Satellite startup orbit prediction method, device and equipment

Abstract

The present invention provides a method, device and equipment for predicting satellite startup orbits, which are applied to the field of communication technology. The method comprises: during the satellite rotation process, determining a first orbital arc segment set and a second orbital arc segment set within a preset time length, wherein each first orbital arc segment in the first orbital arc segment set is an arc segment in which the satellite can communicate with a ground observation point, and each second orbital arc segment in the second orbital arc segment set is an arc segment in which the satellite is within the startup range; determining the intersection between all the first orbital arc segments and all the second orbital arc segments, and obtaining the startup orbit prediction result of the ground observation point. The present invention can accurately determine the actual startup range of the satellite above a certain location, thereby determining the arc segment in which the satellite can communicate.

Description

Technical Field

[0001] The present invention relates to the field of communication technology, and in particular to a method, device and equipment for predicting satellite startup orbits. Background Art

[0002] Satellite communications have been applied in various fields due to their unique advantages such as wide coverage, fast transmission speed and stable communication quality.

[0003] The satellite communication system consists of two parts: satellites and ground stations. As long as the ground station is within the coverage of the electromagnetic waves emitted by the satellite, communication can be carried out between any two points. Since the satellite flies around the earth and the earth rotates, a certain location on the ground is not within the coverage of the satellite signal most of the time. This requires ground personnel to grasp the transit information of the satellite at a certain location so that they can communicate with the satellite in a timely and effective manner. However, due to the different payload designs of satellites, the satellite's power-on range will be limited. If the selected location is far away from the power-on range, the predicted time period (also called arc segment) will not be able to communicate. Even at the boundary of the satellite power-on, the predicted transit arc segment is only part of the time available for communication, and ground personnel cannot distinguish which transit arc segments are actually available.

[0004] Therefore, how to determine the time period when the satellite is turned on over a certain location and predict the arc in which the satellite can communicate is a technical problem that urgently needs to be solved. Summary of the invention

[0005] The present invention provides a satellite startup orbit prediction method, device and equipment, which are used to solve the defect in the prior art that it is impossible to determine the startup time period of the satellite above a certain location to determine the arc segment in which the satellite can communicate, and realize that the actual startup range of the satellite above a certain location can be accurately determined, thereby determining the arc segment in which the satellite can communicate.

[0006] The present invention provides a satellite startup orbit prediction method, comprising:

[0007] During the satellite rotation process, a first orbital arc segment set and a second orbital arc segment set within a preset time length are determined, wherein each first orbital arc segment in the first orbital arc segment set is an arc segment in which the satellite can communicate with a ground observation point, and each second orbital arc segment in the second orbital arc segment set is an arc segment in which the satellite is within a power-on range;

[0008] Determine the intersection between all the first orbital arc segments and all the second orbital arc segments to obtain the power-on orbit prediction result of the ground observation point.

[0009] According to a satellite startup orbit prediction method provided by the present invention, during the satellite rotation process, determining a first orbit arc segment set within a preset time length includes:

[0010] Determining a target elevation angle of the satellite relative to the ground observation point based on the current two-row root number of the satellite;

[0011] In the case where the target elevation angle is greater than or equal to a first preset elevation angle, determining a first moment corresponding to the target elevation angle as a first starting moment; the first preset elevation angle is a minimum elevation angle at which the satellite can communicate with the ground observation point;

[0012] As the satellite continues to rotate, determining a new target elevation angle of the satellite relative to the ground observation point;

[0013] When the new target elevation angle is less than the first preset elevation angle, determining a second moment corresponding to the new target elevation angle as a first end moment;

[0014] Determine a time period between the first starting time and the first ending time as a first orbit arc segment;

[0015] Based on each first track arc segment determined within the preset time length, the first track arc segment set is determined.

[0016] According to a satellite startup orbit prediction method provided by the present invention, during the satellite rotation process, a second orbit arc segment set within a preset time length is determined, including:

[0017] Determining a target elevation angle of the satellite relative to the ground observation point based on the current two-row root number of the satellite;

[0018] When the target elevation angle is greater than or equal to a second preset elevation angle, a third moment corresponding to the target elevation angle is determined as a second starting moment; the second preset elevation angle is an elevation angle corresponding to the satellite with the ground center point as the power-on range;

[0019] As the satellite continues to rotate, determining a new target elevation angle of the satellite relative to the ground observation point;

[0020] When the new target elevation angle is less than the second preset elevation angle, determining a fourth moment corresponding to the new target elevation angle as a second end moment;

[0021] Determine a time period between the second starting time and the second ending time as a second orbital arc segment;

[0022] Based on each second orbital arc segment determined within the preset time length, the second orbital arc segment set is determined.

[0023] According to a satellite startup orbit prediction method provided by the present invention, during the satellite rotation process, a second orbit arc segment set within a preset time length is determined, including:

[0024] Based on the current two-row elements of the satellite, determine the sub-satellite point of the satellite;

[0025] In the case where the sub-satellite point is within a preset longitude and latitude range, the fifth time corresponding to the sub-satellite point is determined as the third starting time; the preset longitude and latitude range is the longitude and latitude corresponding to the power-on range of the satellite;

[0026] As the satellite continues to rotate, determining a new sub-satellite point of the satellite;

[0027] When the new sub-satellite point is not within the preset longitude and latitude range, determining the sixth time corresponding to the new sub-satellite point as the third end time;

[0028] Determine the time period between the third starting time and the third ending time as a second orbital arc segment;

[0029] Based on each second orbital arc segment determined within the preset time length, the second orbital arc segment set is determined.

[0030] According to a satellite startup orbit prediction method provided by the present invention, the target elevation angle of the satellite relative to the ground observation point is determined based on the current two-row elements of the satellite, including:

[0031] Determine a first current position of the satellite in the geoinertial coordinate system at a current moment based on the current two-row root number of the satellite;

[0032] Using the SGP4 satellite orbit model, converting the first current position into a second current position of the satellite in the earth-fixed coordinate system at the current moment;

[0033] Based on the second current position, a target elevation angle of the satellite relative to the ground observation point is determined.

[0034] According to a satellite startup orbit prediction method provided by the present invention, the first current position of the satellite in the geoinertial coordinate system at the current moment is determined based on the current two-row elements of the satellite, including:

[0035] The SGP4 satellite orbit model is used to analyze the current two rows of roots to obtain the first current position of the satellite in the geoinertial coordinate system at the current moment.

[0036] According to a satellite startup orbit prediction method provided by the present invention, the sub-satellite point of the satellite is determined based on the current two-row elements of the satellite, including:

[0037] Determine a first current position of the satellite in the geoinertial coordinate system at a current moment based on the current two-row root number of the satellite;

[0038] Converting the first current position into a third current position of the satellite in the geodetic coordinate system at the current moment;

[0039] Based on the third current position, a sub-satellite point of the satellite is determined.

[0040] The present invention also provides a satellite startup orbit prediction device, comprising:

[0041] A first determination module is used to determine a first orbital arc segment set and a second orbital arc segment set within a preset time period during the satellite rotation process, wherein each first orbital arc segment in the first orbital arc segment set is an arc segment in which the satellite can communicate with a ground observation point, and each second orbital arc segment in the second orbital arc segment set is an arc segment in which the satellite is within a power-on range;

[0042] The second determination module is used to determine the intersection between all the first orbital arc segments and all the second orbital arc segments to obtain the power-on orbit prediction result of the ground observation point.

[0043] The present invention also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, any one of the above-mentioned satellite startup orbit prediction methods is implemented.

[0044] The present invention also provides a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, any of the satellite startup orbit prediction methods described above is implemented.

[0045] The present invention also provides a computer program product, comprising a computer program, wherein when the computer program is executed by a processor, the computer program implements any of the above-mentioned satellite startup orbit prediction methods.

[0046] The satellite startup orbit prediction method, device and equipment provided by the present invention determine, during the satellite rotation process, multiple first orbital arc segments in which the satellite can communicate with the ground observation point within a preset time length, and multiple second orbital arc segments in which the satellite is within the startup range, and determine the intersection between all the first orbital arc segments and all the second orbital arc segments, so as to obtain the startup orbit prediction result of the ground observation point. By obtaining the intersection, unusable transit arc segments can be filtered out, and each orbital arc segment in the determined intersection is a visible arc segment in which the satellite is within the startup range and can communicate normally with the ground observation point. Therefore, the visible arc segment of the satellite above any location in the world can be predicted. The visible arc segment not only takes into account the transit time period of the satellite, but also takes into account the actual startup working time range of the satellite, so that the prediction result has high accuracy and small error. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0048] Figure 1 One of the flow charts of the satellite startup orbit prediction method provided by the embodiment of the present invention;

[0049] Figure 2 A second flow chart of a method for predicting satellite orbits when powered on provided by an embodiment of the present invention;

[0050] Figure 3 A schematic diagram of the structure of a satellite startup orbit prediction device provided by an embodiment of the present invention;

[0051] Figure 4 An example physical structure diagram of an electronic device is provided. DETAILED DESCRIPTION

[0052] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0053] As satellites fly around the earth and the earth rotates, a certain location on the ground is not within the coverage of satellite signals most of the time. This requires ground personnel to have information about satellite transit at a certain location so that they can communicate with the satellite in a timely and effective manner. For example, the time analysis function of the STK (Satellite Tool Kit) software can be used for setting and analysis to obtain multiple satellite transit time periods at a specific location in the future.

[0054] In addition, many satellites will only operate in a specific geographical area due to payload requirements. If the selected location is at the boundary of the satellite's operating range, only part of the satellite transit time period is the truly usable communication time period. In practical applications, orbit prediction that takes into account the satellite's operating range is what ground users really need. Therefore, how to determine the satellite's operating time range over a certain location and determine the visible arc segment in which the satellite can communicate is a technical problem that urgently needs to be solved.

[0055] Taking the above problems into consideration, an embodiment of the present invention proposes a method for predicting satellite startup orbits. In this method, during the rotation of the satellite, arc segments in which the satellite can communicate with ground observation points within a preset time period and arc segments in which the satellite is within the startup range can be determined, and the intersection of these arc segments can be obtained, so that unusable transit arc segments can be filtered out, so that each orbital arc segment in the determined intersection is a visible arc segment in which the satellite is within the actual startup range and can communicate normally with the ground observation point. In this way, the visible arc segment of the satellite over any location in the world can be predicted, wherein the visible arc segment not only takes into account the transit time period of the satellite, but also takes into account the actual startup time range of the satellite. In this way, the startup orbit prediction result within the startup range of the satellite at that location can be quickly and accurately determined, which helps users or testers to know the communication time period between the ground and the satellite in advance, saves ground waiting time, and realizes timely and effective communication.

[0056] Combine the following Figure 1 and Figure 2 The satellite startup orbit prediction method provided by the embodiment of the present invention is described. The embodiment of the present invention can be applicable to startup orbit prediction in satellite communication scenarios. The execution subject of the method can be a ground observation station, a computer, a server, a server cluster, or a specially designed satellite startup orbit prediction device and other electronic devices, or it can be a satellite startup orbit prediction device set in the electronic device, and the satellite startup orbit prediction device can be implemented by software, hardware, or a combination of both.

[0057] Figure 1 One of the flow charts of the satellite startup orbit prediction method provided by the embodiment of the present invention is as follows: Figure 1As shown, the method includes:

[0058] Step 101: During the rotation of the satellite, a first orbital arc segment set and a second orbital arc segment set within a preset time length are determined, wherein each first orbital arc segment in the first orbital arc segment set is an arc segment in which the satellite can communicate with a ground observation point, and each second orbital arc segment in the second orbital arc segment set is an arc segment in which the satellite is within the power-on range.

[0059] In this step, the preset duration is the preset duration for which the satellite startup orbit forecast is required, such as 24 hours, etc. Since the two-row root parameter places the satellite in a time-space coordinate system, the start and end times of the preset duration can be set arbitrarily. The ground observation point is a position selected on the earth, represented by longitude and latitude coordinates. Through the method described in this embodiment, the startup orbit forecast result of the position in the future period can be calculated.

[0060] If the satellite can communicate normally with the ground observation point, the ground observation point needs to be within the coverage of the satellite signal. Therefore, it is necessary to determine the transit information of the satellite at the ground observation point within a preset time, that is, multiple first orbital arcs in which the satellite can communicate with the ground observation point. Among them, the first orbital arc can be understood as the arc in which the satellite and the ground observation point can communicate assuming that the satellite is in a normal power-on state. The first orbital arc is the orbit prediction result that does not take into account the actual power-on range of the satellite.

[0061] In addition, due to the different payload designs of each satellite, in order to reduce power consumption and extend the communication time of the satellite, the satellite's power-on range will be limited. Therefore, it is also necessary to determine multiple second orbital arcs in which the satellite is in the power-on range within a preset time. It should be understood that the multiple second orbital arcs may include some arcs in which the satellite cannot communicate with the ground observation point.

[0062] Step 102: Determine the intersections between all first orbital arcs and all second orbital arcs to obtain a power-on orbit prediction result of a ground observation point.

[0063] In this step, after determining the plurality of first orbital arc segments and the plurality of second orbital arc segments, the intersection between the plurality of first orbital arc segments and the plurality of second orbital arc segments can be obtained. Since the plurality of first orbital arc segments are arc segments where the satellite can communicate with the ground observation point without considering the power-on time range, and the plurality of second orbital arc segments are arc segments where the satellite is within the power-on range, each orbital arc segment in the determined intersection is an arc segment where the satellite is within the power-on range and can communicate normally with the ground observation point, and thus the power-on orbit prediction result of the ground observation point can be obtained.

[0064] The satellite startup orbit prediction method provided by the embodiment of the present invention determines, during the satellite rotation process, multiple first orbital arc segments in which the satellite can communicate with the ground observation point within a preset time length, and multiple second orbital arc segments in which the satellite is within the startup range, and determines the intersection between all the first orbital arc segments and all the second orbital arc segments, thereby obtaining the startup orbit prediction result of the ground observation point. By obtaining the intersection, unusable transit arc segments can be filtered out, and each orbital arc segment in the determined intersection is a visible arc segment in which the satellite is within the startup range and can communicate normally with the ground observation point. Therefore, the visible arc segment of the satellite above any location in the world can be predicted. The visible arc segment not only takes into account the transit time period of the satellite, but also takes into account the actual startup time range of the satellite, so that the prediction result has high accuracy and small error.

[0065] In addition, since the above prediction results can be obtained by only taking the intersection of all first track arc segments and all second track arc segments, the prediction speed is faster and more efficient, which helps users save unnecessary waiting time in actual applications and enables users to make the next decision in advance, thereby improving the user experience.

[0066] It should be noted that if there is no restriction on the satellite power-on time range, that is, when the satellite is always in the power-on state, the multiple first orbital arc segments in the determined first orbital arc segment set are the satellite orbit prediction results. If there is a restriction on the satellite power-on time range, it is necessary to further determine the second orbital set, thereby determining the intersection between the multiple first orbital arc segments and the multiple second orbital arc segments, so as to obtain the arc segments that can truly achieve communication.

[0067] Figure 2 The second flow chart of the satellite startup orbit prediction method provided by the embodiment of the present invention is as follows. Based on the above embodiment, the present embodiment is Figure 1 The specific implementation process of how to determine the first orbital arc segment set within a preset time length in the illustrated embodiment during the satellite rotation process is described in detail. Figure 2 As shown, the method includes:

[0068] Step 201: Based on the current two-row elements of the satellite, determine the target elevation angle of the satellite relative to the ground observation point.

[0069] In this step, the satellite's current two-line elements (TLE) number is a data format that describes the satellite's orbital parameters. It contains information such as the six satellite orbital roots, epoch time, and satellite identification. TLE data is usually obtained by satellite measurement stations or other data centers through measurement and observation of satellites.

[0070] By analyzing the current TLE number of the satellite, the target elevation angle of the satellite relative to the ground observation point in the earth-fixed coordinate system can be obtained.

[0071] Step 202: When the target elevation angle is greater than or equal to a first preset elevation angle, a first moment corresponding to the target elevation angle is determined as a first starting moment; the first preset elevation angle is a minimum elevation angle at which the satellite can communicate with a ground observation point.

[0072] In this step, the satellite is considered to have the ability to communicate with the ground observation point only when the target elevation angle of the satellite is greater than or equal to the first preset elevation angle, and can achieve communication with the ground observation point. Therefore, after determining the target elevation angle, it is necessary to further determine whether the target elevation angle of the satellite relative to the ground observation point is greater than or equal to the first preset elevation angle. The first preset elevation angle is the starting elevation angle at which the satellite can normally communicate with the ground observation point.

[0073] When the target elevation angle is greater than or equal to the first preset elevation angle, the first moment corresponding to the current target elevation angle is determined as the first starting moment of the first orbital arc segment. That is, assuming that the satellite is in the turned-on state, the satellite and the ground observation point can communicate normally from the first starting moment.

[0074] When the target elevation angle is less than the first preset elevation angle, no processing will be performed, and the time pointer will be moved to continue to determine the new target elevation angle at the next moment according to the two rows of roots, so as to determine whether the new target elevation angle is greater than or equal to the first preset elevation angle. Specifically, a satellite object can be generated according to the two rows of root data through the SGP4 satellite orbit model, and the satellite object and any given time can be passed as parameters to the SGP4 satellite orbit model, so that the position and direction information of the satellite at the time can be obtained, thereby further obtaining the target elevation angle.

[0075] Step 203: As the satellite continues to rotate, determine the new target elevation angle of the satellite relative to the ground observation point.

[0076] In this step, as the satellite continues to rotate around the earth, two rows of satellite roots are obtained and analyzed. Based on the analyzed satellite object and the next time information, the new target elevation angle of the satellite relative to the ground observation point is obtained.

[0077] Step 204: When the new target elevation angle is less than the first preset elevation angle, the second moment corresponding to the new target elevation angle is determined as the first end moment.

[0078] In this step, when the new target elevation angle is less than the first preset elevation angle, it means that the satellite will not be able to communicate normally with the ground observation point. The second moment at this time will be recorded and used as the first end moment.

[0079] If the new target elevation angle is greater than or equal to the first preset elevation angle, no processing is performed, and the new target elevation angle continues to be determined during the satellite rotation until the obtained target elevation angle is less than the first preset elevation angle.

[0080] Step 205: Determine the time period between the first start time and the first end time as the first orbital arc segment.

[0081] In this step, the time period from the first starting moment to the first ending moment can be understood as the time period in which the satellite can communicate normally with the ground observation point assuming that the satellite is in the turned-on state. Therefore, this time period is determined as the first orbital arc segment.

[0082] Step 206: Determine a first track arc segment set based on each first track arc segment determined within a preset time period.

[0083] In this step, since the satellite may have multiple transit arcs relative to a ground observation point within the preset time period, multiple first orbital arcs may be determined within the preset time period, and these multiple first orbital arcs constitute a first orbital arc set.

[0084] In this embodiment, by presetting a first preset elevation angle, the determined target elevation angle of the satellite relative to the ground observation point is compared with the first preset elevation angle, so that the first orbital arc segment in which the satellite can communicate with the ground observation point can be quickly and accurately determined, thereby improving the efficiency of determining the first orbital arc segment.

[0085] Exemplarily, on the basis of the above-mentioned embodiments, when determining the target elevation angle of the satellite relative to the ground observation point based on the current two-row roots of the satellite, the first current position of the satellite in the geoinertial coordinate system at the current moment can be determined based on the current two-row roots of the satellite, and the SGP4 satellite orbit model can be used to convert the first current position into the second current position of the satellite in the geofixed coordinate system at the current moment, and based on the second current position, the target elevation angle of the satellite relative to the ground observation point is determined.

[0086] Specifically, one of the specific text formats of satellite ephemeris is called TLE number, which places the satellite in a time-space coordinate system and uses time to describe the specific position of the satellite in the past, present and future in three-dimensional space. After obtaining the current two rows of satellite elements, the satellite's identity information, orbital six elements, orbital period and other related parameters can be obtained by parsing the two rows of elements, and based on the satellite's related parameters, the first current position of the satellite in the geoinertial coordinate system at the current moment can be determined.

[0087] In a possible implementation, the SGP4 satellite orbit model may be used to analyze the current two rows of elements to obtain the first current position of the satellite in the geoinertial coordinate system at the current moment.

[0088] Among them, the SGP4 satellite orbit model has open source libraries in multiple programming languages, such as C++, Java, and JavaScript. In the embodiment of the present invention, the SGP4 algorithm model library Satellite.js implemented in JavaScript is used. Using the SGP4 satellite orbit model, the position and speed of the satellite in orbit can be calculated based on the relevant parameters of the satellite combined with time information and perturbation terms and other parameters. This position is also the first current position of the satellite in the geoinertial coordinate system at the current moment.

[0089] By analyzing the current two rows of roots through the SGP4 satellite orbit model, the first current position of the satellite in the geoinertial coordinate system at the current moment can be quickly obtained.

[0090] After obtaining the first current position, the first current position in the Earth-inertial coordinate system can be converted into the second current position of the satellite in the Earth-fixed coordinate system at the same time. Exemplarily, the SGP4 satellite orbit model can be used to convert the first current position into the second current position.

[0091] Furthermore, the SGP4 satellite orbit model can be used to calculate the target elevation angle of the satellite relative to the ground observation point in the earth-fixed coordinate system based on the second current position of the satellite in the earth-fixed coordinate system.

[0092] In this embodiment, after determining the first current position of the satellite in the Earth-inertial coordinate system at the current moment based on the current two-row roots of the satellite, the first current position is converted into the second current position of the satellite in the Earth-fixed coordinate system at the current moment, and based on the second current position, the target elevation angle of the satellite relative to the ground observation point is calculated in the Earth-fixed coordinate system. By converting the position in different coordinate systems, the target elevation angle determined based on the converted second current position is more accurate.

[0093] Furthermore, when calculating the satellite power-on time, there may be different calculation methods according to the different power-on ranges of the satellite. For example, some satellites are only powered on in mid- and low-latitude areas, and the power-on range can be approximately regarded as a "rectangle". At this time, the timestamp can be recorded according to the specified longitude and latitude values, and the satellite power-on time within a certain time range can be calculated; or the satellite power-on range is approximately "circular", that is, the power-on center point, radius and power-on semi-beam angle are specified, and the power-on time of the satellite in the range is calculated.

[0094] Therefore, in a possible implementation method, on the basis of the above embodiments, during the rotation of the satellite, a set of second orbital arc segments within a preset time length is determined, including: based on the current two-row roots of the satellite, determining the target elevation angle of the satellite relative to the ground observation point; when the target elevation angle is greater than or equal to the second preset elevation angle, determining the third moment corresponding to the target elevation angle as the second starting moment; the second preset elevation angle is the elevation angle corresponding to the satellite with the ground center point as the power-on range; during the continued rotation of the satellite, determining the new target elevation angle of the satellite relative to the ground observation point; when the new target elevation angle is less than the second preset elevation angle, determining the fourth moment corresponding to the new target elevation angle as the second end moment; determining the time period between the second start moment and the second end moment as the second orbital arc segment; and determining a set of second orbital arc segments based on each second orbital arc segment determined within the preset time length.

[0095] Specifically, assuming that the satellite uses a certain ground center point and an elevation angle of a second preset elevation angle as the power-on range, when determining the arc segment within the actual power-on range of the satellite, the two rows of roots obtained can be analyzed, and the target elevation angle of the satellite relative to the ground observation point can be determined using the SGP4 satellite orbit model. When the target elevation angle is greater than or equal to the second preset elevation angle, it means that the satellite is within the power-on time range at this time, and the third moment corresponding to the target elevation angle is determined as the second starting moment. Among them, the second preset elevation angle can be understood as the elevation angle corresponding to the satellite using the ground center point as the power-on range, for example, it can be an elevation angle of 10 degrees.

[0096] As the time pointer continues to move backward, the satellite continues to rotate, and the electronic device will re-acquire the new target elevation angle of the satellite relative to the ground observation point, and determine whether the new target elevation angle is greater than or equal to the second preset elevation angle. If it is greater than or equal to the second preset elevation angle, the above process will continue to be executed until the new target elevation angle acquired is less than the second preset elevation angle, and the fourth moment corresponding to the target elevation angle is determined as the second end time.

[0097] Furthermore, the time period from the second starting moment to the second ending moment can be understood as the actual power-on time period of the satellite, and therefore, this time period is determined as the second orbital arc segment.

[0098] Since the satellite will have multiple real power-on time periods within the preset duration, multiple second orbital arcs will be determined, and these multiple second orbital arcs constitute a second orbital arc set.

[0099] In this embodiment, by pre-setting a second preset elevation angle, the determined target elevation angle of the satellite relative to the ground observation point is compared with the second preset elevation angle, so that the second orbital arc segment characterizing the actual power-on range of the satellite can be quickly and accurately determined, thereby improving the efficiency and accuracy of determining the second orbital arc segment.

[0100] In another possible implementation, on the basis of the above embodiments, a second orbital arc segment set within a preset time length is determined during the rotation of the satellite, including: determining the sub-satellite point of the satellite based on the current two-row root number of the satellite; when the sub-satellite point is within the preset longitude and latitude range, determining the fifth moment corresponding to the sub-satellite point as the third starting moment; the preset longitude and latitude range is the longitude and latitude corresponding to the power-on range of the satellite; as the satellite continues to rotate, determining a new sub-satellite point of the satellite; when the new sub-satellite point is not within the preset longitude and latitude range, determining the sixth moment corresponding to the new sub-satellite point as the third ending moment; determining the time period between the third starting moment and the third ending moment as the second orbital arc segment; and determining a second orbital arc segment set based on each second orbital arc segment determined within the preset time length.

[0101] Specifically, if the satellite uses other requirements as the power-on range, such as 10-60 degrees latitude and 60-150 degrees longitude as the power-on range, when determining the arc segment within the actual power-on range of the satellite, the current two rows of roots obtained can be parsed to determine the sub-satellite point of the satellite. When the sub-satellite point is within the preset longitude and latitude range, it means that the satellite is within the power-on time range at this time, and the fifth moment corresponding to the sub-satellite point is determined as the third starting moment. Among them, the preset longitude and latitude range can be understood as the longitude and latitude corresponding to the power-on range of the satellite.

[0102] As the time pointer continues to move backward, the satellite continues to rotate, and the electronic device will re-acquire the new sub-satellite point of the satellite and determine whether the new sub-satellite point is within the preset longitude and latitude range. If it is within the preset longitude and latitude range, the above process will continue to be executed until the new sub-satellite point acquired is not within the preset longitude and latitude range, and the sixth moment corresponding to the new sub-satellite point is determined as the third end time.

[0103] Furthermore, the time period from the third starting moment to the third ending moment can be understood as the actual power-on time period of the satellite, and therefore, this time period is determined as the second orbital arc segment.

[0104] Since the satellite will have multiple real power-on time periods within the preset duration, multiple second orbital arcs will be determined, and these multiple second orbital arcs constitute a second orbital arc set.

[0105] In this embodiment, by presetting a preset longitude and latitude range, the determined sub-satellite point of the satellite is compared with the preset longitude and latitude range, so that the second orbital arc segment representing the actual power-on range of the satellite can be quickly and accurately determined, thereby improving the efficiency and accuracy of determining the second orbital arc segment.

[0106] Exemplarily, on the basis of the above-mentioned embodiments, the sub-satellite point of the satellite is determined based on the current two-row roots of the satellite, including: determining the first current position of the satellite in the geoinertial coordinate system at the current moment based on the current two-row roots of the satellite; converting the first current position into a third current position in the geodetic coordinate system of the satellite at the current moment; and determining the sub-satellite point of the satellite based on the third current position.

[0107] Specifically, the SGP4 satellite orbit model can be used to parse the current two rows of roots to obtain the first current position of the satellite in the geoinertial coordinate system at the current moment, and the first current position in the geoinertial coordinate system is converted to the third current position of the satellite in the geodetic coordinate system at the same moment. Exemplarily, the SGP4 satellite orbit model can be used to convert the first current position to the third current position. The geodetic coordinate system can use longitude, latitude and altitude to describe the position of a point on the earth.

[0108] Furthermore, the SGP4 satellite orbit model can be used to calculate the sub-satellite point of the satellite in the geodetic coordinate system based on the third current position of the satellite in the geodetic coordinate system.

[0109] In this embodiment, after determining the first current position of the satellite in the geoidylic coordinate system at the current moment based on the current two-row roots of the satellite, the first current position is converted into the third current position of the satellite in the geodetic coordinate system at the current moment, and based on the third current position, the sub-satellite point of the satellite is calculated in the geodetic coordinate system. By converting the positions in different coordinate systems, the sub-satellite point determined based on the converted third current position has higher accuracy.

[0110] The satellite startup orbit prediction device provided by the present invention is described below. The satellite startup orbit prediction device described below and the satellite startup orbit prediction method described above can be referenced to each other.

[0111] Figure 3 The schematic diagram of the structure of the satellite startup orbit prediction device provided by the embodiment of the present invention is shown in FIG. Figure 3 As shown, the satellite startup orbit prediction device 300 includes:

[0112] A first determination module 301 is used to determine a first orbital arc segment set and a second orbital arc segment set within a preset time period during the satellite rotation process, wherein each first orbital arc segment in the first orbital arc segment set is an arc segment in which the satellite can communicate with a ground observation point, and each second orbital arc segment in the second orbital arc segment set is an arc segment in which the satellite is within a power-on range;

[0113] The second determination module 302 is used to determine the intersections between all the first orbital arcs and all the second orbital arcs to obtain the power-on orbit prediction result of the ground observation point.

[0114] In an exemplary embodiment, the first determining module 301 is specifically configured to:

[0115] Determining a target elevation angle of the satellite relative to the ground observation point based on the current two-row root number of the satellite;

[0116] In the case where the target elevation angle is greater than or equal to a first preset elevation angle, determining a first moment corresponding to the target elevation angle as a first starting moment; the first preset elevation angle is a minimum elevation angle at which the satellite can communicate with the ground observation point;

[0117] As the satellite continues to rotate, determining a new target elevation angle of the satellite relative to the ground observation point;

[0118] When the new target elevation angle is less than the first preset elevation angle, determining a second moment corresponding to the new target elevation angle as a first end moment;

[0119] Determine a time period between the first starting time and the first ending time as a first orbit arc segment;

[0120] Based on each first track arc segment determined within the preset time length, the first track arc segment set is determined.

[0121] In an exemplary embodiment, the first determining module 301 is specifically configured to:

[0122] Determining a target elevation angle of the satellite relative to the ground observation point based on the current two-row root number of the satellite;

[0123] When the target elevation angle is greater than or equal to a second preset elevation angle, a third moment corresponding to the target elevation angle is determined as a second starting moment; the second preset elevation angle is an elevation angle corresponding to the satellite with the ground center point as the power-on range;

[0124] As the satellite continues to rotate, determining a new target elevation angle of the satellite relative to the ground observation point;

[0125] When the new target elevation angle is less than the second preset elevation angle, determining a fourth moment corresponding to the new target elevation angle as a second end moment;

[0126] Determine a time period between the second starting time and the second ending time as a second orbital arc segment;

[0127] Based on each second orbital arc segment determined within the preset time length, the second orbital arc segment set is determined.

[0128] In an exemplary embodiment, the first determining module 301 is specifically configured to:

[0129] Based on the current two-row elements of the satellite, determine the sub-satellite point of the satellite;

[0130] In the case where the sub-satellite point is within a preset longitude and latitude range, the fifth time corresponding to the sub-satellite point is determined as the third starting time; the preset longitude and latitude range is the longitude and latitude corresponding to the power-on range of the satellite;

[0131] As the satellite continues to rotate, determining a new sub-satellite point of the satellite;

[0132] When the new sub-satellite point is not within the preset longitude and latitude range, determining the sixth time corresponding to the new sub-satellite point as the third end time;

[0133] Determine the time period between the third starting time and the third ending time as a second orbital arc segment;

[0134] Based on each second orbital arc segment determined within the preset time length, the second orbital arc segment set is determined.

[0135] In an exemplary embodiment, the first determining module 301 is specifically configured to:

[0136] Determine a first current position of the satellite in the geoinertial coordinate system at a current moment based on the current two-row root number of the satellite;

[0137] Using the SGP4 satellite orbit model, converting the first current position into a second current position of the satellite in the earth-fixed coordinate system at the current moment;

[0138] Based on the second current position, a target elevation angle of the satellite relative to the ground observation point is determined.

[0139] In an exemplary embodiment, the first determining module 301 is specifically configured to:

[0140] The SGP4 satellite orbit model is used to analyze the current two rows of roots to obtain the first current position of the satellite in the geoinertial coordinate system at the current moment.

[0141] In an exemplary embodiment, the first determining module 301 is specifically configured to:

[0142] Determine a first current position of the satellite in the geoinertial coordinate system at a current moment based on the current two-row root number of the satellite;

[0143] Converting the first current position into a third current position of the satellite in the geodetic coordinate system at the current moment;

[0144] Based on the third current position, a sub-satellite point of the satellite is determined.

[0145] The device of this embodiment can be used to execute the method of any embodiment in the satellite startup orbit prediction method embodiment. Its specific implementation process and technical effects are similar to those in the satellite startup orbit prediction method embodiment. For details, please refer to the detailed description in the satellite startup orbit prediction method embodiment, which will not be repeated here.

[0146] Figure 4 An example of a physical structure diagram of an electronic device is shown in FIG. Figure 4 As shown, the electronic device may include: a processor 410, a communication interface 420, a memory 430 and a communication bus 440, wherein the processor 410, the communication interface 420 and the memory 430 communicate with each other through the communication bus 440. The processor 410 may call the logic instructions in the memory 430 to execute the satellite startup orbit prediction method, the method comprising: during the satellite rotation process, determining a first orbital arc segment set and a second orbital arc segment set within a preset time length, each first orbital arc segment in the first orbital arc segment set is an arc segment that the satellite can communicate with the ground observation point, and each second orbital arc segment in the second orbital arc segment set is an arc segment that the satellite is within the startup range; determining the intersection between all the first orbital arc segments and all the second orbital arc segments, and obtaining the startup orbit prediction result of the ground observation point.

[0147] In addition, the logic instructions in the above-mentioned memory 430 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk and other media that can store program codes.

[0148] On the other hand, the present invention also provides a computer program product, which includes a computer program. The computer program can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the satellite power-on orbit prediction method provided by the above-mentioned methods. The method includes: during the rotation of the satellite, determining a first orbital arc segment set and a second orbital arc segment set within a preset time length, each first orbital arc segment in the first orbital arc segment set is an arc segment with which the satellite can communicate with a ground observation point, and each second orbital arc segment in the second orbital arc segment set is an arc segment within the power-on range of the satellite; determining the intersection between all the first orbital arc segments and all the second orbital arc segments to obtain the power-on orbit prediction result of the ground observation point.

[0149] On the other hand, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, it is implemented to execute the satellite power-on orbit prediction method provided by the above-mentioned methods. The method includes: during the rotation of the satellite, determining a first orbital arc segment set and a second orbital arc segment set within a preset time length, each first orbital arc segment in the first orbital arc segment set is an arc segment with which the satellite can communicate with a ground observation point, and each second orbital arc segment in the second orbital arc segment set is an arc segment within the power-on range of the satellite; determining the intersection between all the first orbital arc segments and all the second orbital arc segments to obtain the power-on orbit prediction result of the ground observation point.

[0150] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0151] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0152] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for predicting satellite startup orbit, characterized in that: include: During the satellite rotation process, a first orbital arc segment set and a second orbital arc segment set within a preset time length are determined, wherein each first orbital arc segment in the first orbital arc segment set is an arc segment in which the satellite can communicate with a ground observation point, and each second orbital arc segment in the second orbital arc segment set is an arc segment in which the satellite is within a power-on range; Determine the intersection between all the first orbital arc segments and all the second orbital arc segments to obtain the power-on orbit prediction result of the ground observation point, wherein each orbital arc segment in the intersection is an arc segment in which the satellite is within the power-on range and can communicate normally with the ground observation point.

2. The satellite startup orbit prediction method according to claim 1, characterized in that: The step of determining a first orbital arc segment set within a preset time period during the satellite rotation process includes: Determining a target elevation angle of the satellite relative to the ground observation point based on the current two-row root number of the satellite; In the case where the target elevation angle is greater than or equal to a first preset elevation angle, determining a first moment corresponding to the target elevation angle as a first starting moment; the first preset elevation angle is a minimum elevation angle at which the satellite can communicate with the ground observation point; As the satellite continues to rotate, determining a new target elevation angle of the satellite relative to the ground observation point; When the new target elevation angle is less than the first preset elevation angle, determining a second moment corresponding to the new target elevation angle as a first end moment; Determine a time period between the first starting time and the first ending time as a first orbit arc segment; Based on each first track arc segment determined within the preset time length, the first track arc segment set is determined.

3. The satellite startup orbit prediction method according to claim 1, characterized in that: During the satellite rotation process, determining a set of second orbital arc segments within a preset time period includes: Determining a target elevation angle of the satellite relative to the ground observation point based on the current two-row root number of the satellite; When the target elevation angle is greater than or equal to a second preset elevation angle, a third moment corresponding to the target elevation angle is determined as a second starting moment; the second preset elevation angle is an elevation angle corresponding to the satellite with the ground center point as the power-on range; As the satellite continues to rotate, determining a new target elevation angle of the satellite relative to the ground observation point; When the new target elevation angle is less than the second preset elevation angle, determining a fourth moment corresponding to the new target elevation angle as a second end moment; Determine a time period between the second starting time and the second ending time as a second orbital arc segment; Based on each second orbital arc segment determined within the preset time length, the second orbital arc segment set is determined.

4. The satellite startup orbit prediction method according to claim 1, characterized in that: During the satellite rotation process, determining a set of second orbital arc segments within a preset time period includes: Based on the current two-row elements of the satellite, determine the sub-satellite point of the satellite; In the case where the sub-satellite point is within a preset longitude and latitude range, the fifth time corresponding to the sub-satellite point is determined as the third starting time; the preset longitude and latitude range is the longitude and latitude corresponding to the power-on range of the satellite; As the satellite continues to rotate, determining a new sub-satellite point of the satellite; When the new sub-satellite point is not within the preset longitude and latitude range, determining the sixth time corresponding to the new sub-satellite point as the third end time; Determine the time period between the third starting time and the third ending time as a second orbital arc segment; Based on each second orbital arc segment determined within the preset time length, the second orbital arc segment set is determined.

5. The satellite startup orbit prediction method according to claim 2, characterized in that: The step of determining the target elevation angle of the satellite relative to the ground observation point based on the current two-row root number of the satellite comprises: Determine a first current position of the satellite in the geoinertial coordinate system at a current moment based on the current two-row root number of the satellite; Using the SGP4 satellite orbit model, converting the first current position into a second current position of the satellite in the earth-fixed coordinate system at the current moment; Based on the second current position, a target elevation angle of the satellite relative to the ground observation point is determined.

6. The satellite startup orbit prediction method according to claim 5, characterized in that: The determining, based on the current two-row root number of the satellite, a first current position of the satellite in the geoinertial coordinate system at the current moment, comprises: The SGP4 satellite orbit model is used to analyze the current two rows of roots to obtain the first current position of the satellite in the geoinertial coordinate system at the current moment.

7. The satellite startup orbit prediction method according to claim 4, characterized in that: The step of determining the sub-satellite point of the satellite based on the current two-row elements of the satellite comprises: Determine a first current position of the satellite in the geoinertial coordinate system at a current moment based on the current two-row root number of the satellite; Converting the first current position into a third current position of the satellite in the geodetic coordinate system at the current moment; Based on the third current position, a sub-satellite point of the satellite is determined.

8. A satellite startup orbit prediction device, characterized in that: include: A first determination module is used to determine a first orbital arc segment set and a second orbital arc segment set within a preset time period during the satellite rotation process, wherein each first orbital arc segment in the first orbital arc segment set is an arc segment in which the satellite can communicate with a ground observation point, and each second orbital arc segment in the second orbital arc segment set is an arc segment in which the satellite is within a power-on range; The second determination module is used to determine the intersection between all the first orbital arc segments and all the second orbital arc segments to obtain the power-on orbit prediction result of the ground observation point, and each orbital arc segment in the intersection is an arc segment in which the satellite is within the power-on range and can communicate normally with the ground observation point.

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the program, the satellite startup orbit prediction method as described in any one of claims 1 to 7 is implemented.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the satellite startup orbit prediction method as claimed in any one of claims 1 to 7 is implemented.

Images