Design method of spaceborne elliptical beam reflector and its satellite reflector antenna

Abstract

This application provides a design method for a spaceborne elliptical beam reflector and its satellite reflector antenna, relating to the field of spaceborne communication technology. The method involves obtaining preset operating parameters for the reflector antenna; calculating the primary and secondary primary curves according to preset Cassegrain forms based on these parameters; shaping the primary and secondary primary curves using preset primary aperture distribution functions, preset feed distribution functions, and preset transition functions based on the feed angle and edge illumination level to obtain the primary and secondary reflectors; constructing a simulation model and simulating it to obtain the simulated antenna performance; and optimizing the primary and secondary reflectors by adjusting at least one parameter of the primary aperture distribution function, the transition function, and / or the structural parameters of the supporting structure when the antenna performance does not meet preset specifications, regenerating the primary and secondary reflectors until the antenna performance meets the preset specifications, thereby improving overall efficiency and reducing sidelobes.

Description

Technical Field

[0001] This application relates to the field of spaceborne communication technology, specifically to a design method for a spaceborne elliptical beam reflector and its satellite reflector antenna. Background Technology

[0002] In the field of satellite communications, spectrum resources are becoming increasingly scarce, and orbital positions are becoming increasingly congested. Against this backdrop, reducing antenna sidelobes has become a key indicator for minimizing interference with neighboring satellites and improving communication quality. At the same time, improving aperture efficiency is also crucial, meaning that higher signal gain can be achieved while keeping antenna size and transmit power constant. This is of paramount importance for satellite platforms that are highly sensitive to cost and weight.

[0003] In related technologies, axisymmetric reflector design methods are relatively mature for reflector antenna design. However, when it comes to elliptical aperture / elliptical beam reflector antennas, the available solutions are relatively limited. For elliptical aperture reflector designs, most current methods employ axisymmetric annular focal reflectors or cutting the Cassegrain primary reflector. However, these design methods suffer from severe leakage, resulting in low overall efficiency and difficulty in guaranteeing antenna sidelobe performance. Summary of the Invention

[0004] To address the aforementioned issues, this application provides a design method for a spaceborne elliptical beam reflector and its satellite reflector antenna, which can improve overall efficiency and reduce sidelobes.

[0005] The technical solution of this application embodiment is as follows:

[0006] In a first aspect, embodiments of this application provide a design method for a spaceborne elliptical beam reflector, applied to a satellite reflector antenna, the method comprising:

[0007] Obtain the preset operating parameters of the reflector antenna, including the feed angle, edge illumination level, preset main reflector aperture size, and preset sub-reflector aperture size;

[0008] Based on the feed angle, the edge illumination level, the aperture size of the main reflector and the aperture size of the sub-reflector, the primary original curve and the secondary original curve are calculated according to the preset Cassegrain form.

[0009] Based on the feed angle and the edge illumination level, the primary original curve and the secondary original curve are shaped using a preset primary aperture distribution function, a preset feed distribution function, and a preset transition function to obtain the primary reflecting surface corresponding to the primary original curve and the secondary reflecting surface corresponding to the secondary original curve, wherein the primary aperture distribution function is a polynomial function;

[0010] A simulation model is constructed using the main reflector, the sub-reflector, the feed angle, the edge illumination level, and a preset support structure for connecting the main reflector and the sub-reflector. The simulation model is then simulated to obtain the simulated antenna performance.

[0011] If the antenna performance does not meet the preset specifications, at least one of the parameters of the main aperture distribution function and the parameters of the transition function, and / or the structural parameters of the support structure are adjusted for optimization. The steps of shaping the main original curve and the sub-original curve using the preset main aperture distribution function, the preset feed distribution function and the preset transition function to obtain the main reflector corresponding to the main original curve and the sub-reflector corresponding to the sub-original curve are performed until the antenna performance meets the preset specifications.

[0012] In the above technical solution, preset operating parameters of the reflector antenna are obtained. These parameters include the feed angle, edge illumination level, preset main reflector aperture size, and preset sub-reflector aperture size. Obtaining these parameters provides a precise basis for subsequent antenna design. Based on the feed angle, edge illumination level, main reflector aperture size, and sub-reflector aperture size, the primary and secondary original curves are calculated according to a preset Cassegrain form. The physical and electromagnetic characteristic parameters are transformed into specific geometric curves using the Cassegrain form, providing a basic geometric shape for subsequent antenna reflector shaping. Based on the feed angle and edge illumination level, the primary and secondary original curves are shaped using a preset main aperture distribution function, a preset feed distribution function, and a preset transition function to obtain the primary reflector corresponding to the primary original curve and the sub-reflector corresponding to the sub-reflector corresponding to the sub-reflector. The primary aperture distribution function is a polynomial function. Through the synthesis of the above multiple functions... This collaborative approach yields high-performance primary and secondary reflectors, improving the overall antenna performance. A simulation model is constructed using the primary and secondary reflectors, feed angle, edge illumination level, and a pre-defined support structure connecting them. Simulation of this model yields simulated antenna performance, allowing for rapid acquisition of various performance indicators that directly reflect the antenna design's quality, providing clear direction and basis for subsequent optimization. If the antenna performance does not meet the pre-defined specifications, optimization is achieved by adjusting at least one parameter of the primary aperture distribution function, the transition function, and / or the structural parameters of the support structure. This involves shaping the primary and secondary original curves using the pre-defined primary aperture distribution function, feed distribution function, and transition function to obtain the primary reflector corresponding to the primary curve and the secondary reflector corresponding to the secondary curve, continuing until the antenna performance meets the pre-defined specifications. Through continuous iteration, the antenna design gradually approaches the pre-defined specifications, ensuring the final reflector antenna exhibits excellent performance, improving overall performance and reducing sidelobes.

[0013] In summary, the Cassegrain form is used to transform the physical and electromagnetic parameters in the operating parameters into specific geometric curves. Various functional forms, such as the feed distribution function, principal aperture distribution function, and transition function, are employed for shaping to improve the overall antenna performance. The shaped data is then simulated to quickly calculate performance indicators. Based on these indicators, the various functional forms are adjusted. Through multiple iterations, an antenna design that meets the specifications can be obtained, ensuring that the final reflector antenna has excellent performance, improving overall performance and reducing sidelobes.

[0014] Secondly, embodiments of this application provide a satellite reflector antenna, which includes a main reflector, a sub-reflector, a support structure, and a feed source.

[0015] The support structure connects the main reflector and the sub-reflector, or the support structure connects the sub-reflector and the feed source;

[0016] The primary reflector, the secondary reflector, and the support structure are constructed by performing any one of the methods provided in the first aspect.

[0017] Thirdly, embodiments of this application provide an electronic device including a processor, a memory, a user interface, a communication bus, and a network interface. The processor, the memory, the user interface, and the network interface are respectively connected to the communication bus. The memory is used to store instructions. The user interface and the network interface are used to communicate with other devices. The processor is used to execute the instructions stored in the memory to cause the electronic device to perform the method described in any one of the first aspects.

[0018] Fourthly, embodiments of this application provide a computer-readable storage medium storing instructions that, when executed, perform the method described in any one of the methods provided in the first aspect above.

[0019] In summary, one or more technical solutions provided in the embodiments of this application have at least the following technical effects or advantages:

[0020] 1. By employing the Cassegrain form to transform the physical and electromagnetic parameters in the operating parameters into specific geometric curves, and using various function forms such as the feed distribution function, principal aperture distribution function, and transition function for shaping, the overall performance of the antenna can be improved. The shaped data is then simulated to quickly calculate performance indicators, and the aforementioned function forms can be adjusted based on these indicators. Through multiple iterations, an antenna design that meets the specifications can be obtained, ensuring that the final reflector antenna has excellent performance, improving overall performance and reducing sidelobes. Therefore, this effectively solves the problem in related technologies where the design process of elliptical beam reflector antennas results in a long-axis sidelob design of only -14dB and a short-axis sidelob design of only -12dB, indicating a high sidelob ratio that limits the application range and results in low overall performance.

[0021] 2. By judging the shape of the three-dimensional structure of the main surface, if it exceeds the preset reflective surface size, the parameters of the transition function are adjusted so that the generated main reflective surface can meet the antenna outline size requirements.

[0022] 3. Using antenna gain and sidelobe performance as parameters, the parameters of different functions are adjusted to optimize performance under various conditions where the preset performance is not met. Through multiple iterations, the overall performance is improved and the sidelobe is reduced.

[0023] 4. By combining multiple distribution functions with the support structure, adjusting the shape of the support structure according to changes in indicators, and combining these adjustments with the aforementioned multiple distribution functions, the sidelobes of the elliptical aperture reflector antenna achieve -15dB, and the aperture efficiency reaches 60%. Compared to existing technologies where the short-axis sidelobes are -12dB and the long-axis sidelobes are -14dB, achieving -15dB for both the long-axis and short-axis sidelobes represents a significant improvement for satellite reflector antennas, signifying a performance leap. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the structure of a satellite reflector antenna provided in one embodiment of this application;

[0025] Figure 2 This is a flowchart illustrating a design method for a spaceborne elliptical beam reflector provided in one embodiment of this application;

[0026] Figure 3 This is a schematic diagram of a Cassegrain-type elliptical beam, illustrating a design method for a spaceborne elliptical beam reflector provided in one embodiment of this application.

[0027] Figure 4 This is a schematic diagram of the main surface three-dimensional structure constraint of the design method of the spaceborne elliptical beam reflector provided in one embodiment of this application;

[0028] Figure 5 This is a schematic diagram of the main and secondary reflector structures of a design method for a spaceborne elliptical beam reflector provided in one embodiment of this application;

[0029] Figure 6 This is a schematic diagram of the support structure for a design method of a spaceborne elliptical beam reflector provided in one embodiment of this application;

[0030] Figure 7(a) is a schematic diagram of the major axis result of the design method of the spaceborne elliptical beam reflector provided in an embodiment of this application at an operating frequency of 41.5 GHz;

[0031] Figure 7(b) is a schematic diagram of the short axis result of the design method of the spaceborne elliptical beam reflector provided in an embodiment of this application at an operating frequency of 41.5 GHz;

[0032] Figure 8(a) is a schematic diagram of the major axis result of the design method of the spaceborne elliptical beam reflector provided in an embodiment of this application at a working frequency of 62.7 GHz;

[0033] Figure 8(b) is a schematic diagram of the short axis result of the design method of the spaceborne elliptical beam reflector provided in an embodiment of this application at an operating frequency of 62.7 GHz;

[0034] Figure 9 This is a schematic diagram of the design device for a spaceborne elliptical beam reflector provided in one embodiment of this application;

[0035] Figure 10 This is a schematic diagram of an electronic device structure provided in one embodiment of this application. Detailed Implementation

[0036] To enable those skilled in the art to better understand the technical solutions in this specification, the technical solutions in the embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments.

[0037] In the description of the embodiments of this application, the words "for example" or "for instance" are used to indicate examples, illustrations, or explanations. Any embodiment or design that is described as "for example" or "for instance" in the embodiments of this application should not be construed as being more preferred or advantageous than other embodiments or design options. Rather, the use of the words "for example" or "for instance" is intended to present the relevant concepts in a specific manner.

[0038] In the description of the embodiments of this application, the term "multiple" means two or more. For example, multiple systems means two or more systems, and multiple screen terminals means two or more screen terminals. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the indicated technical features. Thus, a feature defined with "first" or "second" may explicitly or implicitly include one or more of that feature. The terms "comprising," "including," "having," and variations thereof all mean "including but not limited to," unless otherwise specifically emphasized.

[0039] In related technologies, the support structure has a significant degrading effect on the antenna radiation pattern (causing scattering and obstruction). Traditional designs often optimize the ideal reflector first and then add the support structure to mitigate performance losses, without adjusting the support structure itself, thus failing to achieve a synergistic improvement in overall performance and reduction of sidelobes.

[0040] Based on this, embodiments of this application provide a design method for a spaceborne elliptical beam reflector and its satellite reflector antenna, electronic equipment, and readable storage medium. The design method first obtains preset operating parameters for the reflector antenna, including the feed angle, edge illumination level, preset main reflector aperture size, and preset sub-reflector aperture size. Obtaining these parameters provides a precise basis for subsequent antenna design. Based on the feed angle, edge illumination level, main reflector aperture size, and sub-reflector aperture size, the primary and secondary original curves are calculated according to a preset Cassegrain form. The physical and electromagnetic characteristic parameters are transformed into specific geometric curves using the Cassegrain form, providing a basic geometric shape for subsequent antenna reflector shaping. Based on the feed angle and edge illumination level, the primary and secondary original curves are shaped using a preset main aperture distribution function, a preset feed distribution function, and a preset transition function to obtain the primary reflector corresponding to the primary original curve and the secondary reflector corresponding to the secondary original curve. The antenna design involves several steps. First, the main reflector aperture distribution function is a polynomial function. Through the combined effect of these multiple functions, high-performance main and sub-reflectors can be obtained, improving the overall antenna performance. A simulation model is constructed using the main reflector, sub-reflector, feed angle, edge illumination level, and a pre-defined support structure connecting the main and sub-reflectors. Simulation of this model yields the simulated antenna performance. This simulation allows for the rapid acquisition of various antenna performance indicators, which directly reflect the quality of the antenna design, providing clear direction and basis for subsequent optimization. If the antenna performance does not meet the pre-defined specifications, at least one parameter of the main reflector aperture distribution function, the transition function, and / or the structural parameters of the support structure is adjusted for optimization. This involves shaping the original main and sub-reflector curves using the pre-defined main reflector aperture distribution function, feed angle, and transition function to obtain the main reflector curve corresponding to the original main reflector curve and the sub-reflector curve corresponding to the original sub-reflector curve. This process continues until the antenna performance meets the pre-defined specifications. Through continuous iteration, the antenna design can be gradually approached to meet the preset specifications, ensuring that the final reflector antenna has excellent performance, which can improve the overall performance and reduce sidelobes.

[0041] It should be noted that this design method for a spaceborne elliptical beam reflector is used in spaceborne communication systems, specifically for Q / V / E high-frequency antennas on satellites. These antennas require precise signal coverage of ground areas with a specific elliptical beam. The aforementioned design method can reduce sidelobes to -15dB, representing a significant leap forward in spaceborne communication.

[0042] The technical solutions provided in the embodiments of this application will be further described below with reference to the accompanying drawings.

[0043] Reference Figure 1 , Figure 1This paper presents a simulated overall model of a satellite reflector antenna. The satellite's reflector antenna is an elliptical beam reflector antenna, comprising a feed, a main reflector, a sub-reflector, and a support structure. The support structure can be mounted on either the feed or the main reflector, connecting the main and sub-reflectors. The support structure has a teardrop-like shape, which can be modified by tightening or loosening the support structure near the feed end, thereby reducing sidelobe reflections at the main reflector. The specific process is as follows: the feed emits a beam, which is reflected by the sub-reflector to the main reflector. By adjusting the parameters of various distribution functions, the beam reflected from the sub-reflector to the main reflector is distributed across the entire aperture, ensuring an aperture efficiency of 60%. Combined with the support structure, the beam is then reflected by the main reflector to the beam coverage area. This improves overall efficiency and ensures that the sidelobe of the elliptical aperture reflector antenna reaches -15dB. The main reflector, sub-reflector, and support structure are constructed using the design method for spaceborne elliptical beam reflectors described below.

[0044] Reference Figure 2 , Figure 2 This is a flowchart illustrating the design method for a spaceborne elliptical beam reflector provided in this application embodiment. The design method for a spaceborne elliptical beam reflector is applied to a satellite reflector antenna. The design method is executed by a processor in an electronic device or a readable storage medium, and includes steps S100, S200, S300, S400, and S500.

[0045] Step S100: Obtain the preset operating parameters of the reflector antenna, including the feed illumination angle, edge illumination level, preset main reflector aperture size, and preset sub-reflector aperture size.

[0046] In one embodiment, the operating parameters include the feed angle, the edge illumination level, the preset primary reflector aperture size, and the preset secondary reflector aperture size.

[0047] The feed angle refers to the angular range from which the beam of the "feed," acting as the energy source in the antenna system, covers the edge of the sub-reflector, determining the relative geometric layout of the feed and the sub-reflector. If the angle is too large, energy will overflow from the sub-reflector, causing loss (overflow loss); if it is too small, the sub-reflector will not be fully utilized, leading to reduced efficiency. In this embodiment, the feed angle is set to 45° to improve efficiency.

[0048] Edge illumination level refers to the ratio of the field strength (or power) of the electromagnetic wave radiated from the feed at the edge of the subreflector to the field strength (or power) at the center of the subreflector. It is usually expressed in decibels (dB) and is a negative value. A lower edge illumination level (e.g., -20dB, very dark edges) is beneficial for reducing antenna sidelobes, but it will sacrifice some aperture efficiency; a higher edge illumination level (e.g., -8dB, very bright edges) is more efficient, but the sidelobes will be correspondingly increased. In this embodiment, the edge illumination level is set to -10dB.

[0049] The main reflector aperture size is determined by the space constraints of the satellite fairing or the ground mounting platform. The sub-reflector aperture size is determined by the distance from the feed to the sub-reflector surface and the overall structural compactness. In this embodiment, the main reflector aperture size is set to 500mm*315mm, the major axis size of the main surface is 500mm, the minor axis size is 315mm, and the sub-reflector aperture size is selected as 56mm, etc.

[0050] The operating parameters also include the operating frequency, which is set to 41GHz~64GHz. The feed is designed using the feed angle, edge illumination level, and operating frequency as input conditions. By setting these parameters, the preset operating parameters of the reflector antenna are obtained through preset data readout functions, thus defining the initial boundary conditions and providing prerequisites for subsequent calculations and optimization functions. The preset data readout functions include the `read()` and `open()` functions.

[0051] Step S200: Based on the feed angle, edge illumination level, main reflector aperture size, and sub-reflector aperture size, calculate the main original curve and sub-original curve according to the preset Cassegrain form.

[0052] In one embodiment, the Cassegrain form consists of a parabolic primary reflector and a hyperboloid secondary reflector. Based on the aperture sizes of the primary and secondary reflectors, and the desired antenna focal length ratio (F / D), the focal length F of the equivalent parabola and the positions of the two foci of the hyperboloid (one coinciding with the parabola's focus, and the other at the feed phase center) are calculated. Then, using the standard quadratic equation in analytical geometry, a set of two-dimensional cross-sectional coordinates for the primary primitive curve (parabola) and the secondary primitive curve (hyperbola) is generated. The resulting combination of primitive curves, under the geometrical optics approximation, can convert a spherical wave emitted from one focus of the hyperboloid (at the feed) into a plane wave parallel to the antenna axis after two reflections.

[0053] The parameters in step S100 are set as follows: feed illumination angle is 45°, edge illumination level is -10dB, operating frequency is 41GHz~64GHz, and main reflector aperture size is 500mm*315mm. These parameters are then substituted into the Cassegrain form to calculate the main original curve and the secondary original curve, providing a basis for subsequent shaping.

[0054] according to Figure 3 As shown, the primary and secondary original curves for constructing the Cassegrain form are displayed. It can be seen that the beam emitted by the elliptical beam reflector antenna through the feed can cover both the secondary and primary reflectors.

[0055] Step S300: Based on the feed angle and edge illumination level, the main original curve and the secondary original curve are shaped using a preset main aperture distribution function, a preset feed distribution function, and a preset transition function to obtain the main reflecting surface corresponding to the main original curve and the secondary reflecting surface corresponding to the secondary original curve. The main aperture distribution function is a polynomial function.

[0056] In one embodiment, the direction of the feed illumination angle is set to the central direction at (0,0) so that the transmitted beam can be reflected uniformly. Then, the primary and secondary original curves are shaped using a preset primary aperture distribution function, a preset feed distribution function, and a preset transition function to obtain the primary and secondary reflectors. The above shaping process breaks the inherent aperture field distribution (usually strong in the center and weak at the edges) in classical Cassegrain antennas. By perturbating and correcting the shape of the primary and secondary reflectors (i.e., "shaping"), energy is actively redistributed to achieve advanced performance goals such as "low sidelobes," "high efficiency," or "specific coverage area."

[0057] Specifically, the primary and secondary original curves are shaped using a preset primary aperture distribution function, a preset feed distribution function, and a preset transition function to obtain the primary reflecting surface corresponding to the primary original curve and the secondary reflecting surface corresponding to the secondary original curve, including but not limited to the following steps:

[0058] Step S310: Normalize the feed illumination angle using the feed distribution function to obtain the normalized electric field strength.

[0059] In some possible embodiments of this application, the feed distribution function is expressed as: f(θ)=exp(-p*(θ / θ) m ) 2 );

[0060] Where f(θ) is the normalized electric field strength, θ is the feed angle, and θ m p is the preset illumination angle, which adjusts the beam shape parameters.

[0061] Specifically, the above describes the normalization process for the Gaussian model. θ represents the angle and direction, measuring the degree to which a given direction deviates from the feed's central axis. When θ = 0°, it represents the direction directly in front of the feed, the "axis direction" where energy is most concentrated. When θ > 0°, it represents a direction deviating from the center. The larger θ is, the farther the direction deviates from the center. m The preset illumination angle is the reference angle defining the Gaussian beamwidth. The maximum angle of illumination from the feed is set to 45°, serving as a normalization factor for the feed illumination angle. p is the taper factor or shaping parameter; a larger p results in a sharp decrease in the function, forming a narrower, more concentrated beam, while a smaller p exponent results in a slower decrease in the function, forming a wider, more diffuse beam. The value of parameter P is determined by the feed illumination angle and the edge illumination level. When the feed edge illumination level is -10dB, θ... m When the angle is 45°, the value of P is calculated to be 1.0362 according to the formula.

[0062] Set the edge illumination level to -10dB, p to 1.0362, and θ to... m The angle is set to 45°. By substituting the feed distribution function into the feed illumination angle, the corresponding electric field intensity in different deviations from the center can be obtained, thus yielding the normalized electric field intensity, which is beneficial for subsequent shaping.

[0063] It should be noted that the feed distribution function can also be a cosine distribution function, specifically expressed as: f(θ) = cos p(θ) Where f(θ) is the normalized electric field strength, θ is the feed illumination angle, and p is the beamforming parameter. Similar to the above formula, the value of parameter P is related to the edge illumination level of the feed. When the edge illumination level of the feed is -10dB, P is 1.0362. The above normalization process provides the basic data source for subsequent beamforming.

[0064] Step S320: The aperture size of the main reflecting surface is set using the main surface aperture distribution function to obtain the energy distribution at the aperture position.

[0065] In some possible embodiments of this application, the formula for the main aperture distribution function is expressed as: y=a0x 0 +a1x 1 +a2x 2 +...anx n ;

[0066] Where ai is the parameter of the principal aperture distribution function, and x i Let y be the position of the aperture, and y be the electric field amplitude corresponding to the position of the aperture, i = 0, 1, 2, ..., n.

[0067] Specifically, based on the elliptical beam antenna, a two-dimensional coordinate system is established with the center of the elliptical aperture as the origin. u represents the direction of the major axis of the ellipse, and v represents the direction of the minor axis of the ellipse. The coordinates of any point on the aperture can be represented by (u, v). The intensity value of each point on the elliptical aperture is characterized by the principal aperture distribution function, which provides a basis for subsequent shaping.

[0068] It should be noted that the positions can also be normalized to make the above formula independent of the specific antenna size. The specific normalization process is as follows: taking the main reflector aperture size as 500mm*315mm as an example, divide the major axis radius of 500mm by 2 and the minor axis radius of 315mm by 2 to obtain the normalization factor. Divide each position coordinate by the above normalization factor to normalize.

[0069] It should also be noted that the principal aperture distribution function is in polynomial form. This polynomial can be a continuous power-law polynomial or a polynomial containing only even-degree terms. In this embodiment, it is a continuous power-law polynomial. The values ​​of a0, a1, a2, ..., an are represented by the major and minor axes. The minor axis polynomial is [1.02, -13.76, 143.27, -590.27, 1236.75, -1415.5, 845.18, -206.0], and the major axis polynomial parameters are [0.8, -6.18, 81.08, -369.57, 845.35, -1073.7, 720.6, -197.83].

[0070] The principal surface distribution function and feed distribution function are mainly used for reflector surface shaping calculations. The specific calculation formulas are existing technologies and will not be elaborated here. Substituting the original reflector surface curve parameters, feed distribution function, and principal surface aperture distribution function into the shaping formula of the transition function yields the major and minor axis shaped surfaces. The specific calculation process is also existing technology. In this embodiment, the feed distribution function, principal surface aperture distribution function, and transition function are combined, along with the support structure, and subsequent comprehensive adjustments are made to improve overall efficiency and reduce the influence of sidelobes.

[0071] Step S330: Based on the mapping relationship between the normalized electric field strength and the energy distribution at the aperture position, shaping is performed to obtain the shaped principal surface curve and the shaped secondary surface curve. The shaped principal surface curve and the shaped secondary surface curve are then used to construct the principal surface three-dimensional structure and the secondary surface three-dimensional structure using a transition function.

[0072] In some possible embodiments of this application, an energy mapping relationship is constructed between the normalized electric field strength and the energy distribution at the aperture position according to the law of conservation of energy. Based on the above mapping relationship, a differential equation is constructed, and a system of differential equations is solved to calculate the shaped principal surface curve and the shaped secondary surface curve. The shaped principal surface curve and the shaped secondary surface curve include a major axis and a minor axis, so that a three-dimensional surface can be constructed on the shaped major axis and minor axis using a transition function.

[0073] The specific process can be divided into the following steps: According to the law of conservation of energy, the total power emitted from the feed source must be equal to the total power passing through the aperture plane. Then, a differential relationship between θ and the principal aperture r is established, and differential calculations are performed using Leibniz's differential law. Next, the profile of the reflecting surface is iteratively solved using the "equal optical path principle" and "Snell's law" to obtain the shaped curve. Finally, calculations are performed using the shaped curve to obtain a three-dimensional structure composed of discrete points. The aforementioned Leibniz's differential law, "equal optical path principle," and "Snell's law" are existing technologies and will not be elaborated upon here.

[0074] Finally, a transition function is used to construct the 3D structures of the principal and secondary surfaces after shaping, respectively. Specifically, the major and minor axes of the principal and secondary surfaces are obtained, and the reflection position distributions corresponding to different normalized feed illumination angles are interpolated using the transition function. This allows for the 3D construction of the principal and secondary surfaces, resulting in 3D point cloud data. The 3D structures of the principal and secondary surfaces are then derived from this point cloud data.

[0075] In some possible embodiments of this application, the transition function may be a hyperelliptic transition function, an exponential transition function, a sine-square transition function, or a polynomial transition function. The specific function construction methods are discussed in detail in the prior art. In this embodiment, the transition function is chosen as a sine-square function, and the formula for the sine-square function is: S(ψ) = sin g (ψ);

[0076] Where g is the parameter of the transition function, ψ is the input object of the mapping, and S(ψ) is the output object of the mapping.

[0077] Specifically, the input objects of the mapping are the major and minor axes of the original curve corresponding to the feed illumination angle, and the output objects of the mapping are the energy distribution reflected on the main surface aperture at different feed illumination angles. Point cloud data is obtained by interpolation mapping through the sine square function. These point cloud data constitute the three-dimensional structure of the main and sub-surfaces, so that the light emitted from the feed can be reflected from the constructed three-dimensional structure of the main and sub-surfaces, thereby increasing the antenna gain and reducing the sidelobes.

[0078] The parameter g is adjustable, and by adjusting g, the "intensity" of the mapping relationship can be adjusted, representing the degree of energy contraction or mapping concentration. A larger g value results in a more abrupt transition from the major axis to the minor axis, a smaller reflector profile, and lower antenna gain; conversely, a smaller g value results in a slower transition, a larger reflector profile, and higher antenna gain. Subsequently, based on a comprehensive consideration of antenna gain and sidelobes, parameter g is adjusted to improve overall efficiency and reduce the impact of sidelobes.

[0079] In this embodiment, the value of g is limited by the main surface not exceeding the outer dimensions. The smaller the value of g, the larger the main surface profile, which means a larger size of the reflector and a higher theoretical gain. When g is 1.7, the main reflector profile exceeds the outer dimensions of the reflector. Therefore, g is set to a value greater than 1.7. During the optimization of the reflector antenna gain and sidelobe performance, the value of g needs to be optimized to ensure that both the antenna gain and sidelobe performance meet the requirements.

[0080] like Figure 4 As shown, when g is 1.7, the profile of the main reflector exceeds the dimensional limit of the reflector. In related technologies, the excess portion is typically cut off, which fails to improve antenna gain. By adjusting the value of g and the transition function to regenerate the three-dimensional structure, the antenna gain and sidelobes are ensured to meet the requirements.

[0081] Step S340: Based on the three-dimensional structure of the secondary surface and the three-dimensional structure of the primary surface, the primary reflecting surface and the secondary reflecting surface are obtained.

[0082] In one embodiment, a primary reflecting surface and a secondary reflecting surface are obtained based on the three-dimensional structure of the secondary surface and the three-dimensional structure of the primary surface, including but not limited to the following steps:

[0083] Step S341: Determine whether the three-dimensional structure of the main surface exceeds the preset outer dimensions of the reflective surface. If it exceeds the outer dimensions of the reflective surface, adjust the parameters of the transition function to generate the adjusted three-dimensional structure of the secondary surface and the adjusted three-dimensional structure of the main surface.

[0084] In some possible embodiments of this application, the preset reflector shape dimensions are set based on the satellite antenna's shape dimensions being smaller than the external carrying space, or determined based on the area of ​​the ground station antenna installation site, transportation conditions, and the size of the radome. First, it is determined whether the main surface three-dimensional structure exceeds the preset reflector shape dimensions. This determination ensures a reflector that meets the requirements. If it exceeds the reflector shape dimensions, it indicates that the main surface three-dimensional structure cannot meet the external rigid requirements. The excess portion may cause the satellite shape to exceed the envelope, affecting satellite stacking efficiency and increasing launch costs. In this case, the parameters of the transition function are adjusted, specifically g, by increasing g to ensure the main reflector contour meets the reflector shape dimension limitations. Then, based on the adjusted value, the transition function is recalculated to generate the adjusted secondary surface three-dimensional structure and the adjusted main surface three-dimensional structure.

[0085] Step S342: If the adjusted three-dimensional structure of the main surface does not exceed the outer dimensions of the reflective surface, the adjusted three-dimensional structure of the secondary surface is used as the secondary reflective surface, and the adjusted three-dimensional structure of the main surface is used as the main reflective surface.

[0086] In some possible embodiments of this application, if the adjusted primary three-dimensional structure does not exceed the outer dimensions of the reflector, it indicates that the generated adjusted secondary three-dimensional structure and the adjusted primary three-dimensional structure satisfy the outer dimensions of the reflector. The adjusted secondary three-dimensional structure is used as the secondary reflector, and the adjusted primary three-dimensional structure is used as the primary reflector, so that subsequent simulation can be performed to obtain the antenna performance of this parameter.

[0087] In other possible embodiments of this application, by adjusting the g-value once and determining whether the three-dimensional structure of the primary surface still exceeds the preset reflective surface dimensions, the adjustment calculation is performed again to generate the adjusted three-dimensional structure of the secondary surface and the adjusted three-dimensional structure of the primary surface. This process is repeated until the adjusted three-dimensional structure of the primary surface does not exceed the reflective surface dimensions, thus obtaining the primary reflective surface and the secondary reflective surface. The primary reflective surface and the secondary reflective surface, as... Figure 5 As shown.

[0088] Step S343: Determine whether the main surface three-dimensional structure exceeds the preset reflector surface dimensions. If it does not exceed the reflector surface dimensions, generate the secondary surface three-dimensional structure and the main surface three-dimensional structure. Use the secondary surface three-dimensional structure as the secondary reflector surface and the main surface three-dimensional structure as the primary reflector surface. This is for subsequent simulation to obtain the antenna performance of this parameter.

[0089] Step S400: Using the main reflector, sub-reflector, feed illumination angle, edge illumination level, and a preset support structure for connecting the main reflector and sub-reflector, a simulation model is constructed, and the simulation model is simulated to obtain the simulated antenna performance.

[0090] In one embodiment, electrical performance simulation is performed using electromagnetic simulation software. The simulation is conducted using the known main reflector, sub-reflector, feed angle, edge illumination level, and a preset support structure for connecting the main reflector and sub-reflector. The corresponding parameters are set according to the steps S100-S300 above, and the simulation model is simulated to obtain the antenna performance corresponding to each set parameter.

[0091] The above simulation records and saves the parameters set in the electromagnetic simulation software and the simulated antenna performance. The simulated antenna performance is then retrieved using a preset data read function to determine if it meets the requirements. The preset data read function is `read()`, but `open()` is also acceptable.

[0092] Step S500: If the antenna performance does not meet the preset specifications, at least one of the parameters of the main aperture distribution function and the parameters of the transition function, and / or the structural parameters of the support structure are adjusted for optimization. The steps of shaping the main original curve and the sub-original curve using the preset main aperture distribution function, the preset feed distribution function and the preset transition function are performed to obtain the main reflector corresponding to the main original curve and the sub-reflector corresponding to the sub-original curve, until the antenna performance meets the preset specifications.

[0093] In one embodiment, antenna performance includes antenna gain and sidelobe index, where antenna gain reflects the overall performance of the reflector antenna and sidelobe index reflects the degree of sidelobe influence of the reflector antenna.

[0094] Specifically, when the antenna performance does not meet the preset specifications, optimization is performed by adjusting at least one of the parameters of the main aperture distribution function, the parameters of the transition function, and / or the structural parameters of the supporting structure, including but not limited to the following steps:

[0095] Step S510: If the antenna gain is less than the preset gain threshold in the preset specifications, adjust the parameters of the transition function for optimization.

[0096] In some possible embodiments of this application, the preset gain threshold is the required gain value of the satellite's reflector antenna. If the antenna gain is less than the preset gain threshold in the preset specifications, it indicates that the electromagnetic simulation software has not met the requirements under the parameters set above. In this case, to increase the gain, the parameters of the transition function are adjusted and optimized by decreasing the value of parameter g, thereby increasing the profile of the main reflector surface and thus increasing the gain. Through the above parameter adjustment and optimization, the gain threshold meets the requirements.

[0097] Step S520: If the sidelobe index is greater than the preset sidelobe threshold in the preset index, adjust the parameters of the transition function and the parameters of the principal aperture distribution function for optimization.

[0098] In some possible embodiments of this application, the preset sidelobe thresholds can be set to -12dB for the short axis and -14dB for the long axis, or both the short and long axes can be set to -15dB. When the sidelobe index exceeds the preset sidelobe threshold, it indicates that the surrounding area may be affected. To reduce the impact of the sidelobes, the parameters of the multiplicity function and the principal aperture distribution function can be optimized, thereby adjusting their settings to reduce the sidelobe effect.

[0099] Step S530: When there is a support structure but the antenna performance does not meet the preset indicators, the structural parameters of the support structure are adjusted for optimization.

[0100] In one embodiment, when the antenna performance does not meet the preset specifications, the structural parameters of the support structure are adjusted for optimization, including but not limited to: the support structure is teardrop-shaped, and when the antenna gain is less than the gain threshold or the sidelobe index is greater than the sidelobe threshold, the width of the teardrop-shaped end near the feed source is adjusted.

[0101] Specifically, the support structure is teardrop-shaped; see [reference needed for details]. Figure 6 The support structure can be configured as either a sub-reflector supporting the main reflector or a sub-reflector supporting the feed. Taking the sub-reflector-to-main-reflector configuration as an example, the support structure should be as narrow as possible near the feed to reduce reflections onto the feed's backscatter pattern, thereby minimizing the support structure's impact on the antenna pattern. If the antenna gain is less than the gain threshold, or the sidelobe index is less than the sidelobe threshold, the width of the teardrop-shaped section near the feed can be adjusted to further reduce its impact on the antenna pattern.

[0102] It should be noted that if either the antenna gain or the sidelobe index fails to meet the conditions, the system will identify which of steps S510 and S520 the failed condition meets and make the corresponding adjustments and optimizations.

[0103] In one embodiment, when the antenna gain and sidelobe performance do not meet the requirements, the main aperture distribution function and transition function are first adjusted to determine if the antenna performance meets the requirements. If not, the support structure is adjusted. Through the above multi-layered adjustments, a gradual adjustment can be made, and the antenna can be quickly adjusted to meet the requirements.

[0104] In one embodiment, through the above adjustments and optimizations, the primary and secondary original curves are shaped using a preset primary aperture distribution function, a preset feed distribution function, and a preset transition function to obtain the primary reflector corresponding to the primary original curve and the secondary reflector corresponding to the secondary original curve, until the antenna performance meets the preset specifications. The corresponding parameter settings are recorded and saved to provide data support for the actual antenna construction.

[0105] In one embodiment, when both antenna gain and sidelobe performance meet the requirements, the corresponding parameter settings are recorded and saved to provide data support for the construction of the actual antenna.

[0106] Figures 7(a), 7(b), 8(a) and 8(b) show the simulation diagrams of the electromagnetic simulation software mentioned above. Specifically, the title is far-field directivity, the horizontal axis is angle in degrees, the vertical axis is decibel, the curve is the radiation pattern, the main lobe is the lobe corresponding to 0 degrees, and the side lobes are the small lobes on both sides.

[0107] Figure 7(a) shows the long-axis radiation pattern at an operating frequency of 41.5 GHz, with a main lobe amplitude of 42.2 dB, a main lobe direction of 0 degrees, an angular width of 0.9 degrees, and a side lobe level of -15.5 dB. These data indicate that the antenna has high gain, extremely high directional resolution, and strong anti-interference capabilities, effectively suppressing the effects of sidelobes.

[0108] Figure 7(b) shows the short-axis radiation pattern at an operating frequency of 41.5 GHz. The main lobe amplitude is 42.2 dB; the main lobe direction is 0 degrees; the angular width (3 dB) is 1.4 degrees; and the side lobe level is -16.1 dB. These data indicate that the antenna has high gain, extremely high directional resolution, and strong anti-interference capabilities, effectively suppressing the influence of sidelobes.

[0109] Figure 8(a) shows the long-axis radiation pattern at a working frequency of 62.7 GHz, with a main lobe amplitude of 46.4 dB, a main lobe direction of 0 degrees, an angular width of 0.6 degrees, and a side lobe level of -16.3 dB. These data indicate that the antenna has high gain, extremely high directional resolution, and strong anti-interference capabilities, effectively suppressing the effects of sidelobes.

[0110] Figure 8(b) shows the short-axis radiation pattern at a working frequency of 62.7 GHz, with a main lobe amplitude of 46.4 dB, a main lobe direction of 0 degrees, an angular width of 0.9 degrees, and a side lobe level of -15.6 dB. These data indicate that the antenna has high gain, extremely high directional resolution, and strong anti-interference capabilities, effectively suppressing the effects of sidelobes.

[0111] The above results demonstrate that, at different operating frequencies, the physical and electromagnetic parameters in the operating parameters are transformed into specific geometric curves using the Cassegrain form. Various functional forms, such as the feed distribution function, principal aperture distribution function, and transition function, are used for shaping. The shaped data is then simulated, and adjustments are made to these various functional forms based on performance indicators. Through multiple iterations, an antenna design that meets the specifications can be obtained, ensuring that the final reflector antenna has excellent performance, improving overall performance and reducing sidelobes.

[0112] like Figure 9As shown, this application provides a design device 100 for a spaceborne elliptical beam reflector. This device 100 is applied to a satellite reflector antenna. A data acquisition module 110 acquires preset operating parameters of the reflector antenna, including the feed angle, edge illumination level, preset main reflector aperture size, and preset sub-reflector aperture size. A curve generation module 120 calculates the primary and secondary original curves according to a preset Cassegrain form based on the feed angle, edge illumination level, main reflector aperture size, and sub-reflector aperture size. A shaping module 130 shapes the primary and secondary original curves based on the feed angle and edge illumination level, using a preset main surface aperture distribution function, a preset feed distribution function, and a preset transition function, to obtain the primary reflector antenna corresponding to the primary original curve. The primary reflector and the secondary reflector corresponding to the original curve are given, where the aperture distribution function of the primary reflector is a polynomial function. Simulation module 140 constructs a simulation model using the primary reflector, secondary reflector, feed angle, edge illumination level, and a preset support structure connecting the primary and secondary reflectors. The simulation model is then used to obtain the simulated antenna performance. Parameter adjustment module 150 optimizes the antenna performance if it does not meet preset specifications by adjusting at least one parameter of the primary aperture distribution function, the transition function, and / or the structural parameters of the support structure. This process involves shaping the primary and secondary original curves using the preset primary aperture distribution function, the preset feed distribution function, and the preset transition function to obtain the primary reflector corresponding to the primary curve and the secondary reflector corresponding to the secondary original curve, until the antenna performance meets the preset specifications.

[0113] It should be noted that the data acquisition module 110 is connected to the curve generation module 120, the curve generation module 120 is connected to the shaping module 130, the shaping module 130 is connected to the simulation module 140, and the simulation module 140 is connected to the parameter adjustment module 150. The above-mentioned design method for a spaceborne elliptical beam reflector is applied to the design device 100 for a spaceborne elliptical beam reflector. The design device 100 uses the Cassegrain form to transform the physical and electromagnetic characteristic parameters in the operating parameters into specific geometric curves, and employs various function forms such as the feed distribution function, the principal aperture distribution function, and the transition function for shaping to improve the overall performance of the antenna. The shaped data is then simulated to quickly calculate performance indicators, and the various function forms are adjusted based on these performance indicators. Through multiple iterations, an antenna design that meets the indicators can be obtained, ensuring that the final reflector antenna has excellent performance, improving overall performance and reducing sidelobes.

[0114] It should also be noted that the apparatus provided in the above embodiments is only illustrated by the division of the above functional modules. In actual applications, the above functions can be assigned to different functional modules as needed, that is, the internal structure of the device can be divided into different functional modules to complete all or part of the functions described above. In addition, the apparatus and method embodiments provided in the above embodiments belong to the same concept, and their specific implementation process can be found in the method embodiments, which will not be repeated here.

[0115] This application also discloses an electronic device. (See reference...) Figure 10 , Figure 10 This is a schematic diagram of an electronic device structure according to an embodiment of this application. The electronic device 500 may include: at least one processor 501, at least one network interface 504, a user interface 503, a memory 505, and at least one communication bus 502.

[0116] The communication bus 502 is used to enable communication between these components.

[0117] The user interface 503 may include a display screen and a camera. Optionally, the user interface 503 may also include a standard wired interface and a wireless interface.

[0118] The network interface 504 may optionally include a standard wired interface or a wireless interface (such as a Wi-Fi interface).

[0119] The processor 501 may include one or more processing cores. The processor 501 connects to various parts of the server using various interfaces and lines, and performs various server functions and processes data by running or executing instructions, programs, code sets, or instruction sets stored in memory 505, and by calling data stored in memory 505. Optionally, the processor 501 may be implemented using at least one hardware form of Digital Signal Processing (DSP), Field-Programmable Gate Array (FPGA), or Programmable Logic Array. The processor 501 may integrate one or a combination of several of the following: Central Processing Unit (CPU), Graphics Processing Unit (GPU), and Modem. The CPU primarily handles the operating system, user interface, and applications; the GPU is responsible for rendering and drawing the content required for display; and the modem handles wireless communication. It is understood that the modem may also be implemented as a separate chip without being integrated into the processor 501.

[0120] The memory 505 may include random access memory (RAM) or read-only memory. Optionally, the memory 505 may include a non-transitory computer-readable storage medium. The memory 505 may be used to store instructions, programs, code, code sets, or instruction sets. The memory 505 may include a program storage area and a data storage area, wherein the program storage area may store instructions for implementing an operating system, instructions for at least one function (such as touch function, sound playback function, image playback function, etc.), instructions for implementing the above-described method embodiments, etc.; the data storage area may store data involved in the above-described method embodiments, etc. Optionally, the memory 505 may also be at least one storage device located remotely from the aforementioned processor 501. (Refer to...) Figure 10 The memory 505, which serves as a computer storage medium, may include an operating system, a network communication module, a user interface module, and an application program for designing a spaceborne elliptical beam reflector.

[0121] exist Figure 10 In the illustrated electronic device 500, the user interface 503 is mainly used to provide an input interface for the user and to acquire user input data; while the processor 501 can be used to call an application program stored in the memory 505 that represents a design method for a spaceborne elliptical beam reflector. When executed by one or more processors 501, the electronic device 500 performs one or more methods as described in the above embodiments. It should be noted that, for the sake of simplicity, the foregoing method embodiments are all described as a series of actions. However, those skilled in the art should understand that this application is not limited to the described order of actions, because according to this application, some steps can be performed in other orders or simultaneously. Furthermore, those skilled in the art should also understand that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily essential to this application.

[0122] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0123] In the various embodiments provided in this application, it should be understood that the disclosed apparatus can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative; for instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some service interface; the indirect coupling or communication connection between apparatuses or units may be electrical or other forms.

[0124] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0125] Furthermore, the functional units in the various embodiments of this application can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0126] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage device (CMD). Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a memory and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods of the various embodiments of this application. The aforementioned memory includes various media capable of storing program code, such as USB flash drives, portable hard drives, magnetic disks, or optical disks.

[0127] The above are merely exemplary embodiments of this disclosure and should not be construed as limiting the scope of this disclosure. Any equivalent changes and modifications made in accordance with the teachings of this disclosure shall still fall within the scope of this disclosure. Other embodiments of this disclosure will readily conceive of those skilled in the art upon consideration of the specification and the disclosure of practical truths.

[0128] This application is intended to cover any variations, uses, or adaptations of this disclosure that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not described in this disclosure. The specification and embodiments are to be considered exemplary only, and the scope and spirit of this disclosure are defined by the claims.

Claims

1. A method of designing a space-borne elliptical wave beam reflector surface, characterized by, The method is applied to a reflector antenna of a satellite, and the method comprises the following steps: obtaining preset working parameters of the reflector antenna, wherein the working parameters comprise a feed irradiation angle, an edge irradiation level, a preset main reflector aperture size, and a preset sub-reflector aperture size; calculating a main original curve and a sub-original curve according to the feed irradiation angle, the edge irradiation level, the main reflector aperture size, and the sub-reflector aperture size in a preset Cassegrain form; performing shaping on the main original curve and the sub-original curve by using a preset main surface aperture distribution function, a preset feed distribution function, and a preset transition function according to the feed irradiation angle and the edge irradiation level, to obtain a main reflector corresponding to the main original curve and a sub-reflector corresponding to the sub-original curve, wherein the main surface aperture distribution function is a polynomial function; constructing a simulation model by using the main reflector, the sub-reflector, the feed irradiation angle, the edge irradiation level, and a preset support structure for connecting the main reflector and the sub-reflector, performing simulation on the simulation model, and obtaining a simulated antenna performance; in a case where the antenna performance does not meet preset indexes, adjusting at least one of parameters of the main surface aperture distribution function, parameters of the transition function, and / or structure parameters of the support structure, performing the step of performing shaping on the main original curve and the sub-original curve by using the preset main surface aperture distribution function, the preset feed distribution function, and the preset transition function to obtain the main reflector corresponding to the main original curve and the sub-reflector corresponding to the sub-original curve, until the antenna performance meets the preset indexes.

2. The method of claim 1, wherein, the step of performing shaping on the main original curve and the sub-original curve by using the preset main surface aperture distribution function, the preset feed distribution function, and the preset transition function to obtain the main reflector corresponding to the main original curve and the sub-reflector corresponding to the sub-original curve, comprises the following steps: performing normalization of the feed irradiation angle by using the feed distribution function to obtain a normalized electric field intensity; setting the main reflector aperture size by using the main surface aperture distribution function to obtain an aperture position energy distribution; performing shaping based on a mapping relationship between the normalized electric field intensity and the aperture position energy distribution to obtain a shaped main surface curve and a shaped sub-surface curve, and constructing a main surface three-dimensional structure and a sub-surface three-dimensional structure by using the transition function to the shaped main surface curve and the shaped sub-surface curve; obtaining the main reflector and the sub-reflector based on the sub-surface three-dimensional structure and the main surface three-dimensional structure.

3. The method of claim 2, wherein, the step of obtaining the main reflector and the sub-reflector based on the sub-surface three-dimensional structure and the main surface three-dimensional structure, comprises the following steps: determining whether the main surface three-dimensional structure exceeds a preset reflector contour size, and adjusting parameters of the transition function to generate an adjusted sub-surface three-dimensional structure and an adjusted main surface three-dimensional structure in a case where the main surface three-dimensional structure exceeds the preset reflector contour size. In a case where the adjusted main surface three-dimensional structure does not exceed the contour size of the reflecting surface, the adjusted secondary surface three-dimensional structure is taken as the secondary reflecting surface, and the adjusted main surface three-dimensional structure is taken as the main reflecting surface.

4. The method of claim 1, wherein, The antenna performance includes antenna gain and sidelobe index. The adjusting at least one of the parameter of the main surface aperture distribution function, the parameter of the transition function, and / or the structural parameter of the support structure in a case where the antenna performance does not satisfy the preset index includes: In a case where the antenna gain is less than a preset gain threshold value in the preset index, the parameter of the transition function is adjusted for optimization. In a case where the sidelobe index is greater than a preset sidelobe threshold value in the preset index, the parameter of the transition function and the parameter of the main surface aperture distribution function are adjusted for optimization. In a case where the antenna performance does not satisfy the preset index with the support structure, the structural parameter of the support structure is adjusted for optimization.

5. The method of claim 4, wherein, The adjusting the structural parameter of the support structure in a case where the antenna performance does not satisfy the preset index with the support structure includes: The support structure is a water-drop-like shape, and in a case where the antenna gain is less than the gain threshold value or the sidelobe index is greater than the sidelobe threshold value, the width of one end of the water-drop-like shape close to the feed source is adjusted.

6. The method according to any one of claims 1 to 5, characterized in that, The formula of the transition function is: S(ψ) = sin g (ψ); The transition function is g(ψ), where g is the parameter of the transition function, and ψ is a mapping input object.

7. The method according to any one of claims 1 to 5, characterized in that, The formula representation of the feed distribution function is: f(θ) = exp(-p*(θ / θ m ) 2 ) wherein f(θ) is a normalized electric field intensity, θ is the feed illumination angle, θ m is a preset illumination angle, and p is a beam wave shape parameter. The formula of the main surface aperture distribution function is: y = a0x 0 +a1x 1 +a2x 2 +...anx n ; Wherein, ai is the parameter of the main surface aperture distribution function, x i is the position of the aperture, y is the field strength amplitude corresponding to the position of the aperture, i=0, 1, 2,..., n.

8. A reflector antenna of a satellite, characterized in that The reflecting surface antenna includes a main reflecting surface, a secondary reflecting surface, a support structure, and a feed source, The support structure connects the main reflecting surface and the secondary reflecting surface, or the support structure connects the secondary reflecting surface and the feed source. The main reflecting surface, the secondary reflecting surface, and the support structure are configured by executing the method in any one of claims 1-7.

9. An electronic device, comprising: The electronic device includes a processor, a memory, a user interface, a communication bus, and a network interface, the processor, the memory, the user interface, and the network interface are connected with the communication bus, the memory is used to store instructions, the user interface and the network interface are used to communicate with other devices, and the processor is used to execute the instructions stored in the memory to enable the electronic device to execute the method in any one of claims 1-7.

10. A computer-readable storage medium, characterized in that, The computer readable storage medium stores instructions, and when the instructions are executed, the method in any one of claims 1-7 is executed.

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