An antenna selection and layout method, device and medium for a small satellite

Abstract

The application relates to the field of antennas, and discloses a small satellite antenna selection and layout method, device and medium. In the design process of the antenna layout, the whole-satellite antenna selection and layout are predicted and designed, electromagnetic compatibility analysis is performed in combination with antenna task requirements, an antenna layout design result is obtained, the antenna layout design result meets the antenna task requirements and can normally operate, the small satellite antenna applicability to specific tasks and electromagnetic compatibility problems can be solved, resource waste caused by subsequent design compensation can be avoided, and task failure can be avoided.

Description

Technical Field

[0001] This application relates to the field of antennas, and in particular to a method, apparatus and medium for antenna selection and layout of a small satellite. Background Technology

[0002] In artificial satellites, those weighing less than 1,000 kilograms are generally referred to as small satellites, based on their mass. Within a satellite system, the proper functioning of the antenna and antenna connection equipment is crucial; the inability of the antenna and receiver to receive signals constitutes a serious mission failure.

[0003] Choosing the right antenna type is crucial for meeting the diverse needs of different missions. Different antenna types have their own unique electrical properties, and selecting an unsuitable antenna type for a specific mission will result in wasted resources and costs, leading to less efficient and less effective missions.

[0004] Compared to large satellites, small satellites have a higher degree of integration and a greater functional density. A large number of satellite functional devices are installed in a small space, especially on the valuable outer surface of the satellite's cabin, which is equipped with various solar panels, sensors, baffles, antennas, and structural components. These devices compete for the optimal position based on their importance to the mission's success. Some device components can distort the ideal radiation pattern of the antenna, disrupt polarization, and affect the line-of-sight angle. This makes the electromagnetic compatibility problems of small satellite antennas more serious than those of large satellites. Furthermore, if the satellite antenna layout cannot meet the mission requirements, it is necessary to compensate by increasing the number of antennas or changing the antenna design, resulting in a waste of resources and even causing mission failure.

[0005] Therefore, providing a method for antenna selection and layout of small satellites, and designing an antenna layout scheme that meets the electromagnetic compatibility and mission requirements of satellites, is a technical problem that urgently needs to be solved by those in the field. Summary of the Invention

[0006] The purpose of this application is to provide a method for antenna selection and layout of small satellites that designs antenna layout schemes that meet satellite electromagnetic compatibility issues and mission requirements.

[0007] To address the aforementioned technical problems, this application provides a method for antenna selection and layout of a small satellite, comprising:

[0008] Obtain antenna task requirements;

[0009] Based on the antenna mission requirements, select a suitable antenna type and perform simulation design;

[0010] Determine whether the simulation design results meet the antenna mission requirements;

[0011] If the simulation design results meet the antenna mission requirements, obtain the initial design scheme based on the simulation design results;

[0012] Determine whether the initial design scheme meets the electromagnetic compatibility requirements;

[0013] If the initial design scheme meets the electromagnetic compatibility requirements, then the antenna layout design result is generated.

[0014] Preferably, in the method for selecting and arranging antennas for small satellites, obtaining the initial design scheme based on the simulation design results includes:

[0015] Obtain the antenna layout scheme based on the simulation design results;

[0016] Determine whether the antenna layout scheme meets the satellite electromagnetic compatibility requirements;

[0017] If the antenna layout scheme meets the satellite electromagnetic compatibility requirements, obtain the antenna installation and connection scheme based on the antenna layout scheme;

[0018] Determine whether the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite;

[0019] If the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite, the antenna layout design result is generated.

[0020] Preferably, in the method for selecting and arranging antennas for small satellites, after obtaining the antenna installation and connection scheme based on the antenna layout scheme, the method further includes:

[0021] Determine whether there is any field of view obstruction in the antenna installation and connection scheme;

[0022] If not, proceed to the step of determining whether the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite;

[0023] If so, return to the step of obtaining the antenna installation and connection scheme based on the antenna layout scheme.

[0024] Preferably, in the method for selecting and laying out the antenna for a small satellite, before obtaining the antenna installation and connection scheme based on the antenna layout scheme, the method further includes:

[0025] Determine whether the antenna layout scheme meets the antenna mission requirements;

[0026] If so, proceed to the step of obtaining the antenna installation and connection scheme based on the antenna layout scheme;

[0027] If not, return to the step of selecting a suitable antenna type and performing simulation design based on the antenna mission requirements.

[0028] Preferably, in the method for selecting and laying out the antenna for a small satellite, before generating the antenna layout design result, the method further includes:

[0029] Determine whether the antenna installation and connection scheme meets the antenna mission requirements;

[0030] If so, proceed to the step of generating the antenna layout design result;

[0031] If not, return to the step of obtaining the antenna installation and connection scheme based on the antenna layout scheme.

[0032] Preferably, in the method for selecting and arranging antennas for small satellites, the step of selecting a suitable antenna type and performing simulation design based on the antenna mission requirements includes:

[0033] Based on the antenna mission requirements, two wide-beam conical spiral antennas were selected as the spaceborne telemetry and control antennas, two ring-focal reflector antennas as the inter-satellite link antennas, one backfire double-arm spiral shaped antenna as the data transmission antenna, one multi-frequency microstrip antenna as the navigation and positioning antenna, one multi-frequency four-arm spiral antenna as the first load antenna, one planar antenna as the second load antenna, one normal-mode spiral antenna as the third load antenna, and one single-arm spiral antenna as the fourth load antenna for simulation design.

[0034] Preferably, in the antenna selection and layout method for the small satellite, the antenna layout scheme is as follows: one onboard telemetry and control antenna is installed on the satellite facing the ground, and another onboard telemetry and control antenna is installed on the satellite facing the sky; two inter-satellite link antennas are respectively located on two side panels of the satellite; the data transmission antenna is located at the edge of the ground-facing panel; the navigation and positioning antenna is installed at the edge of the satellite's sky-facing panel; the first payload antenna is located at the center of the satellite facing the ground; the four antenna elements of the second payload antenna are arrayed and installed at the four corners of the satellite facing the ground; the third payload antenna is located at the edge of the satellite's ground-facing panel; and the fourth payload antenna is located at the edge of the satellite's ground-facing panel.

[0035] Correspondingly, the antenna installation and connection scheme is as follows: two of the spaceborne telemetry and control antennas are mounted on the antenna support; two of the inter-satellite link antennas are mounted on the inclined support with a fixed angle to the satellite; the data transmission antenna is mounted on the antenna support; the navigation and positioning antenna is mounted on the cabin panel; the first load antenna is installed insulated from the cabin panel; the second load antenna is mounted on the cabin panel; the third load antenna is mounted on the inclined support with a fixed angle to the satellite; and the fourth load antenna is mounted on the cabin panel.

[0036] To address the aforementioned technical problems, this application also provides an antenna selection and layout device for small satellites, comprising:

[0037] The acquisition module is used to acquire antenna task requirements;

[0038] The simulation module is used to select an appropriate antenna type and perform simulation design based on the antenna mission requirements.

[0039] The first judgment module is used to determine whether the simulation design results meet the antenna task requirements; if the simulation design results meet the antenna task requirements, the first design module is triggered.

[0040] The first design module is used to obtain an initial design scheme based on the simulation design results;

[0041] The second judgment module is used to determine whether the initial design scheme meets the electromagnetic compatibility requirements; if the initial design scheme meets the electromagnetic compatibility requirements, the second design module is triggered.

[0042] The second design module is used to generate antenna layout design results.

[0043] To address the aforementioned technical problems, this application also provides an antenna selection and layout device for small satellites, comprising:

[0044] Memory, used to store computer programs;

[0045] A processor is used to implement the steps of the above-described method for antenna selection and layout of small satellites when executing the computer program.

[0046] To address the aforementioned technical problems, this application also provides a computer-readable storage medium storing a computer program, which, when executed by a processor, implements the steps of the above-described method for antenna selection and layout of small satellites.

[0047] This application provides a method for antenna selection and layout of a small satellite, comprising: obtaining antenna mission requirements; selecting a suitable antenna type based on the antenna mission requirements and performing simulation design; determining whether the simulation design results meet the antenna mission requirements; if the simulation design results meet the antenna mission requirements, obtaining an initial design scheme based on the simulation design results; determining whether the initial design scheme meets electromagnetic compatibility requirements; if the initial design scheme meets the electromagnetic compatibility requirements, generating an antenna layout design result. In the antenna layout design process, this application combines antenna mission requirements with electromagnetic compatibility analysis to obtain antenna layout design results, ensuring that the antenna layout design results meet the antenna mission requirements and can operate normally, avoiding resource waste or even mission failure caused by subsequent design compensation.

[0048] In addition, this application also provides an antenna selection and layout device for small satellites and a computer-readable storage medium, which correspond to the above method and have the same effect. Attached Figure Description

[0049] To more clearly illustrate the embodiments of this application, the accompanying drawings used in the embodiments 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.

[0050] Figure 1 A flowchart illustrating a method for antenna selection and layout of a small satellite, provided as an embodiment of this application;

[0051] Figure 2 A flowchart illustrating another method for antenna selection and layout of a small satellite provided in this application embodiment;

[0052] Figure 3 A flowchart illustrating another method for antenna selection and layout of a small satellite provided in this application embodiment;

[0053] Figure 4 A schematic diagram illustrating an example layout of a small satellite antenna provided in this application embodiment;

[0054] Figure 5 A structural diagram of an antenna selection and layout device for a small satellite provided in an embodiment of this application;

[0055] Figure 6 This is a structural diagram of another antenna selection and layout device for a small satellite provided in an embodiment of this application. Detailed Implementation

[0056] The technical solutions of the embodiments of this application 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. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of this application.

[0057] The core of this application is to provide a method for antenna selection and layout of small satellites.

[0058] To enable those skilled in the art to better understand the present application, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0059] Since the 1950s, space technology has continuously developed, and artificial Earth satellites have evolved into a series based on their application fields, including communication, meteorology, navigation, resource and environmental, military reconnaissance, and scientific research, and are developing towards high performance and high integration. With the comprehensive integration of satellite functions, satellite mass has also continuously increased, while the continuous improvement of rocket carrying capacity has provided a technological foundation for the development of large satellites. With the continuous development of satellite technology and applications, while demanding reduced satellite costs and risks, there is an urgent need to accelerate the satellite development and research cycle. This is especially true for dedicated satellites for single missions and satellite networking, which require satellite technologies with low investment and quick results. Small satellite technology has thus emerged. Small satellites are not simply small in mass, but rather feature highly integrated and automated technologies, especially the rapid development of computers, enabling the miniaturization of onboard control and processing computers. Small satellites can be rapidly developed from design, manufacturing, launch, to on-orbit operation, generally within less than twelve months. In small satellite antenna design, the choice of antenna type is crucial for the different requirements of different missions. Different types of antennas, such as microstrip antennas, horn antennas, and reflector antennas, have their own unique electrical properties. If an unsuitable antenna type is selected for a specific mission, it will be counterproductive and waste onboard resources and costs.

[0060] Within a satellite system, the proper functioning of antenna connection equipment is crucial. If the receiver connected to the antenna fails to receive a signal, it constitutes a significant mission failure. Therefore, antenna layout is the primary task for electromagnetic compatibility within the system.

[0061] When antennas are placed close together, electromagnetic coupling will occur between them, meaning one antenna will induce an electromotive force on the other. When electromagnetic coupling exists, the antenna's directivity pattern may be distorted. In addition to radiating useful signals, antennas will also radiate interference signals induced by other antennas. Therefore, we must consider the coupling between them when arranging antenna positions. Satellites typically carry multiple transmitting antennas, as well as high-sensitivity receiving antennas, including some radio frequency remote sensing receivers. Due to the coupling between the onboard receiving and transmitting antennas, these radio transmitting and receiving devices generate very complex electromagnetic interference. Moreover, due to the open nature of the onboard antennas, this coupling cannot be reduced by methods such as shielding or grounding. If this interference is only discovered late in the satellite's development, it will become a serious electromagnetic interference problem that disrupts the overall operation of the satellite. For spaceborne antennas, it is difficult to achieve the isolation requirements of the antenna system by increasing the installation distance or installing them back-to-back. This is because there are many types of spaceborne antenna groups. They not only work simultaneously and point in the same direction, but also have the same polarization direction and overlapping operating frequency bands. In addition, the extremely limited space on the satellite restricts the isolation requirements for the antenna installation position. Therefore, certain measures must be taken in the early design stage to meet the system's isolation requirements between antennas.

[0062] Compared to large satellites, small satellites have a higher degree of integration and functional density. A large number of functional devices are housed within a confined space, particularly on the valuable outer surface of the satellite's main body, which is equipped with various solar panels, sensors, baffles, antennas, and structural components. These devices compete for optimal positions based on their importance to mission success. Some components can distort the ideal antenna radiation pattern, disrupt polarization, and affect the line-of-sight angle. This results in more severe electromagnetic compatibility (EMC) issues for small satellite antennas compared to large satellites. Furthermore, if the satellite antenna layout cannot meet mission requirements, compensation must be made by increasing the number of antennas or modifying the antenna design, leading to a waste of valuable onboard resources and significant cost, potentially even affecting mission success or failure.

[0063] To address the aforementioned technical problems, this embodiment provides a method for antenna selection and layout for small satellites. Figure 1 A flowchart illustrating a method for antenna selection and layout of a small satellite, as provided in this application embodiment, is shown below. Figure 1 As shown, it includes:

[0064] S11: Obtain antenna task requirements;

[0065] S12: Select the appropriate antenna type based on the antenna mission requirements and perform simulation design;

[0066] Upon receiving the antenna mission requirements, the appropriate antenna type is selected based on these requirements. For example, a spaceborne telemetry and control antenna, together with a ground-based telemetry and control antenna, establishes a stable and reliable radio transmission channel that meets predetermined requirements, ensuring the transmission, reception, and delivery of satellite-to-ground wireless telemetry, remote control, and tracking information. A data transmission antenna is used for data transmission from the satellite to the ground station. An inter-satellite link antenna is used for data transmission between satellites. A navigation and positioning antenna is used to receive space-based GNSS signals to achieve satellite attitude determination, orbit determination, time synchronization, and absolute and relative positioning functions. Various payload antennas are used to transmit communication service signals provided by the satellite to the user and to receive communication service signals sent by the user to the satellite. Based on the actual antenna mission requirements, a suitable antenna type is selected, followed by simulation design and configuration of antenna parameters and other data.

[0067] S13: Determine whether the simulation design results meet the antenna mission requirements;

[0068] Step S13 determines whether the simulation design results meet the communication performance requirements of the antenna mission. During the simulation design process, the antenna parameters may not meet the antenna mission requirements, such as whether the gain pattern meets the link margin, whether the standing wave ratio meets the requirements, and other specific requirements. Therefore, step S13 determines whether the simulation design results meet the antenna mission requirements. If not, the process returns to step S12 and the simulation design is repeated.

[0069] If the simulation design results meet the antenna mission requirements, proceed to step S14: obtain the initial design scheme obtained based on the simulation design results;

[0070] Based on the antenna simulation design results that meet the antenna mission requirements, an initial design scheme is obtained. This initial design scheme includes the antenna's installation position on the satellite, axis orientation, installation and connection methods, etc. This design scheme can be pre-stored or entered by the staff. This embodiment does not impose specific restrictions and can be designed according to actual needs.

[0071] S15: Determine whether the initial design scheme meets the electromagnetic compatibility requirements;

[0072] To determine if the initial design meets electromagnetic compatibility (EMC) requirements, antennas placed close together will generate electromagnetic coupling, meaning one antenna will induce an electromotive force in the other. When EMC exists, the antenna's directivity pattern may be distorted. Besides radiating useful signals, antennas will also radiate interference signals induced by the other antenna. Therefore, we must consider the coupling between them when arranging antenna positions. Determine if the initial design meets EMC requirements.

[0073] If the initial design meets the electromagnetic compatibility requirements, proceed to step S16: then generate the antenna layout design result.

[0074] If the initial design meets the electromagnetic compatibility requirements, then the initial design will be used as the antenna layout design result.

[0075] This application provides a method for antenna selection and layout of a small satellite, comprising: obtaining antenna mission requirements; selecting a suitable antenna type based on the antenna mission requirements and performing simulation design; determining whether the simulation design results meet the antenna mission requirements; if the simulation design results meet the antenna mission requirements, obtaining an initial design scheme based on the simulation design results; determining whether the initial design scheme meets electromagnetic compatibility requirements; if the initial design scheme meets the electromagnetic compatibility requirements, generating an antenna layout design result. In the antenna layout design process, this application combines antenna mission requirements with electromagnetic compatibility analysis to obtain antenna layout design results, ensuring that the antenna layout design results meet the antenna mission requirements and can operate normally, avoiding resource waste or even mission failure caused by subsequent design compensation.

[0076] According to the above embodiments, the initial design scheme needs to consider not only the antenna's installation position and axis orientation on the satellite, but also the installation and connection method. Each design stage may lead to problems in the design results. In order to adjust the design scheme in a timely manner, this embodiment provides a preferred solution: step S14 obtains the initial design scheme based on the simulation design results. Figure 2A flowchart illustrating another method for antenna selection and layout of a small satellite provided in this application embodiment is shown below. Figure 2 As shown, it includes:

[0077] S21: Obtain the antenna layout scheme based on the simulation design results;

[0078] S22: Determine whether the antenna layout scheme meets the satellite electromagnetic compatibility requirements;

[0079] The antenna layout scheme mentioned in this embodiment refers to the installation position and axis orientation of the antenna on the satellite. It is used to determine whether the antenna layout scheme meets the electromagnetic compatibility requirements of the satellite. That is, based on the antenna layout state, the antenna is simulated under the electromagnetic boundary conditions of the whole satellite to obtain its isolation and radiation characteristics, and to determine whether the isolation and gain pattern meet the requirements.

[0080] If the antenna layout scheme meets the satellite electromagnetic compatibility requirements, proceed to step S23: obtain the antenna installation and connection scheme based on the antenna layout scheme;

[0081] S24: Determine whether the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite;

[0082] If the antenna layout scheme meets the satellite electromagnetic compatibility requirements, the antenna installation and connection scheme obtained based on the antenna layout scheme is further obtained, that is, the installation and connection method of the antenna on the satellite.

[0083] To determine whether the antenna installation and connection scheme meets the overall satellite electromagnetic compatibility requirements, in addition to the inter-antenna electromagnetic compatibility analysis, further analysis should be conducted on the impact of multipath signals received by the on-board antennas on receiver performance, and the impact of the transmitter on other sensitive equipment through the antennas.

[0084] If the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite, proceed to step S16: generate the antenna layout design results.

[0085] If the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite, the final antenna layout design result can be generated.

[0086] In the antenna layout design process, this application first designs the antenna layout scheme with the installation position and axis orientation of the antenna on the satellite, performs an antenna electromagnetic compatibility analysis, and further obtains the antenna installation and connection scheme with the antenna on the satellite based on the antenna layout scheme. Then, it performs a whole-satellite electromagnetic compatibility analysis to obtain the antenna layout design result, so that the antenna layout design result meets the antenna mission requirements and can operate normally, avoiding resource waste or even mission failure caused by subsequent design compensation.

[0087] During the antenna layout design process, solar panels, on-board sensors, structural components, etc., may obstruct the antenna beam. It is necessary to avoid mutual obstruction of the field of view between the antenna and devices such as solar sensors and star sensors. This application provides a preferred solution. Figure 3 A flowchart illustrating another method for antenna selection and layout of a small satellite provided in this application embodiment is shown below. Figure 3 As shown, after obtaining the antenna installation and connection scheme based on the antenna layout scheme in step S23, the method further includes:

[0088] S31: Determine whether there is any field of view obstruction in the antenna installation and connection scheme;

[0089] If not, proceed to step S24 to determine whether the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite.

[0090] If so, return to step S23, which describes obtaining the antenna installation and connection scheme based on the antenna layout scheme.

[0091] To determine whether field-of-view obstruction exists in the antenna installation and connection scheme, it is necessary to consider whether the satellite solar panels will obstruct the antenna's field of view under different satellite operating modes. It is also crucial to avoid mutual obstruction of the field of view between the antenna and devices such as sun sensors and star sensors. If field-of-view obstruction exists, this embodiment does not impose restrictions on how to improve it. For example, for transmitting and receiving antennas in similar frequency bands, the physical distance between them should be increased as much as possible to improve isolation. For layout spaces with limited capacity, polarization isolation and the addition of isolation plates should be considered. Based on actual needs, the antenna installation and connection scheme was redesigned according to the aforementioned antenna layout scheme to cut off the interference path from potential interference sources to sensitive devices.

[0092] Throughout the design process, the design of each stage and the mutual influence between antennas may cause them to fail to meet the initial antenna mission requirements. Therefore, this embodiment provides a preferred solution. Before obtaining the antenna installation and connection scheme based on the antenna layout scheme in step S23, the following steps are also included:

[0093] S32: Determine whether the antenna layout scheme meets the antenna mission requirements;

[0094] If so, proceed to step S23 to obtain the antenna installation and connection scheme obtained based on the antenna layout scheme;

[0095] If not, return to step S12, which involves selecting a suitable antenna type and performing simulation design based on the antenna mission requirements.

[0096] Determine whether the antenna layout scheme, including the installation position and axis orientation of the antenna on the satellite, meets the antenna mission requirements. If it does, proceed to the next step; otherwise, redesign the antenna simulation until the antenna layout scheme meets the antenna mission requirements.

[0097] Preferably, before generating the antenna layout design result in step S16, the method further includes:

[0098] S33: Determine whether the antenna installation and connection scheme meets the antenna mission requirements;

[0099] If so, proceed to step S16 to generate the antenna layout design results;

[0100] If not, return to step S23 to obtain the antenna installation and connection scheme obtained based on the antenna layout scheme.

[0101] Before generating the final antenna layout result, another check is performed to determine whether the antenna installation and connection scheme meets the antenna mission requirements. If it does, the antenna layout design result is generated. If it does not, the installation and connection method of the antenna on the satellite is adjusted until the antenna installation and connection scheme meets the antenna mission requirements. By checking whether the antenna mission requirements are met multiple times in the design process, if they are not met, the previous design step is returned in time to adjust the scheme in order to obtain an antenna layout design result that meets the antenna mission requirements.

[0102] To better understand this solution, this application provides a design scheme for a specific antenna type, which involves selecting a suitable antenna type based on antenna mission requirements and performing simulation design, including:

[0103] Based on the antenna mission requirements, two wide-beam conical spiral antennas were selected as the spaceborne telemetry and control antennas, two ring-focal reflector antennas as the inter-satellite link antennas, one backfire double-arm spiral shaped antenna as the data transmission antenna, one multi-frequency microstrip antenna as the navigation and positioning antenna, one multi-frequency four-arm spiral antenna as the first load antenna, one planar antenna as the second load antenna, one normal-mode spiral antenna as the third load antenna, and one single-arm spiral antenna as the fourth load antenna for simulation design.

[0104] Correspondingly, the antenna layout scheme is as follows: one satellite-borne telemetry and control antenna is installed on the satellite's ground-facing side, and another satellite-borne telemetry and control antenna is installed on the satellite's celestial side; two inter-satellite link antennas are respectively located on the two side panels of the satellite; the data transmission antenna is located at the edge of the ground-facing panel; the navigation and positioning antenna is installed at the edge of the satellite's celestial side panel; the first payload antenna is located at the center of the satellite's ground-facing side; the four antenna elements of the second payload antenna are arrayed and installed at the four corners of the satellite's ground-facing side; the third payload antenna is located at the edge of the satellite's ground-facing panel; and the fourth payload antenna is located at the edge of the satellite's ground-facing panel.

[0105] Correspondingly, the antenna installation and connection scheme is as follows: two of the spaceborne telemetry and control antennas are mounted on the antenna support; two of the inter-satellite link antennas are mounted on the inclined support with a fixed angle to the satellite; the data transmission antenna is mounted on the antenna support; the navigation and positioning antenna is mounted on the cabin panel; the first load antenna is installed insulated from the cabin panel; the second load antenna is mounted on the cabin panel; the third load antenna is mounted on the inclined support with a fixed angle to the satellite; and the fourth load antenna is mounted on the cabin panel.

[0106] Figure 4 This is a schematic diagram of an example layout of a small satellite antenna provided in an embodiment of this application, as shown below. Figure 4 As shown, the first satellite-borne telemetry and control antenna 40, the second satellite-borne telemetry and control antenna 41, the data transmission antenna 42, the navigation and positioning antenna 43, the first inter-satellite link antenna 44, the second inter-satellite link antenna 45, the first payload antenna 46, the second payload antenna 47, the third payload antenna 48, and the fourth payload antenna 49 are all present.

[0107] The spaceborne telemetry and control antenna, together with the ground-based telemetry and control antenna, establishes a stable and reliable radio transmission channel that meets predetermined requirements, ensuring the transmission, reception, and delivery of satellite-to-ground wireless telemetry, remote control, and tracking information. Because the spaceborne telemetry and control antenna needs to form a near-full-space coverage beam to meet the requirements of continuous telemetry and control tracking during satellite launch, and to ensure normal telemetry and control of the satellite in any attitude during attitude adjustment, side-swing operation, or when a malfunction occurs, the first spaceborne telemetry and control antenna 40 and the second spaceborne telemetry and control antenna 41 adopt a wide-beam conical spiral antenna form. One is installed between the satellite and the ground, and the other is installed between the satellite and the sky, forming a binary antenna array to form a near-full-space coverage beam. The antennas are arrayed in the same spiral direction, and the power division ratio of the power distribution network is adjusted to reduce the impact of the overlapping interference area of ​​the two antennas on the telemetry and control link. Both spaceborne telemetry and control antennas are mounted on antenna supports, located at the edges of the ground-facing and sky-facing panels respectively, to avoid field-of-view obstruction from other antennas and devices.

[0108] Inter-satellite link antennas are used for data transmission between satellites. The first inter-satellite link antenna 44 and the second inter-satellite link antenna 45 establish a static inter-satellite link using a ring-focal reflector antenna. The two inter-satellite link antennas are located on two side plates of the satellite, respectively, and are mounted on inclined supports with a fixed angle to the satellite to meet the communication link between satellites under a fixed phase.

[0109] The data transmission antenna is used for data transmission from the satellite to the ground station. To ensure good reception at the ground station throughout the entire operating period, the downlink data transmission signal from the satellite must have a basically consistent level within the coverage area. The data transmission antenna 42 employs a miniaturized backfired double-arm helical shaped antenna, utilizing its leakage radiation characteristics to form an earth-matched saddle-shaped beam. This ensures that its gain distribution within the coverage area perfectly compensates for the level differences caused by transmission path attenuation. The data transmission antenna 42 is mounted on an antenna support, located at the edge of the ground-facing module to avoid obstruction of the field of view from other antennas and devices.

[0110] The navigation and positioning antenna is used to receive space-based GNSS signals to achieve satellite attitude determination, orbit determination, time synchronization, and absolute and relative positioning functions. The navigation and positioning antenna 43 is a miniaturized, wide-beam, multi-frequency microstrip antenna with a low profile, installed at the edge of the satellite's celestial surface panel, for receiving space-based GNSS signals.

[0111] The first payload antenna 46 is a multi-frequency four-arm helical antenna. Its radiating arm and coupling arm are attached to the dielectric support surface. The bottom end of the radiating arm is connected to the feed board, and the bottom end of the coupling arm is short-circuited to the network cavity. The tuning mechanism is attached to the surface of the dielectric cover plate. The coupling stub connects the radiating arm and the coupling arm in series, and then connects the tuning mechanism in parallel. The antenna is small in size, light in weight, has good structural strength, and excellent performance. It is located at the center of the satellite relative to the ground and is installed insulated from the cabin panel to prevent interference signals from the payload transmission channel from entering the satellite structure ground through the radio frequency link and affecting the payload receiving channel and other individual equipment.

[0112] The second payload antenna 47 is a planar antenna consisting of four metal radiating plates and a grounding post. Slots are cut into the radiating plates to achieve miniaturization and weight reduction. The grounded inverted L-shaped metal post couples the radiating plates. The second payload antenna 47 is arrayed with four antenna elements to achieve multi-beam coverage of the ground. The antennas are installed at the four corners of the satellite relative to the ground, keeping them as far away as possible from the first payload antenna 46 to improve the isolation between the transmitting and receiving antennas.

[0113] The third payload antenna 48 is a normal-mode helical antenna located at the edge of the satellite-to-ground module, mounted on an inclined support at a fixed angle to the satellite, using the satellite as a reflector to improve antenna gain. The support is insulated from the module to prevent interference signals from the satellite's structural ground from entering the receiver's radio frequency channel via conduction.

[0114] The fourth payload antenna 49 employs a single-arm helical antenna to achieve high-gain performance. The antenna is located at the edge of the satellite's ground-facing module to avoid obstruction of the field of view between antennas.

[0115] The antenna selection and layout method for small satellites has been described in detail in the above embodiments. This application also provides embodiments corresponding to the antenna selection and layout device for small satellites. It should be noted that this application describes the embodiments of the device part from two perspectives: one is based on the functional module, and the other is based on the hardware.

[0116] Figure 5 A structural diagram of another small satellite antenna selection and layout device provided in this application embodiment is shown below. Figure 5 As shown, it includes:

[0117] Module 51 is used to acquire antenna task requirements;

[0118] Simulation module 52 is used to select the appropriate antenna type and perform simulation design according to the antenna mission requirements;

[0119] The first judgment module 53 is used to determine whether the simulation design results meet the antenna mission requirements.

[0120] If the simulation design results meet the antenna mission requirements, the first design module 54 is triggered to obtain the initial design scheme based on the simulation design results.

[0121] The second judgment module 55 is used to determine whether the initial design scheme meets the electromagnetic compatibility requirements.

[0122] If the initial design scheme does not meet the electromagnetic compatibility requirements, the second design module 56 is triggered, which is used to generate the antenna layout design result.

[0123] Specifically, the acquisition module 51 acquires the antenna mission requirements, the simulation module 52 selects a suitable antenna type based on the antenna mission requirements, and performs simulation design. The first judgment module 53 judges whether the simulation design result meets the antenna mission requirements. If the simulation design result meets the antenna mission requirements, the first design module 54 is triggered to acquire the initial design scheme obtained from the simulation design result. The second judgment module 55 judges whether the initial design scheme meets the electromagnetic compatibility requirements. If the initial design scheme meets the electromagnetic compatibility requirements, the second design module 56 is triggered to generate the antenna layout design result. In the antenna layout design process, this application combines the antenna mission requirements with electromagnetic compatibility analysis to obtain the antenna layout design result, so that the antenna layout design result meets the antenna mission requirements and can operate normally, avoiding resource waste or even mission failure caused by subsequent design compensation.

[0124] Since the embodiments of the apparatus and the embodiments of the method correspond to each other, please refer to the description of the embodiments of the method for the embodiments of the apparatus, which will not be repeated here.

[0125] Figure 6A structural diagram of another small satellite antenna selection and layout device provided in this application embodiment is shown below. Figure 6 As shown, the antenna selection and layout device for small satellites includes: a memory 60 for storing computer programs;

[0126] The processor 61 is used to execute a computer program to implement the steps of the method for obtaining user operation habit information as described in the above embodiment (antenna selection and layout method for small satellites).

[0127] The antenna selection and layout device for small satellites provided in this embodiment may include, but is not limited to, smartphones, tablets, laptops, or desktop computers.

[0128] The processor 61 may include one or more processing cores, such as a quad-core processor or an octa-core processor. The processor 61 may be implemented using at least one of the following hardware forms: Digital Signal Processor (DSP), Field-Programmable Gate Array (FPGA), or Programmable Logic Array (PLA). The processor 61 may also include a main processor and a coprocessor. The main processor, also known as the Central Processing Unit (CPU), is used to process data in the wake-up state; the coprocessor is a low-power processor used to process data in the standby state. In some embodiments, the processor 61 may integrate a Graphics Processing Unit (GPU), which is responsible for rendering and drawing the content to be displayed on the screen. In some embodiments, the processor 61 may also include an Artificial Intelligence (AI) processor, which handles computational operations related to machine learning.

[0129] The memory 60 may include one or more computer-readable storage media, which may be non-transitory. The memory 60 may also include high-speed random access memory and non-volatile memory, such as one or more disk storage devices or flash memory devices. In this embodiment, the memory 60 is used to store at least the following computer program 601, which, after being loaded and executed by the processor 61, is capable of implementing the relevant steps of the antenna selection and layout method for small satellites disclosed in any of the foregoing embodiments. In addition, the resources stored in the memory 60 may also include an operating system 602 and data 603, etc., and the storage method may be temporary storage or permanent storage. The operating system 602 may include Windows, Unix, Linux, etc. The data 603 may include, but is not limited to, data involved in implementing the antenna selection and layout method for small satellites.

[0130] In some embodiments, the antenna selection and layout device for small satellites may further include a display screen 62, an input / output interface 63, a communication interface 64, a power supply 65, and a communication bus 66.

[0131] Those skilled in the art will understand that Figure 6 The structure shown does not constitute a limitation on the antenna selection and layout of small satellites, and may include more or fewer components than shown.

[0132] The antenna selection and layout apparatus for small satellites provided in this application includes a memory and a processor. When the processor executes the program stored in the memory, it can implement the following method: antenna selection and layout method for small satellites, obtaining antenna mission requirements; selecting a suitable antenna type according to the antenna mission requirements and performing simulation design; determining whether the simulation design result meets the antenna mission requirements; if the simulation design result meets the antenna mission requirements, obtaining an initial design scheme obtained based on the simulation design result; determining whether the initial design scheme meets electromagnetic compatibility requirements; if the initial design scheme meets the electromagnetic compatibility requirements, generating an antenna layout design result. In the antenna layout design process, this application combines the antenna mission requirements with electromagnetic compatibility analysis to obtain the antenna layout design result, so that the antenna layout design result meets the antenna mission requirements and can operate normally, avoiding resource waste or even mission failure caused by subsequent design compensation.

[0133] Finally, this application also provides an embodiment corresponding to a computer-readable storage medium. The computer-readable storage medium stores a computer program, which, when executed by a processor, implements the steps described in the above embodiment of the small satellite antenna selection and layout method.

[0134] It is understood that if the methods in the above embodiments are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. 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 storage medium and executes all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0135] The computer-readable storage medium provided in this embodiment stores a computer program. When the processor executes the program, it can implement the following methods: a method for antenna selection and layout of a small satellite, obtaining antenna mission requirements; selecting a suitable antenna type based on the antenna mission requirements and performing simulation design; determining whether the simulation design results meet the antenna mission requirements; if the simulation design results meet the antenna mission requirements, obtaining an initial design scheme based on the simulation design results; determining whether the initial design scheme meets electromagnetic compatibility requirements; if the initial design scheme meets the electromagnetic compatibility requirements, generating an antenna layout design result. In the antenna layout design process, this application combines antenna mission requirements with electromagnetic compatibility analysis to obtain antenna layout design results, ensuring that the antenna layout design results meet the antenna mission requirements and can operate normally, avoiding resource waste or even mission failure caused by subsequent design compensation.

[0136] The antenna selection and layout method, apparatus, and medium for small satellites provided in this application have been described in detail above. The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to in the method section. It should be noted that those skilled in the art can make several improvements and modifications to this application without departing from the principles of this application, and these improvements and modifications also fall within the protection scope of the claims of this application.

[0137] It should also be noted that, in this specification, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

Claims

1. A method for antenna selection and layout of a small satellite, characterized in that, include: Obtain antenna task requirements; Based on the antenna mission requirements, select a suitable antenna type and perform simulation design; Determine whether the simulation design results meet the antenna mission requirements; If the simulation design results meet the antenna mission requirements, obtain the initial design scheme based on the simulation design results; Determine whether the initial design scheme meets the electromagnetic compatibility requirements; If the initial design scheme meets the electromagnetic compatibility requirements, then the antenna layout design result is generated; The step of obtaining the initial design scheme based on the simulation design results includes: Obtain the antenna layout scheme based on the simulation design results; Determine whether the antenna layout scheme meets the satellite electromagnetic compatibility requirements; If the antenna layout scheme meets the satellite electromagnetic compatibility requirements, obtain the antenna installation and connection scheme based on the antenna layout scheme; Determine whether the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite; If the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite, the antenna layout design result is generated. The step of selecting a suitable antenna type and performing simulation design based on the antenna mission requirements includes: Based on the antenna mission requirements, two wide-beam conical spiral antennas were selected as the spaceborne telemetry and control antennas, two ring-focal reflector antennas as the inter-satellite link antennas, one backfire double-arm spiral shaped antenna as the data transmission antenna, one multi-frequency microstrip antenna as the navigation and positioning antenna, one multi-frequency four-arm spiral antenna as the first load antenna, one planar antenna as the second load antenna, one normal mode spiral antenna as the third load antenna, and one single-arm spiral antenna as the fourth load antenna for simulation design. Correspondingly, the antenna layout scheme is as follows: one satellite-borne telemetry and control antenna is installed on the satellite's ground-facing side, and another satellite-borne telemetry and control antenna is installed on the satellite's celestial side; two inter-satellite link antennas are respectively located on the two side panels of the satellite; the data transmission antenna is located at the edge of the ground-facing panel; the navigation and positioning antenna is installed at the edge of the satellite's celestial side panel; the first payload antenna is located at the center of the satellite's ground-facing side; the four antenna elements of the second payload antenna are arrayed and installed at the four corners of the satellite's ground-facing side; the third payload antenna is located at the edge of the satellite's ground-facing panel; and the fourth payload antenna is located at the edge of the satellite's ground-facing panel. Correspondingly, the antenna installation and connection scheme is as follows: two of the spaceborne telemetry and control antennas are mounted on an antenna support; two of the inter-satellite link antennas are mounted on an inclined support with a fixed angle to the satellite; the data transmission antenna is mounted on the antenna support; and the navigation and positioning antenna is mounted on the cabin panel; the first load antenna is insulated from the cabin panel; the second load antenna is mounted on the cabin panel; the third load antenna is mounted on an inclined support with a fixed angle to the satellite; and the fourth load antenna is mounted on the cabin panel.

2. The antenna selection and layout method for small satellites according to claim 1, characterized in that, After obtaining the antenna installation and connection scheme based on the antenna layout scheme, the method further includes: Determine whether there is any field of view obstruction in the antenna installation and connection scheme; If not, proceed to the step of determining whether the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite; If so, return to the step of obtaining the antenna installation and connection scheme based on the antenna layout scheme.

3. The antenna selection and layout method for small satellites according to claim 1, characterized in that, Before obtaining the antenna installation and connection scheme based on the antenna layout scheme, the method further includes: Determine whether the antenna layout scheme meets the antenna mission requirements; If so, proceed to the step of obtaining the antenna installation and connection scheme based on the antenna layout scheme; If not, return to the step of selecting a suitable antenna type and performing simulation design based on the antenna mission requirements.

4. The antenna selection and layout method for small satellites according to claim 3, characterized in that, Before generating the antenna layout design result, the process also includes: Determine whether the antenna installation and connection scheme meets the antenna mission requirements; If so, proceed to the step of generating the antenna layout design result; If not, return to the step of obtaining the antenna installation and connection scheme based on the antenna layout scheme.

5. A device for antenna selection and layout of a small satellite, characterized in that, include: The acquisition module is used to acquire antenna task requirements; The simulation module is used to select an appropriate antenna type and perform simulation design based on the antenna mission requirements. The first judgment module is used to determine whether the simulation design results meet the antenna task requirements; If the simulation design results meet the antenna task requirements, the first design module is triggered; The first design module is used to obtain an initial design scheme based on the simulation design results; The second judgment module is used to determine whether the initial design scheme meets the electromagnetic compatibility requirements. If the initial design scheme meets the electromagnetic compatibility requirements, the second design module is triggered. The second design module is used to generate antenna layout design results; The step of obtaining the initial design scheme based on the simulation design results includes: Obtain the antenna layout scheme based on the simulation design results; Determine whether the antenna layout scheme meets the satellite electromagnetic compatibility requirements; If the antenna layout scheme meets the satellite electromagnetic compatibility requirements, obtain the antenna installation and connection scheme based on the antenna layout scheme; Determine whether the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite; If the antenna installation and connection scheme meets the electromagnetic compatibility requirements of the entire satellite, the antenna layout design result is generated. The step of selecting a suitable antenna type and performing simulation design based on the antenna mission requirements includes: Based on the antenna mission requirements, two wide-beam conical spiral antennas were selected as the spaceborne telemetry and control antennas, two ring-focal reflector antennas as the inter-satellite link antennas, one backfire double-arm spiral shaped antenna as the data transmission antenna, one multi-frequency microstrip antenna as the navigation and positioning antenna, one multi-frequency four-arm spiral antenna as the first load antenna, one planar antenna as the second load antenna, one normal mode spiral antenna as the third load antenna, and one single-arm spiral antenna as the fourth load antenna for simulation design. Correspondingly, the antenna layout scheme is as follows: one satellite-borne telemetry and control antenna is installed on the satellite's ground-facing side, and another satellite-borne telemetry and control antenna is installed on the satellite's celestial side; two inter-satellite link antennas are respectively located on the two side panels of the satellite; the data transmission antenna is located at the edge of the ground-facing panel; the navigation and positioning antenna is installed at the edge of the satellite's celestial side panel; the first payload antenna is located at the center of the satellite's ground-facing side; the four antenna elements of the second payload antenna are arrayed and installed at the four corners of the satellite's ground-facing side; the third payload antenna is located at the edge of the satellite's ground-facing panel; and the fourth payload antenna is located at the edge of the satellite's ground-facing panel. Correspondingly, the antenna installation and connection scheme is as follows: two of the spaceborne telemetry and control antennas are mounted on an antenna support; two of the inter-satellite link antennas are mounted on an inclined support with a fixed angle to the satellite; the data transmission antenna is mounted on the antenna support; and the navigation and positioning antenna is mounted on the cabin panel; the first load antenna is insulated from the cabin panel; the second load antenna is mounted on the cabin panel; the third load antenna is mounted on an inclined support with a fixed angle to the satellite; and the fourth load antenna is mounted on the cabin panel.

6. A device for antenna selection and layout of a small satellite, characterized in that, include: Memory, used to store computer programs; A processor, configured to execute the computer program to implement the steps of the antenna selection and layout method for small satellites as described in any one of claims 1 to 4.

7. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that, when executed by a processor, implements the steps of the antenna selection and layout method for small satellites as described in any one of claims 1 to 4.

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