Satellite rescue method, device, equipment and storage medium

Abstract

The present application discloses a satellite rescue method, apparatus, device, and storage medium. The present application relates to the field of satellite rescue technology. The satellite rescue method includes: obtaining solar position information, satellite positioning data, and imaging parameters of an optical payload carried by a rescue satellite, wherein the satellite positioning data includes orbital parameters of the faulty satellite and the orbital parameters of the rescue satellite; adjusting the orbital parameters of the rescue satellite based on the orbital parameters of the faulty satellite so that the rescue satellite and the faulty satellite share the same orbital plane; controlling the rescue satellite to orbit around the faulty satellite based on the solar position information and / or imaging parameters to obtain fault information about the faulty satellite; adjusting the orbital parameters of the rescue satellite to control the rescue satellite to approach the faulty satellite until the relative positions of the faulty satellite and the rescue satellite reach a preset distance range, and repairing the faulty satellite using the rescue satellite based on the fault information. The present application can solve the technical problems of low efficiency and success rate of satellite rescue.

Description

Technical Field

[0001] The present application relates to the field of satellite rescue technology, and in particular to a satellite rescue method, apparatus, equipment, and storage medium. Background Art

[0002] In the field of satellite rescue, traditional methods for rescuing faulty satellites in geosynchronous orbit typically follow a series of steps: remote adjustment, planned approach, flyby observation, and close rendezvous. However, these traditional methods have certain shortcomings. For example, the rescue satellite requires orbital maneuvers during these stages, including remote adjustment, planned approach, flyby observation, and close rendezvous. Improper fuel management can lead to premature termination of the rescue mission. Rescue satellites face complex and ever-changing mission environments, requiring real-time processing of large amounts of data and decision-making, making the rescue process challenging to control.

[0003] Therefore, how to improve the efficiency and success rate of satellite rescue is a problem that needs to be solved urgently. Summary of the Invention

[0004] The main purpose of this application is to provide a satellite rescue method, device, equipment and storage medium, aiming to solve the technical problems of low efficiency and success rate of satellite rescue.

[0005] To achieve the above-mentioned object, the present application provides a satellite rescue method, which is applied to a satellite rescue system, wherein the satellite rescue system includes a faulty satellite and a rescue satellite, and the satellite rescue method includes:

[0006] Acquiring sun position information, satellite positioning data, and imaging parameters of an optical payload carried by the rescue satellite, wherein the satellite positioning data includes orbital parameters of the faulty satellite and the rescue satellite;

[0007] Adjusting the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite so that the rescue satellite and the faulty satellite share the same orbital plane;

[0008] controlling the rescue satellite to fly around the faulty satellite according to the sun position information and / or the imaging parameters, and obtaining fault information of the faulty satellite;

[0009] adjusting the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite, and controlling the rescue satellite to approach the faulty satellite until the relative positions of the faulty satellite and the rescue satellite reach a preset distance range;

[0010] Within the distance range, the faulty satellite is repaired according to the fault information by the rescue satellite.

[0011] In one embodiment, the step of adjusting the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite so that the rescue satellite and the faulty satellite are in the same orbital plane comprises:

[0012] Determining the orbital inclination of the faulty satellite and the orbital inclination of the rescue satellite according to the orbital parameters of the faulty satellite and the orbital parameters of the rescue satellite;

[0013] Determining an orbital inclination change according to the orbital inclination of the faulty satellite and the orbital inclination of the rescue satellite;

[0014] determining an initial orbital velocity of the rescue satellite according to orbital parameters of the rescue satellite;

[0015] Calculating a velocity increment of the rescue satellite according to the orbital inclination change and the initial orbital velocity of the rescue satellite;

[0016] The orbital parameters of the rescue satellite are adjusted according to the speed increment, and the rescue satellite is controlled to share the same orbital plane with the faulty satellite.

[0017] In one embodiment, the step of controlling the rescue satellite to fly around the faulty satellite based on the sun position information and / or the imaging parameters and obtaining fault information of the faulty satellite includes:

[0018] Adjusting the relative phase relationship between the rescue satellite and the faulty satellite according to a preset orbital maneuvering strategy;

[0019] When the phase of the rescue satellite is synchronized with the phase of the faulty satellite, the rescue satellite is controlled to fly around the faulty satellite according to the solar position information and / or the imaging parameters, and the fault information of the faulty satellite is obtained.

[0020] In one embodiment, the step of adjusting the relative phase relationship between the rescue satellite and the faulty satellite according to a preset orbital maneuvering strategy includes:

[0021] Determining a preset tangential velocity increment and phase value of the rescue satellite according to a preset orbital maneuvering strategy;

[0022] reducing the orbital semi-major axis of the rescue satellite according to the tangential velocity increment;

[0023] When the relative phase relationship between the rescue satellite and the faulty satellite reaches the preset phase value, the orbital semi-major axis of the rescue satellite is increased according to the tangential velocity increment, and the phase of the rescue satellite is controlled to be synchronized with the phase of the faulty satellite.

[0024] In one embodiment, the satellite positioning data includes position information of the faulty satellite and position information of the rescue satellite, the imaging parameters include camera angular resolution and maximum field of view, and the step of controlling the rescue satellite to orbit around the faulty satellite based on the sun position information and / or the imaging parameters when the phase of the rescue satellite is synchronized with the phase of the faulty satellite, and obtaining fault information of the faulty satellite includes:

[0025] When the phase of the rescue satellite is synchronized with the phase of the faulty satellite, calculating the solar illumination angle according to the solar position information, the position information of the faulty satellite and the position information of the rescue satellite;

[0026] Calculating the number of imaging pixels of the rescue satellite based on the pre-acquired characteristic size of the faulty satellite, the camera angular resolution, the position information of the faulty satellite, and the position information of the rescue satellite;

[0027] determining a relative distance constraint value between the faulty satellite and the rescue satellite according to the maximum field of view angle;

[0028] According to the solar illumination angle and / or the number of imaging pixels and / or the relative distance constraint value, the rescue satellite is controlled to fly around the faulty satellite and obtain fault information of the faulty satellite.

[0029] In one embodiment, the step of calculating the number of imaging pixels of the rescue satellite based on the pre-acquired characteristic size of the faulty satellite, the camera angular resolution, the position information of the faulty satellite, and the position information of the rescue satellite further includes:

[0030] Calculating an imaging distance according to the position information of the faulty satellite and the position information of the rescue satellite;

[0031] The number of imaging pixels of the rescue satellite is calculated based on the pre-acquired characteristic size of the faulty satellite, the imaging distance, and the camera angular resolution.

[0032] In one embodiment, the step of controlling the rescue satellite to orbit around the faulty satellite based on the solar illumination angle and / or the number of imaging pixels and / or the relative distance constraint value, and obtaining fault information of the faulty satellite includes:

[0033] Comparing the solar illumination angle with a preset solar illumination angle constraint value;

[0034] If the solar illumination angle is greater than the solar illumination angle constraint value, adjusting the position of the rescue satellite; and / or

[0035] Comparing the size relationship between the number of imaging pixels and a preset minimum number of pixels;

[0036] If the number of imaging pixels is less than the minimum number of pixels, adjusting the position of the rescue satellite; and / or

[0037] comparing the imaging distance with the relative distance constraint value;

[0038] If the imaging distance is greater than the relative distance constraint value, adjusting the position of the rescue satellite;

[0039] Based on the adjusted position of the rescue satellite, the rescue satellite is controlled to fly around the faulty satellite and the fault information of the faulty satellite is acquired.

[0040] In addition, to achieve the above-mentioned purpose, the present application also provides a satellite rescue device, which includes:

[0041] a position information acquisition module, configured to acquire sun position information, satellite positioning data, and imaging parameters of the optical payload carried by the rescue satellite, wherein the satellite positioning data includes orbital parameters of the faulty satellite and the rescue satellite;

[0042] A first orbital parameter adjustment module is configured to adjust the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite so that the rescue satellite and the faulty satellite are in the same orbital plane;

[0043] a fault information acquisition module, configured to control the rescue satellite to fly around the faulty satellite according to the sun position information and / or the imaging parameters, and to acquire fault information of the faulty satellite;

[0044] a second orbital parameter adjustment module, configured to adjust the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite, and control the rescue satellite to approach the faulty satellite until the relative positions of the faulty satellite and the rescue satellite reach a preset distance range;

[0045] The satellite fault repair module is used to repair the fault satellite within the distance range through the rescue satellite according to the fault information.

[0046] In addition, to achieve the above-mentioned purpose, the present application also proposes a satellite rescue device, which includes: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the computer program is configured to implement the steps of the satellite rescue method described above.

[0047] In addition, to achieve the above-mentioned purpose, the present application also provides a storage medium, which is a computer-readable storage medium. The computer-readable storage medium stores a program for implementing the satellite rescue method. The program for implementing the satellite rescue method is executed by a processor to implement the steps of the satellite rescue method as described above.

[0048] The present application provides a satellite rescue method, which obtains solar position information, satellite positioning data, and imaging parameters of the optical payload carried by the rescue satellite, and adjusts the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite, so that the two are in the same orbital plane, so that the rescue satellite can approach the faulty satellite more effectively, reducing the additional maneuvering requirements caused by the difference in orbital planes, thereby saving fuel and time. After the same orbital plane, the rescue satellite is controlled to fly in an orbit according to the solar position information and / or imaging parameters, fully considering the lighting conditions and imaging quality. By intelligently adjusting the orbiting trajectory and attitude, the rescue satellite can obtain clear, multi-angle images of the faulty satellite, providing rich information for fault diagnosis. By precisely controlling the orbital parameters of the rescue satellite, it can efficiently approach the faulty satellite, ensuring the timeliness and effectiveness of the rescue operation. After approaching, the rescue satellite can directly perform repair operations based on the fault information, improving the efficiency and success rate of satellite rescue. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0050] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0051] Figure 1 A schematic diagram of the flow chart provided for the first embodiment of the satellite rescue method of this application;

[0052] Figure 2 This is a flow chart of the satellite rescue method according to an embodiment of the present application;

[0053] Figure 3 This is a schematic diagram of a rescue satellite flying around a faulty satellite according to an embodiment of the present application;

[0054] Figure 4 This is a schematic diagram of the phase adjustment of the rescue satellite according to the embodiment of the present application;

[0055] Figure 5 This is a schematic diagram of the first solar illumination angle according to an embodiment of the present application;

[0056] Figure 6 This is a schematic diagram of the second solar illumination angle according to an embodiment of the present application;

[0057] Figure 7 This is a schematic diagram of the effective load range of the optical payload carried by the rescue satellite according to the embodiment of the present application;

[0058] Figure 8 This is a schematic diagram of the module structure of the satellite rescue device according to an embodiment of the present application;

[0059] Figure 9 This is a schematic diagram of the device structure of the hardware operating environment involved in the satellite rescue method in the embodiment of the present application.

[0060] The purpose, features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0061] It should be understood that the specific embodiments described herein are merely used to explain the technical solutions of the present application and are not intended to limit the present application.

[0062] In order to better understand the technical solution of the present application, a detailed description will be given below in conjunction with the accompanying drawings and specific implementation methods.

[0063] The main solution of the present application is: obtaining solar position information, satellite positioning data and imaging parameters of the optical payload carried by the rescue satellite, the satellite positioning data including the orbital parameters of the faulty satellite and the orbital parameters of the rescue satellite; adjusting the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite so that the rescue satellite and the faulty satellite share the same orbital plane; controlling the rescue satellite to fly around the faulty satellite as the center according to the solar position information and / or the imaging parameters, and obtaining the fault information of the faulty satellite; adjusting the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite, and controlling the rescue satellite to approach the faulty satellite until the relative positions of the faulty satellite and the rescue satellite reach a preset distance range; within the distance range, repairing the faulty satellite according to the fault information by the rescue satellite.

[0064] The faulty satellite and the rescue satellite are both located at different longitudes near the geosynchronous orbital belt. Due to unknown reasons, the faulty satellite's onboard equipment is malfunctioning, requiring fault location and repair. The rescue satellite, equipped with optical payloads and repair capabilities, maneuvers to approach the faulty satellite to carry out imaging, fault location, and rescue missions. The rescue satellite first plans a relative approach path based on the satellite's status and relative position information, taking into account constraints such as fuel consumption, mission time, relative distance, and solar illumination angle. This allows the rescue satellite to approach, fly around, perform optical imaging, and perform rescue missions at a relatively low cost.

[0065] Reference Figure 2 For satellites in geosynchronous orbit that require rescue and have functional problems (referred to as faulty satellites), the rescue satellite carries out the rescue according to a series of steps: remote adjustment, planned approach, flyby observation, and close rendezvous. During the remote adjustment phase, the rescue satellite uses its own GNSS (Global Navigation Satellite System) data to obtain information about the satellite's relative motion state and adjusts its orbital plane through orbital maneuvers to bring the rescue satellite and the faulty satellite into alignment. During the planned approach phase, the rescue satellite adjusts its relative orbital position through orbital maneuvers to achieve fixed-point stationing with the faulty satellite. During the flyby phase, the rescue satellite performs timed orbital maneuvers to achieve a follow-the-light orbit around the rescue satellite and, using the onboard optical payload, images the faulty satellite to locate the faulty component at close range. During the close rendezvous phase, the rescue satellite approaches the faulty satellite to carry out the rescue mission. During the rescue process, the rescue satellite needs to consider constraints such as fuel consumption, mission time, solar illumination angle, and relative distance to comprehensively plan the approach path and rescue strategy, thereby improving the efficiency and success rate of satellite rescue.

[0066] This application obtains solar position information, satellite positioning data, and imaging parameters of the optical payload carried by the rescue satellite, and adjusts the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite, so that the two are in the same orbital plane, allowing the rescue satellite to approach the faulty satellite more effectively, reducing the need for additional maneuvers due to differences in orbital planes, thereby saving fuel and time. After sharing the same orbital plane, the rescue satellite is controlled to fly around based on the solar position information and / or imaging parameters, fully considering the lighting conditions and imaging quality. By intelligently adjusting the orbiting trajectory and attitude, the rescue satellite can obtain clear, multi-angle images of the faulty satellite, providing rich information for fault diagnosis. By precisely controlling the orbital parameters of the rescue satellite, it can efficiently approach the faulty satellite, ensuring the timeliness and effectiveness of the rescue operation. After approaching, the rescue satellite can directly perform repair operations based on the fault information, improving the efficiency and success rate of satellite rescue.

[0067] It should be noted that the execution entity of this embodiment may be a satellite rescue system, a computing service device with data processing, network communication, and program execution capabilities, such as a tablet computer, personal computer, or mobile phone, or a satellite rescue device capable of performing the aforementioned functions, and this embodiment is not specifically limited thereto. This embodiment and the following embodiments will be described below using a satellite rescue system as the execution entity.

[0068] Based on this, this application proposes a satellite rescue method of the first embodiment, please refer to Figure 1 The satellite rescue method is applied to a satellite rescue system, wherein the satellite rescue system includes a faulty satellite and a rescue satellite. The satellite rescue method includes steps S10 to S50:

[0069] Step S10, obtaining sun position information, satellite positioning data, and imaging parameters of the optical payload carried by the rescue satellite, wherein the satellite positioning data includes orbital parameters of the faulty satellite and the rescue satellite;

[0070] It should be noted that since the position of the sun directly affects the satellite's lighting conditions, thermal environment, and imaging quality of the optical payload, it is necessary to obtain information on the sun's position. This can be achieved through astronomical algorithms or querying relevant databases. These algorithms and databases will calculate the exact position of the sun based on the date, time, and geographic location of the observation point.

[0071] Satellite positioning data, acquired through the satellite's own GNSS (Global Navigation Satellite System), includes the orbital parameters and position information of the faulty and rescue satellites. These orbital parameters may include semi-major axis, eccentricity, orbital inclination, right ascension of the ascending node, argument of perigee, and true anomaly. Position information includes the three-dimensional coordinates of the faulty and rescue satellites in space.

[0072] Optical payloads are important observation and imaging equipment on rescue satellites. Their imaging parameters are crucial for obtaining high-quality image data. These parameters may include camera resolution, maximum field of view, focal length, aperture, or exposure time.

[0073] Step S20, adjusting the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite so that the rescue satellite and the faulty satellite are in the same orbital plane;

[0074] It should be noted that although the rescue satellite and the faulty satellite are both located near the geosynchronous orbital belt, they are located above different longitudes. Therefore, the rescue satellite needs to perform orbital maneuvers to adjust its relative position with the faulty satellite and gradually approach the faulty satellite. Satellite orbital maneuvers require the consumption of its own fuel to achieve the purpose of orbit change. Fuel is a major factor affecting the satellite's on-orbit lifespan. The corresponding approach mission needs to be completed with the minimum cost, that is, the consumption of as little fuel as possible.

[0075] During the remote adjustment phase, the primary goal is to adjust the relative motion trend between the rescue satellite and the faulty satellite to meet the mission's time constraints. When two geosynchronous satellites are not in the same orbital plane, the rescue satellite and the faulty satellite have two windows of time per day when they are in the same orbital plane. Without adjusting the orbital inclination, these windows are very short and imaging quality is difficult to guarantee. Therefore, by adjusting the rescue satellite's orbital plane, the constraint of not being in the same orbital plane can be eliminated, ensuring high-quality optical imaging for a longer period of time. By acquiring information about the satellite's on-orbit motion status through global navigation satellite system equipment, the rescue satellite's orbital plane is adjusted to align with the faulty satellite's orbital plane. This is primarily achieved by adjusting the orbital inclination. For geosynchronous satellites, due to their lower eccentricity, only the orbital inclination adjustment is usually required. Once the rescue satellite and the faulty satellite are in the same orbital plane, the time window for optical imaging can be expanded, improving imaging quality and mission flexibility.

[0076] Step S30: controlling the rescue satellite to fly around the faulty satellite according to the sun position information and / or the imaging parameters, and acquiring fault information of the faulty satellite;

[0077] It's important to note that after the rescue satellite and the faulty satellite enter the same orbital plane, careful planning of orbital control tasks during the approach phase is required to quickly and effectively troubleshoot the problem. This process requires considering the relative phase and approach velocity between the two. By adjusting the rescue satellite's semi-major axis, it is controlled to approach the faulty satellite at an appropriate speed. When time is critical, a large adjustment of the semi-major axis is used to accelerate approach, but this will sacrifice more fuel. When time is ample, a smaller adjustment can be used to reduce fuel consumption. When the rescue satellite's phase is synchronized with the faulty satellite, the flyby phase begins. The rescue satellite adjusts the optical payload's attitude to achieve a forward-looking flyby centered on the faulty satellite to ensure image quality. By setting an elliptical orbit (approximately one day) that closely matches the Earth's rotation period of the faulty satellite, the rescue satellite utilizes a high-precision attitude control system to maintain constant alignment of the optical payload with the faulty satellite, enabling multi-angle imaging to comprehensively collect fault information, laying a solid foundation for subsequent diagnosis and repair work.

[0078] Step S40, adjusting the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite, and controlling the rescue satellite to approach the faulty satellite until the relative positions of the faulty satellite and the rescue satellite reach a preset distance range;

[0079] It should be noted that during the close rendezvous phase, the rescue satellite's primary mission is to approach the faulty satellite at close range so that it can repair the problem using its onboard repair payload. The rescue satellite first needs to perform precise orbital adjustments based on the faulty satellite's orbital parameters. This involves adjusting speed, altitude, and phase to ensure it can gradually approach the faulty satellite until the relative positions of the faulty satellite and the rescue satellite reach a preset distance range. This preset distance range can be set based on satellite performance, the space environment, or the actual requirements of the satellite rescue mission. During the approach, the rescue satellite must maintain stable attitude and orbital control to cope with the complex environment and potential interference factors in space. Using a high-precision navigation and positioning system, the rescue satellite can obtain precise real-time position information of itself and the faulty satellite, ensuring that no collision or deviation from the planned orbit occurs during the rendezvous.

[0080] Step S50: Repairing the faulty satellite within the distance range by using the rescue satellite according to the fault information.

[0081] It should be noted that the fault repair payload carried by the rescue satellite may include various specialized tools and equipment, such as a robotic arm, repair robots, and spare parts replacement devices. Once the rescue satellite approaches the faulty satellite and reaches a predetermined distance, it will first conduct a comprehensive inspection and diagnosis of the satellite using its onboard fault diagnosis system. Based on the fault information obtained during the flyby phase, the rescue satellite will then use the fault repair payload to repair the faulty satellite, completing the satellite rescue mission.

[0082] The present application provides a satellite rescue method, which obtains solar position information, satellite positioning data, and imaging parameters of the optical payload carried by the rescue satellite, and adjusts the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite, so that the two are in the same orbital plane, so that the rescue satellite can approach the faulty satellite more effectively, reducing the additional maneuvering requirements caused by the difference in orbital planes, thereby saving fuel and time. After the same orbital plane, the rescue satellite is controlled to fly in an orbit according to the solar position information and / or imaging parameters, fully considering the lighting conditions and imaging quality. By intelligently adjusting the orbiting trajectory and attitude, the rescue satellite can obtain clear, multi-angle images of the faulty satellite, providing rich information for fault diagnosis. By precisely controlling the orbital parameters of the rescue satellite, it can efficiently approach the faulty satellite, ensuring the timeliness and effectiveness of the rescue operation. After approaching, the rescue satellite can directly perform repair operations based on the fault information, improving the efficiency and success rate of satellite rescue.

[0083] In a feasible implementation, step S20 may include steps S201 to S205:

[0084] Step S201, determining the orbital inclination of the faulty satellite and the orbital inclination of the rescue satellite according to the orbital parameters of the faulty satellite and the orbital parameters of the rescue satellite;

[0085] Step S202, determining an orbital inclination change according to the orbital inclination of the faulty satellite and the orbital inclination of the rescue satellite;

[0086] Step S203, determining the initial orbital velocity of the rescue satellite according to the orbital parameters of the rescue satellite;

[0087] Step S204, calculating a velocity increment of the rescue satellite according to the orbital inclination change and the initial orbital velocity of the rescue satellite;

[0088] Step S205: adjusting the orbital parameters of the rescue satellite according to the speed increment, and controlling the rescue satellite to be on the same orbital plane as the faulty satellite.

[0089] It should be noted that during the remote adjustment phase, the main task is to adjust the relative motion trend between the rescue satellite and the faulty satellite. Based on the satellite's on-orbit motion status information obtained by the global navigation satellite system equipment on board, the semi-major axis of the rescue satellite's orbit is adjusted so that the relative motion trend between the rescue satellite and the faulty satellite can meet the mission time constraints. The relationship between the semi-major axis of the orbit and the orbital period is:

[0090]

[0091] In the above formula, T is the orbital period, μ is the Earth's gravitational constant, and a is the semi-major axis of the satellite orbit.

[0092] Another task in the remote adjustment phase is to adjust the orbital plane of the rescue satellite so that it is on the same orbital plane as the faulty satellite. Orbital plane adjustment involves adjusting two orbital elements: the orbital inclination i and the right ascension Ω of the ascending node. However, for geosynchronous orbit satellites with a small eccentricity e, generally only the orbital inclination i is adjusted. The velocity increment required to adjust the orbital inclination is:

[0093]

[0094] In the above formula, Δv is the velocity increment, v 初始 is the initial orbital velocity, and Δθ is the change in orbital inclination, which is determined by the difference in orbital inclination between the faulty satellite and the rescue satellite.

[0095] Compared with orbital maneuvers within the orbital plane, changing the orbital inclination requires a larger velocity increment, which comes at the cost of consuming a large amount of fuel.

[0096] If two satellites in the geosynchronous orbital zone are not in the same orbital plane, they have two co-orbital windows per cycle. Since the period of satellites in the geosynchronous orbital zone is generally similar to the Earth's rotation in the late stage, that is, about one day, the two satellites actually have two opportunities to be in the same orbital plane every day, that is, the daily window exists twice a day. If the orbital inclination is not adjusted, the time when the two satellites are in the same orbital plane must be calculated and used as the time window for optical imaging. This time window is very short and it is difficult to guarantee imaging quality. To extend the optical imaging window, the orbital plane of the rescue satellite is usually adjusted so that the rescue satellite is in the same orbital plane as the faulty satellite, thus eliminating the impact of the non-co-orbital constraint.

[0097] In this embodiment, based on the orbital inclinations of the faulty satellite and the rescue satellite, the relative positional relationship between the two in space can be accurately understood, and the change in orbital inclination can be determined. Using the initial orbital velocity information of the rescue satellite, combined with the necessary orbital inclination change, the required velocity increment can be accurately calculated. This helps the rescue satellite achieve the predetermined orbital adjustment target while minimizing the waste of propulsion system resources when performing orbit change operations, thereby improving the efficiency of satellite rescue. Placing the rescue satellite on the same orbital plane as the faulty satellite can reduce the difficulty of subsequent satellite docking or close-range fault repair operations, improve the success rate of satellite rescue missions, and reduce the risk of collisions caused by position errors, thereby ensuring the safety of the satellite and its operations.

[0098] In a feasible implementation, step S30 may include steps S301 to S302:

[0099] Step S301, adjusting the relative phase relationship between the rescue satellite and the faulty satellite according to a preset orbital maneuvering strategy;

[0100] Step S302: When the phase of the rescue satellite is synchronized with the phase of the faulty satellite, the rescue satellite is controlled to fly around the faulty satellite according to the solar position information and / or the imaging parameters, and the fault information of the faulty satellite is obtained.

[0101] It should be noted that after the rescue satellite and the faulty satellite are in the same orbital plane, adjustments are made during the planned approach phase. Since satellite rescue operations require a certain timeframe, namely, the rescue satellite must arrive near the faulty satellite within a specified timeframe to locate and troubleshoot the fault. Therefore, during orbital control mission planning, the rescue satellite must consider the relative phase relationship and relative approach velocity between the rescue satellite and the faulty satellite. The relative phase relationship between the rescue satellite and the faulty satellite is adjusted to ensure that the rescue satellite approaches the stationary point near the faulty satellite.

[0102] The relative approach velocity is typically related to the satellite's semi-major axis. If the satellite's semi-major axis is smaller than that of a geosynchronous orbit satellite, the satellite will tend to drift eastward relative to Earth. If the satellite's semi-major axis is larger than that of a geosynchronous orbit satellite, the satellite will tend to drift westward relative to Earth. Therefore, the rescue satellite's semi-major axis must be adjusted to keep it constantly "drifting" closer to the damaged satellite.

[0103] The size of the rescue satellite's semi-major axis relative to the faulty satellite determines its relative speed during approach. If the rescue mission is time-sensitive, the size of the rescue satellite's semi-major axis relative to the damaged satellite should be adjusted as much as possible to accelerate the approach. Larger semi-major axis adjustments require larger speed increments, which results in greater fuel consumption for the rescue satellite. If the rescue mission has less time constraints, small adjustments to the semi-major axis can be made to allow the rescue satellite to "drift" closer to the faulty satellite at a lower relative speed.

[0104] When the phase of the rescue satellite is synchronized with the phase of the faulty satellite, the fly-by phase is controlled to control the rescue satellite to adjust the attitude of the optical payload and complete the position adjustment of the fly-by along the light, for example Figure 3 shown.

[0105] After the rescue satellite completes its fixed-point stay on the faulty satellite, it completes the elliptical orbit around the faulty satellite by adjusting the speed increment of the rescue satellite. The period of the orbiting ellipse is the same as the period of the faulty satellite's rotation around the earth, which is approximately equal to 1 day. The rescue satellite is equipped with optical payloads (such as cameras, telescopes, etc.) for imaging the faulty satellite. These optical payloads need to be precisely aligned with the faulty satellite to ensure the clarity and accuracy of the imaging. In order to ensure that the optical payload always points to the faulty satellite, and the imaging effect of the rescue satellite is affected by the position of the sun, the rescue satellite needs to perform complex attitude control. Attitude control refers to maintaining or changing the direction of the satellite by adjusting its attitude. The attitude control system of the rescue satellite will continuously adjust its attitude to ensure that the line of sight of the optical payload is always aligned with the faulty satellite.

[0106] As the rescue satellite orbits the faulty satellite in an elliptical orbit, its position relative to the satellite is constantly changing. By adjusting parameters such as the optical payload's focal length and exposure time, combined with the rescue satellite's orbital parameters and attitude information, multi-angle imaging of the faulty satellite can be achieved during the orbit. This helps obtain comprehensive information about the faulty satellite, providing a crucial basis for subsequent fault diagnosis and repair.

[0107] Furthermore, step S301 may include steps S3011 to S3013:

[0108] Step S3011, determining a preset tangential velocity increment and phase value of the rescue satellite according to a preset orbital maneuvering strategy;

[0109] Step S3012, reducing the orbital semi-major axis of the rescue satellite according to the tangential velocity increment;

[0110] Step S3013: When the relative phase relationship between the rescue satellite and the faulty satellite reaches the preset phase value, the semi-major axis of the rescue satellite's orbit is increased according to the tangential velocity increment, and the phase of the rescue satellite is controlled to be synchronized with the phase of the faulty satellite.

[0111] It should be noted that the relative position relationship between the rescue satellite and the faulty satellite is adjusted so that the rescue satellite approaches the stationary point near the faulty satellite. Since the orbital angular velocity n of the geosynchronous orbit satellite is only related to the semi-major axis a of the orbit, that is:

[0112]

[0113] In the above formula, μ is the Earth's gravitational constant, n is the angular velocity, and a is the semi-major axis of the orbit.

[0114] Lowering the orbital semi-major axis can increase the orbital angular velocity, while increasing the orbital semi-major axis can reduce the orbital angular velocity. In order to change the orbital semi-major axis of the satellite with the greatest efficiency, the tangential velocity increment is usually used to change the orbital semi-major axis. The preset orbital maneuver strategy for the approach phase is planned, for example Figure 4 As shown in the figure, the rescue satellite adjusts its relative phase relationship with the faulty satellite by lowering or raising its semi-major axis. This adjustment is accomplished by two tangential velocity increments, Δv1 and Δv2, from a0 to a1 and back to a0. After the phase adjustment, the rescue satellite's phase is synchronized with the faulty satellite's, and the two satellites have the same semi-major axis and are in a relative stationary state.

[0115] After the rescue satellite and the faulty satellite are in the same orbital plane, that is, the two satellites have the same orbital inclination, the rescue satellite only needs to perform in-orbit maneuvers to achieve relative approach motion path planning. When performing in-orbit maneuvers, tangential velocity increments are generally used for control instead of radial velocity increments. This is because tangential velocity increments are the fastest way to increase the mechanical energy of the rescue satellite:

[0116]

[0117] In the above formula, ξ 变轨后 is the mechanical energy after track change, ξ 变轨前 is the mechanical energy before orbit change, v is the initial orbital velocity of the satellite, and Δv is the increment of tangential orbital velocity.

[0118] As can be seen from the above formula, if the direction of the rescue satellite's velocity increment is tangential to the satellite's velocity, then the unit velocity increment maximizes the change in mechanical energy. This means that a tangential velocity increment causes the fastest change in the satellite's mechanical energy. If the direction of the rescue satellite's velocity increment is perpendicular to the satellite's velocity, then the unit velocity increment does not change the mechanical energy. This means that a radial velocity increment does not cause a change in the satellite's mechanical energy. A satellite's mechanical energy is closely related to its semi-major axis and mechanical energy. Tangential velocity increments can minimize the efficiency of changing the relative motion position of the satellites, while radial velocity increments are typically used to adjust the satellites' phase relationship.

[0119] Furthermore, the satellite positioning data includes the position information of the faulty satellite and the position information of the rescue satellite, and the imaging parameters include the camera angular resolution and the maximum field of view. Step S302 may include steps S3021 to S3024:

[0120] Step S3021, when the phase of the rescue satellite is synchronized with the phase of the faulty satellite, calculating the solar illumination angle according to the solar position information, the position information of the faulty satellite, and the position information of the rescue satellite;

[0121] Step S3022, calculating the number of imaging pixels of the rescue satellite based on the pre-acquired characteristic size of the faulty satellite, the camera angular resolution, the position information of the faulty satellite, and the position information of the rescue satellite;

[0122] Step S3023: determining a relative distance constraint value between the faulty satellite and the rescue satellite according to the maximum field of view angle;

[0123] Step S3024: Control the rescue satellite to fly around the faulty satellite based on the solar illumination angle and / or the number of imaging pixels and / or the relative distance constraint value, and obtain fault information of the faulty satellite.

[0124] It should be noted that the rescue satellite carries an optical imaging payload. The rescue satellite flies around the faulty satellite and simultaneously performs optical imaging of the faulty satellite. It is necessary to meet certain solar illumination angle constraints to achieve imaging of the faulty satellite. The solar illumination angle is the angle formed by the rescue satellite, the faulty satellite, and the sun. Figure 5 and Figure 6 shown.

[0125] In addition to being affected by the sun's angle of illumination, imaging quality is also affected by the relative distance between the faulty satellite and the rescue satellite. The precise position information of the faulty and rescue satellites is obtained, and their coordinates in three-dimensional space are determined. The straight-line distance between the faulty and rescue satellites, known as the imaging distance, is calculated. Based on this imaging distance, the number of imaging pixels can be calculated to assess the image clarity of the rescue satellite.

[0126] The effective load of the optical payload carried by the rescue satellite is also constrained by the field of view of the device itself. Figure 7 , the shape of the light cone is the maximum field angle θ max Given a 5° payload range, the rescue satellite can only image within the light cone. This requires ensuring the faulty satellite is within the light cone for imaging. Therefore, the relative distance constraint between the faulty satellite and the rescue satellite can be determined based on the maximum field of view. Based on the faulty satellite's imaging results, image analysis and fault confirmation are performed to obtain fault information about the faulty satellite.

[0127] Furthermore, step S3022 may include steps S30221 to S30222:

[0128] Step S30221, calculating the imaging distance according to the position information of the faulty satellite and the position information of the rescue satellite;

[0129] Step S30222: Calculate the number of imaging pixels of the rescue satellite based on the pre-acquired characteristic size of the faulty satellite, the imaging distance, and the camera angular resolution.

[0130] It should be noted that the imaging distance is the straight-line distance between the faulty satellite and the rescue satellite. The coordinate point of the faulty satellite is determined based on the position information of the faulty satellite, and the coordinate point of the rescue satellite is determined based on the position information of the rescue satellite. The imaging distance is calculated using the distance formula between two points in three-dimensional space.

[0131] The calculation method of the number of imaging pixels of the rescue satellite is shown in the following formula:

[0132]

[0133] Where N is the number of imaging pixels of the rescue satellite. The number of imaging pixels can reflect the clarity of the rescue satellite's image of the faulty satellite.

[0134] Furthermore, step S3024 may include steps S30241 to S30246:

[0135] Step S30241, comparing the solar illumination angle with a preset solar illumination angle constraint value;

[0136] Step S30242: If the solar illumination angle is greater than the solar illumination angle constraint value, adjust the position of the rescue satellite; and / or

[0137] Step S30243, comparing the number of imaging pixels with a preset minimum number of pixels;

[0138] Step S30244: if the number of imaging pixels is less than the minimum number of pixels, adjust the position of the rescue satellite; and / or

[0139] Step S30245, comparing the imaging distance and the relative distance constraint value;

[0140] Step S30245: If the imaging distance is greater than the relative distance constraint value, adjust the position of the rescue satellite;

[0141] Step S30246: Based on the adjusted position of the rescue satellite, control the rescue satellite to fly around the faulty satellite and obtain fault information of the faulty satellite.

[0142] It should be noted that the solar angle constraint value can be set to 90°, refer to Figure 5 When the sunlight angle is greater than 90°, the rescue satellite will be affected by the strong sunlight when performing optical imaging on the faulty satellite, resulting in the inability to perform optical imaging; Figure 6 When the solar illumination angle is less than 90°, the rescue satellite can meet the optical imaging conditions for the faulty satellite and can perform optical imaging of specific components of the faulty satellite. When the solar illumination angle is greater than the solar illumination angle constraint, the position or attitude of the rescue satellite is adjusted to reduce the solar illumination angle to less than the solar illumination angle constraint, ensuring that the rescue satellite can perform optical imaging of the faulty satellite.

[0143] Preferably, the preset minimum pixel count can be set to 50. Clear imaging of the faulty satellite can only be achieved when N ≥ 50. Alternatively, the minimum pixel count can be set accordingly based on the actual observation accuracy requirements to achieve the desired imaging clarity. If the number of imaging pixels is less than the minimum, the position of the rescue satellite is adjusted to adjust the imaging distance and obtain a clear image of the faulty satellite.

[0144] The effective load of the optical payload carried by the rescue satellite is also constrained by the field of view of the device itself. According to the maximum field of view, the relative distance constraint value between the faulty satellite and the rescue satellite can be determined. Figure 7 , maximum field of view angle θ max The relative distance constraint value L is 5° max The imaging distance between the faulty satellite and the rescue satellite must be less than the relative distance constraint value. If the imaging distance is greater than the relative distance constraint value, the position of the rescue satellite is adjusted to adjust the imaging distance to obtain a clear imaging result of the faulty satellite.

[0145] The present application also provides a satellite rescue device, please refer to Figure 8 , the satellite rescue device includes:

[0146] A position information acquisition module 10 is used to obtain sun position information, satellite positioning data, and imaging parameters of the optical payload carried by the rescue satellite, wherein the satellite positioning data includes orbital parameters of the faulty satellite and the rescue satellite;

[0147] A first orbital parameter adjustment module 20 is configured to adjust the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite so that the rescue satellite and the faulty satellite are in the same orbital plane;

[0148] a fault information acquisition module 30, configured to control the rescue satellite to fly around the faulty satellite according to the sun position information and / or the imaging parameters, and to acquire fault information of the faulty satellite;

[0149] a second orbital parameter adjustment module 40, configured to adjust the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite, and control the rescue satellite to approach the faulty satellite until the relative positions of the faulty satellite and the rescue satellite reach a preset distance range;

[0150] The satellite fault repair module 50 is configured to repair the faulty satellite within the distance range by using the rescue satellite according to the fault information.

[0151] The satellite rescue device provided in the embodiments of the present application, utilizing the satellite rescue method of the aforementioned embodiments, can address the technical issues of low efficiency and success rate of satellite rescue. Compared to the prior art, the beneficial effects of the satellite rescue device provided in the embodiments of the present application are the same as those of the satellite rescue method provided in the aforementioned embodiments. Other technical features of the satellite rescue device are the same as those disclosed in the aforementioned embodiments and are not further described here.

[0152] The present application provides a satellite rescue device, which includes: at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores instructions that can be executed by the at least one processor, and the instructions are executed by the at least one processor so that the at least one processor can execute the satellite rescue method in the above-mentioned embodiment 1.

[0153] Reference below Figure 9 , which shows a schematic diagram of the structure of a satellite rescue device suitable for implementing an embodiment of the present application. The satellite rescue device in the embodiment of the present application may include, but is not limited to, mobile terminals such as mobile phones, laptop computers, digital broadcast receivers, PDAs (Personal Digital Assistants), PADs (Portable Application Descriptions), PMPs (Portable Media Players), and vehicle-mounted terminals (e.g., vehicle-mounted navigation terminals), as well as fixed terminals such as digital TVs and desktop computers. Figure 9 The satellite rescue equipment shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0154] like Figure 9 As shown, the satellite rescue equipment may include a processing device 1001 (e.g., a central processing unit, a graphics processing unit, etc.), which can perform various appropriate actions and processes based on programs stored in a read-only memory (ROM) 1002 or programs loaded from a storage device 1003 into a random access memory (RAM) 1004. RAM 1004 also stores various programs and data required for the operation of the satellite rescue equipment. Processing device 1001, ROM 1002, and RAM 1004 are interconnected via a bus 1005. An input / output (I / O) interface 1006 is also connected to the bus. Typically, the following systems may be connected to I / O interface 1006: input device 1007 including, for example, a touch screen, touchpad, keyboard, mouse, image sensor, microphone, accelerometer, gyroscope, etc.; output device 1008 including, for example, a liquid crystal display (LCD), speaker, vibrator, etc.; storage device 1003 including, for example, a magnetic tape, hard disk, etc.; and communication device 1009. Communication device 1009 can allow the satellite rescue device to communicate with other devices wirelessly or by wire to exchange data. Although the figure shows a satellite rescue device with various systems, it should be understood that it is not required to implement or have all of the systems shown. More or fewer systems may be implemented or provided instead.

[0155] In particular, according to the embodiments disclosed in the present application, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, the embodiments disclosed in the present application include a computer program product comprising a computer program carried on a computer-readable medium, the computer program comprising program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from a network via a communication device, or installed from a storage device 1003, or installed from a ROM 1002. When the computer program is executed by the processing device 1001, the above-mentioned functions defined in the method of the embodiment disclosed in the present application are executed.

[0156] The satellite rescue device provided in this application utilizes the satellite rescue method described in the aforementioned embodiment to address the technical issues of satellite rescue. Compared to the prior art, the beneficial effects of the satellite rescue device provided in this application are the same as those of the satellite rescue method described in the aforementioned embodiment. Other technical features of the satellite rescue device are the same as those disclosed in the aforementioned embodiment and are not further detailed here.

[0157] It should be understood that the various parts disclosed in this application can be implemented using hardware, software, firmware, or a combination thereof. In the description of the above embodiments, specific features, structures, materials, or characteristics can be combined in any one or more embodiments or examples in a suitable manner.

[0158] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of this application. Therefore, the scope of protection of this application should be based on the scope of protection of the claims.

[0159] The present application provides a computer-readable storage medium having computer-readable program instructions (ie, computer program) stored thereon, and the computer-readable program instructions are used to execute the satellite rescue method in the above embodiment.

[0160] The computer-readable storage medium provided in this application may be, for example, a USB flash drive, but is not limited to electrical, magnetic, optical, electromagnetic, infrared, or semiconductor systems, systems or devices, or any combination thereof. More specific examples of computer-readable storage media may include, but are not limited to: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In this embodiment, the computer-readable storage medium may be any tangible medium that contains or stores a program that can be used by or in conjunction with an instruction execution system, system or device. The program code contained on the computer-readable storage medium may be transmitted using any appropriate medium, including but not limited to: wires, optical cables, RF (Radio Frequency), etc., or any suitable combination thereof.

[0161] The computer-readable storage medium may be included in the satellite rescue device; or it may exist independently without being assembled into the satellite rescue device.

[0162] The above-mentioned computer-readable storage medium carries one or more programs. When the above-mentioned one or more programs are executed by the satellite rescue equipment, the satellite rescue equipment is enabled to: obtain solar position information, satellite positioning data and imaging parameters of the optical payload carried by the rescue satellite, wherein the satellite positioning data includes the orbital parameters of the faulty satellite and the orbital parameters of the rescue satellite; adjust the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite so that the rescue satellite and the faulty satellite share the same orbital plane; control the rescue satellite to fly around the faulty satellite as the center according to the solar position information and / or the imaging parameters, and obtain the fault information of the faulty satellite; adjust the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite, and control the rescue satellite to approach the faulty satellite until the relative position of the faulty satellite and the rescue satellite reaches a preset distance range; within the distance range, the fault of the faulty satellite is repaired by the rescue satellite according to the fault information.

[0163] Computer program code for performing the operations of the present application may be written in one or more programming languages, or a combination thereof, including object-oriented programming languages such as Java, Smalltalk, C++, and conventional procedural programming languages such as "C" or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, as a stand-alone software package, partially on the user's computer and partially on a remote computer, or entirely on the remote computer or server. In cases involving a remote computer, the remote computer may be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computer (e.g., through the Internet using an Internet service provider).

[0164] The flow charts and block diagrams in the accompanying drawings illustrate the possible architecture, functions and operations of the systems, methods and computer program products according to various embodiments of the present application. In this regard, each box in the flow chart or block diagram can represent a module, program segment or a part of code, and the module, program segment or a part of code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in a different order than that marked in the accompanying drawings. For example, two boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each box in the block diagram and / or flow chart, and the combination of the boxes in the block diagram and / or flow chart can be implemented by a dedicated hardware-based system that performs the specified function or operation, or can be implemented by a combination of dedicated hardware and computer instructions.

[0165] The modules described in the embodiments of the present application may be implemented in software or hardware, wherein the name of a module does not necessarily limit the unit itself.

[0166] The computer-readable storage medium provided in this application stores computer-readable program instructions (i.e., a computer program) for executing the aforementioned satellite rescue method, thereby resolving the technical issues of low satellite rescue efficiency and success rate. Compared to the prior art, the beneficial effects of the computer-readable storage medium provided in this application are the same as those of the satellite rescue method provided in the aforementioned embodiments, and are not further elaborated here.

[0167] The above are only preferred embodiments of the present application and do not limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent processing scope of the present application.

Claims

1. A satellite rescue method, characterized in that: The satellite rescue method is applied to a satellite rescue system, wherein the satellite rescue system includes a faulty satellite and a rescue satellite. The satellite rescue method includes: Acquiring sun position information, satellite positioning data, and imaging parameters of an optical payload carried by the rescue satellite, wherein the satellite positioning data includes orbital parameters of the faulty satellite and the rescue satellite; Adjusting the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite so that the rescue satellite and the faulty satellite share the same orbital plane; controlling the rescue satellite to fly around the faulty satellite according to the sun position information and / or the imaging parameters, and obtaining fault information of the faulty satellite; adjusting the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite, and controlling the rescue satellite to approach the faulty satellite until the relative positions of the faulty satellite and the rescue satellite reach a preset distance range; Within the distance range, the faulty satellite is repaired according to the fault information by the rescue satellite.

2. The method according to claim 1, wherein The step of adjusting the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite so that the rescue satellite and the faulty satellite are in the same orbital plane comprises: Determining the orbital inclination of the faulty satellite and the orbital inclination of the rescue satellite according to the orbital parameters of the faulty satellite and the orbital parameters of the rescue satellite; Determining an orbital inclination change according to the orbital inclination of the faulty satellite and the orbital inclination of the rescue satellite; determining an initial orbital velocity of the rescue satellite according to orbital parameters of the rescue satellite; Calculating a velocity increment of the rescue satellite according to the orbital inclination change and the initial orbital velocity of the rescue satellite; The orbital parameters of the rescue satellite are adjusted according to the speed increment, and the rescue satellite is controlled to share the same orbital plane with the faulty satellite.

3. The method according to claim 1, wherein The step of controlling the rescue satellite to fly around the faulty satellite according to the sun position information and / or the imaging parameters and obtaining fault information of the faulty satellite includes: Adjusting the relative phase relationship between the rescue satellite and the faulty satellite according to a preset orbital maneuvering strategy; When the phase of the rescue satellite is synchronized with the phase of the faulty satellite, the rescue satellite is controlled to fly around the faulty satellite according to the solar position information and / or the imaging parameters, and the fault information of the faulty satellite is obtained.

4. The method according to claim 3, wherein The step of adjusting the relative phase relationship between the rescue satellite and the faulty satellite according to a preset orbital maneuvering strategy includes: Determining a preset tangential velocity increment and phase value of the rescue satellite according to a preset orbital maneuvering strategy; reducing the orbital semi-major axis of the rescue satellite according to the tangential velocity increment; When the relative phase relationship between the rescue satellite and the faulty satellite reaches the preset phase value, the orbital semi-major axis of the rescue satellite is increased according to the tangential velocity increment, and the phase of the rescue satellite is controlled to be synchronized with the phase of the faulty satellite.

5. The method according to claim 3, wherein The satellite positioning data includes position information of the faulty satellite and position information of the rescue satellite, the imaging parameters include camera angular resolution and maximum field of view angle, and the step of controlling the rescue satellite to orbit around the faulty satellite based on the sun position information and / or the imaging parameters when the phase of the rescue satellite is synchronized with the phase of the faulty satellite, and obtaining fault information of the faulty satellite includes: When the phase of the rescue satellite is synchronized with the phase of the faulty satellite, calculating the solar illumination angle according to the solar position information, the position information of the faulty satellite and the position information of the rescue satellite; Calculating the number of imaging pixels of the rescue satellite based on the pre-acquired characteristic size of the faulty satellite, the camera angular resolution, the position information of the faulty satellite, and the position information of the rescue satellite; determining a relative distance constraint value between the faulty satellite and the rescue satellite according to the maximum field of view angle; According to the solar illumination angle and / or the number of imaging pixels and / or the relative distance constraint value, the rescue satellite is controlled to fly around the faulty satellite and obtain fault information of the faulty satellite.

6. The method according to claim 5, wherein The step of calculating the number of imaging pixels of the rescue satellite based on the pre-acquired characteristic size of the faulty satellite, the camera angular resolution, the position information of the faulty satellite, and the position information of the rescue satellite further includes: Calculating an imaging distance according to the position information of the faulty satellite and the position information of the rescue satellite; The number of imaging pixels of the rescue satellite is calculated based on the pre-acquired characteristic size of the faulty satellite, the imaging distance, and the camera angular resolution.

7. The method according to claim 6, wherein The step of controlling the rescue satellite to fly around the faulty satellite as the center according to the solar illumination angle and / or the number of imaging pixels and / or the relative distance constraint value, and obtaining fault information of the faulty satellite includes: Comparing the solar illumination angle with a preset solar illumination angle constraint value; If the solar illumination angle is greater than the solar illumination angle constraint value, adjusting the position of the rescue satellite; and / or Comparing the size relationship between the number of imaging pixels and a preset minimum number of pixels; If the number of imaging pixels is less than the minimum number of pixels, adjusting the position of the rescue satellite; and / or comparing the imaging distance with the relative distance constraint value; If the imaging distance is greater than the relative distance constraint value, adjusting the position of the rescue satellite; Based on the adjusted position of the rescue satellite, the rescue satellite is controlled to fly around the faulty satellite and the fault information of the faulty satellite is acquired.

8. A satellite rescue device, characterized in that: The satellite rescue device comprises: A position information acquisition module, configured to acquire sun position information, satellite positioning data, and imaging parameters of an optical payload carried by a rescue satellite, wherein the satellite positioning data includes orbital parameters of the faulty satellite and the orbital parameters of the rescue satellite; A first orbital parameter adjustment module is configured to adjust the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite so that the rescue satellite and the faulty satellite are in the same orbital plane; a fault information acquisition module, configured to control the rescue satellite to fly around the faulty satellite according to the sun position information and / or the imaging parameters, and to acquire fault information of the faulty satellite; a second orbital parameter adjustment module, configured to adjust the orbital parameters of the rescue satellite according to the orbital parameters of the faulty satellite, and control the rescue satellite to approach the faulty satellite until the relative positions of the faulty satellite and the rescue satellite reach a preset distance range; The satellite fault repair module is used to repair the fault satellite within the distance range through the rescue satellite according to the fault information.

9. A satellite rescue device, characterized in that: The satellite rescue device includes: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the computer program is configured to implement the steps of the satellite rescue method according to any one of claims 1 to 7.

10. A storage medium, characterized in that: The storage medium is a computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, the steps of the satellite rescue method according to any one of claims 1 to 7 are implemented.

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