Satellite payload field-of-view overlap simulation methods, devices, equipment, and media

Abstract

This invention provides a method, apparatus, device, and medium for simulating satellite payload field-of-view overlap, comprising: acquiring epoch orbit and payload field-of-view configuration information for satellites within a constellation; determining the corner position history of satellites within the constellation based on the epoch orbit and payload field-of-view configuration information; taking any satellite within the constellation as the primary satellite and other satellites within the constellation as target satellites, and determining the overlap between the payload field of view determined by the corner position history and the payload field of view of the primary satellite; and determining the overlap simulation result corresponding to the primary satellite based on the overlap situation. This invention addresses the shortcomings of specialized software in efficiently extracting overlap period information, providing one-click overlap simulation results needed for formulating countermeasures, thus meeting the practical application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a method, apparatus, equipment, and medium for simulating the overlap of satellite payload fields of view. Background Technology

[0002] When any two or more satellites in an IoT or Earth-to-ground communication satellite constellation provide services to the same location on the ground, the use of the same beam by each satellite is equivalent to using the same frequency signal, which may cause mutual interference and affect service quality. To prevent this, during in-orbit operation, it is necessary to predict the overlap of the fields of view of the communication payloads of each satellite, and design countermeasures based on the overlap period and specific overlap conditions, such as designing the power on / off periods of the corresponding beams.

[0003] In the industry, general-purpose orbit simulation software is typically used for coverage analysis. The most widely used STK (Systems Tool Kit) software is broadly applicable for calculating the field of view coverage of general payloads on various remote sensing satellites. However, this simulation software is not convenient for directly extracting the Earth coverage area and time-series data of each satellite's communication payload, making it difficult to directly obtain simulation data for developing countermeasures. Even when attempting to use this software, it often requires manual intervention and post-processing during the simulation data generation process, placing high demands on the technical capabilities and development efficiency of engineers, making it difficult to meet the practical application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates. Summary of the Invention

[0004] In view of this, the purpose of this invention is to provide a satellite payload field-of-view overlap simulation method, apparatus, equipment and medium, which addresses the shortcomings of professional software in efficiently extracting overlap time period information, and provides overlap simulation results required for formulating countermeasures with one click, thus meeting the practical application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates.

[0005] In a first aspect, embodiments of the present invention provide a satellite payload field-of-view overlap simulation method, comprising:

[0006] Obtain epochal orbit and payload field-of-view configuration information for satellites within the constellation;

[0007] Based on the epoch orbit and payload field-of-view configuration information, the corner position history of the satellites within the constellation is determined.

[0008] Taking any satellite in the constellation as the primary star and other satellites in the constellation besides the primary star as target stars, the overlap between the payload field of view of the target star and the payload field of view of the primary star is determined based on the corner position history.

[0009] The overlap simulation results corresponding to the primary star are determined based on the overlap situation; among them, the overlap simulation results are used to record the identifier, overlap start time and overlap end time of the target star that has a payload field of view overlap with the primary star.

[0010] In one implementation, based on epoch orbit and payload field-of-view configuration information, the corner position history of the satellites within the constellation is determined, including:

[0011] Based on the epoch orbit, the orbit is recursively extrapolated according to the pre-set prediction duration to generate time series data of the position, velocity, and attitude matrices of the satellites in the constellation in the inertial frame;

[0012] Based on time series data and payload field of view configuration information, the corner position history of the satellite is determined. The corner position history includes the corner position of the satellite at each time point within the forecast duration. The corner position is the position information of the intersection between the side prism ray of the payload field of view of the satellite and the Earth's surface.

[0013] In one implementation, the corner position history of the satellite is determined based on time-series data and payload field-of-view configuration information, including:

[0014] For any point in time within the forecast duration, based on the satellite's attitude matrix and payload field of view configuration information at that point in time, determine the side prism ray direction vector of the satellite, and solve for the scaling factor based on the satellite's position and side prism ray direction vector at that point in time.

[0015] Based on the satellite's position, side prism ray direction vector, and scaling factor at that time point, determine the satellite's corner point position at that time point;

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

[0017] In one implementation, determining the overlap between the payload field of view of the target star and the payload field of view of the host star based on the corner position history includes:

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

[0019] If all the judgment results are yes, then the overlap is determined to be: 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 host star.

[0020] If any judgment result is negative, then the overlap 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 host star at that time point.

[0021] In one implementation, based on the corner position of the target star and the payload field of view configuration information of the primary star at that time point, it is sequentially determined whether any corner 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 transformed to the orbital system of the main star to determine the azimuth and elevation angles corresponding to the corner point position in the field of view of the main star;

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

[0024] In one implementation, the payload field of view configuration information includes the maximum and minimum azimuth angles, the maximum and minimum complementary off-axis angles; based on the azimuth and elevation angles corresponding to the corner points, and the payload field of view configuration information corresponding to the primary star, it is sequentially determined whether any corner point of the target star is within the payload field of view of the primary star, including:

[0025] For any corner point of the target star, if the azimuth angle corresponding to the corner point is between the maximum and minimum azimuth angles corresponding to the primary star, and the elevation angle corresponding to the corner point is between the maximum and minimum complementary off-axis angles corresponding to the primary star, then the corner point is determined to be within the payload field of view of the primary star.

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

[0027] Determine the first angle between the vector from the angular point of the target star at that time to the Earth's center and the vector from the position of the primary star at that time to the Earth's center; and determine the second angle between the vector from the point on the local horizon of the primary star to the Earth's center and the vector from the position of the primary star at that time to the Earth's center.

[0028] If the first included angle is less than the second included angle, then the corner point located within the payload field of view of the primary star is determined to be above the horizon of the primary star.

[0029] Secondly, embodiments of the present invention also provide a satellite payload field-of-view overlap simulation device, comprising:

[0030] The data acquisition module is used to acquire epoch orbit and payload field-of-view configuration information for satellites within the constellation;

[0031] The corner position determination module is used to determine the corner position history of satellites within the constellation based on epoch orbit and payload field of view configuration information;

[0032] The overlap determination module is used to determine the overlap between the payload field of view of the target star and the payload field of view of the main star, and other satellites in the constellation other than the main star, based on the corner position history.

[0033] The overlap simulation result determination module is used to determine the overlap simulation result corresponding to the primary star based on the overlap situation. The overlap simulation result is used to record the identifier, overlap start time and overlap end time of the target star that has overlap with the primary star's payload field of view.

[0034] Thirdly, embodiments of the present invention also provide an electronic device, including 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 of the methods provided in the first aspect.

[0035] Fourthly, embodiments of the present invention also provide a computer-readable storage medium storing computer-executable instructions, which, when invoked and executed by a processor, cause the processor to implement any of the methods provided in the first aspect.

[0036] This invention provides a satellite payload field-of-view overlap simulation method, apparatus, device, and medium. First, it acquires the epoch orbit and payload field-of-view configuration information for satellites within a constellation. Then, based on the epoch orbit and payload field-of-view configuration information, it determines the corner position history of the satellites within the constellation. Taking any satellite within the constellation as the primary satellite and other satellites within the constellation as target satellites, it determines the overlap between the payload field of view of the target satellites and the payload field of view of the primary satellites based on the corner position history. Finally, it determines the overlap simulation result corresponding to the primary satellite based on the overlap situation. The overlap simulation result is used to record the identifier, overlap start time, and overlap end time of the target satellites that have payload field-of-view overlap with the primary satellite. The above method uses the epoch orbit and payload field of view configuration information of the satellites in the constellation as input to determine the corner position history of the satellites. Based on this, it simulates and calculates the overlap between the payload field of view of the target star and the payload field of view of the host star to obtain the overlap simulation result containing the target star identifier, overlap start time and overlap end time. This invention addresses the shortcomings of professional software in efficiently extracting overlap period information, and provides the overlap simulation result required for formulating countermeasures with one click, meeting the practical application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates.

[0037] Other features and advantages of the invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention are realized and obtained in accordance with the structures particularly pointed out in the description, claims and drawings.

[0038] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description

[0039] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0040] Figure 1 A flowchart illustrating a satellite payload field-of-view overlap simulation method provided in an embodiment of the present invention;

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

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

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

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

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

[0046] Figure 7 This is a schematic diagram of the structure of a satellite payload field-of-view overlap simulation device provided in an embodiment of the present invention;

[0047] Figure 8 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention. Detailed Implementation

[0048] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0049] Currently, existing professional software requires manual intervention and post-processing during the simulation data generation process, which places high demands on the technical capabilities and development efficiency of engineering technicians. This makes it difficult to meet the practical application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates. Based on this, the present invention provides a satellite payload field-of-view overlap simulation method, device, equipment, and medium. It addresses the shortcomings of professional software in efficiently extracting overlap time period information, and provides overlap simulation results needed for formulating countermeasures with a single click, thus meeting the practical application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates.

[0050] To facilitate understanding of this embodiment, a satellite payload field-of-view overlap simulation method disclosed in this embodiment of the invention will first be described in detail. (See [link to relevant documentation]). Figure 1 The diagram shows a flowchart of a satellite payload field-of-view overlap simulation method, which mainly includes the following steps S102 to S108:

[0051] Step S102: Obtain the epoch orbit and payload field of view configuration information corresponding to the satellites within the constellation.

[0052] The payload field of view configuration information includes the maximum and minimum azimuth angles, the maximum and minimum complementary off-axis angles. Additionally, the current time and forecast duration can be obtained.

[0053] Preferably, after inputting the current time point, forecast duration, epoch orbit of the satellites in the constellation, and payload field of view configuration information, subsequent steps S104 to S108 are automatically executed through a one-click operation to generate the overlapping simulation results corresponding to each primary satellite, which can be directly used for strategy design work.

[0054] Step S104: Based on the epoch orbit and payload field of view configuration information, determine the corner position history of the satellites within the constellation.

[0055] The corner position history includes the corner position of the satellite at each time point within the forecast duration. The corner position is the location information corresponding to the intersection of the side prism ray of the satellite's corresponding payload field of view with the Earth's surface. In one example, the orbits of each satellite can be recursively extrapolated according to the forecast duration to generate time-series data of the position, velocity, and attitude matrices of each satellite in the inertial frame. Based on this time-series data and the payload field of view configuration information, the location information of the intersection of the side prism ray of each satellite's payload field of view with the Earth's surface, i.e., the corner position, is calculated to describe the projection area of ​​the payload on the ground. Furthermore, the satellite positions and attitudes are updated sequentially over time, thus repeatedly forming the corner position history.

[0056] Step S106: Take any satellite in the constellation as the primary star and other satellites in the constellation other than the primary star as target stars, and determine the overlap between the payload field of view of the target star and the payload field of view of the primary star based on the corner position history.

[0057] In one example, each satellite in the constellation is traversed in a loop, and each satellite is taken as the primary star in turn. During each loop, the other satellites besides the primary star determined in this loop are taken as target stars. Based on the corner position history, it is determined whether any corner of the target star is within the payload field of view of the primary star, and whether any corner within the payload field of view of the primary star is above the horizon of the primary star. If the result of both judgments is 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 primary star, and the time period of the overlap (reflected by the start time and end time of the overlap). 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 primary star.

[0058] Step S108: Determine the overlap simulation results corresponding to the primary star based on the overlap situation.

[0059] The overlap simulation results are used to record the identifier, overlap start time, and overlap end time of the target star whose payload field of view overlaps with that of the host 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 host star during each loop traversal is known, as well as the time period during which the payload field of view overlap occurs. By summarizing these, the overlap simulation results can be obtained.

[0060] The satellite payload field-of-view overlap simulation method provided in this invention uses the epoch orbit and payload field-of-view range configuration information of the satellites within the constellation as input to determine the corner position history of the satellites. Based on this, it simulates and calculates the overlap between the payload field of view of the target satellite and the payload field of view of the host satellite, so as to obtain the overlap simulation result containing the target satellite identifier, overlap start time, and overlap end time. This invention addresses the shortcomings of professional software in efficiently extracting overlap period information, and provides the overlap simulation result required for formulating countermeasures with one click, meeting the practical application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates.

[0061] For ease of understanding, see [link to relevant documentation]. Figure 2 The diagram illustrates a visual scenario where a constellation contains multiple satellites. This embodiment of the invention further provides a brief description of the satellite's communication payload beam; see [link to documentation]. Figure 3 The diagram shown is a schematic of a communication payload beam. Figure 3 Different filling patterns represent different beams (i.e., frequency signals), and a single satellite can use different beams to provide services to the ground. See also... Figure 4 The diagram shown illustrates a communication payload beam overlap, for example... Figure 4 In (a), two satellites use different frequency signals to provide services to the same location on the ground. Therefore, (a) represents a non-overlapping case, for example... Figure 4 In (b), the two satellites use the same frequency signal when providing services to the same location on the ground, so (b) is an overlapping case.

[0062] Further, see Figure 5 The image shown is a 3D scene diagram of a single beam of a satellite's main payload, illustrating the spatial shape and conceptual explanation of the payload's field of view. The points where the lateral rays of the payload's field of view intersect with the Earth's surface are called "corner points." Figure 5 The projection area of ​​the payload on the ground is described by the four corner points, and this shape is represented by four parameters: the maximum / minimum azimuth angle, the maximum / minimum off-axis angle, and so on. This allows the ray directions of the four side edges of the onboard payload's spatial field of view to be described within the satellite orbital coordinate system. Furthermore, embodiments of the present invention also provide... Figure 6 The image shown is a 3D scene diagram of a single beam of a constellation payload.

[0063] Based on this, and to facilitate understanding of the foregoing embodiments, this invention provides a specific implementation method for simulating satellite payload field-of-view overlap. It mainly includes the following steps one through five:

[0064] Step 1: Provide users with a data upload channel to obtain the calculation conditions input by the users, 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 and minimum azimuth angles, the maximum and minimum complementary off-axis angles, as detailed above. Figure 5 As shown.

[0065] Step 2: Based on the epoch orbit, perform orbit recursion according to the pre-set prediction duration to generate time series data of the position, velocity, and attitude matrices of satellites in the constellation in the inertial frame.

[0066] In one implementation, the recursive orbit is considered in conjunction with J4 perturbation and atmospheric drag perturbation. A method combining mapping J4 with linear decay of the orbit's semi-major axis is used to compensate for the decay of the semi-major axis and the resulting phase drift after J4 recursion. Specifically, the orbit recursion uses a combined J4 + atmospheric perturbation analytical model. Unlike numerical recursion and general J2 or J4 analytical recursion, this recursive model eliminates the need for numerical recursion while maintaining computational accuracy. The calculation of the semi-major axis and the mean anomaly angle in the compensation is performed using the following formula:

[0067]

[0068] In the formula, and , respectively, are the recursive values ​​of the orbital semi-major axis and the angle of approach under non-spherical perturbation and atmospheric drag in J4; t is the time elapsed since the initial time; a0, e0, i0, Ω0, ω0, and M0 are the orbital elements at the initial time; the mapping of J4 uses the quasi-square root recursive method; a2 is the second-order quantity of the semi-major axis, substituted with the orbital altitude decay rate; n is the orbital translational angular velocity, obtained from equation n2a0. 3 =μ is determined (μ is the Earth's gravitational constant).

[0069] The other four orbital elements are calculated using the standard J4 recursive method, which is omitted here.

[0070] After recursion, we obtain the orbital elements corresponding to any time t between the initial and final times, denoted as a. t e t i t Ω t ω y M t The conversion to Cartesian coordinates for position and velocity using standard methods is omitted here.

[0071] In one example, for steps one and two mentioned above, the satellite epoch orbit is input in the form of orbital elements; the position sequence is represented in rectangular coordinates.

[0072] In one example, for steps one and two above, the transformation relationship between the aforementioned satellite orbit coordinate system and the inertial frame is as follows:

[0073]

[0074] Among them, R i With R o These are the expressions for a certain vector in the inertial frame and the satellite orbit frame, respectively. The inertial frame position of the satellite; L oi This is the rotation matrix from the inertial frame to the orbital frame, i.e., the attitude matrix, which is calculated from the satellite's position and velocity. The superscript T denotes the transpose of the matrix.

[0075] Step 3: Calculate the projection area of ​​each satellite payload on the ground. That is, based on time-series data and payload field-of-view configuration information, determine the corner position history of the corresponding satellite. In this embodiment of the invention, the coverage area of ​​the payload field of view is described by the corner position, transforming the problem of determining the coverage of the area into the problem of determining the visibility of a point within the satellite payload field of view. In addition, the intersection position in this embodiment of the invention is directly calculated using an analytical method, constructing an analytical expression of the ray and the Earth's surface, and solving it in the form of equations.

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

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

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

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

[0080]

[0081] Where E is the satellite's maximum or minimum complementary off-axis angle, and A is the satellite's maximum or minimum azimuth angle. In practical applications, each side ridge ray corresponds one-to-one with the complementary off-axis angle and azimuth angle.

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

[0083] The satellite's corresponding position vector P s The direction vector D of the lateral ray is denoted as P. s = [x0, y0, z0] TD = [a, b, c] T ,but:

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

[0085] Where k1 and k2 are two solutions to the quadratic equation in one variable, respectively 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 6371.004 km.

[0093] Step 3.2: Based on the satellite's position, side prism ray direction vector, and scaling factor at that time point, determine the corner position of the satellite at that time point. The corner position is the position of the satellite's four corner points.

[0094] Specifically, for a given point in time, the position P of each corner point t Both can be represented as the known quantity, satellite position vector P. s The linear combination of the lateral ray direction vector D corresponding to the field of view range of the corner point is expressed as follows (the inertial frame subscript i is omitted here):

[0095] P t =P s +k·D.

[0096] Step 3.3: Based on the corner position of the satellite at each time point, obtain the corner position history of the satellite.

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

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

[0099] Optionally, the visibility judgment mentioned above, and the processing of massive time series data for each piece of information, are completed by relying on the efficient matrix / vector computing capabilities of the Matlab platform, rather than by iterating through the time scale, thus improving computational efficiency.

[0100] This invention provides a specific implementation method for determining the overlap between the payload field of view of the target star and the payload field of view of the host star, as detailed in steps 4.1 to 4.3 below:

[0101] Step 4.1: For any time point within the forecast duration, based on the corner position of the target star and the payload field of view configuration information of the main 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 main star; and based on the corner position of the target star and the position of the main star at that time point, determine whether the corner point within the payload field of view of the main star is above the horizon of the main star.

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

[0103] (1A) Transform the coordinates of the corner point position of the target star at that time point to the main star orbit system to determine the azimuth and elevation angles corresponding to the corner point position in the field of view of the main star.

[0104] In one example, for any one of the four corner points of the target star, the vector T of its position in the field of view of the primary star can be determined using the following formula. o :

[0105]

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

[0107] In one example, the azimuth and elevation angles corresponding to the lower corner of the main star's field of view can be determined using 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 The azimuth angle corresponding to the lower corner of the main star's field of view, E t The elevation angle corresponding to the lower corner of the main star's field of view.

[0111] (1B) Based on the azimuth and elevation angles corresponding to the corner points and the payload field of view configuration information corresponding to the main star, determine in turn whether any corner point of the target star is within the payload field of view of the main star.

[0112] Specifically, for any corner point of the target star, if the azimuth angle corresponding to the corner point is between the maximum and minimum azimuth angles corresponding to the main star, and the elevation angle corresponding to the corner point is between the maximum and minimum complementary off-axis angles corresponding to the main star, then the corner point is determined to be within the payload field of view of the main star.

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

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

[0115] (2A) Determine the first angle φ between the vector from the angular position of the target star to the Earth's center at that time point and the vector from the position of the primary star to the Earth's center at that time point; and determine the second angle φ between the vector from the point on the local horizon of the primary star to the Earth's center and the vector from the position of the primary star to the Earth's center at that time point. H The calculation formula is as follows:

[0116]

[0117] (2B) If the first included angle is less than the second included angle, then the corner point located within the payload field of view of the primary star is determined to be above the horizon of the primary star. In one example, if φ < φ H If the condition is met, it is considered true; otherwise, it is considered false.

[0118] Step 4.2: If all the judgment results are yes, then the overlap 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 host star. That is, if any one of the four corner points of the target star is within the payload field of view of the host star and above the local horizon of the host 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 host star.

[0119] Step 4.3: If any judgment result is negative, the overlap 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 host star at that time point. That is, if all four corner points of the target star are located outside the payload field of view of the host star, and / or below the local horizon of the host 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 host star.

[0120] In one example, the time information corresponding to the time series of the data in steps one, two, three, and four above is expressed in epoch seconds, and the simulation start time is the epoch time.

[0121] Step 5: For each primary star, summarize the start and end times when the target star's corner point is visible, and mark the target star's sequence number for each set of start and end times.

[0122] In one example, this embodiment of the invention employs a one-click operation. That is, after inputting the initial epoch orbits and payload field-of-view model configurations for each star in the constellation, a one-click operation automatically generates the overlap periods and auxiliary information (i.e., satellite identifiers involving overlap) of the payload fields of view for each star, which can be directly used for strategy design.

[0123] This invention provides a self-developed simulation system development method independent of professional simulation software and manual intervention. It includes all simulation results needed for formulating countermeasures. The simulation generates overlapping time periods and related information for the satellite payload fields of view of a constellation, including: parameter setting, orbit recursion, payload coverage area calculation, visibility assessment, overlap determination, and data processing. Embodiments of this invention can generate the time periods and related overlap information for the overlapping of ground coverage areas by the payloads of each satellite in the constellation, providing necessary design input for countermeasure design. By adopting the above technical solution, a complete simulation calculation method for describing the overlap of the payload fields of view of constellation satellites is formed. The algorithm can be run with a single click, requiring no manual intervention, thus improving work efficiency and adaptability. This simulation method can meet the practical application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates.

[0124] Based on the foregoing embodiments, this invention provides a satellite payload field-of-view overlap simulation device, see [link to previous document]. Figure 7 The diagram shows a structural schematic of a satellite payload field-of-view overlap simulation device, which mainly includes the following parts:

[0125] Data acquisition module 702 is used to acquire epoch orbit and payload field of view configuration information for satellites within the constellation;

[0126] The corner position determination module 704 is used to determine the corner position history of satellites within the constellation based on epoch orbit and payload field of view configuration information.

[0127] The overlap determination module 706 is used to determine the overlap between the payload field of view of the target star and the payload field of view of the main star based on the corner position history, taking any satellite in the constellation as the main star and other satellites in the constellation other than the main star as the target star.

[0128] The overlap simulation result determination module 708 is used to determine the overlap simulation result corresponding to the main star based on the overlap situation; wherein, the overlap simulation result is used to record the identifier, overlap start time and overlap end time of the target star that has a payload field of view overlap with the main star.

[0129] The satellite payload field-of-view overlap simulation device provided in this invention uses the epoch orbit and payload field-of-view range configuration information of the satellites within the constellation as input to determine the corner position history of the satellites. Based on this, it simulates and calculates the overlap between the payload field of view of the target satellite and the payload field of view of the host satellite, so as to obtain the overlap simulation result containing the target satellite identifier, overlap start time, and overlap end time. This invention addresses the shortcomings of professional software in efficiently extracting overlap period information, and provides the overlap simulation result required for formulating countermeasures with one click, meeting the practical application needs of high-frequency mission analysis and responding to on-orbit orbit and strategy updates.

[0130] In one implementation, the corner point location determination module 704 is specifically used for:

[0131] Based on the epoch orbit, the orbit is recursively extrapolated according to the pre-set prediction duration to generate time series data of the position, velocity, and attitude matrices of the satellites in the constellation in the inertial frame;

[0132] Based on time series data and payload field of view configuration information, the corner position history of the satellite is determined. The corner position history includes the corner position of the satellite at each time point within the forecast duration. The corner position is the position information of the intersection between the side prism ray of the payload field of view of the satellite and the Earth's surface.

[0133] In one implementation, the corner point location determination module 704 is specifically used for:

[0134] For any point in time within the forecast duration, based on the satellite's attitude matrix and payload field of view configuration information at that point in time, determine the side prism ray direction vector of the satellite, and solve for the scaling factor based on the satellite's position and side prism ray direction vector at that point in time.

[0135] Based on the satellite's position, side prism ray direction vector, and scaling factor at that time point, determine the satellite's corner point position at that time point;

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

[0137] In one implementation, the overlap determination module 706 is specifically used for:

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

[0139] If all the judgment results are yes, then the overlap is determined to be: 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 host star.

[0140] If any judgment result is negative, then the overlap 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 host star at that time point.

[0141] In one implementation, the overlap determination module 706 is specifically used for:

[0142] The coordinates of the corner point position corresponding to the target star at that time point are transformed to the orbital system of the main star to determine the azimuth and elevation angles corresponding to the corner point position in the field of view of the main star;

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

[0144] In one embodiment, the load field of view configuration information includes the maximum azimuth angle, the minimum azimuth angle, the maximum off-axis complementary angle, and the minimum off-axis complementary angle; the overlap determination module 706 is specifically used for;

[0145] For any corner point of the target star, if the azimuth angle corresponding to the corner point is between the maximum and minimum azimuth angles corresponding to the primary star, and the elevation angle corresponding to the corner point is between the maximum and minimum complementary off-axis angles corresponding to the primary star, then the corner point is determined to be within the payload field of view of the primary star.

[0146] In one implementation, the overlap determination module 706 is specifically used for:

[0147] Determine the first angle between the vector from the angular point of the target star at that time to the Earth's center and the vector from the position of the primary star at that time to the Earth's center; and determine the second angle between the vector from the point on the local horizon of the primary star to the Earth's center and the vector from the position of the primary star at that time to the Earth's center.

[0148] If the first included angle is less than the second included angle, then the corner point located within the payload field of view of the primary star is determined to be above the horizon of the primary star.

[0149] The device provided in this embodiment of the invention has the same implementation principle and technical effect as the aforementioned method embodiment. For the sake of brevity, any parts not mentioned in the device embodiment can be referred to the corresponding content in the aforementioned method embodiment.

[0150] This invention provides an electronic device, specifically, the electronic device includes a processor and a storage device; the storage device stores a computer program, and the computer program, when run by the processor, executes the method described in any of the above embodiments.

[0151] Figure 8 This is a schematic diagram of the structure 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. The processor 80, the communication interface 83, and the memory 81 are connected through the bus 82. The processor 80 is used to execute executable modules, such as computer programs, stored in the memory 81.

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

[0153] Bus 82 can be an ISA bus, PCI bus, or EISA bus, etc. The bus can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 8The symbol is represented by a single double-headed arrow, but this does not mean that there is only one bus or one type of bus.

[0154] The memory 81 is used to store programs. After receiving an execution instruction, the processor 80 executes the program. The method executed by the device for defining the flow process disclosed in any of the foregoing 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 implementation, each step of the above method can be completed by the integrated logic circuitry in the hardware of the processor 80 or by software instructions. The processor 80 may be a general-purpose processor, including a Central Processing Unit (CPU), a Network Processor (NP), etc.; it may 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 gate or transistor logic devices, or discrete hardware components. It can implement or execute the methods, steps, and logic block diagrams disclosed in the embodiments of this invention. The general-purpose processor may be a microprocessor or any conventional processor. The steps of the methods disclosed in the embodiments of this invention can be directly embodied in the execution of a hardware decoding processor, or executed by a combination of hardware and software modules in the decoding processor. The software modules may reside in random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, registers, or other mature storage media in the art. The storage medium is located in memory 81. The processor 80 reads the information in memory 81 and, in conjunction with its hardware, completes the steps of the above method.

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

[0157] If the aforementioned functions are implemented as 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 this invention, essentially, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0158] Finally, it should be noted that the above-described embodiments are merely specific implementations of the present invention, used to illustrate the technical solutions of the present invention, and not to limit it. The scope of protection of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that any person skilled in the art can still modify or easily conceive of changes to the technical solutions described in the foregoing embodiments within the technical scope disclosed in the present invention, or make equivalent substitutions for some of the technical features; and these modifications, changes, or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be covered within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A method for simulating overlapping fields of view of satellite payloads, characterized in that, include: Obtain epochal orbit and payload field-of-view configuration information for satellites within the constellation; Based on the epoch orbit and the payload field of view configuration information, determine the corner position history of the satellite within the constellation; Taking any one of the satellites in the constellation as the primary star and the other satellites in the constellation besides the primary star as target stars, the overlap between the payload field of view of the target star and the payload field of view of the primary star is determined based on the corner position history. This includes: for any time point within the forecast duration, based on the corner position of the target star and the payload field of view range configuration information of the primary star at that time point, sequentially determining whether any corner point of the target star is within the payload field of view of the primary star; and based on the corner position of the target star and the position of the primary star at that 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; if the determination result is yes for all, then the overlap is determined to be: there is an overlap between the payload field of view of the target star and the payload field of view of the primary star at that time point; if any determination result is no, then the overlap is determined to be: 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 that time point. Determining the overlap simulation result corresponding to the primary star based on the overlap situation includes: summarizing the overlap situation between the payload field of view of the target star and the payload field of view of the primary star, as well as the time period during which the payload field of view overlap occurs, to obtain the overlap simulation result; wherein, the overlap simulation result is used to record the identifier, overlap start time, and overlap end time of the target star that has a payload field of view overlap with the primary star.

2. The satellite payload field-of-view overlap simulation method according to claim 1, characterized in that, Based on the epoch orbit and the payload field of view configuration information, the corner position history of the satellites within the constellation is determined, including: Based on the epoch orbit, orbit recursion is performed according to a pre-set prediction duration to generate time series data of the position, velocity, and attitude matrices of the satellites in the constellation in the inertial frame; Based on the time series data and the payload field of view configuration information, the corner position history of the satellite is determined; wherein, the corner position history includes the corner position of the satellite at each time point within the forecast duration, and the corner position is the position information corresponding to the intersection of the side prism ray of the payload field of view of the satellite and the Earth surface.

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

4. The satellite payload field-of-view overlap simulation method according to claim 1, characterized in that, Based on the corner position of the target star and the payload field of view configuration information of the primary star at that time point, it is sequentially determined whether any corner of the target star is within the payload field of view of the primary star, including: The coordinates of the corner point position corresponding to the target star at that time point are transformed to the orbital system of the main star to determine the azimuth and elevation angles corresponding to the corner point position in the field of view of the main star; Based on the azimuth and elevation angles corresponding to the corner points, and the payload field of view configuration information corresponding to the primary star, it is sequentially determined whether any corner point of the target star is within the payload field of view of the primary star.

5. The satellite payload field-of-view overlap simulation method according to claim 4, characterized in that, The payload field of view configuration information includes the maximum and minimum azimuth angles, the maximum and minimum complementary off-axis angles; based on the azimuth and elevation angles corresponding to the corner points, and the payload field of view configuration information corresponding to the primary star, it is sequentially determined whether any corner point of the target star is within the payload field of view of the primary star, including: For any corner point of the target star, if the azimuth angle corresponding to the corner point is between the maximum and minimum azimuth angles corresponding to the main star, and the elevation angle corresponding to the corner point is between the maximum and minimum complementary off-axis angles corresponding to the main star, then the corner point is determined to be within the payload field of view of the main star.

6. The satellite payload field-of-view overlap simulation method according to claim 1, characterized in that, Based on the corner point position of the target star and the position of the primary star at that time point, determining whether the corner point located within the payload's field of view of the primary star is above the primary star's horizon includes: Determine the first angle between the vector from the corner point of the target star at that time point to the Earth's center and the vector from the position of the primary star at that time point to the Earth's center; and determine the second angle between the vector from the point on the local horizon of the primary star to the Earth's center and the vector from the position of the primary star at that time point to the Earth's center. If the first included angle is smaller than the second included angle, then the corner point located within the payload field of view of the primary star is determined to be above the horizon of the primary star.

7. A satellite payload field-of-view overlap simulation device, characterized in that, include: The data acquisition module is used to acquire epoch orbit and payload field-of-view configuration information for satellites within the constellation; The corner position determination module is used to determine the corner position history of the satellite within the constellation based on the epoch orbit and the payload field of view configuration information. An overlap determination module is used to take any one of the satellites in the constellation as the primary star and other satellites in the constellation besides the primary star as target stars, and determine the overlap between the payload field of view of the target star and the payload field of view of the primary star based on the corner position history. This includes: for any time point within the forecast duration, based on the corner position of the target star and the payload field of view range configuration information of the primary star at that time point, sequentially determining whether any corner point of the target star is within the payload field of view of the primary star; and based on the corner position of the target star and the position of the primary star at that 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; if all determinations are yes, then the overlap is determined to be: there is an overlap between the payload field of view of the target star and the payload field of view of the primary star at that time point; if any determination is no, then the overlap is determined to be: 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 that time point. The overlap simulation result determination module is used to determine the overlap simulation result corresponding to the host star based on the overlap situation, including: summarizing the overlap situation between the payload field of view of the target star and the payload field of view of the host star, as well as the time period during which the payload field of view overlap occurs, to obtain the overlap simulation result; wherein, the overlap simulation result is used to record the identifier, overlap start time, and overlap end time of the target star that has a payload field of view overlap with the host star.

8. An electronic device, characterized in that, The method includes a processor and a memory, the memory storing computer-executable instructions executable by the processor, the processor executing the computer-executable instructions to implement the method of any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer-executable instructions that, when invoked and executed by a processor, cause the processor to perform the method according to any one of claims 1 to 6.

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