Methods, computing devices, and storage media for restoring communication links after solar outage avoidance.

Abstract

Embodiments of the present invention relate to a method, computing device, and storage medium for restoring communication links after solar interference avoidance. The method includes: calculating a first angle between the sun's position vector and the line of sight of the local satellite's laser payload, to determine whether the local satellite has entered a solar interference region based on the first angle; if the local satellite is determined to be in the solar interference region, performing distance measurements between the local satellite and a target satellite at predetermined time intervals to obtain an array of distance values ​​between the local satellite and the target satellite, thereby determining the relative motion direction between the local satellite and the target satellite; based on the relative motion direction between the local satellite and the target satellite, determining a first step direction for establishing a link between the local satellite and the target satellite after the solar interference ends; if the local satellite is determined to have left the solar interference region, performing a step-by-step link establishment scan based on the first step direction until the target satellite is recaptured, so as to re-establish a communication link between the local satellite and the target satellite. Therefore, inter-satellite communication links can be efficiently restored after a satellite leaves the solar interference region.

Description

Technical Field

[0001] The embodiments of the present invention generally relate to the field of satellite laser communication, and more specifically to a method, computing device and storage medium for restoring communication links after solar outage avoidance. Background Technology

[0002] Inter-satellite laser communication uses lasers as carriers for massive data transmission. Currently, mainstream laser payloads are typically based on CCD / CMOS detection and imaging mechanisms. These mechanisms make laser payloads susceptible to background noise in space. Among this background noise, the light from the sun and stars is a major source. For example, when sunlight strikes a laser payload and is detected and imaged on a CCD / CMOS sensor, it can affect the aiming, acquisition, and tracking between two communicating satellites, significantly impacting the stability of the laser communication system.

[0003] However, solar interference is a very common physical phenomenon in celestial motion. During direct sunlight (i.e., solar interference), inter-satellite laser communication links experience the following: sunlight directly strikes the photosensitive surface of the tracking detector, causing a severe decrease in the optical tracking performance of the laser payload; the laser payload temperature rises, potentially even to the point of burning out the detector; solar interference also affects the optical communication performance of the laser payload, increasing the overall bit error rate. Therefore, when encountering solar interference, satellites need to perform avoidance maneuvers, and after the interference ends, inter-satellite links need to be re-established.

[0004] Traditional methods for restoring communication links after solar outage avoidance typically involve a strategy where the satellite at the outage-spotting end rescans the location of the outage, while the satellite at the back-spotting end stares at the location of the outage. This approach suffers from low re-acquisition probability and long inter-satellite link re-establishment time. Communication links are frequently interrupted due to solar outage, requiring ground control stations to perform pointing operations again to re-establish inter-satellite links, resulting in high time and labor costs.

[0005] In summary, the traditional methods for restoring communication links after solar outage avoidance have the following shortcomings: they cannot be avoided in time when solar outage occurs, and the efficiency and cost of restoring inter-satellite communication links are low. Summary of the Invention

[0006] To address the aforementioned problems, this invention provides a method, computing device, and storage medium for restoring communication links after solar outage avoidance, which can promptly avoid the outage when a satellite enters the outage area and efficiently restore inter-satellite communication links after the satellite leaves the outage area.

[0007] According to a first aspect of the present invention, a method for restoring a communication link after solar interference avoidance is provided, comprising: calculating a first angle between the position vector of the sun and the line of sight of a local satellite's laser payload, so as to determine whether the local satellite has entered a solar interference region based on the first angle; performing a solar interference avoidance operation in response to determining that the local satellite has entered a solar interference region; performing distance measurement between the local satellite and a target satellite based on a predetermined time interval in response to the local satellite being in a solar interference region, so as to obtain an array of distance values ​​between the local satellite and the target satellite, thereby determining the relative motion direction between the local satellite and the target satellite; determining a first step direction for establishing a link between the local satellite and the target satellite after the solar interference ends based on the relative motion direction between the local satellite and the target satellite; and performing a step-by-step link establishment scan based on the first step direction in response to determining that the local satellite has left the solar interference region, until the target satellite is recaptured, so as to re-establish a communication link between the local satellite and the target satellite.

[0008] According to a second aspect of the invention, a computing device is provided, the computing device comprising: at least one processing unit; at least one memory coupled to the at least one processing unit and storing instructions for execution by the at least one processing unit, the instructions, when executed by the at least one processing unit, causing the device to perform steps according to the method of the first aspect.

[0009] According to a third aspect of the present invention, a computer-readable storage medium is provided, on which a computer program is stored, which, when executed by a machine, implements the method according to the first aspect.

[0010] According to a fourth aspect of the present invention, a computer program product is also provided, comprising a computer program that, when executed by a machine, performs the method of the first aspect of the present invention.

[0011] In some embodiments, in response to determining that the local satellite has left the interstellar transit region, the local satellite performs a link-building scan in leaps based on a first leap direction until the target satellite is recaptured, including: determining the first leap step size; and the local satellite's laser payload being gradually shifted toward the first leap direction by the first leap step size, and performing a coarse-fine composite helical scan in the direction indicated by each step point in order to recapture the target satellite.

[0012] In some embodiments, the method for restoring the communication link after solar outage avoidance further includes: in response to determining that the local satellite has not recaptured the target satellite when the first hop count is reached, performing any of the following: recalculating the first hop direction such that the laser payload of the local satellite gradually shifts its pointing direction toward the new first hop direction, and performing a coarse-fine composite spiral scan in the direction indicated by each step point in order to recapture the target satellite; or determining one or more second hop directions such that the local satellite performs a field-of-view coverage scan stepwise based on each of the determined one or more hop directions in order to recapture the target satellite.

[0013] In some embodiments, determining one or more second step directions, such that the local satellite performs a field-of-view coverage scan step by step based on each of the determined one or more step directions, includes: determining two different second step directions; and the local satellite's laser payload gradually shifting from the scanning start point toward one of the two determined second step directions, performing a 360° field-of-view coverage scan in the direction indicated by each step point, until the local satellite recaptures the target satellite.

[0014] In some embodiments, in response to the local satellite being in the solar overpass region, ranging between the local satellite and the target satellite is performed based on a predetermined time interval to obtain an array of distance values ​​between the local satellite and the target satellite, thereby determining the relative motion direction of the local satellite and the target satellite. This includes: obtaining a set of distance change values ​​between the local satellite and the target satellite based on the distance value array; calculating the summation average of the distance change values ​​between the local satellite and the target satellite based on the set of distance change values; and obtaining the relative motion direction of the local satellite and the target satellite based on the summation average of the distance change values.

[0015] In some embodiments, the method for restoring the communication link after solar outage avoidance further includes: in response to determining that the local satellite has left the solar outage region, determining the relative motion direction of the local satellite and the target satellite, and determining the first jump direction includes any one of the following: when the sum of the distance changes is less than 0, determining that the local satellite and the target satellite are approaching each other, thereby determining the first jump direction as the direction of approaching the solar outage; when the sum of the distance changes is greater than 0, determining that the local satellite and the target satellite are moving away from each other, thereby determining the first jump direction as the direction of exiting the solar outage; when the sum of the distance changes is equal to 0, determining that the distance change between the local satellite and the target satellite is less than a predetermined range, thereby determining that the local satellite does not need to jump.

[0016] In some embodiments, determining whether the local satellite has entered the solar interference region based on the first included angle includes: determining that the local satellite has entered the solar interference region in response to a first included angle between the sun's position vector and the local satellite's laser payload line of sight in the y-axis direction of the laser payload coordinate system being less than or equal to 3°; and / or determining that the local satellite has entered the solar interference region in response to a first included angle between the sun's position vector and the local satellite's laser payload line of sight in the z-axis direction of the laser payload coordinate system being less than or equal to 3°.

[0017] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of the present invention, nor is it intended to limit the scope of the invention. Other features of the invention will become readily apparent from the following description. Attached Figure Description

[0018] The above and other features, advantages, and aspects of the various embodiments of the present invention will become more apparent from the accompanying drawings and the following detailed description. In the drawings, the same or similar reference numerals denote the same or similar elements.

[0019] Figure 1 A schematic diagram is shown for implementing a communication link recovery environment after solar outage avoidance according to an embodiment of the present invention.

[0020] Figure 2 A schematic diagram of a satellite for restoring communication links after solar overpass avoidance is shown according to an embodiment of the present invention.

[0021] Figure 3 A flowchart of a method for restoring a communication link after solar outage avoidance according to an embodiment of the present invention is shown.

[0022] Figure 4 A flowchart of a method for overlay scanning for inter-satellite link establishment according to an embodiment of the present invention is shown.

[0023] Figure 5 A flowchart of a method for obtaining the relative motion direction between a local star and a target star according to an embodiment of the present invention is shown.

[0024] Figure 6 A schematic diagram of the satellite laser payload coordinate system according to an embodiment of the present invention is shown.

[0025] Figure 7 A schematic diagram of the first included angle according to an embodiment of the present invention is shown.

[0026] Figure 8 A schematic diagram of a skip-step chain-building scan according to an embodiment of the present invention is shown.

[0027] Figure 9 A schematic diagram of a field-of-view coverage scan according to an embodiment of the present invention is shown.

[0028] Figure 10 A block diagram of an electronic device according to an embodiment of the present invention is shown. Detailed Implementation

[0029] The following description, in conjunction with the accompanying drawings, illustrates exemplary embodiments of the present invention, including various details to aid understanding. These details should be considered merely exemplary. Therefore, those skilled in the art will recognize that various changes and modifications can be made to the embodiments described herein without departing from the scope and spirit of the invention. Similarly, for clarity and brevity, descriptions of well-known functions and structures are omitted in the following description.

[0030] The term "comprising" and its variations as used herein signify open inclusion, i.e., "including but not limited to". Unless otherwise stated, the term "or" means "and / or". The term "based on" means "at least partially based on". The terms "one example embodiment" and "one embodiment" mean "at least one example embodiment". The term "another embodiment" means "at least one additional embodiment". The terms "first", "second", etc., may refer to different or the same objects. Other explicit and implicit definitions may also be included below.

[0031] As described above, traditional methods for restoring communication links after solar outage avoidance, such as having the satellite at the outage-spotting end rescan and the satellite at the outage-rear-spotting end stare at the location where the outage occurs, have a low probability of re-capturing the satellite after it leaves the outage area. This results in long inter-satellite link re-establishment time and often leads to communication link loss due to solar outage, requiring ground control stations to perform pointing operations again to re-establish the inter-satellite link, resulting in high time and labor costs.

[0032] In summary, the shortcomings of traditional methods for restoring communication links after solar outage avoidance are: they cannot be avoided in time when solar outage occurs, and the efficiency and cost of restoring inter-satellite communication links are low.

[0033] To at least partially address one or more of the aforementioned problems and other potential issues, an exemplary embodiment of the present invention proposes a scheme for restoring communication links after solar outage avoidance. In this scheme, a first angle is calculated between the sun's position vector and the laser payload line of the local satellite to determine whether the local satellite has entered the solar outage region. This allows for timely determination of whether a satellite has entered the solar outage region, enabling timely solar outage avoidance. Furthermore, if the local satellite is determined to be in the solar outage region, distance measurements are performed between the local satellite and a target satellite at predetermined time intervals to obtain an array of distance values, thereby determining the relative motion direction between the local satellite and the target satellite. Based on the relative motion direction, a first step direction for establishing a link between the local satellite and the target satellite after the solar outage ends is determined. In response to determining that the local satellite has left the solar outage region, based on the first step direction, the local satellite performs a step-by-step link establishment scan until the target satellite is recaptured, thus re-establishing a communication link between the local satellite and the target satellite. This allows for the precise calculation of the relative motion directions of the local and target satellites. Based on this, the first hop direction for link establishment scanning between the local and target satellites is determined after the solar interference ends. This enables the satellite to efficiently acquire the target satellite after leaving the solar interference region, achieving rapid link restoration and thus restoring the inter-satellite communication link. Therefore, this invention can promptly perform solar interference avoidance operations when a satellite enters the solar interference region and efficiently restore the inter-satellite communication link after the satellite leaves the region.

[0034] Figure 1 A schematic diagram is shown of an operating environment 100 for implementing communication link restoration after solar outage avoidance according to an embodiment of the present invention. Figure 1 As shown in the diagram, the operating environment 100 illustrates the Sun (including positions 91 and 92), Earth, the binary orbit 30, and Satellite 10 and Satellite 20. Satellite 10 and Satellite 20 operate along orbit 30, and an inter-satellite laser communication link can be established between them.

[0035] like Figure 1 As shown, the laser payload of Satellite-10 is facing the sun at this time, which is the solar interference viewing end; the laser payload of Satellite-20 is facing away from the sun at this time, which is the solar interference back-viewing end; when the laser payload is facing the sun and the angle with the sunlight is less than a certain range, a solar interference phenomenon occurs. For example, Figure 1 When the sun is at position 91°, the angle between the line of sight of the laser payload of satellite-10 and the sunlight is θ1; when the sun is at position 92°, the angle between the line of sight of the laser payload of satellite-10 and the sunlight is θ2. For example, at this time, the direction of solar transit is as follows: Figure 1As shown, the sun moves from position 91 to position 92. When θ1 ≤ 3°, satellite-10 enters the solar interference region; when θ2 < -3°, satellite-10 leaves the solar interference region. For example, in the scheme provided in this application, the angle between the laser payload line of the satellite and the sunlight is defined as the first angle θ. When θ ∈ (-3°, +3°), the satellite is in the solar interference region.

[0036] It should be understood that as the satellites operate in orbit, both Satellite-10 and Satellite-20 may be located in the solar outage region. When a satellite is in the solar outage region, it is the solar outage looking end. At this time, the laser payload of the other satellite forming an inter-satellite link with it is opposite to it, thus the other satellite is the satellite looking away. The satellite located at the solar outage looking end needs to perform solar outage avoidance operations to avoid equipment damage or communication disruption caused by direct sunlight. The solution provided in this application enables the satellite to perform avoidance operations in a timely manner before or when entering the solar outage region. In addition, when the satellites leave the solar outage region, the relative positions between the satellites change, and the inter-satellite link needs to be restored. The solution provided in this application also enables the rapid reconstruction of the inter-satellite link between the solar outage looking end satellite and the solar outage looking away satellite to restore inter-satellite communication.

[0037] Regarding Satellite-10 and Satellite-20, each satellite includes, for example, a control unit, a broadcast communication unit, a steering platform, and a laser payload. Figure 2 As shown, Satellite 10 includes a control unit 112, a broadcast communication unit 114, and a laser payload 12; Satellite 20 includes a control unit 213, a broadcast communication unit 214, and a laser payload 22. The control unit communicates with the broadcast communication unit, and the control unit communicates with the laser payload. Satellite 10 and Satellite 20 conduct broadcast communication through the broadcast communication unit 114 and broadcast communication unit 214, respectively, and conduct inter-satellite laser communication through the laser payload 12 and laser payload 22, respectively. It should be understood that the communication interfaces in the above examples include, but are not limited to, CAN communication interfaces, RS422 communication interfaces, and LVDS communication interfaces. The above communication interfaces are only illustrative of data interaction via multiple communication interfaces; other communication interfaces may also be used in this invention.

[0038] In some embodiments, the control units (control units 112 and 213) are also configured to interact with broadcast communication units, laser payloads, and control units of other satellites. In some embodiments, the control units (control units 112 and 213) may have one or more processing units, including dedicated processing units such as graphics processing units (GPUs), field programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), or general-purpose computing on graphics processing units (GPGPUs), as well as general-purpose processing units such as CPUs.

[0039] Regarding the control units (control unit 112, control unit 213), they are used to calculate a first angle between the position vector of the sun and the line of sight of the local star's laser payload in order to determine whether the local star has entered the solar transit region based on the first angle.

[0040] Regarding the control units (control unit 112, control unit 213), they are used to perform solar interference avoidance operations in response to determining that the local satellite has entered the solar interference region; and to determine the first hop direction for link establishment scanning between the local satellite and the target satellite after the solar interference ends, based on the relative motion direction of the local satellite and the target satellite. Regarding the broadcast communication units (broadcast communication unit 114, broadcast communication unit 214), they are used for inter-satellite communication to perform inter-satellite ranging when the satellites are in the solar interference region.

[0041] Regarding the control units (control unit 112, control unit 213), they are used to respond to the local satellite being in the solar overpass region, and perform distance measurement between the local satellite and the target satellite based on a predetermined time interval, so as to obtain an array of distance values ​​between the local satellite and the target satellite, thereby determining the relative motion direction of the local satellite and the target satellite.

[0042] Regarding the laser payloads (laser payload 12 and laser payload 22), in response to determining that the local satellite has left the solar transit region, the local satellite performs a link-establishing scan step by step based on the first step direction until it recaptures the target satellite, so as to re-establish a communication link between the local satellite and the target satellite.

[0043] Figure 3 A flowchart of a method 300 for restoring a communication link after solar outage avoidance according to an embodiment of the present invention is shown. Method 300 can be performed by, for example... Figure 1 The satellites shown (Satellite 1-10, Satellite 2-20) can also be used. Figure 10 The method is performed at the illustrated electronic device 1000. It should be understood that method 300 may also include additional steps not shown and / or the steps shown may be omitted, and the scope of the invention is not limited in this respect.

[0044] In step 302, the satellites (Satellite 10 and Satellite 20) calculate the first angle between the position vector of the sun and the line of sight of the local satellite's laser payload, so as to determine whether the local satellite has entered the solar interference region based on the first angle.

[0045] Regarding the main satellite, it should be understood that both Satellite 10 and Satellite 20 can be used as the main satellite. For the sake of ease of description and understanding of the scheme, in the embodiments of this application specification, the satellite at the solar outage observation end when entering the solar outage area is used as the main satellite. According to the accompanying drawings, in the following embodiments, Satellite 10 is located at the solar outage observation end, and Satellite 10 is used as the main satellite for specific description of the scheme.

[0046] In some embodiments, for example, the position vector of the sun in the field of view of the laser payload and the pointing vector of the two-dimensional turntable of the laser payload are calculated using information such as the sun's position vector, the position, velocity, and attitude of the satellite itself, in order to calculate the first angle between the sun's position vector and the line of sight of the satellite's laser payload. Furthermore, the pointing vector of the two-dimensional turntable of the satellite's laser payload (i.e., the line of sight of the laser payload, i.e., the direction of the satellite's communication laser emission), and the adjustment of the line of sight of the laser payload, are also achieved by controlling the two-dimensional turntable through the satellite's control unit.

[0047] Therefore, the above scheme can transform the sun's position vector into the satellite's laser payload coordinate system, thereby enabling efficient calculation of the first angle between the sun's position vector and the satellite's laser payload line of sight. It can also promptly determine when the satellite enters the solar interference region and perform avoidance operations; and promptly determine when the satellite leaves the solar interference region and restore the inter-satellite communication link.

[0048] For example, regarding the laser payload field-of-view coordinate system, please refer to... Figure 1 and Figure 6This will be further explained. First, regarding the installation position of the laser payloads, for example: the two docked laser payloads are installed on the satellite body respectively. For example, laser payload 12 is installed on satellite body 11 of satellite 10, and laser payload 22 is installed on satellite body 21 of satellite 20. The laser payloads are installed on the -Z plane of the satellite body, and the Z-axis direction of the laser payload is the same as the Z-axis direction of the satellite (the Z-axis points to the Earth's center, and -Z is away from the Earth's center). The initial zero position of laser payload 12 points to the X direction of satellite body 11, and the X direction of laser payload 12 is the same as the X direction of satellite body 11. The Y direction of laser payload 12 is the same as the Y direction of satellite body 11. On the other hand, the initial zero position of laser payload 22 points to the -X direction of the target satellite body 21, and the X direction of laser payload 22 is opposite to the X direction of the target satellite body 21. The Y direction of laser payload 22 is opposite to the Y direction of the target satellite body 21. The location information of the satellite terminal conforms to the right-hand rule, which is defined as follows: the thumb pointing towards the center of the earth is the +Z axis; the four fingers pointing is the +X axis; and the direction of the four fingers bending is the +Y axis.

[0049] For example, please refer to Figure 6 This further clarifies the laser payload coordinate systems of Satellite-10 and Satellite-20. Figure 6 In the middle, along the satellite's orbital direction, the laser payload 12 of Satellite 10 (the main satellite) and the laser payload 22 of Satellite 20 (the target satellite) are docked in pairs. The X1-1 axis, Y1-1 axis, and Z1-1 axis of the laser payload 12 are parallel to the +X1 axis, +Y1 axis, and +Z1 axis of the satellite body 11 of Satellite 10. The direction of the +X1 axis is the orbital direction of the satellite body 11. The laser payload 12 is installed on the -Z1 axis and +X1 axis of the satellite body 11. The X2-1 axis, Y2-1 axis, and Z2-1 axis of the laser payload 22 are opposite to the +X2 axis, opposite to the +Y2 axis, and in phase with the +Z2 axis of the satellite body 21 of Satellite 20. The direction of the +X2 axis is the orbital direction of Satellite 20. The laser payload 22 is installed on the -Z2 axis and -X2 axis of the satellite body 21.

[0050] In some embodiments, determining whether the local satellite has entered the solar interference region based on the first included angle includes: determining that the local satellite has entered the solar interference region in response to a first included angle between the sun's position vector and the local satellite's laser payload line of sight in the y-axis direction of the laser payload coordinate system being less than or equal to 3°; and / or determining that the local satellite has entered the solar interference region in response to a first included angle between the sun's position vector and the local satellite's laser payload line of sight in the z-axis direction of the laser payload coordinate system being less than or equal to 3°.

[0051] For example, please refer to Figure 6 and Figure 7The first angle between the sun's position vector and the laser payload's line of sight of the local satellite, in the y-axis direction of the laser payload coordinate system, is defined as θY; the first angle between the sun's position vector and the laser payload's line of sight of the local satellite, in the z-axis direction of the laser payload coordinate system, is defined as θZ; at least either θY or θZ satisfying Θ∈(-3°,+3°) indicates that the satellite has entered the solar interference region.

[0052] Therefore, by using the above method, it is possible to determine the first angle between the position vector of the sun and the line of sight of the satellite's laser payload on multiple axes, thereby timely and comprehensively determining whether the satellite has entered or left the solar interference region.

[0053] In some embodiments, if a satellite (Satellite 10, Satellite 20) determines that it has entered a solar interference region, it performs a solar interference avoidance operation. For example, in some embodiments, the solar interference avoidance operation includes one or more of the following: deflecting the direction of the laser payload, adjusting the two-dimensional turntable, covering the laser payload transmitter, suspending laser communication, and thermal power management. For example, if Satellite 10 confirms that it has entered a solar interference region, it adjusts the direction of its laser payload so that the line of sight of the laser payload is deflected to avoid direct sunlight.

[0054] In some embodiments, if it is determined that the local satellite has entered the solar interference region, performing a solar interference avoidance operation includes: performing a solar interference avoidance operation in response to a first included angle between the position vector of the sun and the line of sight of the local satellite's laser payload, on the y-axis and / or z-axis of the laser payload coordinate system, being less than or equal to a minimum monitoring interval threshold; wherein the minimum monitoring interval threshold is greater than 3°.

[0055] Regarding the minimum monitoring interval value, for example, the position difference Δ is calculated based on the actual pointing position of the laser payload's line of sight and its pointing position within the solar eclipse area. 方位 and △ 俯仰 According to △ 方位 and △ 俯仰 The value changes, and the changes in the anti-counterfeiting and elevation angle difference of the laser payload are monitored. For example, the minimum monitoring interval threshold is 5° and the solar interference area threshold is 3°. If the first angle between the sun's position vector and the laser payload line of the local satellite gradually decreases, and the first angle is less than or equal to 5° (i.e. less than or equal to the minimum detection interval threshold), a solar interference avoidance operation is performed. If the first angle between the sun's position vector and the laser payload line of the local satellite gradually increases, and the first angle is greater than 3°, it is determined that the local satellite has left the solar interference area.

[0056] Therefore, based on the above method, by setting a minimum monitoring interval, avoidance operations can be performed in advance before the satellite enters the solar interference area, leaving sufficient time margin to avoid being unable to avoid it.

[0057] In step 304, if the satellite (Satellite 10, Satellite 20) determines that it is in the solar overpass region, it performs distance measurement between itself and the target satellite based on a predetermined time interval in order to obtain an array of distance values ​​between itself and the target satellite in order to determine the relative motion direction of itself and the target satellite.

[0058] The following will combine Figure 5 The methods for obtaining the relative motion direction between the local star and the target star are explained in detail here and will not be repeated.

[0059] In step 306, the satellites (Satellite 10 and Satellite 20) determine the first jump direction for establishing a link between themselves and the target satellite after the solar overpass ends, based on the relative motion directions of the satellite and the target satellite.

[0060] The following will combine Figure 4 The method for coverage scanning used for inter-satellite link establishment will not be elaborated here.

[0061] In step 308, in response to determining that the satellite has left the solar interference region, the satellite (Satellite 10, Satellite 20) performs a link-establishing scan step by step based on the first jump direction until it recaptures the target satellite, so as to re-establish a communication link between the satellite and the target satellite.

[0062] In some embodiments, if it is determined that the local satellite has left the solar transit region, the local satellite performs a link-building scan in leaps based on a first leap direction until the target satellite is recaptured, including: determining the first leap step size; and the local satellite's laser payload being gradually shifted toward the first leap direction by the first leap step size, and performing coarse and fine composite spiral scans in the direction indicated by each step point in order to recapture the target satellite.

[0063] Regarding the first hop step distance, it can be determined based on the change in distance between the local star and the target star, for example, by determining the hop step distance Δσ (generally < 3 mrad). This also allows for more flexible configuration of link establishment scans, thereby improving the efficiency of recapturing the target star.

[0064] Regarding the laser payload of this satellite, the direction is shifted progressively in the first hop step direction, with the first hop step increment, and coarse and fine composite helical scans are performed in the direction indicated by each step point in order to recapture the target satellite. The following combines... Figure 8 This section provides a detailed explanation of how to perform skip-step chain establishment scanning and how to execute coarse-fine combined spiral scanning.

[0065] Please refer to Figure 8Starting point 0 is the initial direction of the laser payload when it leaves the solar interference region. The first jump step direction D1 and the first jump step distance Δσ1 are determined. For example, if Satellite-10 is the target satellite, its laser payload gradually shifts its direction from starting point 0 to the first jump step direction D1 with the first jump step distance Δσ1. First, it shifts to the first jump step position and performs a coarse scan (circled in red in the figure). Then, it performs a fine spiral scan at the first jump step position (indicated by the small black circle within the red circle in the figure). If the target satellite is not captured (such as Satellite-20), the first jump step position is used as the new starting point, and the laser payload shifts its direction one step to the first jump step direction D1 with the first jump step distance Δσ1. The fine spiral scan is repeated. If the target satellite is still not captured, the above operation is repeated, and the fine spiral scan is performed step by step to capture the target satellite.

[0066] Therefore, by combining coarse and fine scanning, this satellite can further improve the efficiency of link establishment recovery; and the laser payload does not need to perform link establishment scanning from the direction when leaving the solar transit region, but instead jumps to a new starting point to perform link establishment scanning, which can further improve the efficiency of inter-satellite link establishment recovery.

[0067] In some embodiments, in response to determining that the local satellite has not recaptured the target satellite when the first hop count is reached, any of the following is performed: recalculating the first hop direction such that the local satellite's laser payload is gradually shifted toward the new first hop direction, and performing a coarse-fine composite helical scan in the direction indicated by each step point in order to recapture the target satellite; or determining one or more second hop directions such that the local satellite performs a field-of-view coverage scan stepwise based on each of the determined one or more hop directions in order to recapture the target satellite.

[0068] For example, combining Figure 8 If n=5, meaning that the target star is not recaptured after 5 consecutive jumps, the first jump direction can be recalculated, for example, a new first jump direction D2, so that the laser payload of the local star gradually shifts towards the new first jump direction D2, and coarse and fine composite spiral scans are performed in the direction indicated by each step point. The details of how to perform coarse and fine composite spiral scans and how to jump have been described in detail above, and will not be repeated here.

[0069] Regarding the starting point from which the chain is established and scanned in the direction of the new first jump step, for example, it can start from the starting point 0 or from the nth jump step position, and the specific calculation is based on the actual situation.

[0070] The following will combine Figure 4 The method for coverage scanning used for inter-satellite link establishment will not be elaborated here.

[0071] Therefore, if the target star is not found after reaching the predetermined number of steps, it may be due to a deviation in the jump direction calculation. This solution can provide an update to the jump direction for a single-direction jump scan, or an update to the jump direction for a coverage scan, thereby achieving a more accurate and comprehensive scan in multiple ways, improving scanning efficiency, and avoiding wasting too much time on the wrong direction.

[0072] In the above scheme, by calculating the first angle between the sun's position vector and the laser payload line of the local satellite, it is possible to determine in a timely manner whether the local satellite has entered the solar interference region, thereby efficiently performing solar interference avoidance operations. Furthermore, after determining that the local satellite has left the solar interference region, the jump direction can be determined based on the relative motion direction of the local satellite and the target satellite. Thus, by using a jump scan method, the local satellite performs link establishment scan step by step until the target satellite is recaptured. Therefore, the above scheme achieves rapid execution of solar interference avoidance operations when entering the solar interference region and efficient restoration of inter-satellite links after leaving the solar interference region.

[0073] Figure 4 A flowchart of a coverage scan method 400 for inter-satellite link establishment according to an embodiment of the present invention is shown. Method 400 may be performed by, for example... Figure 1 The satellites shown (Satellite 1-10, Satellite 2-20) can also be used. Figure 10 The method is performed at the illustrated electronic device 1000. It should be understood that method 400 may also include additional steps not shown and / or the steps shown may be omitted, and the scope of the invention is not limited in this respect.

[0074] In some embodiments, the satellite (Satellite 10, Satellite 20) determines one or more second hop directions, such that the local satellite performs a field-of-view coverage scan based on each of the determined one or more hop directions, hop-by-hop, including the following steps:

[0075] In step 402, the satellites (Satellite 10, Satellite 20) determine two different second jump directions.

[0076] For example, the two second step directions are opposite. For example, multiple second step directions are determined, starting with an initial second step direction D21, and a new second step direction is generated for each predetermined deflection angle β°, for example... Figure 9 The angle between D22 and D21 shown is β°.

[0077] In step 404, the laser payload of the satellite (Satellite 10, Satellite 20) gradually shifts from the scanning starting point to one of the two determined second step directions, and performs a 360° field-of-view scan in the direction indicated by each step point until the satellite recaptures the target satellite.

[0078] For example, please refer to Figure 9The laser payload of this satellite gradually shifts from the starting point 2 along the second jump direction D21, performing a 360° field-of-view coverage scan in the direction indicated by each step point. For example, a 360° field-of-view coverage scan is performed at step point 211 (the area is circled in blue, each red circle represents a coarse scan, and a small black circle represents a fine scan). The 360° field-of-view coverage scan includes multiple coarse and fine composite spiral scans. If the target satellite is not captured, a step is skipped along the second jump direction D21 to step point 212, where a 360° field-of-view coverage scan is performed again. The above operation is repeated to perform the jump-step field-of-view coverage scan until the predetermined number of second jump steps (e.g., m times) is reached.

[0079] For example, if m jump-step field-of-view coverage scans are performed along a second jump direction D21 without capturing the target star, then m more jump-step field-of-view coverage scans are performed along another second jump direction, starting from point 2, for example, jumping to step points 221, 222, ..., 22m. If the target star is still not captured, then a new second jump direction is determined, and a jump-step field-of-view coverage scan is performed. For example, determining a new second jump direction could be based on the previous second jump direction with a predetermined angle deflection.

[0080] Therefore, when a unidirectional skip-step link establishment scan cannot efficiently capture the target star, this solution provides a multi-directional skip-step 360° field-of-view coverage scan link establishment method, which can restore inter-satellite link establishment as soon as possible.

[0081] Figure 5 A flowchart of a method 500 for obtaining the relative motion direction between a local star and a target star according to an embodiment of the present invention is shown. Method 500 may be derived from, for example... Figure 1 The satellites shown (Satellite 1-10, Satellite 2-20) can also be used. Figure 10 The method is performed at the illustrated electronic device 1000. It should be understood that method 500 may also include additional steps not shown and / or the steps shown may be omitted, and the scope of the invention is not limited in this respect.

[0082] In step 502, the satellites (Satellite 10 and Satellite 20) obtain the distance change values ​​between themselves and the target satellite based on the distance value array.

[0083] In step 504, the satellites (Satellite 10 and Satellite 20) calculate the sum of the distance changes between themselves and the target satellite based on the distance change numerical group.

[0084] In step 506, the satellites (Satellite 10 and Satellite 20) obtain the relative motion direction between themselves and the target satellite based on the sum of the distance changes and the average value.

[0085] For example, when Satellite 10 is in the solar outage region, Satellite 10 and Satellite 20 simultaneously send ranging frames to each other. Satellite 10 (for example, the local satellite, located at the solar outage observation end) records a set of distance values ​​between the local satellite and the target satellite within a time interval Δt, S = S(S1, S2, S3…Sn), where n is an odd number. Then, based on the inter-satellite distance value array S, the inter-satellite distance change value array ΔS = (S2-S1, S3-S2, …Sn-Sn-1) is obtained. The summation average of the distance change value array ΔS between the local satellite and the target satellite is obtained as s = {(S2-S1) + (S3-S2) + … + (Sn-Sn-1)} / (n-1). Based on the sign of the value of ∈s, the relative motion direction between the local star and the target star can be determined. When ∈s>0, the local star and the target star separate, and the target star moves faster than the local star. When ∈s<0, the local star and the target star move closer, and the target star moves slower than the local star. When ∈s=0, the local star and the target star are relatively fixed, and the target star moves at approximately the same speed as the local star.

[0086] For example, the satellite can obtain the link pointing relationship R1 between itself and the target satellite before the solar outage (i.e., the inter-satellite link relationship between the two before the solar outage, including relative position, laser payload pointing relationship, etc.) by querying the log. Then, combined with the positional relationship between the two when the satellite leaves the solar outage, the link pointing relationship R2 between the satellite and the target satellite when the satellite leaves the solar outage region can be obtained. Based on R1 and R2, the jump direction of the satellite when leaving the solar outage region can be determined.

[0087] In some embodiments, in response to determining that the local satellite leaves the interstellar transit region, the relative motion direction of the local satellite and the target satellite is determined. Determining the first jump direction includes any of the following: when the sum of the distance changes is less than 0, it is determined that the local satellite and the target satellite are approaching each other, thereby determining the first jump direction as the interstellar transit direction; when the sum of the distance changes is greater than 0, it is determined that the local satellite and the target satellite are moving away from each other, thereby determining the first jump direction as the interstellar transit direction; when the sum of the distance changes is equal to 0, it is determined that the distance change between the local satellite and the target satellite is less than a predetermined range, thereby determining that the local satellite does not need to jump.

[0088] Therefore, based on the distance changes between the local satellite and the target satellite when the local satellite is in the interstellar transit region, and combined with the link pointing relationship between the local satellite and the target satellite before the interstellar transit, it is possible to quickly determine the direction in which the laser payload of the local satellite should deflect after leaving the interstellar transit region in order to facilitate the rapid restoration of the inter-satellite link. This improves the efficiency of determining the jump direction, which is beneficial for the local satellite to recapture the target satellite and for the restoration and establishment of the inter-satellite link between the local satellite and the target satellite.

[0089] Figure 10 A schematic step diagram of an example electronic device 1000 that can be used to implement embodiments of the contents of this specification is shown. For example, as Figure 1The satellites shown (Satellite 10, Satellite 20) can be implemented by electronic device 1000. As shown, electronic device 1000 includes a central processing unit (CPU) 1001, which can perform various appropriate actions and processes according to computer program instructions stored in read-only memory (ROM) 1002 or loaded from storage unit 1008 into random access memory (RAM) 1003. The random access memory 1003 can also store various programs and data required for the operation of electronic device 1000. The CPU 1001, ROM 1002, and RAM 1003 are interconnected via bus 1004. Input / output (I / O) interface 1005 is also connected to bus 1004.

[0090] Multiple components in electronic device 1000 are connected to input / output interface 1005, including: input unit 1006, such as keyboard, mouse, microphone, etc.; output unit 1007, such as various types of monitors, speakers, etc.; storage unit 1008, such as disk, optical disk, etc.; and communication unit 1009, such as network card, modem, wireless transceiver, etc. Communication unit 1009 allows electronic device 1000 to exchange information / data with other devices through computer networks such as the Internet and / or various telecommunications networks.

[0091] The various processes and procedures described above, such as methods 300 to 500, can be executed by the central processing unit 1001. For example, in some embodiments, methods 300 to 500 can be implemented as computer software programs tangibly contained in a machine-readable medium, such as storage unit 1008. In some embodiments, part or all of the computer program can be loaded and / or installed on the electronic device 1000 via read-only memory 1002 and / or communication unit 1009. When the computer program is loaded into random access memory 1003 and executed by the central processing unit 1001, one or more actions of methods 300 to 500 described above can be performed.

[0092] This invention relates to methods, apparatus, systems, electronic devices, computer-readable storage media, and / or computer program products. The computer program product may include computer-readable program instructions for performing various aspects of the invention.

[0093] Computer-readable storage media can be tangible devices capable of holding and storing instructions for use by an instruction execution device. Computer-readable storage media can be, for example—but not limited to—electrical storage devices, magnetic storage devices, optical storage devices, electromagnetic storage devices, semiconductor storage devices, or any suitable combination of the foregoing. More specific examples (a non-exhaustive list) of computer-readable storage media include: portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), static random access memory (SRAM), portable compact disc read-only memory (CD-ROM), digital multifunction disc (DVD), memory sticks, floppy disks, mechanical encoding devices, such as punch cards or recessed protrusions storing instructions thereon, and any suitable combination of the foregoing. The computer-readable storage media used herein are not to be construed as transient signals themselves, such as radio waves or other freely propagating electromagnetic waves, electromagnetic waves propagating through waveguides or other transmission media (e.g., light pulses through fiber optic cables), or electrical signals transmitted through wires.

[0094] The computer-readable program instructions described herein can be downloaded from computer-readable storage media to various computing / processing devices, or downloaded via a network, such as the Internet, local area network, wide area network, and / or wireless network, to an external computer or external storage device. The network may include copper transmission cables, fiber optic transmission, wireless transmission, routers, firewalls, switches, gateway computers, and / or edge computing devices. A network adapter card or network interface in each computing / processing device receives the computer-readable program instructions from the network and forwards them to computer-readable storage media within the respective computing / processing device.

[0095] The computer program instructions used to perform the operations of this invention may be assembly instructions, instruction set architecture (ISA) instructions, machine instructions, machine-dependent instructions, microcode, firmware instructions, state setting data, or source code or object code written in any combination of one or more programming languages, including object-oriented programming languages ​​such as Smalltalk, C++, etc., and conventional procedural programming languages ​​such as the "C" language or similar programming languages. The computer-readable program instructions may be executed entirely on the user's computer, partially on the user's computer, as a standalone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving a remote computer, the remote computer may be connected to the user's computer via 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., via the Internet using an Internet service provider). In some embodiments, electronic circuitry, such as programmable logic circuitry, field-programmable gate arrays (FPGAs), or programmable logic arrays (PLAs), is personalized by utilizing state information from the computer-readable program instructions. This electronic circuitry can execute the computer-readable program instructions to implement various aspects of the invention.

[0096] Various aspects of the present invention are described herein with reference to flowchart illustrations and / or step diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It should be understood that each step in the flowchart illustrations and / or step diagrams, as well as combinations of steps in the flowchart illustrations and / or step diagrams, can be implemented by computer-readable program instructions.

[0097] These computer-readable program instructions can be provided to a processing unit of a general-purpose computer, a special-purpose computer, or other programmable data processing apparatus to produce a machine such that, when executed by the processing unit of the computer or other programmable data processing apparatus, they create means for implementing the functions / actions specified in one or more steps of the flowchart and / or diagram of steps. These computer-readable program instructions can also be stored in a computer-readable storage medium that causes a computer, programmable data processing apparatus, and / or other device to operate in a particular manner. Thus, the computer-readable medium storing the instructions comprises an article of manufacture that includes instructions for implementing aspects of the functions / actions specified in one or more steps of the flowchart and / or diagram of steps.

[0098] Computer-readable program instructions may also be loaded onto a computer, other programmable data processing apparatus, or other device to cause a series of operational steps to be performed on the computer, other programmable data processing apparatus, or other device to produce a computer-implemented process, thereby causing the instructions executed on the computer, other programmable data processing apparatus, or other device to perform the functions / actions specified in one or more steps of a flowchart and / or a diagram of steps.

[0099] The flowcharts and step diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of the present invention. In this regard, each step in the flowchart or step diagram may represent a module, segment, or part of an instruction, which contains one or more executable instructions for implementing the specified logical function. In some alternative implementations, the functions indicated in the step may occur in a different order than those indicated in the drawings. For example, two consecutive step steps may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each step in the step diagram and / or flowchart, and combinations of steps in the step diagram and / or flowchart, can be implemented using a dedicated hardware-based system that performs the specified function or action, or using a combination of dedicated hardware and computer instructions.

[0100] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein.

Claims

1. A method for restoring communication links after solar outage avoidance, characterized in that, The method includes: Calculate the first angle between the Sun's position vector and the line of sight of the local star's laser payload, so as to determine whether the local star has entered the solar interference region based on the first angle; In response to determining that the local satellite is in the solar interference region, the distance between the local satellite and the target satellite is measured based on a predetermined time interval in order to obtain an array of distance values ​​between the local satellite and the target satellite, thereby determining the relative motion direction of the local satellite and the target satellite; Based on the relative motion directions of the local satellite and the target satellite, determine the first jump direction for establishing a link between the local satellite and the target satellite after the solar overpass ends; and In response to determining that the local satellite has left the solar transit region, the local satellite performs a link-establishing scan in a step-by-step manner based on the first step direction until the target satellite is recaptured, so as to re-establish a communication link between the local satellite and the target satellite.

2. The method according to claim 1, characterized in that, In response to determining that the local star has left the interstellar transit region, based on the first jump direction, the local star performs a jump-based link-building scan until the target star is recaptured, including: Determine the stride length of the first jump; and The laser payload of the local satellite is directed toward the first step direction, gradually shifting its direction with the first step distance, and performing coarse and fine composite spiral scans in the direction indicated by each step point in order to recapture the target satellite.

3. The method according to claim 2, characterized in that, The method further includes: In response to the determination that the local satellite has not recaptured the target satellite when the first hop count is reached, perform any of the following: The first jump direction is recalculated, causing the laser payload of the local satellite to gradually shift towards the new first jump direction, and coarse and fine composite helical scans are performed in the direction indicated by each step point in order to recapture the target satellite; or One or more second hop directions are determined such that the local satellite performs a field-of-view scan based on each of the determined one or more hop directions, in order to recapture the target satellite.

4. The method according to claim 3, characterized in that, Determining one or more second hop directions, such that the local satellite performs a field-of-view coverage scan based on each of the determined one or more hop directions, including: Determine two distinct second jump directions; and The laser payload of the local satellite gradually shifts from the scanning starting point to one of the two determined second step directions, performing a 360° field-of-view scan in the direction indicated by each step point until the local satellite recaptures the target satellite.

5. The method according to claim 1, characterized in that, In response to determining that the local satellite is in the solar interference region, distance measurements are performed between the local satellite and the target satellite based on predetermined time intervals to obtain an array of distance values ​​between the local satellite and the target satellite. This process determines the relative motion direction of the local satellite and the target satellite, including: Based on the distance value array, obtain the distance change value array between the local star and the target star; Based on the aforementioned set of distance variation values, calculate the summation average of the distance variations between the local star and the target star; and Based on the sum of the distance changes and their average values, the relative motion direction between the local star and the target star is obtained.

6. The method according to claim 5, characterized in that, The method further includes: In response to determining that the local satellite has left the solar transit region, the relative motion direction of the local satellite and the target satellite is determined, and the direction of the first jump includes any of the following: When the sum of the distance changes is less than 0, it is determined that the local star and the target star are approaching each other, thereby determining that the first jump direction is the transit direction; When the sum of the distance changes is greater than 0, it is determined that the local star and the target star are moving away from each other, thereby determining that the first jump direction is the direction of the solar transit. When the sum of the distance changes equals 0, it is determined that the distance change between the local satellite and the target satellite is less than a predetermined range, thus determining that the local satellite does not need to skip steps.

7. The method according to claim 1, characterized in that, Determining whether the local satellite has entered the solar transit region based on the first included angle includes: In response to a first angle of less than or equal to 3° between the position vector of the Sun and the line of sight of the local satellite's laser payload in the y-axis direction of the laser payload coordinate system, the local satellite is determined to have entered the solar interference region in order to perform a solar interference avoidance operation; and / or In response to the first angle between the position vector of the sun and the line of sight of the local satellite's laser payload in the z-axis direction of the laser payload coordinate system being less than or equal to 3°, the local satellite is determined to have entered the solar interference region in order to perform a solar interference avoidance operation.

8. A computing device, characterized in that, include: At least one processing unit; At least one memory coupled to the at least one processing unit and storing instructions for execution by the at least one processing unit, the instructions, when executed by the at least one processing unit, causing the device to perform the steps of the method according to any one of claims 1 to 7.

9. A computer-readable storage medium, characterized in that, It stores a computer program that, when executed by a machine, implements the method according to any one of claims 1 to 7.

10. A computer program product, characterized in that, Includes a computer program, which, when executed by a machine, performs the method according to any one of claims 1 to 7.

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