Layout method of satellite measurement and control antenna and satellite

Abstract

The invention discloses a layout method of a satellite measurement and control antenna and a satellite. The layout method comprises the following steps: S1, carrying out gridding processing modeling on a position relationship between a satellite body and a solar panel on one side; s2, simulating to obtain a non-shielding gain of the measurement and control antenna according to the illumination condition and the condition that the satellite body is not shielded; s3, arranging the measurement and control antenna at different positions of the satellite body according to the light condition and the shielding relationship of the solar panel on the satellite body, performing simulation to obtain gains of the measurement and control antenna under different shielding relationships, and selecting the measurement and control antenna position with the minimum gain change; and S4, designing connection structures between the satellite body and the solar panel in different shapes, performing simulation to obtain gains of the measurement and control antenna under different connection structures, and selecting a connection structure shape with the minimum gain change. The method can guarantee the stability and reliability of the measurement and control link of the satellite.

Description

Technical Field

[0001] This invention relates to the field of spacecraft overall design technology, specifically to a satellite telemetry and control antenna layout method for optimizing satellite communication performance and a satellite using this method. Background Technology

[0002] With the rapid development of satellite technology, especially the widespread application of small satellites and constellation satellites, the integration level of satellite platforms is becoming increasingly high, and their shape and layout are strictly limited by factors such as size, weight, and power. Solar panels, as the primary energy source for satellites, are typically large in size and require directional adjustments based on lighting conditions. This inevitably creates dynamic obstruction of the telemetry and control antennas mounted on the satellite. This obstruction severely degrades the antenna's radiation pattern, leading to decreased gain and signal interruption in the telemetry and control link, thus affecting the reliable operation and data transmission of the satellite.

[0003] Traditional satellite telemetry and control antenna placement methods are mostly based on experience or simple geometric analysis, typically prioritizing antenna placement on specific panels of the satellite that point to the ground or into the air, with little systematic consideration of the dynamic shading effect of solar panels caused by satellite motion. This method struggles to quantify the specific impact of shading on antenna gain under different orbital positions and different solar panel rotation angles.

[0004] Therefore, there is an urgent need for a systematic, simulation-driven method for satellite telemetry and control antenna layout that can accurately assess and optimize antenna performance in the early stages of design, and minimize the adverse effects of dynamic shading by solar panels. Summary of the Invention

[0005] The purpose of this invention is to overcome the shortcomings of existing technologies and provide a method for the layout of satellite telemetry and control antennas and a satellite. This method, through systematic modeling, simulation, and optimization, can effectively avoid or mitigate the dynamic obstruction of telemetry and control antennas by solar panels during the overall satellite design phase, thereby ensuring the stability and reliability of the telemetry and control link throughout the satellite's orbital period.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: In a first aspect, the present invention provides a method for arranging a satellite telemetry and control antenna, characterized in that it includes: Step S1: Establish a meshed model. The positional relationship between the satellite body and the solar panel on one side is modeled using a mesh. Specifically, the surfaces of the satellite body and the solar panel are divided into several fine mesh cells, and position coordinates and geometric attribute information are established for each mesh cell. The geometric attribute information preferably includes the normal direction of the mesh cell, material properties (such as conductivity and dielectric constant), and the field of view relative to the candidate position of the telemetry and control antenna. This model forms the geometric basis for subsequent occlusion analysis and gain simulation.

[0007] Step S2: Simulate Unobstructed Gain. Based on the model established in Step S1, and assuming the solar panels are absent during satellite operation and considering the dynamic illumination conditions, simulate the unobstructed gain of the telemetry and control antenna at a candidate location on the satellite. This gain serves as a benchmark for evaluating the degree of obstruction impact.

[0008] Step S3: Optimize the position of the telemetry and control antenna. A solar panel is introduced into the model. Based on the illumination conditions and the movement of the solar panel relative to the satellite body, the telemetry and control antenna is placed at different candidate positions on the satellite body, such as the bottom, top, and sides. Simulations are performed to obtain the gain of the telemetry and control antenna under different shading conditions. By comparison, the position of the telemetry and control antenna with the smallest gain change is selected. "Smallest gain change" means that within one complete orbital period of the satellite, the difference between the gain of the telemetry and control antenna caused by shading from the solar panel and the unshaded gain obtained in step S2 has the smallest fluctuation range.

[0009] As a preferred option, in step S3, the candidate positions for the telemetry and control antenna can be preferentially set on the satellite body, on the side that is coplanar or perpendicular to the rotation axis of the solar panel, because such positions may be relatively regularly or less affected by the rotation sweep of the solar panel.

[0010] Step S4: Optimize the shape of the solar panel connection structure. After determining the preferred antenna position, further design the connection structure between the satellite body and the solar panel with different shapes. Simulations are used to obtain the gain of the telemetry and control antenna under different connection structure shapes, and the connection structure shape that minimizes the gain change is selected. The shape of the connection structure may include, but is not limited to: single rod shape, multi-segment bending shape, curved surface shape, or triangular support structure. The evaluation criterion for "minimum gain change" in this step is similar to that in Step S3, focusing on the shading effect introduced by the connection structure throughout the entire orbital period.

[0011] In one embodiment, step S5 is also included: integration verification. The selected telemetry and control antenna positions and connection structure shapes from steps S3 and S4 are integrated to establish a complete high-fidelity satellite model. Real orbits, attitudes, and solar panel propulsion are simulated under dynamic mission scenarios to verify the end-to-end communication performance, ensuring that the design meets the overall performance requirements.

[0012] The method described in this invention is applicable to various types of satellites equipped with single-sided or double-sided solar panels.

[0013] Secondly, the present invention provides a satellite, characterized in that the layout of the satellite's telemetry and control antenna is designed and determined using any of the satellite telemetry and control antenna layout methods described in the first aspect. Because the antenna position and solar panel connection structure are systematically optimized in the design of this satellite, the impact of solar panel shading on its telemetry and control antenna is significantly reduced throughout the entire orbital period, resulting in a more stable and reliable communication link.

[0014] Compared with existing technologies, the present invention not only optimizes the position of the satellite telemetry and control antenna through its layout method, but also uses the connection structure of the solar panels as a designable variable for collaborative optimization, realizing the transformation of the telemetry and control antenna from avoiding obstruction to actively designing to minimize the impact.

[0015] It should be understood that the above general description and the following specific embodiments are merely exemplary and illustrative, and do not limit the scope of the invention. Attached Figure Description

[0016] The accompanying drawings, which are part of the specification of this invention, illustrate exemplary embodiments of the invention. The drawings, together with the description in the specification, serve to illustrate the principles of the invention.

[0017] Figure 1 This is a flowchart of a satellite telemetry and control antenna layout method according to an embodiment of the present invention; Figure 2 This is a schematic diagram of a satellite and solar panels according to an embodiment of the present invention; Figure 3 This is a schematic diagram of a satellite, solar panels, and telemetry antenna according to an embodiment of the present invention; Figure 4 This is a simulation diagram of the gain curve of the telemetry and control antenna installed on the Z-plane of the satellite body according to an embodiment of the present invention. Detailed Implementation

[0018] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and to exemplify the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of the present invention.

[0019] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0020] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0021] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., and should not be considered limiting. Similar terms are used throughout the description to refer to similar elements.

[0022] It will be apparent to those skilled in the art that the present invention can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.

[0023] Figure 1 This is a flowchart of a satellite telemetry and control antenna layout method according to an embodiment of the present invention. Figure 2 This is a schematic diagram of a satellite and solar panels according to an embodiment of the present invention. Figure 3 This is a schematic diagram of a satellite, solar panels, and telemetry antenna according to an embodiment of the present invention. Figure 4 This is a simulation diagram of the gain curve of the telemetry and control antenna installed on the Z-plane of the satellite body according to an embodiment of the present invention.

[0024] Example 1: Reference Figure 1This embodiment discloses a layout method for a satellite telemetry and control antenna, applied to an Earth observation satellite equipped with a large solar panel on one side. The specific steps are as follows: Step S1: Model the positional relationship between the satellite body and the solar panel on one side using a mesh.

[0025] like Figure 2 As shown, a preliminary geometric model was created using 3D modeling software based on the spatial positions of the satellite body 10 and the solar panel 20. This model was then imported into a professional mesh generation tool, dividing the outer surface of the satellite body 10 and the two sides of the solar panel 20 into tens of thousands of small triangular or quadrilateral mesh elements. Each element was labeled with its spatial coordinates, surface normal, and material properties. The solar panel is typically set as a metal or composite material patch, and its field of view relative to several preset candidate antenna mounting points (such as the bottom, top, and side surfaces of the satellite body) was calculated, forming an accurate model suitable for electromagnetic calculations.

[0026] The embodiments of this application improve the occlusion effect from qualitative analysis to quantitative evaluation through gridded modeling and high-fidelity electromagnetic simulation, enabling accurate prediction of antenna gain changes in dynamic scenarios.

[0027] Step S2: Based on the lighting conditions and the fact that the satellite itself is unobstructed, simulate the unobstructed gain of the telemetry and control antenna T.

[0028] The solar panel 20 is temporarily removed from the model. The satellite is set to operate in a typical sun-synchronous orbit. Using electromagnetic simulation software, the radiation pattern and gain are simulated when the telemetry and control antenna T is installed at the center of the -Z plane (i.e., the bottom surface of the satellite body) of the satellite body 10, without the solar panel obstructing the radiation. The gain G(±65°) is calculated within ±65°, denoted as G0, and used as the ideal reference for the gain.

[0029] In this embodiment, the telemetry and control antenna T can be a conical spiral antenna with an operating frequency of 7~8GHz and a gain of greater than or equal to -2dBi within the range of ±65°.

[0030] Step S3: Based on the lighting conditions and the shading relationship of the solar panels on the satellite body, set the telemetry and control antenna T at different positions on the satellite body, simulate the gain of the telemetry and control antenna T under different shading relationships, and select the position of the telemetry and control antenna T with the smallest gain change.

[0031] The solar panel 20 model is reconstructed and set to rotate within ±180 degrees around the mounting axis according to the solar orientation law. In one embodiment, the telemetry and control antenna model is placed at four candidate positions on the satellite body 10: +Z plane (i.e., the top surface of the satellite body), -Z plane (i.e., the bottom surface of the satellite body), +X plane (lateral 1), and -X plane (lateral 2). For each position, the antenna gain at different rotation angles of the solar panel is simulated and calculated to obtain a series of gain values ​​G_actual(θ).

[0032] like Figure 4 As shown, the curves of G_actual(θ) versus rotation angle θ at different positions are plotted. The difference ΔG between G_actual(±65°) and the reference gain G0 within the ±65° range is calculated. The results show that the antenna mounted on the -Z plane (i.e., the bottom surface of the satellite body) has the smoothest gain curve and the smallest fluctuation range of ΔG. Therefore, the -Z plane, i.e., the bottom surface of the satellite body near the solar panels, is selected as the mounting surface of the telemetry and control antenna T.

[0033] Step S4: Design connection structures between satellite bodies and solar panels of different shapes, simulate the gain of telemetry and control antenna T under different connection structures, and select the connection structure shape with the smallest gain change.

[0034] After selecting the Z-plane for antenna installation, a support structure 30 connecting the satellite body 10 and the solar panel 20 needs to be designed. Traditional designs may use a simple single rod; this invention designs four alternative shapes for comparison: single rod, L-shaped bend, streamlined curved surface, and triangular truss shape 30a, such as... Figure 3 As shown.

[0035] In one embodiment, the satellite body has dimensions of 3×3×0.3 meters, the solar panels have dimensions of 3×10 meters, and the triangular truss-shaped base and height have dimensions of 1.5×0.7 meters.

[0036] Keeping the satellite's attitude, orbit, and solar panel motion constant, the original simple connection parts were replaced with models of these four structures in electromagnetic simulation software, and the gain of the telemetry and control antenna T in the -Z plane was simulated. The evaluation criterion was also to minimize the fluctuation of the antenna gain throughout the entire orbital period. Simulations revealed that the streamlined curved surface and the triangular truss 30a structure had weaker blocking and scattering effects on the antenna direction. Among them, the triangular truss 30a structure minimized the change in antenna gain relative to the unconnected structure while ensuring mechanical strength, and was therefore selected as the final design.

[0037] Step S5: Integration verification.

[0038] The finalized design, with the antenna located in the -Z plane and the solar panel connection structure being a triangular truss-shaped 30a, was modeled as a whole. A complete orbital dynamics and attitude dynamics simulation environment was set up to simulate the satellite's operation under the worst lighting conditions of the year, and end-to-end communication link budget analysis was performed. Verification results show that the margin of the telemetry, tracking, and command (TT&C) link meets the design requirements, and there is no risk of interruption throughout the entire simulation period. Its gain remains stable throughout the entire orbital period with minimal fluctuations.

[0039] This method can be implemented in the early stages of satellite overall design, identifying and resolving potential communication interference problems in advance, reducing major changes in the later stages of design, shortening the development cycle, and lowering costs. Satellites designed through simulation have more robust telemetry and control systems to the movement of solar panels, significantly improving the success rate and safety of satellite missions in orbit.

[0040] The layout method in this embodiment can effectively solve the problem of satellite solar panels blocking telemetry and control antennas, greatly improving the satellite-to-ground telemetry and control communication time. Especially in the early stage of satellite entry into orbit, when the satellite has not yet entered a stable working state, the satellite can receive telemetry data and send remote control commands at a low elevation angle, ensuring the efficient and safe operation of the satellite.

[0041] Example 2: This embodiment provides a satellite whose telemetry, tracking, and command (TT&C) antenna system is manufactured according to the layout design described in Embodiment 1. Specifically, the TT&C antenna T is installed at the center of the Z-side of the satellite body, which is perpendicular to the rotation axis of the large single-sided solar panel; and the solar panel is connected to the satellite body through a triangular truss support structure. On-orbit testing showed that the TT&C signal strength of the satellite remained stable throughout the entire orbital period, verifying the effectiveness of the layout method of this invention.

[0042] The above are merely 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 within the protection scope of the present invention.

Claims

1. A method of arranging a satellite TT&C antenna, characterized in that, The method comprises the following steps: Step S1: grid modeling of the position relationship between the satellite body and the solar panel on one side thereof; Step S2: simulation of the unobstructed gain of the TT&C antenna according to the illumination condition and the unobstructed satellite body; Step S3: simulation of the gain of the TT&C antenna in different obstructed relationships according to the illumination condition and the obstructed relationship between the solar panel and the satellite body, and selection of the position of the TT&C antenna with the minimum gain variation; Step S4: design of the connection structure between the satellite body and the solar panel in different shapes, simulation of the gain of the TT&C antenna in different connection structures, and selection of the connection structure shape with the minimum gain variation.

2. The method of claim 1, wherein, The grid modeling in step S1 comprises: dividing the surface of the satellite body and the surface of the solar panel into a plurality of grid units, and establishing position coordinates and geometric attribute information for each grid unit.

3. The method of claim 2, wherein, The geometric attribute information comprises the normal direction, material attribute, and field of view angle relative to the candidate position of the TT&C antenna.

4. The method of claim 1, wherein, In step S3, the minimum gain variation refers to the minimum difference between the gain of the TT&C antenna due to the obstruction of the solar panel and the unobstructed gain in one complete orbit period of the satellite.

5. The method of arranging satellite TT&C antennas according to claim 1 or 4, characterized in that, Step S3 further comprises: preferentially arranging the TT&C antenna on the side of the satellite body coplanar with or perpendicular to the rotation axis of the solar panel.

6. The method of arranging satellite TT&C antennas according to claim 1, characterized in that, The connection structure in step S4 in different shapes comprises: single rod, multi-segment bending, curved surface, or triangular support structure.

7. The method of claim 6, wherein, In step S4, the minimum gain variation refers to the minimum difference between the gain of the TT&C antenna due to the obstruction of the connection structure in different shapes and the unobstructed gain in one complete orbit period of the satellite.

8. The method of claim 1, wherein, After the simulation selection in steps S3 and S4, the method further comprises: integrated modeling according to the selected installation position of the TT&C antenna on the satellite body and the shape of the connection structure between the satellite body and the solar panel, and verification of the full-link communication performance in a dynamic task scenario.

9. The method of claim 1, wherein, The method is suitable for satellites equipped with single-sided or double-sided solar panels.

10. A satellite, characterized by The satellite adopts the layout method of the satellite TT&C antenna according to any one of claims 1-9.

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