Method and system for designing a reflector antenna pointing motion satellite configuration

Abstract

This invention provides a method and system for designing a satellite configuration with a reflector antenna for pointing motion. The method includes: determining the installation method based on the antenna's pointing requirements, wherein the installation method includes upright mounting or oblique mounting; determining the configuration of the entire satellite coordinate system and the antenna's extended arm based on the installation method; handling the bending of the extended arm according to the installation method; determining the interface configuration between the antenna's extended arm and a two-dimensional pointing mechanism based on the installation method; calculating the retraction angle of the two-dimensional pointing mechanism based on the installation method; and determining the installation position of the antenna's extended arm base. This invention enables small-sized satellites to accommodate large-sized reflector antennas while ensuring a wide range of pointing motion in orbit.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, specifically relating to a method and system for designing satellite configurations with reflector antennas that point towards motion. More specifically, it is a satellite configuration design method for large-size reflector antennas that point towards motion over a wide range in orbit.

[0002] The large size is ≥Φ2.5m, where Φ represents the diameter; the large range is defined as the antenna's field of view not being obstructed when rotating ≥±60° around the two axes in the orbital coordinate system. Background Technology

[0003] With the deepening and development of satellite applications in Earth remote sensing, communication and broadcasting, deep space exploration, and especially in acquiring signals with small transmission or radiation power, the demand for large-aperture fixed reflector antennas has become increasingly urgent, prompting satellite antennas to develop towards larger size and wider pointing range in their on-orbit operation.

[0004] Payload, orbit, and attitude control method determine the on-orbit configuration, while the launch fairing affects the configuration during launch. Existing literature has designed satellite configurations with large-aperture solid-surface reflector antennas, large-size planar phased array antennas, and large mesh antennas as the main payloads, proposing many configuration schemes and ideas. The schemes mainly focus on the antenna retracting during launch and deploying in place during on-orbit, and the ideas mainly focus on satisfying the fairing envelope during launch and the non-independent pointing operation state during on-orbit. This is completely different from the problem of large-size reflector antennas with large-range pointing motion in on-orbit that this invention addresses.

[0005] Patent document CN105501471B discloses a satellite configuration for mounting a large, deployable dual-reflector antenna. It proposes a configuration with two large-aperture, on-orbit deployable reflector antennas. This configuration aims to address the needs of satellite launch and on-orbit flight. The large-aperture reflector antennas can be mounted on the satellite in a fully retracted state without requiring extensive on-orbit directional movement. This solution does not address the technical challenge of ensuring extensive on-orbit directional movement of a small satellite while mounting large reflector antennas.

[0006] Patent document CN109927938B discloses a configuration for a geostationary orbit solid aperture microwave detection satellite. It discloses an integrated configuration of a remote sensing satellite platform and payload with an on-orbit deployable reflector antenna. This configuration aims to solve practical engineering challenges such as high payload system integration, large mechanical dimensions, and large span. Although the large-aperture reflector antenna is also obliquely mounted, it is not installed in a fully deployed state, nor does it require large-scale directional movement in orbit. This solution does not address the technical problem of ensuring large-scale directional movement in orbit for a small-sized satellite while mounting a large-sized reflector antenna.

[0007] Patent document CN110329542B discloses a satellite configuration suitable for the cooperative control of ultra-large flexible satellites. The scheme proposes an ultra-large flexible satellite configuration with a large-aperture, on-orbit deployable mesh antenna. This configuration aims to solve problems such as the large payload size and stability of large-size flexible structures in ultra-large flexible satellites. The 15m diameter parabolic antenna can be mounted on the satellite in a fully retracted state without requiring extensive on-orbit directional movement. This scheme does not address the technical challenge of ensuring extensive on-orbit directional movement of a small-sized satellite while mounting a large reflector antenna.

[0008] Patent document CN116845531A discloses a satellite configuration and switching method for a dual-band planar phased array antenna. The proposed configuration aims to address the mounting requirements of dual-band planar phased array antennas, allowing the antenna to be folded and mounted on the satellite without requiring extensive on-orbit directional movement. This solution does not address the technical challenge of ensuring extensive on-orbit directional movement of a small satellite while mounting a large reflector antenna.

[0009] Patent document CN119239988A discloses a satellite configuration and satellite equipped with a deployable antenna. The proposed configuration features a large-sized, on-orbit deployable antenna. This configuration aims to provide a satellite configuration for mounting a deployable antenna, allowing the large flat-panel antenna to be folded and mounted on the satellite without requiring extensive on-orbit directional movement. However, this solution does not address the technical challenge of ensuring extensive on-orbit directional movement of a small satellite while simultaneously mounting a large reflector antenna.

[0010] Patent document CN113471661A discloses a method for mounting and testing a large-aperture reflector antenna with a pointing mechanism on a satellite. This method solves the problem of difficult installation in multi-dimensional space by using a gravity balancing device inside the satellite to adjust the antenna's deployment and retraction states, and by using pyrotechnics to press and fix it in place. However, it fails to address the technical challenge of ensuring a wide range of pointing motion in orbit for a small satellite while mounting a large reflector antenna.

[0011] This problem urgently needs to be solved. Summary of the Invention

[0012] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method and system for designing a reflector antenna configuration for pointing towards a moving satellite.

[0013] A method for designing a reflector antenna configuration for pointing at a moving satellite, according to the present invention, includes: The installation method is determined according to the antenna's pointing requirements, and the installation method includes upright mounting or angled mounting; The configuration of the entire satellite coordinate system and the extended arm of the antenna is determined according to the installation method described above; The bending of the deployable arm is handled according to the installation method described above; The interface configuration between the antenna deployment arm and the two-dimensional pointing mechanism is determined according to the installation method described above; Calculate the convergence angle of the two-dimensional pointing mechanism based on the installation method described above; Determine the installation location of the antenna deployable arm base.

[0014] Preferably, the bending of the deployable arm is handled according to the installation method. When the installation method is oblique mounting, the bending angle of the deployable arm is calculated; the expression for the bending angle is: α = 90° - β + γ Where α represents the bending angle of the antenna extension arm, β is the tilt angle of the reflector antenna mounting surface, and γ is the adjustment amount.

[0015] Preferably, the origin of the whole-satellite coordinate system is located at the geometric center of the star-rocket separation surface.

[0016] Preferably, the two-dimensional pointing mechanism is of type XY, with the two rotation axes being orthogonal. The X-axis is connected to the unfolded arm of the reflector antenna, and the Y-axis is connected to the X-axis and the reflector antenna.

[0017] Preferably, the interface configuration between the antenna deployable arm and the two-dimensional pointing mechanism is determined according to the installation method. That is, when the reflector antenna is mounted upright, the deployable arm is directly connected to the two-dimensional pointing mechanism, and when the two-dimensional pointing mechanism is retracted, the X-axis is 90° and the Y-axis is 0°. When the reflector antenna is mounted at an angle, a right-angled triangular adapter block is added between the unfolding arm and the two-dimensional pointing mechanism, with one of the acute angles being 90°-α. When the two-dimensional pointing mechanism is retracted, the X-axis is β and the Y-axis is 0°.

[0018] A reflector antenna configuration design system for pointing at moving satellites according to the present invention includes: Installation method determination module: Determines the installation method based on the antenna's pointing requirements, including upright mounting or angled mounting; Coordinate system and deployable arm configuration determination module: Determines the overall satellite coordinate system and the configuration of the antenna's deployable arm based on the installation method; Bending processing module: processes the bending of the unfolded arm according to the installation method described; Interface configuration determination module: Determines the interface configuration between the antenna deployment arm and the two-dimensional pointing mechanism based on the installation method; Retraction Angle Calculation Module: Calculates the retraction angle of the two-dimensional pointing mechanism based on the installation method described; Base position determination module: Determines the installation position of the antenna deployment arm base.

[0019] Preferably, the bending processing module is further configured to: calculate the bending angle of the unfolded arm when the installation method is oblique mounting; the expression for the bending angle is: α = 90° - β + γ Where α represents the bending angle of the antenna extension arm, β is the tilt angle of the reflector antenna mounting surface, and γ is the adjustment amount.

[0020] Preferably, the origin of the whole-satellite coordinate system is located at the geometric center of the star-rocket separation surface.

[0021] Preferably, the two-dimensional pointing mechanism is of type XY, with the two rotation axes being orthogonal. The X-axis is connected to the unfolded arm of the reflector antenna, and the Y-axis is connected to the X-axis and the reflector antenna.

[0022] Preferably, the interface configuration determination module is further configured such that: when the reflector antenna is mounted upright, the unfolding arm is directly connected to the two-dimensional pointing mechanism, and when the two-dimensional pointing mechanism is retracted, the X-axis is 90° and the Y-axis is 0°; When the reflector antenna is mounted at an angle, a right-angled triangular adapter block is added between the unfolding arm and the two-dimensional pointing mechanism, with one of the acute angles being 90°-α. When the two-dimensional pointing mechanism is retracted, the X-axis is β and the Y-axis is 0°.

[0023] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention employs two installation methods: upright or oblique mounting, combined with the straight or curved rod design of the deployable arm and the X-axis of the two-dimensional pointing mechanism. The Y-orthogonal configuration allows small satellites to carry large reflector antennas and meets their requirements for a wide range of pointing motion in orbit, breaking through the limitations of satellite envelope.

[0024] 2. Based on the antenna's pointing requirements, this invention adopts either upright or oblique mounting schemes, achieving different pointing tasks without altering the main structure of the satellite, thus significantly improving the adaptability and versatility of satellite configuration design.

[0025] 3. The present invention determines the installation position of the deployable arm base based on the principle of "non-interference", which effectively avoids collisions between the antenna and the satellite during the on-orbit deployment and pointing movement, and ensures the structural safety and motion reliability of the entire satellite in its retracted and deployed states. Attached Figure Description

[0026] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 A flowchart illustrating the steps of the method provided by this invention; Figure 2A schematic diagram of the configuration of the reflector antenna provided by the present invention when the satellite is in its retracted state and mounted upright; Figure 3 A schematic diagram of the configuration of the reflector antenna when it is obliquely mounted and the satellite is folded up, as provided by the present invention. Figure 4 A schematic diagram of the configuration of the reflector antenna provided by the present invention in the deployed state of the satellite when it is mounted upright; Figure 5 This is a schematic diagram of the configuration of the satellite in its deployed state when the reflector antenna is obliquely mounted, as provided by the present invention.

[0027] The diagram shows: 1. Large-size reflector antenna; 11. X-axis of the two-dimensional pointing mechanism; 12. Y-axis of the two-dimensional pointing mechanism; 13. Deployment arm; 14. Deployment shaft; 15. Deployment arm base; 16. Adapter block between the deployment arm and the two-dimensional pointing mechanism. 2. Whole Star Coordinate System 3. Satellite body; 31. Satellite-rocket separation surface 4. Inclined truss Detailed Implementation The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0028] The present invention aims to solve the problem of on-orbit pointing over a wide range of areas using a large-size reflector antenna on a small-size celestial body.

[0029] This invention provides a satellite configuration design method for large-size reflector antennas with wide-range on-orbit pointing motion. The method determines the installation method and the coordinate system of the entire satellite based on the on-orbit wide-range pointing requirements of the large-size reflector antenna, further determines the type of the unfolding arm, the bending angle and the configuration of the two-dimensional pointing mechanism, and finally finalizes the configuration of the entire satellite in both its folded and unfolded states.

[0030] This invention provides a method for designing satellite configurations with reflector antennas that point towards motion, specifically a method for designing satellite configurations for large-size transmitting antennas that point over a wide range of motion in orbit, comprising: Step A: Determine the installation method and satellite configuration based on the pointing requirements of the reflector antenna; Step B: Determine the overall satellite coordinate system based on the installation method; Step C: Determine the configuration of the antenna deployment arm; Step D: Calculate the bending angle of the deployment arm; Step E: Determine the interface configuration between the deployment arm and the two-dimensional pointing mechanism; Step F: Determine the configuration of the two-dimensional pointing mechanism; Step G: Calculate the retraction angle of the two-dimensional pointing mechanism; Step H: Determine the installation position of the deployment arm base.

[0031] Specifically, in step A: the reflector antenna is a solid parabolic antenna, and the installation method is divided into upright mounting and oblique mounting; the satellite body is a hexagonal prism configuration. Specifically, in step B: the origin of the entire star coordinate system is at the geometric center of the star-rocket separation surface; Specifically, in step C: the cross-section of the unfolding arm is quadrilateral; Specifically, in step D: when the reflector antenna is mounted upright, the unfolding arm does not need to be bent; when the reflector antenna is mounted at an angle, the unfolding arm needs to be bent, and the expression for the bending angle α is: α = 90° - β + γ Where β is the tilt angle of the reflector antenna mounting surface, which is the angle between the antenna mounting surface normal and the -X axis. γ is the adjustment amount, used to adjust the space occupied by the two-dimensional pointing mechanism, and its value is determined according to the actual size of the two-dimensional pointing mechanism.

[0032] Specifically, in step E: when the reflector antenna is mounted upright, the unfolding arm is directly connected to the two-dimensional pointing mechanism; when the reflector antenna is mounted obliquely, a right-angled triangular connecting block is added between the unfolding arm and the two-dimensional pointing mechanism, one of which has an acute angle of 90-α. Specifically, in step F: the two-dimensional pointing mechanism is XY type, with the two rotation axes orthogonal. The X-axis is connected to the deployable arm, and the Y-axis is connected to the reflector antenna. Specifically, in step G: when the reflector antenna is mounted upright, the X-axis is 90° and the Y-axis is 0° when the two-dimensional pointing mechanism is retracted; when the reflector antenna is mounted at an angle, the X-axis is β and the Y-axis is 0° when the two-dimensional pointing mechanism is retracted. Specifically, in step H: when the reflector antenna is mounted upright, the mounting surface of the unfolding arm base is parallel to the mounting surface of the reflector antenna; when the reflector antenna is mounted obliquely, the angle between the mounting surface of the unfolding arm base and the mounting surface of the transmitting antenna is 90-β.

[0033] To make the objectives and features of the present invention more apparent and understandable, the specific embodiments of the present invention will be further described below with reference to the accompanying drawings, including the implementation steps, as follows: Figure 1 As shown.

[0034] Step 1: Determine the installation method and satellite configuration based on the pointing requirements of the reflector antenna.

[0035] Specifically, if the on-track pointing of reflector antenna 1 is mainly forward-backward, such as Figure 2 As shown. Therefore, the reflector antenna 1 is mounted upright, directly on the satellite body 3, as shown. Figure 4 As shown; If the on-orbit pointing of reflector antenna 1 is mainly in the sky-to-ground direction, such as Figure 3 As shown. The reflector antenna 1 is mounted obliquely on the inclined truss 4, which in turn is mounted on the satellite body 3. Figure 5 As shown.

[0036] Step 2: Determine the coordinate system of the entire satellite based on the installation method.

[0037] Specifically, if reflector antenna 1 is mounted upright, then the three axes of the entire satellite coordinate system 2 are oriented as follows: Figure 4 As shown. The origin of the coordinate system is at the geometric center of the star-rocket separation surface 31, +X points towards the reflector antenna 1, and +Z points away from the deployable arm base 15. When the deployment axis 14 moves from... Figure 4 After unfolding 180° as shown, the reflector antenna 1 can be realized. Figure 2 The front-back direction is shown; If the reflector antenna 1 is mounted at an angle, then the three axes of the entire satellite coordinate system 2 will point as follows: Figure 5 As shown. The origin of the coordinate system remains at the geometric center of the star-rocket separation surface 31, +X is away from the reflector antenna 1, and +Z is away from the deployable arm 13. When the deployable axis 14 moves from... Figure 5 After unfolding 180° as shown, the reflector antenna 1 can achieve [property adjustment] due to the steering effect of the transition block 16 between the unfolding arm and the two-dimensional pointing mechanism. Figure 3 The sky-to-ground orientation is shown.

[0038] Step 3: Determine the configuration of the antenna deployment arm.

[0039] Specifically, if the reflector antenna 1 is mounted upright, then the extended arm 13 is a straight rod with a quadrilateral cross-section, such as... Figure 4 As shown; If the reflector antenna 1 is mounted at an angle, then the extended arm 13 is a curved rod with a quadrilateral cross-section, such as... Figure 5 As shown.

[0040] Step 4: Calculate the bending angle of the unfolding arm.

[0041] For the case where the outstretched arm 13 is a bent rod, if we take β as 30° and γ as 2°, then according to α=90°-β+γ, we can calculate α as 62°.

[0042] Step 4: Determine the interface configuration between the deployable arm and the two-dimensional pointing mechanism; In the case where the unfolding arm 13 is a straight rod, the unfolding arm 13 is directly connected to the Y-axis of the two-dimensional pointing mechanism; To address the issue of the extended arm 13 being a bent rod, a right-angled triangular adapter block 16 is added between the extended arm 13 and the Y-axis of the two-dimensional pointing mechanism. One acute angle of its cross-section is 28°. The adapter block 16, located at the end of the bent section of the extended arm 13, transforms the bend into a horizontal and vertical alignment, aiming to ensure that after the extended arm is extended 180°, the mounting surface of the Y-axis of the two-dimensional pointing mechanism is perpendicular to the X-axis of the entire star. Figure 5 As shown.

[0043] Step 5: Determine the configuration of the two-dimensional pointing mechanism.

[0044] Specifically, for the case where the deployable arm 13 is a straight rod, the X-axis 11 of the two-dimensional pointing mechanism is directly connected to the deployable arm 13, and the Y-axis 12 of the two-dimensional pointing mechanism is connected to the reflector antenna 1. The two axes are orthogonal, as shown below. Figure 4 As shown; For the case where the deployable arm 13 is a bent rod, the X-axis 11 of the two-dimensional pointing mechanism is connected to the adapter block 16 between the deployable arm and the two-dimensional pointing mechanism, and the Y-axis 12 of the two-dimensional pointing mechanism is connected to the reflector antenna 1. The two axes are orthogonal, as shown below. Figure 5 As shown.

[0045] Step Six: Calculate the convergence angle of the two-dimensional pointing mechanism; When the X-axis 11 of the two-dimensional pointing mechanism is directly connected to the unfolding arm 13, the X-axis 11 of the two-dimensional pointing mechanism is at -90° or 90° when retracted, with a rotation range of [-90°, 90°]. The Y-axis of the two-dimensional pointing mechanism is at position 0, and its polarity is defined by the designer as needed, with a rotation range of [-90°, 90°]. Figure 4 As shown; Regarding the connection between the X-axis 11 of the two-dimensional pointing mechanism and the adapter block 16 between the unfolding arm and the two-dimensional pointing mechanism, when retracted, the X-axis 11 of the two-dimensional pointing mechanism is at position β, with a rotation range of [-90°, 90°], and the Y-axis 12 of the two-dimensional pointing mechanism is at position 0, with a rotation range of [-90°, 90°]. Figure 5 As shown.

[0046] Step 7: Determine the installation position of the deployable arm base.

[0047] Specifically, the present invention determines the installation position of the deployable arm base based on the principle of "non-interference," including: When the reflector antenna 1 is mounted upright, the unfolding arm base 15 is installed on the Z side of the satellite body 3+X plate. The length of the unfolding arm 13 and the quantization position of the unfolding arm base 15 are determined by unfolding the reflector antenna 1 to the on-orbit state with the distance between the antenna and the satellite body 3 ≥ 0 and the antenna field of view unobstructed. When the reflector antenna 1 is mounted at an angle, the unfolding arm base 15 is installed on the -Z side plate of the satellite body 3. The length of the unfolding arm 13 and the quantization position of the unfolding arm base 15 are determined by unfolding the reflector antenna 1 to the on-orbit state with the distance between the antenna and the satellite body 3 ≥ 0 and the antenna field of view unobstructed.

[0048] The present invention also provides a system for designing a configuration of a reflector antenna pointing towards a moving satellite. The system can be implemented by executing the process steps of the method for designing a configuration of a reflector antenna pointing towards a moving satellite. That is, those skilled in the art can understand the method for designing a configuration of a reflector antenna pointing towards a moving satellite as a preferred embodiment of the system for designing a configuration of a reflector antenna pointing towards a moving satellite.

[0049] A reflector antenna configuration design system for pointing at moving satellites according to the present invention includes: Installation method determination module: Determines the installation method based on the antenna's pointing requirements, including upright mounting or angled mounting; Coordinate system and deployable arm configuration determination module: Determines the overall satellite coordinate system and the configuration of the antenna's deployable arm based on the installation method; Bending processing module: processes the bending of the unfolded arm according to the installation method described; Interface configuration determination module: Determines the interface configuration between the antenna deployment arm and the two-dimensional pointing mechanism based on the installation method; Retraction Angle Calculation Module: Calculates the retraction angle of the two-dimensional pointing mechanism based on the installation method described; Base position determination module: Determines the installation position of the antenna deployment arm base.

[0050] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0051] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0052] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for designing a reflector antenna configuration for pointing at a moving satellite, characterized in that, include: The installation method is determined according to the antenna's pointing requirements, and the installation method includes upright mounting or angled mounting; The configuration of the entire satellite coordinate system and the extended arm of the antenna is determined according to the installation method described above; The bending of the deployable arm is handled according to the installation method described above; The interface configuration between the antenna deployment arm and the two-dimensional pointing mechanism is determined according to the installation method described above; Calculate the convergence angle of the two-dimensional pointing mechanism based on the installation method described above; Determine the installation location of the antenna deployable arm base.

2. The method for designing a reflector antenna configuration for pointing at a moving satellite according to claim 1, characterized in that, The bending of the deployable arm is handled according to the installation method. When the installation method is oblique, the bending angle of the deployable arm is calculated; the expression for the bending angle is: α = 90° - β + γ Where α represents the bending angle of the antenna extension arm, β is the tilt angle of the reflector antenna mounting surface, and γ is the adjustment amount.

3. The method for designing a reflector antenna configuration for pointing at a moving satellite according to claim 1, characterized in that, The origin of the entire star coordinate system is located at the geometric center of the star-rocket separation surface.

4. The method for designing a reflector antenna configuration for pointing at a moving satellite according to claim 1, characterized in that, The two-dimensional pointing mechanism is of type XY, with two orthogonal rotation axes. The X-axis is connected to the unfolded arm of the reflector antenna, and the Y-axis is connected to the X-axis and the reflector antenna.

5. The method for designing a reflector antenna configuration for pointing at a moving satellite according to claim 1, characterized in that, The interface configuration between the antenna deployable arm and the two-dimensional pointing mechanism is determined according to the installation method. That is, when the reflector antenna is mounted upright, the deployable arm is directly connected to the two-dimensional pointing mechanism. When the two-dimensional pointing mechanism is retracted, the X-axis is 90° and the Y-axis is 0°. When the reflector antenna is mounted at an angle, a right-angled triangular adapter block is added between the unfolding arm and the two-dimensional pointing mechanism, with one of the acute angles being 90°-α. When the two-dimensional pointing mechanism is retracted, the X-axis is β and the Y-axis is 0°.

6. A system for designing a reflector antenna configuration for pointing at a moving satellite, characterized in that, include: Installation method determination module: Determines the installation method based on the antenna's pointing requirements, including upright mounting or angled mounting; Coordinate system and deployable arm configuration determination module: Determines the overall satellite coordinate system and the configuration of the antenna's deployable arm based on the installation method; Bending processing module: processes the bending of the unfolded arm according to the installation method described; Interface configuration determination module: Determines the interface configuration between the antenna deployment arm and the two-dimensional pointing mechanism based on the installation method; Retraction Angle Calculation Module: Calculates the retraction angle of the two-dimensional pointing mechanism based on the installation method described; Base position determination module: Determines the installation position of the antenna deployment arm base.

7. The reflector antenna pointing configuration design system for moving satellites according to claim 6, characterized in that, The bending processing module is further configured to: calculate the bending angle of the unfolding arm when the installation method is oblique mounting; the expression for the bending angle is: α = 90° - β + γ Where α represents the bending angle of the antenna extension arm, β is the tilt angle of the reflector antenna mounting surface, and γ is the adjustment amount.

8. The reflector antenna pointing configuration design system for moving satellites according to claim 6, characterized in that, The origin of the entire star coordinate system is located at the geometric center of the star-rocket separation surface.

9. The reflector antenna pointing configuration design system for moving satellites according to claim 6, characterized in that, The two-dimensional pointing mechanism is of type XY, with two orthogonal rotation axes. The X-axis is connected to the unfolded arm of the reflector antenna, and the Y-axis is connected to the X-axis and the reflector antenna.

10. The reflector antenna pointing configuration design system for moving satellites according to claim 6, characterized in that, The interface configuration determination module is further configured such that: when the reflector antenna is mounted upright, the unfolding arm is directly connected to the two-dimensional pointing mechanism, and when the two-dimensional pointing mechanism is retracted, the X-axis is 90° and the Y-axis is 0°; When the reflector antenna is mounted at an angle, a right-angled triangular adapter block is added between the unfolding arm and the two-dimensional pointing mechanism, with one of the acute angles being 90°-α. When the two-dimensional pointing mechanism is retracted, the X-axis is β and the Y-axis is 0°.

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