first and second operating frequency bands, thus meeting the circular polarization requirements of the four-arm helical antenna.

[0049] For example, the adjustment process of multiple feed parameters of the feed structure may include: Determine the value range for each power supply parameter; For each power supply parameter, multiple candidate values ​​are selected from the range of values ​​of the power supply parameter based on a preset step size, and these are used as the candidate set for the power supply parameter. Based on the candidate sets of multiple feed parameters, all possible combinations of values ​​for the multiple feed parameters are determined, resulting in multiple sets of feed parameter combinations; The feeding parameters are iterated based on multiple combinations of feeding parameters until the second preset condition is met. The steps for each iteration of the power supply parameters include: Select one of the multiple unused feeder parameter combinations as the current feeder parameter combination; Based on the current combination of feeding parameters, a collaborative simulation of the antenna and satellite installation scenario is performed to extract circular polarization excitation feature data of the first operating frequency band and the second operating frequency band; the circular polarization excitation feature data includes amplitude data and phase characteristic data; The second preset condition is: the circular polarization excitation characteristic data of the first working frequency band shows that the power supply structure forms four channels of circular polarization excitation characteristic data with equal amplitude and sequential phase shift of 90° in the first working frequency band, and the circular polarization excitation characteristic data of the second working frequency band shows that the power supply structure forms four channels of circular polarization excitation characteristic data with equal amplitude and sequential phase shift of 90° in the second working frequency band.

[0050] In this embodiment, the power supply structure adopts a power divider to realize a one-to-four power divider architecture. Each output of the power divider constitutes an independent power supply branch, and each power supply branch integrates a dual-frequency matching transition section and a phase adjustment branch. The dual-frequency matching transition section is used to realize impedance matching in two frequency bands, and the phase adjustment branch is used to adjust the signal phase. The two work together to keep the four output signals in the two operating frequency bands in a circularly polarized excitation state with approximately equal amplitude and a phase difference of 90°.

[0051] Multiple feed parameters can include feed branch length, feed branch line width, dual-frequency matching transition section length, and dual-frequency matching transition section width. For small satellite installation scenarios, the value ranges for each of these feed parameters can be set as follows: feed branch length is 0.67λ. g ~2.67λ g The feeder branch line width is 0.01λ. g ~0.02λ g The length of the dual-frequency matching transition section is 0.32λ. g ~1.28λ g The width of the dual-frequency matching transition section is 0.005λ. g ~0.013λ g Where λg represents the waveguide wavelength on the feed transmission line.

[0052] Based on this, the same adjustment method as that used for multiple radiator parameters of a four-armed spiral radiator can be adopted to iteratively optimize multiple feed parameters of the feed structure until four equal-amplitude circularly polarized excitations with sequential 90° phase shifts are formed in both the first and second operating frequency bands.

[0053] In the iterative optimization process of multiple feed parameters, the single adjustment step size of the feed branch length, the dual-frequency matching transition section length and the dual-frequency matching transition section width is preferably 0.005λg~0.01λg, and the single adjustment step size of the feed branch line width is preferably 5%~10% of the original line width.

[0054] The above-mentioned collaborative design process of the four-armed spiral radiator and the feeding structure is constrained by the actual satellite installation environment. It integrates the design of structural layout, electromagnetic compatibility, impedance matching and circular polarization excitation, which can take into account both space adaptability and electrical performance indicators, and ensure the stability of the antenna's radiation and polarization performance in dual frequency bands.

[0055] In one embodiment of this application, after constructing the platform collaborative compensation structure based on the overall structure, the method further includes: Co-simulation of antenna and satellite installation scenarios is performed to extract the gain, axial ratio, radiation pattern, and back radiation gain in the damaged airspace. Calculate the first gain difference between the gain in the damaged airspace and the initial gain before compensation; the initial gain before compensation is the gain in the damaged airspace obtained by co-simulating the antenna and satellite installation scenario before constructing the platform co-compensation structure. The radiation pattern is compared with a preset reference radiation pattern, and the presence of distortion in the radiation pattern is determined based on the comparison results. Calculate the second gain difference between the initial back radiation gain before compensation and the back radiation gain before compensation; the initial back radiation gain before compensation is the back radiation gain obtained by co-simulating the antenna and satellite installation scenario before constructing the platform co-compensation structure. If the first gain difference is less than a preset first threshold, the axial ratio in the damaged space domain is greater than a preset axial ratio threshold, the radiation pattern is distorted, or the second gain difference is less than a preset second threshold, then multiple compensation parameters of the platform's collaborative compensation structure are adjusted so that the first gain difference is greater than or equal to the preset first threshold, the axial ratio in the damaged space domain is less than or equal to the preset axial ratio threshold, the radiation pattern is not distorted, and the second gain difference is greater than or equal to the preset second threshold.

[0056] In this embodiment, after constructing the platform collaborative compensation structure based on the overall structure, the compensation effect of the platform collaborative compensation structure can be verified. If the verification results show that the radiation pattern compensation or axis ratio correction effect for the damaged airspace is insufficient, the radiation pattern optimization and axis ratio improvement can be achieved by adjusting multiple compensation parameters of the platform collaborative compensation structure.

[0057] Specifically, a collaborative simulation can be performed on the actual installation scenario of the antenna and satellite to collect four core indicators: gain, axial ratio, radiation pattern, and back radiation gain of the damaged airspace. These indicators are then compared with the simulation data before the collaborative compensation structure of the platform is constructed. The first gain difference between the gain of the damaged airspace and the initial gain before compensation (first gain difference = gain of the damaged airspace - initial gain before compensation) and the second gain difference between the initial back radiation gain before compensation and the back radiation gain before compensation (second gain difference = initial back radiation gain before compensation - back radiation gain) are calculated. At the same time, the measured radiation pattern is compared with the reference radiation pattern to determine whether radiation pattern distortion occurs.

[0058] If the first gain difference is less than the preset first threshold (e.g., 1dB), the axis ratio in the damaged space domain is greater than the preset axis ratio threshold (e.g., 3dB), the radiation pattern is distorted, or the second gain difference is less than the preset second threshold (e.g., 3dB), it indicates that the platform cooperative compensation structure is insufficient in compensating for the radiation pattern or correcting the axis ratio in the damaged space domain. In this case, it is necessary to adjust multiple compensation parameters of the platform cooperative compensation structure until the third preset condition is met, namely: the first gain difference is greater than or equal to the preset first threshold, the axis ratio in the damaged space domain is less than or equal to the preset axis ratio threshold, the radiation pattern is not distorted, and the second gain difference is greater than or equal to the preset second threshold.

[0059] The platform's collaborative compensation structure includes several compensation parameters, such as the height of the base boundary isolation wall, the distance between the base boundary isolation wall and the outer edge of the four-armed helical radiators, the central angle of the local parasitic conductor sheet, the distance between the local parasitic conductor sheet and the four-armed helical radiators, and the length and offset position of the top offset loading plate. For small satellite installation scenarios, the value ranges for each of these compensation parameters can be set as follows: the height of the base boundary isolation wall is 0.01λ. L ~0.04λ L The distance between the base boundary isolation wall and the outer edge of the four-armed spiral radiating body is 0.01λ. L ~0.06λ L The central angle of the locally parasitic conductor plate is 30°–120°, and the distance between the locally parasitic conductor plate and the outer edge of the four-armed spiral radiator is 0.01λ. L ~0.08λ L The length of the top offset loading piece is 0.03λ. H ~0.08λ H The top bias loading plate is offset from the antenna's principal axis λ. H / 8.

[0060] Based on this, the same adjustment method used for multiple radiator parameters can be employed to iteratively optimize multiple compensation parameters of the platform's collaborative compensation structure until the aforementioned third preset condition is met. Specifically, during the iterative optimization of multiple compensation parameters, the preferred single adjustment step size for the height of the base boundary isolation wall is 0.005λ. L The preferred step size for adjusting the distance between the base boundary isolation wall and the outer edge of the four-arm spiral radiating body is 0.005λ. L The preferred step size for adjusting the central angle of the local parasitic conductor sheet is 10°–15°, and the preferred step size for adjusting the distance between the local parasitic conductor sheet and the outer edge of the four-armed spiral radiator is 0.005λ. L The preferred step size for adjusting the length of the top offset loading piece is 0.005λ. H The preferred step size for adjusting the offset position of the top offset loading plate is 5° to 10° offset along the circumference of the radiator.

[0061] In one embodiment of this application, the following steps can be used to determine whether a radiation pattern is distorted: The radiation pattern is compared point by point with a preset reference radiation pattern, and multiple deviation values ​​between the radiation pattern and the preset reference radiation pattern are calculated. The multiple deviation values ​​include gain deviation, main lobe shape deviation, beam pointing deviation and side lobe level deviation. If at least one of the multiple deviation values ​​is greater than the corresponding preset deviation threshold, then the radiation pattern is determined to be distorted. If all deviation values ​​are less than or equal to the corresponding preset deviation thresholds, then the radiation pattern is determined to be free of distortion.

[0062] In this embodiment, the radiation pattern can be compared point by point with the reference radiation pattern, and the gain deviation, main lobe shape deviation, beam pointing deviation and side lobe level deviation can be statistically analyzed to fully cover the key features of the radiation pattern.

[0063] Based on this, a separate deviation threshold can be set for each deviation. For example, the preset deviation threshold for gain deviation can be set to ±1dB, the preset deviation threshold for main lobe shape deviation can be set to 3dB for main lobe beamwidth deviation and ±5° for beam pointing deviation, the preset deviation threshold for beam pointing deviation can be set to ±3°, and the preset deviation threshold for sidelobe level deviation can be set to ±2dB.

[0064] If any one of the four deviations exceeds the corresponding deviation threshold, it is determined that the key indicators of the radiation pattern deviate from the standard shape, and the radiation pattern is distorted; if all deviations do not exceed the limit, it indicates that the radiation pattern is consistent with the reference standard in terms of gain, main lobe, beam pointing, and side lobes, and it is determined that there is no distortion.

[0065] Therefore, this embodiment determines whether there is distortion in the radiation pattern based on multiple key features of the radiation pattern, which can effectively identify various morphological anomalies in the radiation pattern and ensure that the radiation pattern detection results are objective and reliable.

[0066] In summary, compared with the prior art, the present invention has the following beneficial effects: Firstly, this embodiment takes typical satellite installation scenarios as the design premise, and extends antenna design from free space body optimization to platform collaborative design in real satellite installation scenarios, which can more effectively deal with coupling, scattering and shading problems caused by satellite metal cabin, mounting bracket, solar panel boundary and adjacent metal structure; Secondly, this embodiment achieves an overall antenna height of 0.10λ through a low-profile and miniaturized design. L ~0.16λ L The height of the four-armed spiral radiator is controlled at 0.08λ. L ~0.13λ L The maximum lateral dimension is controlled at 0.18λ. L ~0.30λ L The side length or equivalent diameter of the mounting base is controlled to be 0.12λ. L ~0.25λ L This allows for a balance between size reduction, structural support, and dual-frequency operation requirements within a limited installation space. Third, this embodiment uses a base boundary isolation wall, a local parasitic conductor sheet and a top bias loading sheet to form a local asymmetric platform collaborative compensation structure, which can perform directional compensation for specific airspace that is significantly affected by the platform, and improve the problems of pattern collapse, gain reduction, axial ratio deterioration and circular polarization purity reduction in the satellite-mounted state; Fourth, this embodiment integrates dual-frequency capability with platform co-design, enabling the same quad-arm helical antenna to cover two key mission frequency bands, reducing surface occupation, structural weight and overall satellite integration complexity caused by the coexistence of multiple single-frequency antennas, and improving platform resource utilization and mission compatibility. Under typical small satellite installation scenarios and target S-frequency operating conditions, the design expectation of this embodiment is as follows: the circular polarization gain in the critical mission airspace of the low-frequency band (second operating frequency band) is not less than -1 dBic, the circular polarization gain in the critical mission airspace of the high-frequency band (first operating frequency band) is not less than 0 dBic, the gain of the specific damaged airspace that is significantly affected by the platform is increased by 1 dB to 2 dB relative to the uncompensated structure after collaborative compensation, the axial ratio in the critical mission airspace is not greater than 3 dB, the standing wave ratio is not greater than 2, and the back radiation is reduced by more than 3 dB compared with the uncompensated structure.

[0067] The above are merely specific embodiments of this application, but the scope of protection of this application is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this application, and these modifications or substitutions should all be covered within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A spaceborne quad-helical antenna, the overall structure of which includes a mounting base, a quad-helical radiator, and a feeding structure, wherein the mounting base is used to mount the quad-helical radiator and the feeding structure on a satellite mounting surface, and the quad-helical radiator is disposed on the lower side of the mounting base, characterized in that, The antenna also includes a platform cooperative compensation structure, which is parasitic on the overall structure and includes a base boundary isolation wall, a local parasitic conductor sheet, and a top bias loading sheet; The base boundary isolation wall is formed by extending downward from a local edge of the mounting base, and the lower part of the base boundary isolation wall is open. The height of the base boundary isolation wall is less than a preset height threshold. The local parasitic conductor piece is disposed on the edge of the mounting base, and the local parasitic conductor piece is a ring segment located in the azimuth corresponding to the damaged airspace of the antenna. The local parasitic conductor piece is insulated from the mounting base. The damaged airspace of the antenna is the airspace affected by the satellite, which is obtained by co-simulating the antenna and satellite installation scenario. The airspace affected by the satellite refers to the airspace where, when the antenna is directly mounted on the satellite's mounting surface, the satellite's metal structure will generate electromagnetic coupling, electromagnetic wave blockage, and surface current crosstalk with the antenna, causing pattern distortion, axial ratio deterioration, decreased circular polarization purity, and performance degradation in key coverage airspace in the local airspace of the antenna. The top bias loading plate is located near the lower end of the four-armed helical radiator, offset from the main axis of the antenna, and in the orientation corresponding to the damaged airspace of the antenna. The top bias loading plate is a local metal loading unit located near the lower end of the radiator, in the form of a short sheet-shaped conductor. One end of the plate is connected to the helical arm segment of the four-armed helical radiator, and the other end is suspended or maintains a predetermined coupling gap with the nearby conductor, thereby forming a biased local loading path.

2. The spaceborne four-arm helical antenna as described in claim 1, characterized in that, The base boundary isolation wall adopts a rounded rectangular frame, and the height of the base boundary isolation wall is 0.01λ. L ~0.04λ L The wall thickness is 0.005λ. L ~0.02λ L The distance between the outer edge of the four-armed helical radiator and the outer edge is 0.01λ. L ~0.06λ L ; where λ L This indicates the wavelength corresponding to the lowest operating frequency of the antenna.

3. The spaceborne four-arm helical antenna as described in claim 1, characterized in that, The radial deviation between the geometric center of the local parasitic conductor sheet and the main axis of the antenna satisfies the smaller of the first and second error ranges. Wherein, the first error range is: not greater than 0.05λ L The second error range is: no more than 5% of the diameter of the mounting base; where λ L This indicates the wavelength corresponding to the lowest operating frequency of the antenna.

4. The spaceborne four-arm helical antenna as described in claim 3, characterized in that, The central angle of the locally parasitic conductor sheet is Furthermore, the width of the locally parasitic conductor sheet is 0.01λ. L ~0.05λ L The distance between the outer edge of the four-armed helical radiator and the outer edge is 0.01λ. L ~0.08λ L .

5. The spaceborne four-arm helical antenna as described in claim 1, characterized in that, The top bias loading plate is a short-section conductor with a length of 0.03λ. H ~0.08λ H The width is 0.01λ H ~0.04λ H The height difference between the reference surface at the lower end of the four-armed helical radiator and the reference surface is 0 to 0.03λ. H ; where λ H This indicates the wavelength corresponding to the highest operating frequency of the antenna.

6. A design method for a spaceborne quad-helical antenna, wherein the overall structure of the antenna includes a mounting base, a quad-helical radiator, and a feeding structure, the mounting base being used to mount the quad-helical radiator and the feeding structure on a satellite mounting surface, and the quad-helical radiator being disposed on the lower side of the mounting base, characterized in that, The overall structure is parasitic with a platform collaborative compensation structure, and the method includes: Construct a satellite installation scenario and determine the satellite platform boundary conditions; The corresponding operating frequency band is determined based on the preset task requirements. The overall structure of the spaceborne four-arm helical antenna is constructed based on the satellite platform boundary conditions and the operating frequency band. A platform collaborative compensation structure is constructed based on the overall structure described above; The construction steps of the platform collaborative compensation structure include: The local edge of the mounting base is extended downward to form a base boundary isolation wall, and the lower part of the base boundary isolation wall is open, and the height of the base boundary isolation wall is less than a preset height threshold. A local parasitic conductor sheet is provided at the edge of the mounting base, and the local parasitic conductor sheet is a ring segment located at the azimuth corresponding to the damaged airspace of the antenna. The local parasitic conductor sheet is insulated from the mounting base. The damaged airspace of the antenna is the airspace affected by the satellite, which is obtained by co-simulating the installation scenario of the antenna and the satellite. The airspace affected by the satellite refers to the airspace where, when the antenna is directly installed on the mounting surface of the satellite, the satellite's metal structure will generate electromagnetic coupling, electromagnetic wave blockage, and surface current crosstalk with the antenna, causing pattern distortion, axial ratio deterioration, decreased circular polarization purity, and performance degradation in key coverage airspace in the local airspace of the antenna. A top bias loading plate is provided near the lower end of the four-armed helical radiator. The top bias loading plate is offset from the main axis of the antenna and is located in the azimuth corresponding to the damaged airspace of the antenna. The top bias loading plate is a local metal loading unit located near the lower end of the radiator. It adopts the form of a short sheet-shaped conductor. One end of the plate is connected to the helical arm segment of the four-armed helical radiator, and the other end is suspended or maintains a predetermined coupling gap with the nearby conductor, thereby forming a biased local loading path.

7. The design method of the spaceborne four-arm helical antenna as described in claim 6, characterized in that, The satellite platform boundary conditions include the available range of the mounting surface, the distance to the cabin edge, the support boundary, the solar panel boundary, and the relative orientation of the adjacent metal structure; The operating frequency band includes a first operating frequency band and a second operating frequency band, and the frequency of the first operating frequency band is greater than the frequency of the second operating frequency band. Before constructing the platform collaborative compensation structure based on the overall structure, the design method of the spaceborne four-arm helical antenna also includes: The lateral deployment mode of the four-armed spiral radiators is determined based on the available range of the mounting surface and the distance to the edge of the cabin. The power supply lead-out direction and local coupling branch arrangement of the power supply structure are adjusted according to the relative directions of the support boundary, the solar fin boundary and the adjacent metal structure. Adjust the multiple radiator parameters of the four-armed spiral radiator to achieve impedance matching in the first and second operating frequency bands; Adjusting multiple feeding parameters of the feeding structure to ensure that four channels with equal amplitude and sequential phase shift are formed in both the first and second operating frequency bands. Circular polarization excitation.

8. The design method of the spaceborne four-arm helical antenna as described in claim 7, characterized in that, The adjustment of multiple radiator parameters of the four-armed helical radiator to achieve impedance matching in the first and second operating frequency bands includes: Determine the value range of each of the radiator parameters; For each radiator parameter, multiple candidate values ​​are selected from the range of values ​​of the radiator parameter based on a preset step size, and these are used as the candidate set for the radiator parameter. Based on the candidate sets of each of the multiple radiator parameters, all possible combinations of values ​​for the multiple radiator parameters are determined to obtain multiple sets of radiator parameter combinations. The radiator parameters are iterated based on multiple combinations of the radiator parameters until the first preset condition is met. Each iteration of the radiator parameters includes the following steps: Select one radiator parameter combination from the multiple radiator parameter combinations that have never been used as the current radiator parameter combination; Based on the current combination of radiator parameters, a collaborative simulation of the antenna and the satellite installation scenario is performed to extract impedance characteristic data of the first operating frequency band and impedance characteristic data of the second operating frequency band. The impedance characteristic data of the first operating frequency band is compared with the preset impedance matching threshold, and the impedance characteristic data of the second operating frequency band is compared with the preset impedance matching threshold. The first preset condition is: the comparison results show that impedance matching is achieved in both the first and second operating frequency bands.

9. The design method of the spaceborne four-arm helical antenna as described in claim 7, characterized in that, The multiple feeding parameters of the feeding structure are adjusted to ensure that four channels with equal amplitude and sequential phase shift are formed in both the first and second operating frequency bands. The circular polarization excitation includes: Determine the value range for each of the aforementioned power supply parameters; For each of the aforementioned power supply parameters, multiple candidate values ​​are selected from the range of values ​​of the power supply parameter based on a preset step size, forming a candidate set for the power supply parameter. Based on the candidate sets of each of the multiple feed parameters, all possible combinations of values ​​for the multiple feed parameters are determined, resulting in multiple sets of feed parameter combinations; The feeding parameters are iterated based on multiple sets of feeding parameter combinations until the second preset condition is met. The steps for each iteration of the power supply parameters include: Select one set of feeder parameters from the multiple sets of feeder parameter combinations that have never been used as the current feeder parameter combination; Based on the current feed parameter combination, a collaborative simulation of the antenna and satellite installation scenario is performed to extract circular polarization excitation feature data of the first operating frequency band and the second operating frequency band; the circular polarization excitation feature data includes amplitude data and phase characteristic data; The second preset condition is: the circular polarization excitation characteristic data of the first operating frequency band shows that the feeding structure forms four equal-amplitude, sequentially phase-shifted channels in the first operating frequency band. The circular polarization excitation characteristic data, and the circular polarization excitation characteristic data of the second operating frequency band show that the feeding structure forms four equal amplitude, sequentially phase-shifted channels in the second operating frequency band. Circular polarization excitation characteristic data.

10. The design method of the spaceborne four-arm helical antenna as described in claim 6, characterized in that, After constructing the platform collaborative compensation structure based on the overall structure, it also includes: The antenna and satellite installation scenario are co-simulated to extract the gain, axial ratio, radiation pattern, and back radiation gain in the damaged airspace. Calculate the first gain difference between the gain in the damaged airspace and the initial gain before compensation; the initial gain before compensation is the gain in the damaged airspace obtained by co-simulating the antenna and the satellite installation scenario before constructing the platform co-compensation structure. The radiation pattern is compared with a preset reference radiation pattern, and the presence of distortion in the radiation pattern is determined based on the comparison results. Calculate the second gain difference between the initial back radiation gain before compensation and the back radiation gain; the initial back radiation gain before compensation is the back radiation gain obtained by co-simulating the antenna and the satellite installation scenario before constructing the platform co-compensation structure. If the first gain difference is less than a preset first threshold, the axis ratio in the damaged spatial domain is greater than a preset axis ratio threshold, the radiation pattern has distortion, or the second gain difference is less than a preset second threshold, then multiple compensation parameters of the platform collaborative compensation structure are adjusted so that the first gain difference is greater than or equal to the preset first threshold, the axis ratio in the damaged spatial domain is less than or equal to the preset axis ratio threshold, the radiation pattern has no distortion, and the second gain difference is greater than or equal to the preset second threshold.

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