Method and device for determining visible time period of remote sensing satellite and high-orbit communication satellite

Abstract

The present disclosure discloses a remote sensing satellite and high-orbit communication satellite visible period determination method, which relates to the technical field of aerospace, and the specific implementation scheme is: receiving the communication instruction sequence sent by the ground section of the remote sensing satellite, and analyzing the communication instruction sequence; according to the visible period calculation interval, the filtered real-time orbit data is screened out; the orbit determination model is corrected to obtain the corrected orbit determination model of the remote sensing satellite; according to the corrected orbit determination model, the initial orbit six elements of the remote sensing satellite visible period are determined; according to the initial orbit six elements of the remote sensing satellite visible period and the extrapolation correction coefficient of the remote sensing satellite, the first corrected orbit prediction data is determined; according to the initial orbit six elements of the high-orbit communication satellite visible period and the extrapolation correction coefficient of the high-orbit communication satellite, the second corrected orbit prediction data is determined; according to the first corrected orbit prediction data, the second corrected orbit prediction data, the earth radius and the use constraint data, the visible period is determined, which improves the accuracy of the visible period.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aerospace, and particularly relates to the technical field of inter-satellite remote control, telemetry, image data interaction of space satellites, and in particular to a method and device for determining a visible period of a remote sensing satellite and a high-orbit communication satellite, an electronic device, and a computer readable storage medium. BACKGROUND

[0002] The remote sensing satellite operates on an orbit close to the earth's surface and is mainly used for obtaining high-resolution images of the earth's surface. When the remote sensing satellite passes through a non-ground station, it cannot directly transmit the obtained data to the ground station, which may cause a delay in data transmission between the remote sensing satellite and the ground station. Moreover, when the remote sensing satellite cannot transmit data to the ground station, it needs to save the data in the on-board storage with limited capacity, which may cause the problem of early data loss. Therefore, how to ensure the continuity of data transmission between the remote sensing satellite and the ground station has become an important research direction.

[0003] The current mainstream technical means is to forward the data of the low-orbit satellite to the ground station through the relay satellite. Since the low-orbit satellite moves at a high speed relative to the earth's surface, the visibility between the low-orbit satellite and the relay satellite is the premise of establishing a communication link. In the prior art, whether the two satellites are visible is mainly determined by comparing the relevant parameters of the low-orbit satellite and the relay satellite, and the ground verification is performed by using the existing telemetry data of the low-orbit satellite and the relay satellite. This method is based on the real-time orbiting data (telemetry data) of the satellite speed and position, and cannot accurately reflect the flight situation of the satellite within a certain time, so it cannot predict the future visible period of the low-orbit satellite to the relay satellite. The vector parameters of the low-orbit satellite and the relay satellite are not obtained, so the satellite orbit cannot be accurately determined, which leads to the problem of visibility analysis error between the satellites. Generally, the visibility calculation of the low-orbit satellite and the relay satellite is performed in the ground segment of the high-orbit communication satellite, and there is a delay in obtaining the data of the remote sensing satellite and the high-orbit communication satellite in the ground segment of the high-orbit communication satellite. In the case of instant decision, the ground segment of the high-orbit communication satellite cannot respond in time, and the analysis of the ground segment of the high-orbit communication satellite depends on the communication link among the remote sensing satellite, the low-orbit communication satellite and the ground station, so there is a risk of being attacked and interfered.

[0004] The information disclosed in this Background section is only for the purpose of increasing the understanding of the general background of the application, and should not be taken as an acknowledgment or any form of suggestion that it forms the prior art that is already known to those of ordinary skill in the art. SUMMARY

[0005] The present application aims to solve the technical problem of poor prediction effect of the existing satellite visible period, and provides a method for determining a visible period of a remote sensing satellite and a high-orbit communication satellite.

[0006] The first aspect of the present disclosure provides a method for determining visible time periods of a remote sensing satellite and a high-orbit communication satellite. The method is applied to a space segment of the remote sensing satellite and comprises the following steps: receiving a communication instruction sequence sent by a ground segment, and parsing at least one visible time period calculation interval, initial orbit elements of the visible time period of the high-orbit communication satellite, and usage constraint data of the high-orbit communication satellite and the remote sensing satellite from the communication instruction sequence; screening out filtered real-time orbit data from accumulated real-time orbit data of the remote sensing satellite according to the visible time period calculation interval; correcting an orbit determination model of the remote sensing satellite to obtain a corrected orbit determination model of the remote sensing satellite; processing the filtered real-time orbit data according to the corrected orbit determination model of the remote sensing satellite to determine initial orbit elements of the visible time period of the remote sensing satellite; determining first corrected orbit prediction data of the remote sensing satellite in the visible time period calculation interval according to the initial orbit elements of the visible time period of the remote sensing satellite and extrapolation correction coefficients of the remote sensing satellite; determining second corrected orbit prediction data of the high-orbit communication satellite in the visible time period calculation interval according to the initial orbit elements of the visible time period of the high-orbit communication satellite and extrapolation correction coefficients of the high-orbit communication satellite; and determining the visible time period of the remote sensing satellite and the high-orbit communication satellite in the visible time period calculation interval according to the first corrected orbit prediction data, the second corrected orbit prediction data, the radius of the Earth, and the usage constraint data.

[0007] The second aspect of the present disclosure provides another method for determining visible time periods of a remote sensing satellite and a high-orbit communication satellite. The method is applied to a ground segment of the remote sensing satellite and comprises the following steps: determining a non-service time period during which spaceflight control and measurement services cannot be carried out between the remote sensing satellite and a ground station according to overflight ground station data of the remote sensing satellite; determining at least one visible time period calculation interval of the remote sensing satellite and the high-orbit communication satellite according to the non-service time period and an overflight area of the remote sensing satellite; obtaining initial orbit elements of the visible time period of the high-orbit communication satellite, and usage constraint data of the high-orbit communication satellite and the remote sensing satellite; generating a communication instruction sequence based on an instruction template, the at least one visible time period calculation interval, the initial orbit elements of the visible time period of the high-orbit communication satellite, and the usage constraint data; and sending the communication instruction sequence to the space segment when the remote sensing satellite overflies the ground station, so that the space segment of the remote sensing satellite determines the visible time period of the remote sensing satellite and the high-orbit communication satellite in the visible time period calculation interval according to the communication instruction sequence.

[0008] The third aspect of the present disclosure provides a visible period determination device for a remote sensing satellite and a high-orbit communication satellite, which is applied to a space segment of the remote sensing satellite. The device comprises: a receiving unit configured to receive a communication instruction sequence sent by a ground station, and parse at least one visible period calculation interval, initial orbit elements of a visible period of the high-orbit communication satellite, and usage constraint data of the high-orbit communication satellite and the remote sensing satellite from the communication instruction sequence; a screening unit configured to screen out screened real-time orbit data from accumulated real-time orbit data of the remote sensing satellite according to the visible period calculation interval; a model determination unit configured to correct an orbit determination model of the remote sensing satellite to obtain a corrected orbit determination model of the remote sensing satellite; a data determination unit configured to process the screened real-time orbit data according to the corrected orbit determination model of the remote sensing satellite to determine initial orbit elements of a visible period of the remote sensing satellite; a first prediction unit configured to determine first corrected orbit prediction data of the remote sensing satellite in the visible period calculation interval according to the initial orbit elements of the visible period of the remote sensing satellite and extrapolation correction coefficients of the remote sensing satellite; a second prediction unit configured to determine second corrected orbit prediction data of the high-orbit communication satellite in the visible period calculation interval according to the initial orbit elements of the visible period of the high-orbit communication satellite and extrapolation correction coefficients of the high-orbit communication satellite; and a calculation unit configured to determine the visible period of the remote sensing satellite and the high-orbit communication satellite in the visible period calculation interval according to the first corrected orbit prediction data, the second corrected orbit prediction data, the radius of the earth, and the usage constraint data.

[0009] The fourth aspect of the present disclosure provides another visible period determination device for a remote sensing satellite and a high-orbit communication satellite, which is applied to a ground segment of the remote sensing satellite. The device comprises: a period determination unit configured to determine a non-business time period during which spaceflight control and measurement services cannot be carried out between the remote sensing satellite and a ground station according to transit ground station data of the remote sensing satellite; an interval determination unit configured to determine at least one visible period calculation interval of the remote sensing satellite and the high-orbit communication satellite according to the non-business time period and a transit area of the remote sensing satellite; an acquisition unit configured to acquire initial orbit elements of a visible period of the high-orbit communication satellite, and usage constraint data of the high-orbit communication satellite and the remote sensing satellite; a generation unit configured to generate a communication instruction sequence based on an instruction template, the at least one visible period calculation interval, the initial orbit elements of the visible period of the high-orbit communication satellite, and the usage constraint data; and a sending unit configured to send the communication instruction sequence to the space segment when the remote sensing satellite transits the ground station, so that the space segment of the remote sensing satellite determines the visible period of the remote sensing satellite and the high-orbit communication satellite in the visible period calculation interval according to the communication instruction sequence.

[0010] The fifth aspect of the present disclosure provides a computer device, which comprises a memory and a processor. The memory stores a computer program, and the processor implements the steps of the method of the first aspect when executing the computer program.

[0011] The sixth aspect of the present disclosure provides a computer readable storage medium, and a computer program is executed by a processor to implement the steps of the method of the first aspect.

[0012] Compared with the prior art, the present disclosure achieves the following technical effects: the present disclosure realizes a visible period on-board autonomous analysis method for remote sensing satellites and high-orbit communication satellites, provides an effective method and basis for inter-satellite remote control, telemetry, image data interaction and on-orbit task planning of remote sensing satellites and high-orbit communication satellites, improves the timeliness of remote sensing satellite and high-orbit communication visible period resource calculation through space segment visible period calculation, provides effective support for inter-satellite communication of remote sensing satellites and high-orbit communication satellites, and the orbit parameters calculated by the space segment are the latest, the visible period analysis result of the remote sensing satellite on-board is more accurate, and the subsequent communication link establishment and maintenance are more reliable. BRIEF DESCRIPTION OF DRAWINGS

[0013] Figure 1 is a flowchart of an embodiment of the remote sensing satellite and high-orbit communication satellite visible period determination method according to the present disclosure;

[0014] Figure 2 is a flowchart of another embodiment of the remote sensing satellite and high-orbit communication satellite visible period determination method according to the present disclosure;

[0015] Figure 3 is a structural schematic diagram of an embodiment of the remote sensing satellite and high-orbit communication satellite visible period determination device according to the present disclosure;

[0016] Figure 4 is a structural schematic diagram of another embodiment of the remote sensing satellite and high-orbit communication satellite visible period determination device according to the present disclosure;

[0017] Figure 5 is a block diagram of an electronic device for implementing the remote sensing satellite and high-orbit communication satellite visible period determination method according to the present disclosure. DETAILED DESCRIPTION

[0018] Unless otherwise clearly indicated, throughout the specification and claims, the term "comprise" or variations such as "comprises" or "comprising" will be understood to imply the inclusion of a stated element or group of elements but not the exclusion of any other element or group of elements.

[0019] The technical solutions of the present application are described below by means of specific examples. It should be understood that one or more steps mentioned in the present application do not exclude other methods and steps before or after the combination steps, or other methods and steps can be inserted between the explicitly mentioned steps. It should also be understood that these examples are only used to illustrate the present application and not to limit the scope of the present application. Unless otherwise specified, the numbering of the steps of each method is only for the purpose of identifying the steps of each method, and is not intended to limit the arrangement order of each method or to limit the scope of the implementation of the present application. Changes or adjustments of the relative relationship can also be considered as the scope of the implementation of the present application without substantial technical content changes.

[0020] The raw materials and instruments used in the examples are not specifically limited in source, and can be purchased on the market or prepared according to conventional methods well known to those skilled in the art.

[0021] In view of the defects in the prior art, the present disclosure provides a remote sensing satellite and high-orbit communication satellite visible period determination method. Figure 1 A flowchart 100 of one embodiment of a remote sensing satellite and high-orbit communication satellite visible period determination method is shown, the remote sensing satellite and high-orbit communication satellite visible period determination method is applied to a remote sensing satellite space segment, and the remote sensing satellite and high-orbit communication satellite visible period determination method comprises the following steps:

[0022] In step 101, a communication instruction sequence sent by a remote sensing satellite ground segment is received, and at least one visible period calculation interval, an initial orbit element of a high-orbit communication satellite visible period, and usage constraint data of the high-orbit communication satellite and the remote sensing satellite are parsed from the communication instruction sequence.

[0023] In this embodiment, the work is implemented by two parts of a remote sensing satellite space segment and a remote sensing satellite ground segment. The ground segment completes the editing, generation and instruction uploading of the communication instruction sequence of the visible period. The space segment completes the orbit determination of the remote sensing satellite, the orbit prediction of the remote sensing satellite and the high-orbit communication satellite, the vector calculation coordinate system conversion, and the visible period on-board autonomous analysis of the remote sensing satellite and the high-orbit communication satellite.

[0024] In this embodiment, the remote sensing satellite ground segment determines the visible period calculation interval of the remote sensing satellite in combination with the comprehensive consideration of the remote sensing satellite transit area. This interval can be one or multiple time periods.

[0025] In this embodiment, the initial orbit six elements of the high-orbit communication satellite visible period are the latest six elements of the high-orbit communication satellite, and the initial orbit six elements of the high-orbit communication satellite visible period are also the latest orbit six elements that can be obtained by the remote sensing satellite operation control system when generating the visible period calculation instruction sequence, which are used for orbit prediction calculation of the high-orbit communication satellite. Since the high-orbit communication satellite is not within the scope of the remote sensing satellite ground segment management, the latest six element information needs to be provided by the high-orbit communication satellite owner or custodian.

[0026] In this embodiment, the satellite usage constraint data mainly includes satellite energy and constraints during the development of related businesses. For a remote sensing satellite, the usage constraint data mainly includes the working distance of the inter-satellite communication link, the frequency band used by two satellites for communication, and the direction angle limitation (azimuth and elevation scanning range) of the remote sensing satellite inter-satellite communication relay antenna, the remote sensing satellite orbit determination model correction coefficient, the remote sensing satellite extrapolation correction coefficient, etc. For the usage constraint of a high-orbit communication satellite, in addition to the above-mentioned content, there are also related information of a tracking beam (the beam angle and beam width of a traditional communication system satellite are relatively fixed, and for a high-orbit communication satellite of a point beam system, the related information of each beam angle and beam width of a usable beam relay needs to be provided), and a high-orbit communication satellite extrapolation correction coefficient.

[0027] Step 102: According to the visible period calculation interval, the real-time orbit data accumulated by the remote sensing satellite is screened to obtain screened real-time orbit data.

[0028] In this embodiment, the remote sensing satellite space segment finds the data closest to the start time in the visible period calculation interval and available from the real-time orbit data accumulated by the remote sensing satellite according to the visible period calculation interval, and the available data is the screened real-time orbit data.

[0029] Step 103: The orbit determination model of the remote sensing satellite is corrected to obtain a corrected orbit determination model of the remote sensing satellite. In this embodiment, during the operation of the remote sensing satellite, due to the influence of various factors such as atmospheric resistance, non-uniformity of the earth's gravitational field, and solar pressure, the actual operation orbit of the remote sensing satellite will deviate from the theoretical orbit. Considering various force conditions of the remote sensing satellite, the low-orbit satellite usage constraint condition is uploaded by the remote sensing satellite ground segment to correct the orbit determination model coefficient of the remote sensing satellite, so as to determine the corrected orbit determination model of the remote sensing satellite.

[0030] Step 104: According to the corrected orbit determination model of the remote sensing satellite, the screened real-time orbit data is processed to determine the initial orbit six elements of the remote sensing satellite visible period.

[0031] In this embodiment, the low-orbit remote satellite space segment can carry out real-time orbiting of the remote sensing satellite through a precise orbiting program based on telemetry data accumulation and remote sensing satellite orbiting model correction. The remote sensing satellite visible period initial orbit six parameters are a set of parameters describing the position and speed of the spacecraft in space. The remote sensing satellite visible period initial orbit six parameters include semi-major axis, eccentricity, orbit inclination, ascending node right ascension, perigee amplitude angle and true anomaly angle. The six parameters can completely determine the orbit of a spacecraft.

[0032] In this embodiment, the step 104 includes the following sub-steps: a first sub-step of calculating instantaneous parameters; the position (X, Y, Z) and speed (V X ,V Y ,V Z ) of the remote sensing satellite. The six parameters are converted into six parameters by orbit mechanics formula. For example,

[0033] Angular momentum vector: h = r x v, module length h = | | h | |.

[0034] Orbit inclination: i = arccos (h z / h). (The orbit inclination i is determined by the Z component of the angular momentum h).

[0035] Ascending node right ascension: Ω = arctan2 (h y , h x ). (The ascending node right ascension Ω is determined by the projection direction of h in the XY plane).

[0036] Eccentricity vector: , module length e = | | e | |.

[0037] Perigee amplitude angle: , where N is the ascending node direction vector.

[0038] True anomaly angle: .

[0039] The second sub-step is to convert the instantaneous orbit parameters (considering the perturbation) into flat roots (average orbit parameters), which is essentially to extract the long-term average characteristics of the orbit by eliminating short-period perturbation terms (such as periodic changes caused by the Earth's oblateness J2 term, short-period disturbances of the sun and the moon, etc.).

[0040] Specifically, first, the instantaneous elements are inputted, which assumes that the instantaneous orbital elements at time t are known: (a(t), e(t), i(t), Omega(t), omega(t), nu(t)) or position and velocity vectors (r, v), which need to be converted into the instantaneous elements first. Second, the perturbation types are identified: short-period terms (period < T orbit): periodic oscillations of omega and M caused by J2 term, high-frequency disturbances of solar radiation pressure. Long-period terms (period > T orbit: long-term drifts of Omega and omega). Long-term terms (linearly vary with time: long-term decay of semi-major axis due to atmospheric drag). Third, the short-period terms are removed, which can be done by numerical averaging: average each element over multiple orbital periods to filter out high-frequency oscillations. Analytical method: directly strip the short-period terms using perturbation theory formulas (perturbation model needs to be known). Finally, the mean elements are constructed.

[0041] In step 105, the first modified orbit prediction data of the remote sensing satellite in the visible period calculation interval is determined according to the initial orbit six elements of the remote sensing satellite in the visible period and the extrapolation correction coefficient of the remote sensing satellite.

[0042] In this embodiment, the extrapolation correction coefficient of the remote sensing satellite can be the pre-stored correction coefficient of the remote sensing satellite in the space segment, and the extrapolation correction coefficient of the remote sensing satellite can be the extrapolation correction coefficient provided by the ground segment of the remote sensing satellite.

[0043] In this embodiment, the initial orbit six elements of the remote sensing satellite in the visible period are obtained after precise orbit determination, the orbit prediction of the remote sensing satellite is performed by a numerical extrapolation method and an integrator, the prediction result of the remote sensing satellite is obtained, and then the prediction result of the orbit of the remote sensing satellite is corrected according to the extrapolation correction coefficient (coefficient obtained based on atmospheric drag, solar radiation pressure, etc.), to obtain the first modified orbit prediction data.

[0044] In step 106, the second modified orbit prediction data of the high-orbit communication satellite in the visible period calculation interval is determined according to the initial orbit six elements of the high-orbit communication satellite in the visible period and the extrapolation correction coefficient of the high-orbit communication satellite.

[0045] In this embodiment, the initial orbit six elements of the high-orbit communication satellite in the visible period are obtained after precise orbit determination, the orbit prediction of the high-orbit communication satellite is performed by a numerical extrapolation method and an integrator, the prediction result of the high-orbit communication satellite is obtained, and then the prediction result of the orbit of the high-orbit communication satellite is corrected according to the extrapolation correction model coefficient (coefficient obtained based on atmospheric drag, solar radiation pressure, etc.), to obtain the second modified orbit prediction data.

[0046] In step 107, the visible period of the remote sensing satellite and the high-orbit communication satellite in the visible period calculation interval is determined according to the first modified orbit prediction data, the second modified orbit prediction data, the radius of the earth and the use constraint data.

[0047] In the embodiment, the first modified orbit prediction data (including the time stamp of the remote sensing satellite, corresponding orbit information, satellite speed, position, and vector parameters) in the visible period calculation interval is intercepted.

[0048] The second modified orbit prediction data (including the time stamp of the high-orbit communication satellite, corresponding satellite speed, position, and vector parameters) in the visible period calculation interval is intercepted.

[0049] In the embodiment, after the parameters of the remote sensing satellite and the high-orbit communication satellite are calculated, the satellite vectors in the visible period calculation interval are screened according to the formula to determine whether they are visible, and the on-board autonomous analysis of the visible period of the remote sensing satellite and the high-orbit communication satellite is completed.

[0050] The method for determining the visible period of the remote sensing satellite and the high-orbit communication satellite provided by the present disclosure realizes the on-board autonomous analysis method for the visible period of the remote sensing satellite and the high-orbit communication satellite, provides an effective method and basis for the inter-satellite remote control, telemetry, image data interaction, and on-orbit task planning of the remote sensing satellite and the high-orbit communication satellite, improves the timeliness of the visible period resource calculation of the remote sensing satellite and the high-orbit communication satellite through the space segment, provides effective support for the inter-satellite communication of the remote sensing satellite and the high-orbit communication satellite, and the orbit parameters calculated by the space segment are the latest, the result of the visible period analysis on the remote sensing satellite is more accurate, and the subsequent communication link establishment and maintenance are more reliable.

[0051] In some optional implementations of the present disclosure, the first modified orbit prediction data of the remote sensing satellite in the visible period calculation interval is determined according to the initial orbit six elements of the remote sensing satellite in the visible period and the extrapolation correction coefficient of the remote sensing satellite, including: at least one preset time is set in the visible period calculation interval; the time corresponding to the initial orbit six elements of the remote sensing satellite in the visible period is taken as the first epoch time; for any preset time, the mean anomaly of the remote sensing satellite at the preset time is determined according to the time difference between the preset time and the first epoch time and the initial orbit six elements of the remote sensing satellite in the visible period; the eccentric anomaly of the remote sensing satellite at the preset time is determined based on the mean anomaly of the remote sensing satellite at the preset time; the true anomaly of the remote sensing satellite at the preset time is determined according to the eccentric anomaly of the remote sensing satellite at the preset time; the orbit coordinate system position of the remote sensing satellite at the preset time is determined according to the true anomaly of the remote sensing satellite at the preset time; the orbit coordinate system modified position of the remote sensing satellite at the preset time is determined by correcting the orbit coordinate system position of the remote sensing satellite at the preset time according to the extrapolation correction coefficient of the remote sensing satellite; and the orbit coordinate system modified positions of the remote sensing satellite at all preset times are taken as the first modified orbit prediction data.

[0052] In the optional implementation, the mean anomaly is an angle of an object on an orbit relative to a center point on an auxiliary circle, which is different from other anomalies in measurement, and the mean anomaly is linearly related to time.

[0053] In the optional implementation, the eccentric anomaly is an angle between a position of a celestial body on an orbit projected on a circumscribed circle perpendicular to an ellipse semi-major axis and a direction of a perigee.

[0054] In the optional implementation, the mean anomaly can be used to determine the eccentric anomaly of the remote sensing satellite at the preset time by solving the Kepler equation.

[0055] In the optional implementation, the true anomaly refers to an angle swept by a celestial body along an orbit when the celestial body moves from a perigee, and is an angle between an orbit perigee and a position vector of the satellite at a certain time.

[0056] The method for determining the first corrected orbit prediction data provided by the present disclosure comprises the following steps: setting at least one preset time in a visible period calculation interval; taking a time corresponding to an initial orbit six-element of the remote sensing satellite as a first ephemeris time; for any preset time, determining a mean anomaly of the remote sensing satellite at the preset time according to a time difference between the preset time and the first ephemeris time and the initial orbit six-element of the remote sensing satellite; determining an eccentric anomaly of the remote sensing satellite at the preset time based on the mean anomaly; determining a true anomaly of the remote sensing satellite at the preset time according to the eccentric anomaly; determining an orbit coordinate system position of the remote sensing satellite at the preset time according to the true anomaly; correcting the orbit coordinate system position of the remote sensing satellite at the preset time according to an extrapolation correction coefficient of the remote sensing satellite to determine an orbit coordinate system corrected position of the remote sensing satellite at the preset time; and taking the orbit coordinate system corrected positions of the remote sensing satellite at all preset times as the first corrected orbit prediction data.

[0057] In some optional implementations of the present disclosure, the method for determining the second modified orbit prediction data of the high-orbit communication satellite according to the initial orbit six elements of the high-orbit communication satellite in the visible period and the extrapolation correction coefficient of the high-orbit communication satellite comprises: taking the time corresponding to the initial orbit six elements of the high-orbit communication satellite in the visible period as the second epoch time; for any preset time, determining the mean anomaly of the high-orbit communication satellite at the preset time according to the time difference between the preset time and the second epoch time and the initial orbit six elements of the high-orbit communication satellite in the visible period; determining the eccentric anomaly of the high-orbit communication satellite at the preset time based on the mean anomaly of the high-orbit communication satellite at the preset time; determining the true anomaly of the high-orbit communication satellite at the preset time according to the eccentric anomaly of the high-orbit communication satellite at the preset time; determining the orbit coordinate system position of the high-orbit communication satellite at the preset time according to the true anomaly of the high-orbit communication satellite at the preset time; correcting the orbit coordinate system position of the high-orbit communication satellite at the preset time according to the extrapolation correction coefficient of the high-orbit communication satellite to determine the corrected orbit coordinate system position of the high-orbit communication satellite at the preset time; and taking the corrected orbit coordinate system positions of the high-orbit communication satellite at all preset times as the second modified orbit prediction data.

[0058] The method for determining the second modified orbit prediction data provided by the optional implementation improves the reliability and accuracy of the second modified orbit prediction data by correcting the orbit coordinate system position based on the initial orbit six elements of the high-orbit communication satellite in the visible period and the extrapolation correction of the high-orbit communication satellite.

[0059] In some optional implementations of the present disclosure, the method for determining the visible period of the remote sensing satellite and the high-orbit communication satellite in the visible period calculation interval according to the first modified orbit prediction data, the second modified orbit prediction data, the radius of the earth and the use constraint data comprises: converting the first modified orbit prediction data into first vector data in the geocentric inertial coordinate system; converting the second modified orbit prediction data into second vector data in the geocentric inertial coordinate system; and determining the visible period of the remote sensing satellite and the high-orbit communication satellite in the visible period calculation interval according to the first vector data, the second vector data, the radius of the earth and the use constraint data.

[0060] In the optional implementation, the vector of the remote sensing satellite in the visible period calculation interval is converted in the coordinate system. In general, the cumulative real-time orbit data of the remote sensing satellite is vector data in the WGS84 coordinate system, and the orbit prediction (extrapolation result) of the remote sensing satellite is also vector data in the WGS84 coordinate system. This data cannot be directly used for screening the visible period of the remote sensing satellite and the high-orbit communication satellite. It must be converted into vector values in the geocentric inertial coordinate system (WGS84 coordinate system→geocentric and fixed coordinate system→geocentric inertial coordinate system), i.e. the first vector data.

[0061] In the optional implementation, the high-orbit communication satellite vector in the visible arc segment calculation interval is converted in the coordinate system, and in general cases, the orbit prediction (extrapolation result) of the high-orbit communication satellite is a vector data in the WGS84 coordinate system. This data cannot be directly used for screening of the visible arc segment of the remote sensing satellite and the high-orbit communication satellite, and must be converted into a vector value in the geocentric inertial coordinate system (WGS84 coordinate system→geocentric geodetic coordinate system→geocentric inertial coordinate system), that is, the second vector data.

[0062] In the optional implementation, the modified position of the satellite in the geocentric inertial coordinate system is calculated by formula (1) (1)

[0063] In formula (1), a is the orbit semi-major axis, e is the eccentricity, i is the satellite orbit inclination, ω is the argument of perigee, Ω is the ascending node right ascension, and f is the true anomaly.

[0064] In the optional implementation, the first modified orbit prediction data is converted into the first vector data in the geocentric inertial coordinate system, the second modified orbit prediction data is converted into the second vector data in the geocentric inertial coordinate system, and the visible time period in the visible time period calculation interval is calculated by using the first vector data and the second vector data, thereby improving the reliability of the visible time period.

[0065] In some optional implementations of the present disclosure, the use constraint data includes the altitude of the high-orbit communication satellite and the distance between the remote sensing satellite and the high-orbit communication satellite, the first vector data includes the modified position of the remote sensing satellite in the geocentric inertial coordinate system at all preset moments, the second vector data includes the modified position of the high-orbit communication satellite in the geocentric inertial coordinate system at all preset moments, and the visible time period of the remote sensing satellite and the high-orbit communication satellite in the visible time period calculation interval is determined according to the first vector data, the second vector data, the Earth radius and the use constraint data, including: for any preset moment, the vector included angle of the remote sensing satellite and the high-orbit communication satellite at the preset moment is determined according to the modified position of the remote sensing satellite in the geocentric inertial coordinate system at the preset moment and the modified position of the high-orbit communication satellite in the geocentric inertial coordinate system at the preset moment; the included angle threshold is determined according to the Earth radius, the altitude of the high-orbit communication satellite and the distance between the remote sensing satellite and the high-orbit communication satellite; whether the remote sensing satellite and the high-orbit communication satellite are visible at the preset moment is detected according to the vector included angle, the included angle threshold, the Earth radius, the altitude of the high-orbit communication satellite and the distance between the remote sensing satellite and the high-orbit communication satellite; in response to detecting that the remote sensing satellite and the high-orbit communication satellite are visible at the preset moment, the preset moment is taken as a visible moment; and the time period composed of continuous visible moments is taken as the visible time period of the remote sensing satellite and the high-orbit communication satellite in the visible time period calculation interval in chronological order.

[0066] In the optional implementation, in the geocentric inertial coordinate system, assuming that [X1Y1Z1] is the position of the high-orbit communication satellite in the geocentric inertial coordinate system, and [X2Y2Z2] is the position of the remote sensing satellite in the geocentric inertial coordinate system, the vector angle between the high-orbit communication satellite-to-ground vector and the high-orbit communication satellite-to-low-orbit satellite vector is The angle is calculated by formula (2)

[0067] (2)

[0068] In the optional implementation, the angle threshold is σ 0 can be determined by the earth radius and the orbit height of the high-orbit communication satellite, and let

[0069] σ 0 = sin -1 ( Re / ( Re + H 1))(3)

[0070] In formula (3), Re is the earth radius, and H1 is the orbit height of the high-orbit communication satellite.

[0071] The method for determining the visible period in the visible period calculation interval provided by the optional implementation first determines the vector angle between the remote sensing satellite and the high-orbit communication satellite at each preset time at the preset time, and then determines the angle threshold. According to the vector angle, the angle threshold, the earth radius, the height of the high-orbit communication satellite, and the distance between the remote sensing satellite and the high-orbit communication satellite, it is detected whether the remote sensing satellite and the high-orbit communication satellite are visible at the preset time. In response to detecting that the remote sensing satellite and the high-orbit communication satellite are visible at the preset time, the preset time is taken as the visible time. According to the time sequence, the period composed of continuous visible times is taken as the visible period of the remote sensing satellite and the high-orbit communication satellite in the visible period calculation interval. A reliable implementation is provided for obtaining the visible period of the remote sensing satellite and the high-orbit communication satellite in the visible period calculation interval, and the reliability of obtaining the visible period is improved.

[0072] In some optional implementations of this disclosure, the above-mentioned detection of whether the remote sensing satellite and the high-orbit communication satellite are visible at a preset time based on the vector angle, angle threshold, Earth radius, altitude of the high-orbit communication satellite, and distance between the remote sensing satellite and the high-orbit communication satellite includes: determining that the remote sensing satellite and the high-orbit communication satellite are visible at the preset time in response to detecting that the absolute value of the vector angle is greater than or equal to the angle threshold; determining that the remote sensing satellite and the high-orbit communication satellite are visible at the preset time in response to detecting that the absolute value of the vector angle is less than the angle threshold and the distance between the remote sensing satellite and the high-orbit communication satellite is less than the sum of Earth radius and altitude of the high-orbit communication satellite; and determining that the remote sensing satellite and the high-orbit communication satellite are not visible at the preset time in response to detecting that the absolute value of the vector angle is less than the angle threshold and the distance between the remote sensing satellite and the high-orbit communication satellite is greater than or equal to the sum of Earth radius and altitude of the high-orbit communication satellite.

[0073] In this optional implementation, the distance between the remote sensing satellite and the high-orbit communication satellite is L. The visibility of the remote sensing satellite to the high-orbit communication satellite is classified as follows: It is visible to remote sensing satellites and high-orbit communication satellites; And L < (R) e +H1), visible to remote sensing satellites and high-orbit communication satellites; And L > (R) e +H1), remote sensing satellites and high-orbit communication satellites are not visible.

[0074] The optional implementation provides a method for detecting whether remote sensing satellites and high-orbit communication satellites are visible at a preset time. This method improves the reliability of the visibility detection of remote sensing satellites and high-orbit communication satellites at a preset time by comparing the absolute value of the vector angle and the angle threshold, as well as the sum of the distance between the remote sensing satellite and the high-orbit communication satellite and the Earth's radius and the altitude of the high-orbit communication satellite.

[0075] This disclosure provides another embodiment of a method for determining the visible time periods of remote sensing satellites and high-orbit communication satellites. Figure 2 The flowchart 200 illustrates another embodiment of the method for determining the visible time period of remote sensing satellites and high-orbit communication satellites. This method is applied to the ground segment of a remote sensing satellite and includes the following steps:

[0076] Step 201: Based on the data from the ground stations passing over the remote sensing satellite, determine the non-operational time periods when aerospace telemetry, control, and data transmission services cannot be carried out between the remote sensing satellite and the ground stations.

[0077] In the embodiment, the ground segment of the remote sensing satellite determines a time period in which the satellite cannot carry out telemetry, remote control and data transmission services with the ground station according to the situation of the remote sensing satellite passing the ground station, and the time period constitutes a visible period calculation interval. Specifically, a non-service time period in which space measurement and control and data transmission services cannot be carried out is determined first, and a visible period calculation interval in which the visible period can be calculated is determined through the non-service time period.

[0078] In step 202, at least one visible period calculation interval of the remote sensing satellite and the high-orbit communication satellite is determined according to the non-service time period and the passing area of the remote sensing satellite.

[0079] In the embodiment, in the passing area of the remote sensing satellite, all working time periods of the remote sensing satellite are determined, the non-service time period in which space measurement and control services such as telemetry, remote control and data transmission cannot be carried out is removed from the working time period, and at least one visible period calculation interval of the remote sensing satellite and the high-orbit communication satellite is obtained.

[0080] In step 203, initial orbit six elements of the high-orbit communication satellite visible period, and usage constraint data of the high-orbit communication satellite and the remote sensing satellite are obtained.

[0081] In the embodiment, the latest six elements of the high-orbit communication satellite refer to the latest orbit six elements of the high-orbit communication satellite that can be obtained by the remote sensing satellite operation and control system when generating the visible period calculation instruction sequence, and the elements are used for orbit prediction calculation of the high-orbit communication satellite. Since the high-orbit communication satellite is not within the management scope of the remote sensing satellite ground segment, the six element information needs to be provided by the high-orbit communication satellite owner or custodian.

[0082] In the embodiment, the satellite usage constraints mainly include satellite energy and constraints when related services are carried out. For the remote sensing satellite, the main constraints are the working distance of the inter-satellite communication link, the frequency band used for communication between the two satellites, and the direction angle limitation (azimuth and elevation scanning range) of the relay antenna of the remote sensing satellite, the orbit determination model correction coefficient of the remote sensing satellite, the extrapolation correction coefficient of the remote sensing satellite, etc. For the usage constraints of the high-orbit communication satellite, in addition to the above-mentioned contents, there are also related information of the tracking beam (the beam angle and beam width of the traditional communication system satellite are relatively fixed, and for the high-orbit communication satellite of the point beam system, the related information such as the beam angle and beam width of each beam that can be used for beam relay needs to be provided), and the extrapolation correction coefficient of the high-orbit communication satellite.

[0083] In step 204, a communication instruction sequence is generated based on the instruction template, at least one visible period calculation interval, the initial orbit six elements of the high-orbit communication satellite visible period, and the usage constraint data.

[0084] In this embodiment, the remote sensing satellite ground station includes a remote sensing satellite ground operation and control system, etc. The at least one visible period calculation interval, the high-orbit communication satellite visible period initial orbit six elements and the use constraint data are input into the remote sensing satellite ground operation and control system. The ground operation and control system will edit the preset instruction template according to the input related parameters, generate the corresponding communication instruction sequence, and then check the communication instruction sequence. After the checking is completed, the ground operation and control system generates the "communication instruction sequence" for the remote sensing satellite, and completes the instruction uploading through the remote sensing satellite transit ground station.

[0085] Optionally, when the remote sensing satellite ground operation and control system generates the corresponding communication instruction sequence, the remote sensing satellite orbit determination model correction coefficient, the remote sensing satellite extrapolation correction coefficient, the high-orbit communication satellite extrapolation correction coefficient, the at least one visible period calculation interval, the high-orbit communication satellite visible period initial orbit six elements and the use constraint data are also used to edit the instruction template to obtain the communication instruction sequence.

[0086] In step 205, when the remote sensing satellite transits the ground station, the communication instruction sequence is sent to the remote sensing satellite space segment, so that the remote sensing satellite space segment determines the visible period of the remote sensing satellite and the high-orbit communication satellite in the visible period calculation interval according to the communication instruction sequence.

[0087] In this embodiment, the above step 205 includes: according to the communication instruction sequence, the communication instruction sequence is sent to the remote sensing satellite space segment, the instruction uploading of the remote sensing satellite is completed, so that the remote sensing satellite receives the communication instruction sequence sent by the remote sensing satellite ground station, and parses at least one visible period calculation interval, high-orbit communication satellite visible period initial orbit six elements and use constraint data from the communication instruction sequence, and determines the visible period of the remote sensing satellite and the high-orbit communication satellite in the visible period calculation interval through the remote sensing satellite and the high-orbit communication satellite visible period determination method shown in Figure 1 The remote sensing satellite and the high-orbit communication satellite visible period determination method shown in

[0088] The remote sensing satellite and the high-orbit communication satellite visible period determination method provided by the present disclosure does not need to upload the remote sensing satellite ground segment calculation process parameters and a large number of control instructions through the ground station, reduces the dependence on the remote sensing satellite ground station, thereby reducing the data transmission link pressure and improving the autonomy and flexibility of the system.

[0089] Further referring to Figure 3 , as an implementation of the method shown in the above figures, the present disclosure provides an embodiment of a remote sensing satellite and high-orbit communication satellite visible period determination device. The device is applied to a remote sensing satellite space segment. The device embodiment corresponds to the method embodiment shown in Figure 1 The device can be applied to various electronic devices.

[0090] Figure 3As shown, the remote sensing satellite and high-orbit communication satellite visible period determination apparatus 300 provided by the embodiment includes a receiving unit 301, a screening unit 302, a model determination unit 303, a data determination unit 304, a first prediction unit 305, a second prediction unit 306, and a calculation unit 307. The receiving unit 301 can be configured to receive a communication instruction sequence sent by a ground segment of a remote sensing satellite, and parse at least one visible period calculation interval, initial orbit six elements of a high-orbit communication satellite visible period, and usage constraint data of the high-orbit communication satellite and the remote sensing satellite from the communication instruction sequence. The screening unit 302 can be configured to screen screening real-time orbit data from real-time orbit data accumulated by the remote sensing satellite according to the visible period calculation interval. The model determination unit 303 can be configured to correct an orbit determination model of the remote sensing satellite to obtain a corrected orbit determination model of the remote sensing satellite. The data determination unit 304 can be configured to process the screening real-time orbit data according to the corrected orbit determination model of the remote sensing satellite to determine initial orbit six elements of a remote sensing satellite visible period. The first prediction unit 305 can be configured to determine first corrected orbit prediction data of the remote sensing satellite in the visible period calculation interval according to the initial orbit six elements of the remote sensing satellite visible period and extrapolation correction coefficients of the remote sensing satellite. The second prediction unit 306 can be configured to determine second corrected orbit prediction data of the high-orbit communication satellite in the visible period calculation interval according to the initial orbit six elements of the high-orbit communication satellite visible period and extrapolation correction coefficients of the high-orbit communication satellite. The calculation unit 307 can be configured to determine a visible period of the remote sensing satellite and the high-orbit communication satellite in the visible period calculation interval according to the first corrected orbit prediction data, the second corrected orbit prediction data, the radius of the earth, and the usage constraint data.

[0091] In the embodiment, the specific processing of the receiving unit 301, the screening unit 302, the model determination unit 303, the data determination unit 304, the first prediction unit 305, the second prediction unit 306, and the calculation unit 307 in the remote sensing satellite and high-orbit communication satellite visible period determination apparatus 300 and the technical effects brought by the specific processing can be respectively referred to the corresponding processing of the receiving unit 301, the screening unit 302, the model determination unit 303, the data determination unit 304, the first prediction unit 305, the second prediction unit 306, and the calculation unit 307 and the technical effects brought by the specific processing in the corresponding embodiment. Figure 1 The related description of the steps 101, 102, 103, 104, 105, 106, and 107 in the corresponding embodiment will not be repeated here.

[0092] In some embodiments of the present disclosure, the first prediction unit 305 is configured to: set at least one preset time point within the visible period calculation interval; take the time corresponding to the initial orbit six elements of the remote sensing satellite as a first epoch time; for any preset time point, determine the mean anomaly of the remote sensing satellite at the preset time point according to the time difference between the preset time point and the first epoch time and the initial orbit six elements of the remote sensing satellite; determine the eccentric anomaly of the remote sensing satellite at the preset time point based on the mean anomaly of the remote sensing satellite at the preset time point; determine the true anomaly of the remote sensing satellite at the preset time point according to the eccentric anomaly of the remote sensing satellite at the preset time point; determine the position of the remote sensing satellite in the orbit coordinate system at the preset time point according to the true anomaly of the remote sensing satellite at the preset time point; correct the position of the remote sensing satellite in the orbit coordinate system at the preset time point according to the extrapolation correction coefficient of the remote sensing satellite, to determine the corrected position of the remote sensing satellite in the orbit coordinate system at the preset time point; and take the corrected positions of the remote sensing satellite in the orbit coordinate system at all preset time points as the first corrected orbit prediction data.

[0093] In some embodiments of the present disclosure, the second prediction unit 306 is configured to: take the time corresponding to the initial orbit six elements of the high-orbit communication satellite as a second epoch time; for any preset time point, determine the mean anomaly of the high-orbit communication satellite at the preset time point according to the time difference between the preset time point and the second epoch time and the initial orbit six elements of the high-orbit communication satellite; determine the eccentric anomaly of the high-orbit communication satellite at the preset time point based on the mean anomaly of the high-orbit communication satellite at the preset time point; determine the true anomaly of the high-orbit communication satellite at the preset time point according to the eccentric anomaly of the high-orbit communication satellite at the preset time point; determine the position of the high-orbit communication satellite in the orbit coordinate system at the preset time point according to the true anomaly of the high-orbit communication satellite at the preset time point; correct the position of the high-orbit communication satellite in the orbit coordinate system at the preset time point according to the extrapolation correction coefficient of the high-orbit communication satellite, to determine the corrected position of the high-orbit communication satellite in the orbit coordinate system at the preset time point; and take the corrected positions of the high-orbit communication satellite in the orbit coordinate system at all preset time points as the second corrected orbit prediction data.

[0094] In some optional implementations of the present disclosure, the calculation unit 307 is configured to: convert the first corrected orbit prediction data into first vector data in the geocentric inertial coordinate system; convert the second corrected orbit prediction data into second vector data in the geocentric inertial coordinate system; and determine the visible period of the remote sensing satellite and the high-orbit communication satellite within the visible period calculation interval according to the first vector data, the second vector data, the radius of the Earth and the use constraint data.

[0095] In some optional implementations of the present disclosure, the use constraint data includes: an altitude of the high-orbit communication satellite, and a distance between the remote sensing satellite and the high-orbit communication satellite; the first vector data includes: the corrected positions of the remote sensing satellite in the geocentric inertial coordinate system at all preset time instants; the second vector data includes: the corrected positions of the high-orbit communication satellite in the geocentric inertial coordinate system at all preset time instants; the calculation unit 307 is further configured to: for any preset time instant, determine a vector included angle between the remote sensing satellite and the high-orbit communication satellite at the preset time instant according to the corrected position of the remote sensing satellite in the geocentric inertial coordinate system at the preset time instant and the corrected position of the high-orbit communication satellite in the geocentric inertial coordinate system at the preset time instant; determine an included angle threshold according to the Earth radius, the altitude of the high-orbit communication satellite, and the distance between the remote sensing satellite and the high-orbit communication satellite; detect whether the remote sensing satellite and the high-orbit communication satellite are visible at the preset time instant according to the vector included angle, the included angle threshold, the Earth radius, the altitude of the high-orbit communication satellite, and the distance between the remote sensing satellite and the high-orbit communication satellite; in response to detecting that the remote sensing satellite and the high-orbit communication satellite are visible at the preset time instant, take the preset time instant as a visible time instant; and in time sequence, take a time period composed of consecutive visible time instants as a visible time period of the remote sensing satellite and the high-orbit communication satellite in a visible time period calculation interval.

[0096] In some optional implementations of the present disclosure, the calculation unit 307 is further configured to: in response to detecting that the absolute value of the vector included angle is greater than or equal to the included angle threshold, determine that the remote sensing satellite and the high-orbit communication satellite are visible at the preset time instant; in response to detecting that the absolute value of the vector included angle is less than the included angle threshold and the distance between the remote sensing satellite and the high-orbit communication satellite is less than the sum of the Earth radius and the altitude of the high-orbit communication satellite, determine that the remote sensing satellite and the high-orbit communication satellite are visible at the preset time instant; and in response to detecting that the absolute value of the vector included angle is less than the included angle threshold and the distance between the remote sensing satellite and the high-orbit communication satellite is greater than or equal to the sum of the Earth radius and the altitude of the high-orbit communication satellite, determine that the remote sensing satellite and the high-orbit communication satellite are invisible at the preset time instant.

[0097] In the remote sensing satellite and high-orbit communication satellite visible time period determination device provided by the embodiments of the present disclosure, the on-orbit autonomous analysis method for the visible time period of the remote sensing satellite and the high-orbit communication satellite is implemented, which provides an effective method and basis for the inter-satellite remote sensing, remote control, telemetry, image data interaction, and on-orbit task planning of the remote sensing satellite and the high-orbit communication satellite; the visible time period is calculated by the space segment, which improves the timeliness of the visible time period resource calculation of the remote sensing satellite and the high-orbit communication satellite, and provides effective support for the inter-satellite communication of the remote sensing satellite and the high-orbit communication satellite; the orbit parameters calculated by the space segment are the latest, the result of the visible time period analysis on the remote sensing satellite is more accurate, and the subsequent communication link establishment and maintenance are more reliable.

[0098] Further reference is made to Figure 4As an implementation of the method shown in the above figures, the disclosure provides another embodiment of a remote sensing satellite and high-orbit communication satellite visible period determination device, which is applied to a ground segment of a remote sensing satellite, and corresponds to the method embodiment shown in Figure 2 The device can be specifically applied to various electronic devices.

[0099] Figure 4 As shown in the figure, the embodiment provides a remote sensing satellite and high-orbit communication satellite visible period determination device 400, which includes a period determination unit 401, an interval determination unit 402, an acquisition unit 403, a generation unit 404, and a sending unit 405. The period determination unit 401 can be configured to determine a non-business time period in which spaceflight control business cannot be carried out between a remote sensing satellite and a ground station according to transit ground station data of the remote sensing satellite. The interval determination unit 402 can be configured to determine at least one visible period calculation interval of the remote sensing satellite and a high-orbit communication satellite according to the non-business time period and a transit area of the remote sensing satellite. The acquisition unit 403 can be configured to acquire high-orbit communication satellite visible period initial orbit elements, and usage constraint data of the high-orbit communication satellite and the remote sensing satellite. The generation unit 404 can be configured to generate a communication instruction sequence based on an instruction template, the at least one visible period calculation interval, the high-orbit communication satellite visible period initial orbit elements, and the usage constraint data. The sending unit 405 can be configured to send the communication instruction sequence to a space segment when the remote sensing satellite transits the ground station, so that the space segment determines a visible period of the remote sensing satellite and the high-orbit communication satellite in the visible period calculation interval according to the communication instruction sequence.

[0100] In the embodiment, the specific processing of the period determination unit 401, the interval determination unit 402, the acquisition unit 403, the generation unit 404, and the sending unit 405 in the remote sensing satellite and high-orbit communication satellite visible period determination device 400 and the technical effects brought by the specific processing can be respectively referred to the related description of the steps 201, 202, 203, 204, and 205 in the corresponding embodiment. Figure 2 The related description of the steps 201, 202, 203, 204, and 205 in the corresponding embodiment will not be repeated here.

[0101] According to the embodiments of the disclosure, the disclosure further provides an electronic device, a readable storage medium, and a computer program product.

[0102] Figure 5A schematic block diagram of an example electronic device 500 that can be used to implement embodiments of the present disclosure is shown. The electronic device is intended to represent various forms of digital computers, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device may also represent various forms of mobile devices, such as personal digital processors, cellular phones, smartphones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their patterns are merely examples and are not intended to limit the implementations of the present disclosure described and / or claimed herein. For methods applied to the space segment of a remote sensing satellite, the electronic device may be an onboard computer located in the space segment of the remote sensing satellite; for methods applied to the ground segment of a remote sensing satellite, the electronic device may be a desktop computer located in the ground segment of the remote sensing satellite.

[0103] like Figure 5 As shown, device 500 includes a computing unit 501, which can perform various appropriate actions and processes based on a computer program stored in read-only memory (ROM) 502 or a computer program loaded from storage unit 508 into random access memory (RAM) 503. RAM 503 may also store various programs and data required for the operation of device 500. The computing unit 501, ROM 502, and RAM 503 are interconnected via bus 504. Input / output (I / O) interface 505 is also connected to bus 504.

[0104] Multiple components in device 500 are connected to I / O interface 505, including: input unit 506, such as keyboard, mouse, etc.; output unit 507, such as various types of monitors, speakers, etc.; storage unit 508, such as disk, optical disk, etc.; and communication unit 509, such as network card, modem, wireless transceiver, etc. Communication unit 509 allows device 500 to exchange information / data with other devices through computer networks such as the Internet and / or various telecommunications networks.

[0105] The computing unit 501 can be various general and / or special purpose processing components with processing and computing capabilities. Some examples of the computing unit 501 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various specialized artificial intelligence (AI) computing chips, various computing units running machine learning model algorithms, a digital signal processor (DSP), and any appropriate processor, controller, microcontroller, and the like. The computing unit 501 performs various methods and processes described above, such as the remote sensing satellite and high-orbit communication satellite visibility period determination method. For example, in some embodiments, the remote sensing satellite and high-orbit communication satellite visibility period determination method can be implemented as a computer software program that is tangibly embodied in a machine-readable medium, such as the storage unit 508. In some embodiments, part or all of the computer program can be loaded and / or installed onto the apparatus 500 via the ROM 502 and / or the communication unit 509. When the computer program is loaded onto the RAM 503 and executed by the computing unit 501, one or more steps of the remote sensing satellite and high-orbit communication satellite visibility period determination method described above can be performed. Alternatively, in other embodiments, the computing unit 501 can be configured to perform the remote sensing satellite and high-orbit communication satellite visibility period determination method by any other appropriate means, such as by means of firmware.

[0106] Various implementations of the systems and techniques described above can be realized in digital electronic circuitry, integrated circuitry, a field programmable gate array (FPGA), an application specific integrated circuit (ASIC), a system on a chip (SOC), a programmable logic device (CPLD), computer hardware, firmware, software, and / or combinations thereof. These various implementations can include implementation in one or more computer programs that are executable and / or interpretable on a programmable system including at least one programmable processor, which can be special or general purpose, coupled to receive data and instructions from, and to transmit data and instructions to, a storage system, at least one input device, and at least one output device.

[0107] Program code for carrying out methods of the present disclosure can be written in any combination of one or more programming languages. The program code can be provided to a general purpose computer, special purpose computer, or other programmable data processing apparatus to produce a machine, such that the program code, when executed by the machine, produces a means for implementing the methods / operations specified in the flowchart diagrams and / or block diagrams. The program code can be executed entirely on a machine, partially on a machine, partially on a machine as a standalone software package, partially on a machine and partially on a remote machine or entirely on a remote machine or server.

[0108] In the context of the present disclosure, a machine-readable medium can be a tangible medium that contains or stores a program for use by or in connection with an instruction execution system, apparatus, or device. The machine-readable medium can be a machine-readable signal medium or a machine-readable storage medium. A machine-readable medium can include but is not limited to an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. More specific examples of the machine-readable storage medium will include one or more lines of electrical connections, portable computer disks, hard disk drives, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or Flash memory), optical fibers, portable compact disc read-only memories (CD-ROMs), optical storage devices, magnetic storage devices, or any suitable combination of the foregoing.

[0109] To provide for interaction with a user, the systems and techniques described here can be implemented on a computer having a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to the user and a keyboard and a pointing device (e.g., a mouse or a trackball) by which the user can provide input to the computer. Other kinds of devices can be used to provide for interaction with a user as well; for example, feedback provided to the user can be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user can be received in any form, including acoustic, speech, or tactile input.

[0110] The systems and techniques described herein can be implemented in a computing system that includes a back end component, e.g., as a data server, or that includes a middleware component, e.g., an application server, or that includes a front end component, e.g., a user computer having a graphical user interface or a Web browser through which a user can interact with an implementation of the systems and techniques described herein, or any combination of such back end, middleware, or front end components. The components of the system can be interconnected by any form or medium of digital data communication, e.g., a communication network. Examples of communication networks include a local area network (LAN), a wide area network (WAN), and the Internet.

[0111] It should be understood that various forms of flow shown above can be re-ordered, added to, or deleted from without departing from the spirit of the present disclosure. For example, the steps recited in the disclosure can be executed in parallel, executed in series, or executed in different orders, as long as the desired results of the technology disclosed in the disclosure are achieved, which is not limited herein.

[0112] The foregoing description of specific exemplary embodiments of the application has been presented for the purposes of illustration and description. It is not intended to be a limitation on the broad concepts disclosed herein. Obviously, many modifications and variations of the specific exemplary embodiments described herein are possible in light of the above teachings. It is intended that the scope of the application be limited only by the broadest interpretation of the appended claims and their equivalents.

Claims

1. A method for determining the visible time period of remote sensing satellites and high-orbit communication satellites, characterized in that, Applied to the space segment of remote sensing satellites, the method includes: Receive a sequence of communication commands sent by the ground segment, and parse at least one visible time period calculation interval, the initial orbital six roots of the visible time period of the high-orbit communication satellite, and the usage constraint data of the high-orbit communication satellite and the remote sensing satellite from the sequence of communication commands; Based on the visible time period, the real-time orbit data is filtered out from the accumulated real-time orbit data of the remote sensing satellite. The orbit determination model of the remote sensing satellite is corrected to obtain the corrected orbit determination model of the remote sensing satellite; Based on the corrected orbit determination model of the remote sensing satellite, the selected real-time orbit data is processed to determine the initial six orbits of the remote sensing satellite during the visible period. Based on the initial orbital six-root number of the remote sensing satellite during the visible period and the extrapolation correction coefficient of the remote sensing satellite, the first corrected orbital prediction data of the remote sensing satellite within the calculation interval of the visible period is determined; Based on the initial six orbital elements of the high-orbit communication satellite during the visible period and the extrapolation correction coefficient of the high-orbit communication satellite, the second corrected orbital prediction data of the high-orbit communication satellite within the calculation interval of the visible period is determined; Based on the first corrected orbit prediction data, the second corrected orbit prediction data, the Earth's radius, and the usage constraint data, the visible time periods of the remote sensing satellite and the high-orbit communication satellite within the visible time period calculation interval are determined.

2. The method according to claim 1, characterized in that, The step of determining the first corrected orbit prediction data of the remote sensing satellite within the calculation interval of the visible period based on the initial orbit six elements of the remote sensing satellite during the visible period and the extrapolation correction coefficient of the remote sensing satellite includes: At least one preset time is set within the visible time period calculation interval; The time corresponding to the initial orbital root number of the remote sensing satellite during the visible period is taken as the first epoch time; For any preset time, the mean apogee angle of the remote sensing satellite at that preset time is determined based on the time difference between the preset time and the first epoch time, and the initial orbital six-axis number of the visible period of the remote sensing satellite. Based on the mean apogee angle of the remote sensing satellite at the preset time, determine the deviated apogee angle of the remote sensing satellite at the preset time; Based on the anomalous angle of the remote sensing satellite at the preset time, determine the true anomalous angle of the remote sensing satellite at the preset time; Based on the true anomaly angle of the remote sensing satellite at the preset time, determine the orbital coordinate system position of the remote sensing satellite at the preset time; Based on the extrapolation correction coefficient of the remote sensing satellite, the orbital coordinate system position of the remote sensing satellite at the preset time is corrected, and the corrected position of the orbital coordinate system of the remote sensing satellite at the preset time is determined. The corrected orbit coordinate system position of the remote sensing satellite at all preset times is used as the first corrected orbit prediction data.

3. The method according to claim 2, characterized in that, The step of determining the second corrected orbit prediction data of the high-orbit communication satellite within the calculation interval of the visible period based on the initial orbital six elements of the high-orbit communication satellite during the visible period and the extrapolation correction coefficient of the high-orbit communication satellite includes: The time corresponding to the initial orbital root number of the visible period of the high-orbit communication satellite is taken as the second epoch time; For any preset time, the mean perihelion angle of the high-orbit communication satellite at that preset time is determined based on the time difference between the preset time and the second epoch time, and the initial orbital six-axis number of the visible period of the high-orbit communication satellite. Based on the mean aperimeter angle of the high-orbit communication satellite at the preset time, the deviated aperimeter angle of the high-orbit communication satellite at the preset time is determined; Based on the anomalous angle of the high-orbit communication satellite at the preset time, determine the true anomalous angle of the high-orbit communication satellite at the preset time; Based on the true anomaly angle of the high-orbit communication satellite at the preset time, determine the orbital coordinate system position of the high-orbit communication satellite at the preset time; Based on the extrapolation correction coefficient of the high-orbit communication satellite, the orbital coordinate system position of the high-orbit communication satellite at the preset time is corrected, and the corrected position of the orbital coordinate system of the high-orbit communication satellite at the preset time is determined. The corrected orbital coordinate system position of the high-orbit communication satellite at all preset times is used as the second corrected orbit prediction data.

4. The method according to claim 3, characterized in that, The step of determining the visible time period of the remote sensing satellite and the high-orbit communication satellite within the visible time period calculation interval based on the first corrected orbit prediction data, the second corrected orbit prediction data, the Earth's radius, and the usage constraint data includes: The first corrected trajectory prediction data is converted into first vector data in the geocentric inertial coordinate system; The second corrected trajectory prediction data is converted into second vector data in the geocentric inertial coordinate system; Based on the first vector data, the second vector data, the Earth's radius, and the usage constraint data, the visible time periods of the remote sensing satellite and the high-orbit communication satellite within the visible time period calculation interval are determined.

5. The method according to claim 4, characterized in that, The usage constraint data includes: the altitude of the high-orbit communication satellite; the first vector data includes: the geocentric inertial coordinate system corrected position of the remote sensing satellite at all preset times; the second vector data includes: the geocentric inertial coordinate system corrected position of the high-orbit communication satellite at all preset times; determining the visible time period of the remote sensing satellite and the high-orbit communication satellite within the visible time period calculation interval based on the first vector data, the second vector data, the Earth's radius, and the usage constraint data includes: For any preset time, based on the corrected position of the remote sensing satellite in the geocentric inertial coordinate system at that preset time and the corrected position of the high-orbit communication satellite in the geocentric inertial coordinate system at that preset time, the vector angle between the remote sensing satellite and the high-orbit communication satellite at that preset time is determined; the vector angle is the angle between the vectors of the remote sensing satellite and the high-orbit communication satellite in the geocentric inertial coordinate system. The included angle threshold is determined based on the Earth's radius, the altitude of the high-orbit communication satellite, and the distance between the remote sensing satellite and the high-orbit communication satellite; Based on the vector angle, the angle threshold, the Earth's radius, the altitude of the high-orbit communication satellite, and the distance between the remote sensing satellite and the high-orbit communication satellite, it is determined whether the remote sensing satellite and the high-orbit communication satellite are visible at the preset time. In response to the detection that the remote sensing satellite and the high-orbit communication satellite are visible at a preset time, the preset time is taken as the visible time; According to the chronological order, the time period consisting of consecutive visible moments is taken as the visible time period of the remote sensing satellite and the high-orbit communication satellite within the visible time period calculation interval.

6. The method according to claim 5, characterized in that, The step of detecting whether the remote sensing satellite and the high-orbit communication satellite are visible at a preset time based on the vector angle, the angle threshold, the Earth's radius, the altitude of the high-orbit communication satellite, and the distance between the remote sensing satellite and the high-orbit communication satellite includes: In response to detecting that the absolute value of the vector angle is greater than or equal to the angle threshold, it is determined that the remote sensing satellite and the high-orbit communication satellite are visible at the preset time; In response to detecting that the absolute value of the vector angle is less than the angle threshold, and that the distance between the remote sensing satellite and the high-orbit communication satellite is less than the sum of the Earth's radius and the altitude of the high-orbit communication satellite, it is determined that the remote sensing satellite and the high-orbit communication satellite are visible at the preset time; In response to detecting that the absolute value of the vector angle is less than the angle threshold, and that the distance between the remote sensing satellite and the high-orbit communication satellite is greater than or equal to the sum of the Earth's radius and the altitude of the high-orbit communication satellite, it is determined that the remote sensing satellite and the high-orbit communication satellite are invisible at that preset time.

7. A method for determining the visible time period of remote sensing satellites and high-orbit communication satellites, characterized in that, Applied to the ground segment of remote sensing satellites, the method includes: Based on the data from the ground stations over which the remote sensing satellite passes, determine the non-operational time periods during which aerospace telemetry and control services cannot be carried out between the remote sensing satellite and the ground stations; Based on the non-operational time period and the transit area of ​​the remote sensing satellite, at least one visible time period calculation interval for the remote sensing satellite and the high-orbit communication satellite is determined. Acquire the initial orbital root count of high-orbit communication satellites during the visible period, and the usage constraint data of high-orbit communication satellites and remote sensing satellites; Based on the instruction template, the calculation interval of at least one visible time period, the initial orbital six-root number of the visible time period of the high-orbit communication satellite, and the usage constraint data, a communication instruction sequence is generated; When the remote sensing satellite passes over the ground station, it sends the communication command sequence to the space segment so that the remote sensing satellite space segment can determine the visible time period of the remote sensing satellite and the high-orbit communication satellite within the visible time period calculation interval based on the communication command sequence.

8. A device for determining the visible time period of remote sensing satellites and high-orbit communication satellites, characterized in that, The device, used in the space segment of remote sensing satellites, includes: The receiving unit is configured to receive a sequence of communication commands sent by the ground segment, and to parse from the sequence of communication commands at least one visible time period calculation interval, the initial orbital six-root number of the visible time period of the high-orbit communication satellite, and the usage constraint data of the high-orbit communication satellite and the remote sensing satellite. The filtering unit is configured to calculate the interval based on the visible time period and filter out the real-time orbit data accumulated by the remote sensing satellite. The model determination unit is configured to correct the orbit determination model of the remote sensing satellite to obtain the corrected orbit determination model of the remote sensing satellite. The data determination unit is configured to process the filtered real-time orbit data according to the modified orbit determination model of the remote sensing satellite, and determine the initial six orbits of the remote sensing satellite during the visible period. The first forecast unit is configured to determine the first corrected orbit forecast data of the remote sensing satellite within the calculation interval of the visible period based on the initial orbit six-root number of the remote sensing satellite during the visible period and the remote sensing satellite extrapolation correction coefficient. The second forecasting unit is configured to determine the second corrected orbit forecast data of the high-orbit communication satellite within the calculation interval of the visible period based on the initial orbit six-root number of the high-orbit communication satellite during the visible period and the extrapolation correction coefficient of the high-orbit communication satellite. The calculation unit is configured to determine the visible time period of the remote sensing satellite and the high-orbit communication satellite within the visible time period calculation interval based on the first corrected orbit prediction data, the second corrected orbit prediction data, the Earth radius, and the usage constraint data.

9. A device for determining the visible time period of remote sensing satellites and high-orbit communication satellites, characterized in that, The device, applied to the ground segment of remote sensing satellites, includes: The time period determination unit is configured to determine, based on the data from the ground station passing over the remote sensing satellite, the non-operational time period during which aerospace telemetry and control services cannot be carried out between the remote sensing satellite and the ground station; The interval determination unit is configured to determine at least one visible time period calculation interval for the remote sensing satellite and the high-orbit communication satellite based on the non-operational time period and the transit area of ​​the remote sensing satellite. The acquisition unit is configured to acquire the initial orbital six-point count of the high-orbit communication satellite during the visible period, as well as the usage constraint data of the high-orbit communication satellite and the remote sensing satellite. The generation unit is configured to generate a sequence of communication instructions based on the instruction template, the at least one visible time period calculation interval, the initial orbital six-root number of the visible time period of the high-orbit communication satellite, and the usage constraint data. The transmitting unit is configured to send the communication command sequence to the space segment when the remote sensing satellite passes over the ground station, so that the remote sensing satellite space segment can determine the visible time period of the remote sensing satellite and the high-orbit communication satellite within the visible time period calculation interval based on the communication command sequence.

10. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the steps of the method according to any one of claims 1 to 7.

11. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 7.

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