Satellite load view field overlapping simulation method, device, equipment and medium

Abstract

The invention provides a satellite load view field overlapping simulation method, device and equipment and a medium. The method comprises the following steps: acquiring epoch orbits and load view field range configuration information corresponding to satellites in a constellation; based on the epoch orbit and the load view field range configuration information, determining the angular point position history corresponding to the satellites in the constellation; any satellite in the constellation is used as a primary satellite, other satellites except the primary satellite in the constellation are used as target satellites, and the overlapping condition between the load view field and the load view field of the primary satellite is determined based on the angular point position history; and determining an overlapping simulation result corresponding to the primary satellite according to the overlapping condition. In order to overcome the defect that professional software is difficult to efficiently extract overlapping time period information, the overlapping simulation result needed for formulating countermeasures is provided in a one-key mode, and the actual application requirements for high-frequency task analysis and on-orbit track and strategy updating are met.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a method, device, equipment and medium for simulating the overlap of satellite payload visual fields. Background Art

[0002] When any two or more satellites in the IoT and Earth communication satellite constellations provide services to the same location on the ground, the satellites use the same beam, which is equivalent to using the same frequency signal, which may interfere with each other and affect the service quality. To prevent this, it is necessary to predict the overlap of the field of view of the communication payloads of each satellite during orbital operation, and design countermeasures based on the overlap period and specific overlap conditions, such as the design of the on / off period of the corresponding beam.

[0003] The industry generally uses general orbit simulation software for coverage analysis. The most commonly used STK (Systems Tool Kit) software is widely applicable to general payload field of view coverage calculations of various types of remote sensing satellites. However, this simulation software is not convenient for directly extracting the ground coverage area and timing data of each satellite communication payload, and then it is difficult to rely on the simulation software to directly obtain simulation data for the formulation of countermeasures. Even if you try to use this software, it often requires manual participation and data post-processing in the simulation data generation process, which places high demands on the technical capabilities and development efficiency of engineering and technical personnel, and it is difficult to meet the actual application needs of high-frequency mission analysis and responding to on-orbit orbits and strategy updates. Summary of the invention

[0004] In view of this, the purpose of the present invention is to provide a satellite payload field of view overlap simulation method, device, equipment and medium. In view of the deficiency that professional software is difficult to efficiently extract overlapping period information, the overlapping simulation results required for formulating countermeasures are provided in a one-click manner, meeting the actual application needs of high-frequency mission analysis and responding to on-orbit trajectory and strategy updates.

[0005] In a first aspect, an embodiment of the present invention provides a satellite payload field of view overlap simulation method, comprising:

[0006] Obtain the epoch orbit and payload field of view configuration information corresponding to the satellites in the constellation;

[0007] Based on the epoch orbit and payload field of view configuration information, determine the corresponding corner point position history of the satellite in the constellation;

[0008] Taking any satellite in the constellation as the primary satellite and taking other satellites in the constellation except the primary satellite as the target satellite, the overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite is determined based on the corner point position history;

[0009] The overlapping simulation result corresponding to the primary satellite is determined according to the overlapping situation; wherein the overlapping simulation result is used to record the identification, overlapping start time and overlapping end time corresponding to the target satellite having a payload field overlap with the primary satellite.

[0010] In one implementation, determining a corner point position history corresponding to a satellite in a constellation based on epoch orbit and payload field of view range configuration information includes:

[0011] Based on the epoch orbit, orbit recursion is performed according to the preset forecast duration to generate time series data of the position, velocity, and attitude matrix of the satellites in the constellation in the inertial system;

[0012] Based on the time series data and the payload field of view configuration information, the corner point position history corresponding to the satellite is determined; wherein the corner point position history includes the corner point position corresponding to the satellite at each time point within the forecast period, and the corner point position is the position information corresponding to the intersection of the side edge ray of the payload field of view corresponding to the satellite and the earth's surface.

[0013] In one implementation, determining the corner point position history corresponding to the satellite based on the time series data and the payload field of view range configuration information includes:

[0014] For any time point within the forecast duration, the side edge ray direction vector corresponding to the satellite is determined based on the attitude matrix corresponding to the satellite at that time point and the payload field of view configuration information, and the scaling factor is solved based on the position of the satellite at that time point and the side edge ray direction vector;

[0015] Determine the corner point position corresponding to the satellite at the time point based on the position corresponding to the satellite at the time point, the side edge ray direction vector and the scaling factor;

[0016] Based on the corner point position corresponding to the satellite at each time point, the corner point position history corresponding to the satellite is obtained.

[0017] In one embodiment, determining the overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite based on the corner point position history includes:

[0018] For any time point within the forecast duration, based on the corner point position corresponding to the target star and the payload field of view configuration information corresponding to the primary star at that time point, it is determined in turn whether any corner point of the target star is within the payload field of view of the primary star; and based on the corner point position corresponding to the target star and the position corresponding to the primary star at that time point, it is determined whether the corner point within the payload field of view of the primary star is above the horizon of the primary star;

[0019] If the judgment results are all yes, then the overlap situation is determined as follows: at this time point, there is an overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite;

[0020] If any of the judgment results is no, then the overlap situation is determined as follows: at this time point, there is no overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite.

[0021] In one implementation, based on the corner point position corresponding to the target star and the payload field of view range configuration information corresponding to the primary star at the time point, it is sequentially determined whether any corner point of the target star is within the payload field of view of the primary star, including:

[0022] The coordinates of the corner point position corresponding to the target star at that time point are converted to the orbit system of the main star to determine the azimuth and altitude angle corresponding to the corner point position under the main star field of view;

[0023] Based on the azimuth and altitude angles corresponding to the corner point positions, and the payload field of view configuration information corresponding to the primary satellite, it is determined in turn whether any corner point of the target satellite is within the payload field of view of the primary satellite.

[0024] In one implementation, the payload field of view configuration information includes a maximum azimuth angle, a minimum azimuth angle, a maximum off-axis complementary angle, and a minimum off-axis complementary angle; based on the azimuth angle and altitude angle corresponding to the corner point position, and the payload field of view configuration information corresponding to the primary satellite, determining in sequence whether any corner point of the target satellite is within the payload field of view of the primary satellite includes:

[0025] For any corner point of the target satellite, if the azimuth angle corresponding to the corner point position is between the maximum azimuth angle and the minimum azimuth angle corresponding to the primary satellite, and the altitude angle corresponding to the corner point position is between the maximum off-axis complementary angle and the minimum off-axis complementary angle corresponding to the primary satellite, then it is determined that the corner point is within the payload field of view of the primary satellite.

[0026] In one implementation, based on the corner point position corresponding to the target satellite and the position corresponding to the primary satellite at the time point, determining whether the corner point within the payload field of view of the primary satellite is above the horizon of the primary satellite includes:

[0027] Determine a first angle between a vector from a corner point position corresponding to the target star at that time point to the center of the earth and a vector from a position corresponding to the main star at that time point to the center of the earth; and determine a second angle between a vector from a point on the local horizon of the main star to the center of the earth and a vector from a position corresponding to the main star at that time point to the center of the earth;

[0028] If the first angle is smaller than the second angle, it is determined that the corner point within the payload field of view of the primary satellite is above the horizon of the primary satellite.

[0029] In a second aspect, an embodiment of the present invention further provides a satellite payload field of view overlap simulation device, comprising:

[0030] A data acquisition module is used to obtain the epoch orbit and payload field of view configuration information corresponding to the satellites in the constellation;

[0031] A corner point position determination module is used to determine the corner point position history corresponding to the satellite in the constellation based on the epoch orbit and payload field of view range configuration information;

[0032] An overlap determination module is used to take any satellite in the constellation as a primary satellite and take other satellites in the constellation except the primary satellite as target satellites, and determine the overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite based on the corner point position history;

[0033] The overlapping simulation result determination module is used to determine the overlapping simulation result corresponding to the main satellite according to the overlapping situation; wherein the overlapping simulation result is used to record the identification, overlapping start time and overlapping end time corresponding to the target satellite whose payload field of view overlaps with the main satellite.

[0034] In a third aspect, an embodiment of the present invention further provides an electronic device, comprising a processor and a memory, wherein the memory stores computer-executable instructions that can be executed by the processor, and the processor executes the computer-executable instructions to implement any one of the methods provided in the first aspect.

[0035] In a fourth aspect, an embodiment of the present invention further provides a computer-readable storage medium, which stores computer-executable instructions. When the computer-executable instructions are called and executed by a processor, the computer-executable instructions prompt the processor to implement any one of the methods provided in the first aspect.

[0036] An embodiment of the present invention provides a satellite payload field of view overlap simulation method, device, equipment and medium, which first obtains the epoch orbit and payload field of view range configuration information corresponding to the satellite in the constellation; then determines the corner point position history corresponding to the satellite in the constellation based on the epoch orbit and payload field of view range configuration information; takes any satellite in the constellation as the main satellite, and takes other satellites in the constellation except the main satellite as the target satellite, and determines the overlap between the payload field of view of the target satellite and the payload field of view of the main satellite based on the corner point position history; finally, determines the overlap simulation result corresponding to the main satellite according to the overlap situation, and the overlap simulation result is used to record the identification, overlap start time and overlap end time corresponding to the target star whose payload field of view overlaps with the main satellite. The above method uses the epoch orbit and payload field of view range configuration information corresponding to the satellite in the constellation as input to determine the corner point position history corresponding to the satellite, and on this basis simulates and calculates the overlap between the payload field of view of the target satellite and the payload field of view of the main satellite to obtain an overlap simulation result including the target satellite identification, overlap start time and overlap end time. The embodiment of the present invention addresses the deficiency that professional software is difficult to efficiently extract overlapping period information, and provides one-click overlapping simulation results required for formulating countermeasures, thereby meeting the actual application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates.

[0037] Other features and advantages of the present invention will be described in the following description, and partly become apparent from the description, or understood by practicing the present invention. The purpose and other advantages of the present invention are realized and obtained by the structures particularly pointed out in the description, claims and drawings.

[0038] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0040] Figure 1 A schematic diagram of a flow chart of a satellite payload field of view overlap simulation method provided by an embodiment of the present invention;

[0041] Figure 2 A schematic diagram of a visualization scene provided by an embodiment of the present invention;

[0042] Figure 3 A schematic diagram of a communication payload beam provided by an embodiment of the present invention;

[0043] Figure 4 A schematic diagram of communication payload beam overlap provided in an embodiment of the present invention;

[0044] Figure 5 A single beam 3D scene diagram of a satellite main payload provided in an embodiment of the present invention;

[0045] Figure 6 A single beam 3D scene diagram of a constellation payload provided by an embodiment of the present invention;

[0046] Figure 7 A schematic structural diagram of a satellite payload field of view overlap simulation device provided by an embodiment of the present invention;

[0047] Figure 8 A schematic diagram of the structure of an electronic device provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0048] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution of the present invention will be clearly and completely described in combination with the embodiments below. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0049] At present, existing professional software requires manual participation and data post-processing in the process of simulation data generation, which places high demands on the technical capabilities and development efficiency of engineering and technical personnel, and is difficult to meet the actual application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates. Based on this, the present invention implements a satellite payload field of view overlap simulation method, device, equipment and medium. In view of the deficiency that professional software is difficult to efficiently extract overlapping period information, the overlapping simulation results required for formulating countermeasures are provided in a one-click manner, meeting the actual application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates.

[0050] To facilitate understanding of this embodiment, firstly, a satellite payload field of view overlap simulation method disclosed in an embodiment of the present invention is described in detail, see Figure 1 The flowchart of a satellite payload field of view overlap simulation method shown in FIG. 1 mainly includes the following steps S102 to S108:

[0051] Step S102, obtaining the epoch orbit and payload field of view configuration information corresponding to the satellites in the constellation.

[0052] The payload field of view configuration information includes the maximum azimuth angle, the minimum azimuth angle, the maximum off-axis angle, and the minimum off-axis angle. In addition, the current time point and forecast duration can also be obtained.

[0053] Preferably, after inputting the current time point, forecast duration, epoch orbit corresponding to the satellites in the constellation, and payload field of view range configuration information, the subsequent steps S104 to S108 are automatically executed through one-key operation to generate overlapping simulation results corresponding to each master satellite for direct use in strategy design work.

[0054] Step S104, determining the corner point position history corresponding to the satellites in the constellation based on the epoch orbit and the payload field of view range configuration information.

[0055] Among them, the corner point position history includes the corner point position corresponding to the satellite at each time point within the forecast duration, and the corner point position is the position information corresponding to the intersection between the side edge ray of the payload field of view corresponding to the satellite and the earth's surface. In one example, the orbit of each satellite can be recursively calculated according to the forecast duration to generate the time series data of the position, velocity, and attitude matrix of each satellite in the inertial system. Based on the time series data and the payload field of view configuration information, the position information of the intersection of the side edge ray of the payload field of view of each satellite and the earth's surface, that is, the corner point position, is calculated to describe the projection area of ​​the payload on the ground. Further, the satellite position and attitude are updated in sequence according to time, thereby repeatedly forming the corner point position history.

[0056] Step S106, taking any satellite in the constellation as the primary satellite, and taking other satellites in the constellation except the primary satellite as the target satellite, and determining the overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite based on the corner point position history.

[0057] In one example, each satellite in the constellation is traversed in a loop, and each satellite is taken as the main star in turn. In each traversal process, other satellites other than the main star determined in this traversal are taken as target stars. Based on the corner point position history, it is judged whether any corner point of the target star is within the payload field of view of the main star, and whether the corner point within the payload field of view of the main star is above the horizon of the main star. If the judgment results are all yes, it can be known that there is an overlap between the payload field of view of the target star and the payload field of view of the main star, as well as the time period when the payload field of view overlap occurs (reflected by the overlap start time and the overlap end time). If any judgment result is no, it can be known that there is no overlap between the payload field of view of the target star and the payload field of view of the main star.

[0058] Step S108, determining the overlapping simulation result corresponding to the primary satellite according to the overlapping situation.

[0059] The overlap simulation result is used to record the identifier, overlap start time and overlap end time of the target star whose payload field of view overlaps with the primary star. In one example, based on the aforementioned overlap situation, the overlap between the payload field of view of the target star and the payload field of view of the primary star in each cycle traversal process and the time period when the payload field of view overlaps are known, and the overlap simulation result can be obtained by summarizing them.

[0060] The satellite payload field of view overlap simulation method provided by the embodiment of the present invention takes the epoch orbits and payload field of view range configuration information corresponding to the satellites in the constellation as input to determine the corner point position history corresponding to the satellites, and on this basis simulates and calculates the overlap between the payload field of view of the target satellite and the payload field of view of the main satellite to obtain an overlap simulation result including the target satellite identification, overlap start time and overlap end time. The embodiment of the present invention addresses the deficiency that professional software is difficult to efficiently extract overlapping period information, and provides one-click overlapping simulation results required for formulating countermeasures, thereby meeting the actual application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates.

[0061] For easier understanding, see Figure 2 The schematic diagram of a visualization scene shown in FIG. 1 includes multiple satellites in the constellation. The embodiment of the present invention further briefly introduces the communication payload beam of the satellite, see Figure 3 A schematic diagram of a communication payload beam is shown in FIG. Figure 3 Different filling methods represent different beams (that is, frequency signals), and a single satellite can use different beams to provide services to the ground. In addition, see Figure 4 A schematic diagram of a communication payload beam overlap is shown, for example Figure 4 In (a), two satellites use different frequency signals to provide services to the same location on the ground, so (a) is a non-overlapping situation, for example Figure 4 In (b), two satellites use the same frequency signal to provide services to the same location on the ground, so (b) is an overlapping situation.

[0062] For further information, see Figure 5 The 3D scene diagram of a single beam of a satellite main payload is shown to show the spatial shape of the payload field of view and the concept of interpretation. Among them, the intersection of the side edge rays of the on-board payload field of view and the earth's surface is called a "corner point". Figure 5 The projection area of ​​the payload on the ground is described by the positions of four corner points, and the shape is represented by four parameters, namely the maximum / minimum azimuth angle and the maximum / minimum off-axis angle. Thus, the ray directions of the four side edges of the on-board payload space field of view can be described in the satellite orbit coordinate system. In addition, the embodiment of the present invention also provides the following Figure 6 A 3D scene diagram of a single beam of a constellation payload is shown.

[0063] On this basis, in order to facilitate the understanding of the above-mentioned embodiment, the embodiment of the present invention provides a specific implementation method of a satellite payload field of view overlap simulation method. It mainly includes the following steps 1 to 5:

[0064] Step 1: Provide users with a data upload channel to obtain the calculation conditions entered by the user, including the current time point, forecast duration, epoch orbit of each satellite in the constellation, and onboard payload field of view configuration information. The payload field of view configuration information includes the maximum azimuth angle, the minimum azimuth angle, the maximum off-axis angle, and the minimum off-axis angle. Figure 5 shown.

[0065] Step 2: Based on the epoch orbit, orbit recursion is performed according to the preset forecast duration to generate time series data of the position, velocity, and attitude matrix of the satellites in the constellation in the inertial system.

[0066] In one embodiment, the orbit is recursively calculated taking into account the J4 perturbation and the atmospheric drag perturbation. The attenuation of the semi-major axis and the resulting phase drift are compensated after the J4 recursion by combining the mapping of J4 with the linear attenuation of the semi-major axis of the orbit. Specifically, the orbit recursion uses the combined perturbation analytical model of J4+atmosphere according to the model. Different from numerical recursion and general J2 or J4 analytical recursion, this recursive model eliminates the necessity of using numerical recursion while ensuring the calculation accuracy. The calculation of the semi-major axis and the anomaly angle in the compensation is performed as follows:

[0067]

[0068] In the formula, and are the recursive values ​​of the orbital semi-major axis and the mean anomaly angle under the J4 non-spherical perturbation and atmospheric drag; t is the time, that is, the time elapsed from the initial time, a0, e0, i0, Ω0, ω0, M0 are the orbital elements at the initial time; the mapping J4 adopts the quasi-square root recursive method; a2 is the second-order quantity of the semi-major axis, which is substituted by the orbital height decay rate; n is the orbital mean motion angular velocity, which is obtained by the formula n2a0 3 =μ determined (μ is the gravitational constant of the earth).

[0069] The other four orbital elements are deduced using the standard J4 recursion method and are omitted here.

[0070] After recursion, the number of orbital elements corresponding to any time t between the initial time and the final time is obtained, recorded as a t , e t ,i t ,Ω t ,ω y , M t The standard method is used to convert the rectangular coordinates of position and velocity, which is omitted here.

[0071] In one example, for the above steps 1 and 2, the input form of the satellite epoch orbit is the orbital elements; the position sequence is expressed in rectangular coordinate form.

[0072] In one example, for the above steps 1 and 2, the conversion relationship between the above satellite orbit coordinate system and the inertial system is:

[0073]

[0074] Among them, R i With R o are the expressions of a certain vector in the inertial system and the satellite orbit system, respectively. is the inertial position of the satellite; L oi is the rotation matrix from the inertial system to the orbital system, i.e. the attitude matrix, which is calculated from the satellite position and velocity. The superscript T is the transpose of the matrix.

[0075] Step 3: Calculate the projection area of ​​each satellite payload on the ground. That is, based on the time series data and the payload field of view configuration information, determine the corner point position history corresponding to the satellite. In the embodiment of the present invention, the coverage area of ​​the payload field of view is described by the corner point position, and the coverage judgment problem of the area is converted into the visibility judgment problem of the point within the satellite payload field of view. In addition, the intersection position in the embodiment of the present invention is directly calculated using an analytical method, and an analytical expression of the ray and the earth's surface is constructed to solve the problem in the form of an equation.

[0076] For details, please refer to steps 3.1 to 3.3 below:

[0077] Step 3.1: For any time point within the forecast period, determine the side-edge ray direction vector corresponding to the satellite based on the attitude matrix and payload field of view configuration information corresponding to the satellite at that time point, and solve the scaling factor based on the position and side-edge ray direction vector corresponding to the satellite at that time point.

[0078] Specifically, the calculation process of the side edge ray direction vector D in the field of view is as follows:

[0079] The direction vectors D corresponding to the four side edges of the field of view are calculated according to the following formula:

[0080]

[0081] Wherein, E is the maximum off-axis complementary angle or the minimum off-axis complementary angle of the satellite, and A is the maximum azimuth or the minimum azimuth of the satellite. In practical applications, each side edge ray corresponds to the off-axis complementary angle and the azimuth.

[0082] Specifically, the process of solving the scaling factor k is as follows:

[0083] The position vector P corresponding to the satellite s and the lateral ray direction vector D are denoted as P s =[x0,y0,z0] T,D=[a,b,c] T ,but:

[0084] k = min{k1, k2};

[0085] Among them, k1 and k2 are two solutions of the quadratic equation, which are equal to

[0086]

[0087] In the above formula,

[0088] Δ=B 2 -4AC;

[0089] A=a 2 +b 2 +c 2 ;

[0090] B = 2ax0 + 2by0 + 2cz0;

[0091]

[0092] In the formula, R e The average radius of the earth is 6371.004km.

[0093] Step 3.2, based on the position of the satellite at that time point, the lateral ray direction vector and the scaling factor, determine the corner point position corresponding to the satellite at that time point, which is also the position of the four corner points of the satellite.

[0094] Specifically, for a certain time point, the position of each corner point P t Both can be expressed as the known satellite position vector P s and the linear combination of the side edge ray direction vector D of the field of view corresponding to the corner point, that is, the following corner point position expression (the inertial system subscript i is omitted here):

[0095] P t =P s + k·D.

[0096] Step 3.3, based on the corner point position corresponding to the satellite at each time point, obtain the corner point position history corresponding to the satellite.

[0097] Step 4: Define the primary satellite and the target satellite, and perform corner point visibility determination. That is, take any satellite in the constellation as the primary satellite, and take other satellites in the constellation except the primary satellite as the target satellite, and determine the overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite based on the corner point position history.

[0098] In one embodiment, for each master star, the visibility of the four corner points of each target star is determined in turn, that is, whether they are within the payload field of view of the master star and above the local horizon of the master star. The update time is repeated to form a time series of visibility. When any of the four corner points is visible, the field of view of the target star is considered to be in a quasi-overlapping state.

[0099] Optionally, the above-mentioned visibility judgment and the processing of the massive time series data of each information are completed by relying on the efficient matrix / vector computing capability of the Matlab platform, rather than cyclic traversal according to the time scale, thereby improving the computing efficiency.

[0100] The embodiment of the present invention provides a specific implementation method for determining the overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite, see the following steps 4.1 to 4.3:

[0101] Step 4.1, for any time point within the forecast duration, based on the corner point position corresponding to the target star and the payload field of view configuration information corresponding to the primary star at that time point, determine in turn whether any corner point of the target star is within the payload field of view of the primary star; and based on the corner point position corresponding to the target star and the position corresponding to the primary star at that time point, determine whether the corner point within the payload field of view of the primary star is above the horizon of the primary star.

[0102] Furthermore, an embodiment of the present invention provides an implementation method for determining whether any corner point of the target satellite is within the payload field of view of the primary satellite, including:

[0103] (1A) The corner point position corresponding to the target star at that time point is converted into the host star orbit system to determine the azimuth and altitude angle corresponding to the corner point position in the host star field of view.

[0104] In one example, for any of the four corner points of the target star, the vector T of the corner point position under the field of view of the primary star can be determined according to the following formula: o :

[0105]

[0106] in, is the corner position of the target star, The corner position of the main star.

[0107] In one example, the azimuth and altitude angles corresponding to the corner point position of the main satellite field of view can be determined according to the following formula:

[0108] Remember T o =[ξ,η,ζ] T , A T , E t Calculated by the following formula:

[0109]

[0110] Among them, A t is the azimuth corresponding to the position of the lower corner point of the main star field of view, E t It is the altitude angle corresponding to the lower corner point of the main star's field of view.

[0111] (1B) Based on the azimuth and altitude angle corresponding to the corner point position and the payload field of view configuration information corresponding to the primary satellite, it is determined in turn whether any corner point of the target satellite is within the payload field of view of the primary satellite.

[0112] Specifically, for any corner point of the target satellite, if the azimuth angle corresponding to the corner point position is between the maximum azimuth angle and the minimum azimuth angle corresponding to the primary satellite, and the altitude angle corresponding to the corner point position is between the maximum off-axis complementary angle and the minimum off-axis complementary angle corresponding to the primary satellite, then it is determined that the corner point is within the payload field of view of the primary satellite.

[0113] In practical applications, for any corner point, if the corner point position P t The corresponding azimuth A t Between the maximum / minimum azimuth angles set in step 1, and the corner point position P t The corresponding altitude angle E t If the angle is between the complementary angles of the maximum / minimum off-axis angles set in step 1, the corner point is considered to be within the payload field of view of the primary satellite, otherwise it is not.

[0114] Furthermore, an embodiment of the present invention provides an implementation method for determining whether a corner point within the payload field of view of a primary satellite is above the horizon of the primary satellite, including:

[0115] (2A) determining a first angle φ between a vector from a corner point position corresponding to the target star at that time point to the center of the earth and a vector from a position corresponding to the primary star at that time point to the center of the earth; and determining a second angle φ between a vector from a point on the local horizon of the primary star to the center of the earth and a vector from a position corresponding to the primary star at that time point to the center of the earth H The calculation formula is as follows:

[0116]

[0117] (2B) If the first angle is less than the second angle, it is determined that the corner point within the payload field of view of the primary satellite is above the horizon of the primary satellite. In one example, if φ<φ H , then it is judged as yes, otherwise it is no.

[0118] Step 4.2, if the judgment results are all yes, then the overlap situation is determined as follows: at this time point, there is an overlap between the payload field of view of the target star and the payload field of view of the primary star. That is, if any of the four corner points of the target star is within the payload field of view of the primary star and above the local horizon of the primary star, then it is determined that there is an overlap between the payload field of view of the target star and the payload field of view of the primary star.

[0119] Step 4.3, if any of the judgment results is no, then the overlap situation is determined as follows: there is no overlap between the payload field of view of the target star and the payload field of view of the primary star at this time point. That is, if the four corner points of the target star are all outside the payload field of view of the primary star and / or below the local horizon of the primary star, then it is determined that there is no overlap between the payload field of view of the target star and the payload field of view of the primary star.

[0120] In one example, the time information corresponding to the time series of the data in the aforementioned steps 1, 2, 3 and 4 are all expressed in the form of epoch seconds, and the simulation start time is the epoch time.

[0121] Step 5: Taking each main star as a unit, summarize the start and end time of the visible corner point of the target star, and mark the target star serial number for each group of start and end time.

[0122] In one example, the embodiment of the present invention adopts a one-key operation. That is, after inputting the initial epoch orbit of each satellite in the constellation and the payload field of view model configuration, the one-key operation automatically generates the overlapping period and auxiliary information of the payload field of view of each satellite (that is, the identification of the satellite involved in the overlap) for direct use in the strategy design work.

[0123] The present invention provides a self-developed simulation system development method that is independent of professional simulation software and manual participation, which includes all simulation results required for formulating countermeasures. The simulation generates the overlapping time period and related information of the payload field of view of the constellation satellite, including: calculation parameter setting link, orbit recursion link, payload coverage area calculation link, visibility judgment link, overlap judgment and data processing link. The embodiment of the present invention can generate the time period and related overlapping information of the overlap of the ground coverage area of ​​each satellite payload in the constellation, and provide necessary design input for the design of countermeasures. Due to the adoption of the above technical solution, a complete simulation calculation method for describing the overlapping situation of the payload field of view of the constellation satellite is formed. The algorithm runs in a one-click manner without manual participation, which improves work efficiency and adaptability. The simulation method can meet the actual application needs of high-frequency task analysis and responding to on-orbit orbit and strategy updates.

[0124] Based on the above embodiments, the present invention provides a satellite payload field of view overlap simulation device. Figure 7 The schematic diagram of the structure of a satellite payload field of view overlap simulation device is shown in FIG. The device mainly includes the following parts:

[0125] The data acquisition module 702 is used to obtain the epoch orbit and payload field of view configuration information corresponding to the satellites in the constellation;

[0126] A corner point position determination module 704 is used to determine the corner point position history corresponding to the satellite in the constellation based on the epoch orbit and the payload field of view range configuration information;

[0127] The overlap determination module 706 is used to take any satellite in the constellation as the primary satellite and take other satellites in the constellation except the primary satellite as the target satellite, and determine the overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite based on the corner point position history;

[0128] The overlapping simulation result determination module 708 is used to determine the overlapping simulation result corresponding to the primary satellite according to the overlapping situation; wherein the overlapping simulation result is used to record the identification, overlapping start time and overlapping end time corresponding to the target satellite whose payload field of view overlaps with the primary satellite.

[0129] The satellite payload field of view overlap simulation device provided by the embodiment of the present invention takes the epoch orbit and payload field of view range configuration information corresponding to the satellite in the constellation as input to determine the corner point position history corresponding to the satellite, and on this basis simulates and calculates the overlap between the payload field of view of the target satellite and the payload field of view of the main satellite, so as to obtain an overlap simulation result including the target satellite identification, the overlap start time and the overlap end time. The embodiment of the present invention addresses the deficiency that professional software is difficult to efficiently extract the overlap period information, and provides the overlap simulation result required for formulating countermeasures in a one-click manner, thereby meeting the actual application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates.

[0130] In one implementation, the corner point position determination module 704 is specifically configured to:

[0131] Based on the epoch orbit, orbit recursion is performed according to the preset forecast duration to generate time series data of the position, velocity, and attitude matrix of the satellites in the constellation in the inertial system;

[0132] Based on the time series data and the payload field of view configuration information, the corner point position history corresponding to the satellite is determined; wherein the corner point position history includes the corner point position corresponding to the satellite at each time point within the forecast period, and the corner point position is the position information corresponding to the intersection of the side edge ray of the payload field of view corresponding to the satellite and the earth's surface.

[0133] In one implementation, the corner point position determination module 704 is specifically configured to:

[0134] For any time point within the forecast duration, the side edge ray direction vector corresponding to the satellite is determined based on the attitude matrix corresponding to the satellite at that time point and the payload field of view configuration information, and the scaling factor is solved based on the position of the satellite at that time point and the side edge ray direction vector;

[0135] Determine the corner point position corresponding to the satellite at the time point based on the position corresponding to the satellite at the time point, the side edge ray direction vector and the scaling factor;

[0136] Based on the corner point position corresponding to the satellite at each time point, the corner point position history corresponding to the satellite is obtained.

[0137] In one implementation, the overlap determination module 706 is specifically configured to:

[0138] For any time point within the forecast duration, based on the corner point position corresponding to the target star and the payload field of view configuration information corresponding to the primary star at that time point, it is determined in turn whether any corner point of the target star is within the payload field of view of the primary star; and based on the corner point position corresponding to the target star and the position corresponding to the primary star at that time point, it is determined whether the corner point within the payload field of view of the primary star is above the horizon of the primary star;

[0139] If the judgment results are all yes, then the overlap situation is determined as follows: at this time point, there is an overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite;

[0140] If any of the judgment results is no, then the overlap situation is determined as follows: at this time point, there is no overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite.

[0141] In one implementation, the overlap determination module 706 is specifically configured to:

[0142] The coordinates of the corner point position corresponding to the target star at that time point are converted to the orbit system of the main star to determine the azimuth and altitude angle corresponding to the corner point position under the main star field of view;

[0143] Based on the azimuth and altitude angles corresponding to the corner point positions, and the payload field of view configuration information corresponding to the primary satellite, it is determined in turn whether any corner point of the target satellite is within the payload field of view of the primary satellite.

[0144] In one implementation, the payload field of view range configuration information includes a maximum azimuth angle, a minimum azimuth angle, a maximum off-axis angle, and a minimum off-axis angle. The overlap determination module 706 is specifically used for:

[0145] For any corner point of the target satellite, if the azimuth angle corresponding to the corner point position is between the maximum azimuth angle and the minimum azimuth angle corresponding to the primary satellite, and the altitude angle corresponding to the corner point position is between the maximum off-axis complementary angle and the minimum off-axis complementary angle corresponding to the primary satellite, then it is determined that the corner point is within the payload field of view of the primary satellite.

[0146] In one implementation, the overlap determination module 706 is specifically configured to:

[0147] Determine a first angle between a vector from a corner point position corresponding to the target star at that time point to the center of the earth and a vector from a position corresponding to the main star at that time point to the center of the earth; and determine a second angle between a vector from a point on the local horizon of the main star to the center of the earth and a vector from a position corresponding to the main star at that time point to the center of the earth;

[0148] If the first angle is smaller than the second angle, it is determined that the corner point within the payload field of view of the primary satellite is above the horizon of the primary satellite.

[0149] The device provided in the embodiment of the present invention has the same implementation principle and technical effects as those of the aforementioned method embodiment. For the sake of brief description, for matters not mentioned in the device embodiment, reference may be made to the corresponding contents in the aforementioned method embodiment.

[0150] An embodiment of the present invention provides an electronic device. Specifically, the electronic device includes a processor and a storage device. The storage device stores a computer program, and when the computer program is executed by the processor, it executes the method described in any one of the above-mentioned implementation methods.

[0151] Figure 8 A structural diagram of an electronic device provided in an embodiment of the present invention, the electronic device 100 includes: a processor 80, a memory 81, a bus 82 and a communication interface 83, wherein the processor 80, the communication interface 83 and the memory 81 are connected via the bus 82; the processor 80 is used to execute an executable module stored in the memory 81, such as a computer program.

[0152] The memory 81 may include a high-speed random access memory (RAM), and may also include a non-volatile memory, such as at least one disk memory. The communication connection between the system network element and at least one other network element is realized through at least one communication interface 83 (which may be wired or wireless), and the Internet, wide area network, local area network, metropolitan area network, etc. may be used.

[0153] The bus 82 may be an ISA bus, a PCI bus, or an EISA bus, etc. The bus may be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 8Only one bidirectional arrow is used in the diagram, but this does not mean that there is only one bus or only one type of bus.

[0154] Among them, the memory 81 is used to store programs, and the processor 80 executes the program after receiving the execution instruction. The method executed by the device for flow process definition disclosed in any embodiment of the above-mentioned embodiments of the present invention can be applied to the processor 80 or implemented by the processor 80.

[0155] The processor 80 may be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method can be completed by the hardware integrated logic circuit or software instructions in the processor 80. The above processor 80 can be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it can also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. The methods, steps and logic block diagrams disclosed in the embodiments of the present invention can be implemented or executed. The general-purpose processor can be a microprocessor or the processor can also be any conventional processor. The steps of the method disclosed in the embodiments of the present invention can be directly embodied as a hardware decoding processor to be executed, or the hardware and software modules in the decoding processor can be executed. The software module can be located in a mature storage medium in the field such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory, or an electrically erasable programmable memory, a register, etc. The storage medium is located in the memory 81, and the processor 80 reads the information in the memory 81 and completes the steps of the above method in combination with its hardware.

[0156] The computer program product of the readable storage medium provided in the embodiment of the present invention includes a computer-readable storage medium storing program code, and the instructions included in the program code can be used to execute the methods described in the previous method embodiments. The specific implementation can be referred to the previous method embodiments, which will not be repeated here.

[0157] If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium, including several instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the methods described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, etc., which can store program codes.

[0158] Finally, it should be noted that the above-described embodiments are only specific implementations of the present invention, which are used to illustrate the technical solutions of the present invention, rather than to limit them. The protection scope of the present invention is not limited thereto. Although the present invention is described in detail with reference to the above-described embodiments, ordinary technicians in the field should understand that any technician familiar with the technical field can still modify the technical solutions recorded in the above-described embodiments within the technical scope disclosed by the present invention, or can easily think of changes, or make equivalent replacements for some of the technical features therein; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A satellite payload field of view overlap simulation method, characterized in that: include: Obtain the epoch orbit and payload field of view configuration information corresponding to the satellites in the constellation; Determining a corner point position history corresponding to the satellite in the constellation based on the epoch orbit and the payload field of view range configuration information; Taking any satellite in the constellation as a primary satellite, and taking other satellites in the constellation except the primary satellite as target satellites, and determining the overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite based on the corner point position history; The overlapping simulation result corresponding to the primary satellite is determined according to the overlapping situation; wherein the overlapping simulation result is used to record the identification, overlapping start time and overlapping end time corresponding to the target satellite having a payload field overlap with the primary satellite.

2. The satellite payload field of view overlap simulation method according to claim 1, characterized in that: Determining a corner point position history corresponding to the satellite in the constellation based on the epoch orbit and the payload field of view range configuration information includes: Based on the epoch orbit, orbit recursion is performed according to a preset forecast duration to generate time series data of the position, velocity, and attitude matrix of the satellite in the constellation in an inertial system; Based on the time series data and the payload field of view configuration information, the corner point position history corresponding to the satellite is determined; wherein the corner point position history includes the corner point position corresponding to the satellite at each time point within the forecast period, and the corner point position is the position information corresponding to the intersection of the side edge ray of the payload field of view corresponding to the satellite and the earth's surface.

3. The satellite payload field of view overlap simulation method according to claim 2, characterized in that: Determining the corner point position history corresponding to the satellite based on the time series data and the payload field of view range configuration information includes: For any time point within the forecast duration, based on the attitude matrix corresponding to the satellite at the time point and the payload field of view configuration information, determine the side edge ray direction vector corresponding to the satellite, and solve the scaling factor based on the position corresponding to the satellite at the time point and the side edge ray direction vector; Determine the corner point position corresponding to the satellite at the time point based on the position corresponding to the satellite at the time point, the side edge ray direction vector and the scaling factor; Based on the corner point position corresponding to the satellite at each time point, the corner point position history corresponding to the satellite is obtained.

4. The satellite payload field of view overlap simulation method according to claim 2, characterized in that: Determining the overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite based on the corner point position history includes: For any time point within the forecast duration, based on the corner point position corresponding to the target star and the payload field of view configuration information corresponding to the primary star at the time point, it is sequentially determined whether any corner point of the target star is within the payload field of view of the primary star; and based on the corner point position corresponding to the target star and the position corresponding to the primary star at the time point, it is determined whether the corner point within the payload field of view of the primary star is above the horizon of the primary star; If the judgment results are all yes, then the overlap situation is determined as: at this time point, there is an overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite; If any judgment result is no, then the overlap situation is determined as follows: at this time point, there is no overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite.

5. The satellite payload field of view overlap simulation method according to claim 4, characterized in that: Based on the corner point position corresponding to the target star and the payload field of view range configuration information corresponding to the primary star at the time point, it is sequentially determined whether any corner point of the target star is located within the payload field of view range of the primary star, including: The coordinates of the corner point position corresponding to the target star at this time point are converted into the main star orbit system to determine the azimuth and altitude angle corresponding to the corner point position in the main star field of view; Based on the azimuth and altitude angle corresponding to the corner point position, and the payload field of view configuration information corresponding to the primary satellite, it is determined in turn whether any corner point of the target satellite is within the payload field of view of the primary satellite.

6. The satellite payload field of view overlap simulation method according to claim 5, characterized in that: The payload field of view configuration information includes a maximum azimuth angle, a minimum azimuth angle, a maximum off-axis complementary angle, and a minimum off-axis complementary angle; based on the azimuth angle and the altitude angle corresponding to the corner point position, and the payload field of view configuration information corresponding to the primary satellite, determining in sequence whether any corner point of the target satellite is within the payload field of view of the primary satellite includes: For any corner point of the target satellite, if the azimuth angle corresponding to the corner point position is between the maximum azimuth angle and the minimum azimuth angle corresponding to the primary satellite, and the altitude angle corresponding to the corner point position is between the maximum off-axis complementary angle and the minimum off-axis complementary angle corresponding to the primary satellite, it is determined that the corner point is within the payload field of view of the primary satellite.

7. The satellite payload field of view overlap simulation method according to claim 4, characterized in that: Based on the corner point position corresponding to the target star and the position corresponding to the primary star at the time point, determining whether the corner point within the payload field of view of the primary star is above the horizon of the primary star includes: Determine a first angle between a vector from a corner point position corresponding to the target star at the time point to the center of the earth and a vector from the position corresponding to the master star at the time point to the center of the earth; and determine a second angle between a vector from a point on the local horizon of the master star to the center of the earth and a vector from the position corresponding to the master star at the time point to the center of the earth; If the first angle is smaller than the second angle, it is determined that the corner point within the payload field of view of the primary satellite is above the horizon of the primary satellite.

8. A satellite payload field of view overlap simulation device, characterized in that: include: A data acquisition module is used to obtain the epoch orbit and payload field of view configuration information corresponding to the satellites in the constellation; A corner point position determination module, used to determine the corner point position history corresponding to the satellite in the constellation based on the epoch orbit and the payload field of view range configuration information; An overlap determination module, used to take any satellite in the constellation as a primary satellite, and take other satellites in the constellation except the primary satellite as target satellites, and determine the overlap between the payload field of view of the target satellite and the payload field of view of the primary satellite based on the corner point position history; An overlapping simulation result determination module is used to determine the overlapping simulation result corresponding to the primary satellite according to the overlapping situation; wherein the overlapping simulation result is used to record the identifier, overlapping start time and overlapping end time corresponding to the target satellite that has a payload field of view overlap with the primary satellite.

9. An electronic device, characterized in that: The method comprises a processor and a memory, wherein the memory stores computer executable instructions that can be executed by the processor, and the processor executes the computer executable instructions to implement the method according to any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores computer-executable instructions, and when the computer-executable instructions are called and executed by a processor, the computer-executable instructions prompt the processor to implement the method according to any one of claims 1 to 7.

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