High-storage-ratio satellite antenna configuration design method

Abstract

The invention relates to the technical field of antenna design, and provides a high-storage-ratio satellite antenna configuration design method, which comprises a plurality of antenna arrays, each antenna array comprises a foldable module, the module can be folded into a satellite shell, and each module comprises a radio beam forming circuit and a solar cell. In order to enable small-volume satellites to have high network capacity, the present technology relates to a wireless communication method that enhances the performance of a radio system that utilizes multiple antenna arrays.

Description

Technical Field

[0001] The present invention relates to the technical field of antenna design, and in particular to a method for designing a satellite antenna configuration with a high storage ratio. Background Art

[0002] Traditional satellite antenna configuration design usually faces the challenge of space constraints, because the effective space on the satellite is limited, and a high-efficiency antenna design needs to be achieved in a limited space. Single-antenna radio is limited to utilizing time and frequency resources within the geographical area pointed by the antenna, and building large antenna arrays usually requires a large volume, which makes it difficult to integrate into small satellites. Summary of the invention

[0003] The present invention proposes a technical method for integrating a large antenna into a small satellite, which solves the problem of excessive space occupation and low efficiency during the process of integrating a large antenna into a small satellite.

[0004] The technical solution of the present invention is as follows: a method for designing a satellite antenna configuration with a high storage ratio, including multiple antenna arrays, each antenna array including a foldable module, which can be folded into a satellite shell, each module including a radio beamforming circuit and a solar cell, so that a small-volume satellite has a high network capacity. The technology relates to a wireless communication method to enhance the performance of a radio system that utilizes multiple antenna arrays.

[0005] Further, the antenna array is also referred to as antenna spokes, including a top view of a satellite having two linear antenna spokes, including solar cells mounted on top of the antenna array for powering the satellite electronics; a bottom view of a dual-spoke linear antenna array mounted on a satellite, wherein the antennas are mounted along the spokes, and the antenna elements are spaced approximately one wavelength apart from each other of the radio carrier wavelength, and different embodiments may have smaller or larger antenna spacings, wherein larger antenna spacings increase spatial resolution but increase the volume of the antenna array.

[0006] Further, an antenna array of phased array antenna elements is used, but other types of antenna elements that may be used include, but are not limited to, helical antennas, monopole antennas, dipole antennas, aperture-fed antennas, or probe-fed patch antennas.

[0007] Furthermore, each antenna group includes 3 antenna modules in the partially folded configuration.

[0008] Further, the spokes are in a fully folded configuration so that when the module is folded, the antennas are more tightly folded by not exceeding an overlap with an adjacent module antenna.

[0009] Furthermore, one or more strip springs made of steel or composite materials are attached along the edge of the antenna module circuit board. When the antenna module is not fixed in the satellite housing, torque is applied to the adjacent antenna module to unfold the antenna module from the folded structure. One or more flexible PCB boards are used to electrically connect the adjacent antenna module circuit boards. Since the antenna array operates in a zero-gravity environment, only a very small torque is required to expand the folded antenna module into a linear array.

[0010] Further, each module is made of circuit board material and mounted with solar cells, one or more antenna elements and RF, analog and digital beamforming circuits, and in order to increase the compactness of the folded antenna module, openings in the circuit board consisting of slots or holes are integrated into the module circuit board material, which allows beamforming and other electronic components from adjacent modules to be installed in the slots or holes when the module is folded. The solar cells can be mounted separately on the satellite housing, but mounting on the antenna module itself can provide additional additional volume efficiency. The module circuitry and solar cells are assembled on a glass reinforced epoxy resin laminate material, or can also be assembled on Teflon or other material to facilitate mounting of electronic components.

[0011] The working principle and beneficial effects of the present invention are:

[0012] 1. Achieve high-efficiency antenna design in a limited space, and propose a high-storage ratio integration method of large antennas on small satellites;

[0013] 2. To achieve high-efficiency antenna design in a limited space, a large-capacity antenna module composition of an array antenna is proposed;

[0014] 3. To achieve high-efficiency antenna design in a limited space, a flexible connection method between antenna modules suitable for zero-gravity environment is proposed. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0016] Figure 1 A top-down view of a satellite incorporating two linear antenna arrays;

[0017] Figure 2 Base map of satellites with two linear / rectangular antenna arrays integrated;

[0018] Figure 3 Side view of a partially folded linear antenna array;

[0019] Figure 4 Side view of the fully folded linear antenna array;

[0020] Figure 5Multiple antenna modules connected to each other;

[0021] Figure 6 Top and bottom views of the antenna module.

[0022] In the figure: 1. Antenna spokes; 2. Phased array antenna; 3. Strip spring; 4. Flexible PCB board; 5. Solar cell; 6. Antenna element; 7. Digital wave; 8. Beam forming circuit; 9. Slot. DETAILED DESCRIPTION

[0023] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0024] like Figure 1 to Figure 6 As shown, this embodiment provides a method for designing a satellite antenna configuration with a high storage ratio, including multiple antenna arrays, each antenna array including a foldable module, the module can be folded into a satellite housing, each module including a radio beam forming circuit and a solar cell, so that a small-volume satellite has a high network capacity. The technology relates to a wireless communication method, and enhances the performance of a radio system using multiple antenna arrays. In the technology, the antenna array is also referred to as an antenna radiation. Figure 1 shows a top view of a satellite comprising two linear antenna spokes 1, Figure 1 The embodiment includes a solar cell 1 mounted on top of an antenna array for powering satellite electronics; Figure 2 A bottom view of a dual spoke linear antenna array mounted on a satellite is shown, where the antennas are mounted along the spokes. In an embodiment, the antenna elements are spaced about one wavelength of the radio carrier wavelength. Different embodiments may have antennas spaced at smaller or larger intervals. Larger antenna spacing increases spatial resolution but increases the size of the antenna array. Figure 2 An antenna array using a phased array antenna 2 element is shown, but other types of antenna elements that may be used include, but are not limited to, helical antennas, monopole antennas, dipole antennas, aperture-fed antennas, or probe-fed patch antennas; Figure 3 An embodiment showing antenna spoke folding, which includes 3 antenna modules per antenna group in a partially folded configuration; Figure 4 showing the spokes in a fully folded configuration so that when the module is folded, the antennas are more tightly folded by not exceeding an overlap with an adjacent module antenna; Figure 5More details of the electrical and mechanical connections between antenna module circuit boards are shown. One or more strip springs 3 made of steel or composite materials are attached along the edges of the antenna module circuit boards. When the antenna modules are not fixed in the satellite housing, torque is applied to adjacent antenna modules to unfold the antenna modules from the folded structure. One or more flexible PCB boards 4 are used to electrically connect adjacent antenna module circuit boards. Since the antenna array operates in a zero-gravity environment, only a small torque is required to expand the folded antenna modules into a linear array. Top and bottom views of an embodiment of a module for building a linear antenna array are shown in FIG. Figure 6 As shown, each module is made of circuit board material and mounted with solar cells, one or more antenna elements 6 and RF, analog and digital beamforming circuits 7. In one embodiment, in order to increase the compactness of the folded antenna module, openings in the circuit board consisting of slots or holes 8 are integrated into the module circuit board material, which allows beamforming and other electronic components from adjacent modules to be installed in the slots or holes when the module is folded. In an alternative embodiment, the solar cells can be mounted separately on the satellite housing, but mounting on the antenna module itself can provide additional additional volume efficiency. The module circuitry and solar cells are assembled on a glass reinforced epoxy resin laminate material, or can also be assembled on Teflon or other materials to facilitate mounting of electronic components.

[0025] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for designing a satellite antenna configuration with a high storage ratio, including multiple antenna arrays, each antenna array including a foldable module, which can be folded into a satellite housing, each module including a radio beamforming circuit and a solar cell, so that a small-volume satellite has a high network capacity. The technology relates to a wireless communication method that enhances the performance of a radio system that utilizes multiple antenna arrays.

2. A method for designing a satellite antenna configuration with a high storage ratio according to claim 1, characterized in that: Antenna arrays are also called antenna spokes. A top view of a satellite consisting of two linear antenna spokes, including solar cells mounted on top of the antenna array to power the satellite electronics. A bottom view of a dual-spoke linear antenna array mounted on a satellite. The antennas are mounted along the spokes, with antenna elements spaced approximately one wavelength apart from each other, and different embodiments may have smaller or larger antenna spacings, wherein larger antenna spacing increases spatial resolution but increases the volume of the antenna array.

3. The method for designing a satellite antenna configuration with a high storage ratio according to claim 1, characterized in that: An antenna array using phased array antenna elements, but other types of antenna elements that may be used include but are not limited to helical antennas, monopole antennas, dipole antennas, aperture fed antennas, or probe fed patch antennas.

4. The method for designing a satellite antenna configuration with a high storage ratio according to claim 1, characterized in that: It contains 3 antenna modules per antenna group in the partially folded configuration.

5. The method for designing a satellite antenna configuration with a high storage ratio according to claim 1, characterized in that: The spokes are in a fully folded configuration so that when the module is folded, the antennas fold more tightly by not exceeding an overlap with adjacent module antennas.

6. The method for designing a satellite antenna configuration with a high storage ratio according to claim 1, characterized in that: One or more strip springs made of steel or composite materials are attached along the edge of the antenna module circuit board. When the antenna module is not fixed in the satellite housing, torque is applied to the adjacent antenna module to unfold the antenna module from the folded structure. One or more flexible PCB boards are used to electrically connect the adjacent antenna module circuit boards. Since the antenna array operates in a zero-gravity environment, only a small torque is required to expand the folded antenna module into a linear array.

7. The method for designing a satellite antenna configuration with a high storage ratio according to claim 1, characterized in that: Each module is made of circuit board material and mounted with solar cells, one or more antenna elements, and RF, analog and digital beam forming circuits, and in order to increase the compactness of the folded antenna module, the openings in the circuit board consisting of slots or holes are integrated into the module circuit board material; Among other things, the material allows beamforming and other electronic components from adjacent modules to fit into slots or holes when the module is folded. The solar cells can be mounted separately on the satellite housing, but mounting them on the antenna module itself can provide additional volumetric efficiency. The module circuitry and solar cells are assembled on a glass-reinforced epoxy laminate, or can also be assembled on Teflon or other materials to facilitate mounting of electronic components.

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