Method and apparatus for generating a set of solar radiation changes, and storage medium

Abstract

The embodiments of the present application provide a method and device for generating a set of solar radiation changes, and a storage medium. Among them, the method includes: obtaining the orbital parameters of a target operating device within a target orbital period; generating a set of trajectory changes of the solar vector within the target orbital period in the first coordinate system of the target operating device by using the orbital parameters; generating a set of solar radiation changes of the target operating device within the target orbital period based on the set of trajectory changes. Through the present application, the problem in the related art that the change law of sunlight irradiation cannot be determined in the first coordinate system of the target operating device is solved, and thus the effect of intuitively and quantitatively analyzing the law of sunlight irradiation received by the target operating device can be achieved.

Description

Technical Field

[0001] The embodiments of the present application relate to the field of computers, and more specifically, to a method and device for generating a set of solar radiation changes, and a storage medium. Background Art

[0002] In the related art, the external heat flux of a device orbiting the Earth (such as a satellite, a launcher, etc.) is basically analyzed by the following methods: The first method relies on commercial software to obtain the relationship between the external heat flux of each surface of the device and time, and analyzes the variation law of the external heat flux on the device surface; the second method is based on the secondary development of commercial software to reduce the data processing volume of the first method and improve the convenience.

[0003] The device orbits the Earth, and the Earth carries the device around the Sun. In this case, analyzing the sunlight irradiation of the device is relatively complicated. When modeling sunlight irradiation with existing commercial software, generally, the device, the Earth, and the Sun are in a three-dimensional view, and the shadow area and sunlit area of the device orbiting the Earth can be intuitively viewed. However, the change of sunlight irradiation cannot be intuitively given from the perspective of the first coordinate system of the device. Summary of the Invention

[0004] The embodiments of the present application provide a method and device for generating a set of solar radiation changes, and a storage medium, so as to at least solve the problem in the related art that the change law of sunlight irradiation cannot be determined in the first coordinate system of the target operating device.

[0005] According to an embodiment of the present application, a method for generating a set of solar radiation changes is provided, including: obtaining the orbital parameters of a target operating device within a target orbital period, where the orbital parameters are used to represent the position and operating state of the target operating device on a target orbit, and the target orbital period is the time for the target operating device to orbit the target orbit once; using the orbital parameters to generate a set of trajectory changes of the solar vector within the target orbital period in the first coordinate system of the target operating device, where the values in the set of trajectory changes are the coordinates of the solar vector in the first coordinate system; generating a set of solar radiation changes of the target operating device within the target orbital period based on the set of trajectory changes, where the values in the set of solar radiation changes are the radiation values of the external heat flux of solar radiation received by the target operating device within the target orbital period.

[0006] In an exemplary embodiment, obtaining orbital parameters of a target operating device within a target orbital period includes: obtaining a first angle and the orbital altitude of the target orbit, where the first angle is used to represent the pitch angle between the solar vector and the orbital plane of the target orbit; obtaining a set of angles of a second angle within the target orbital period, where the second angle is used to represent the azimuth angle of the solar vector; and determining the first angle, the orbital altitude, and the set of angles of the second angle as the orbital parameters.

[0007] In an exemplary embodiment, generating a set of trajectory changes of the solar vector within the target orbital period in a first coordinate system of the target operating device by using the orbital parameters includes: generating a first set of trajectory changes of the solar vector in a second coordinate system within the target orbital period by using the first angle and the set of angles of the second angle, where the second coordinate system is a coordinate system generated based on the Earth, and the values in the first set of trajectory changes are the coordinates of the solar vector in the second coordinate system; converting the first set of trajectory changes into a second set of trajectory changes in a third coordinate system by using a coordinate transformation matrix, where the coordinate transformation matrix is a matrix for coordinate transformation between the second coordinate system and the third coordinate system, the values in the second set of trajectory changes are the coordinates of the solar vector in the third coordinate system, and the third coordinate system is a coordinate system generated based on the target operating device; and determining the second set of trajectory changes as the set of trajectory changes when the first coordinate system coincides with the third coordinate system.

[0008] In an exemplary embodiment, after generating a set of trajectory changes of the solar vector within the target orbital period in a first coordinate system of the target operating device by using the orbital parameters, the method further includes: calculating, by using the average radius of the Earth and the orbital altitude, an angle of the visible range of the Earth's surface when the target operating device operates on the target orbit in the view of the target operating device to obtain a third angle; comparing the first angle with the third angle to obtain a comparison result; and generating a trajectory change diagram of the solar vector in the first coordinate system within the target orbital period based on the comparison result and the set of trajectory changes.

[0009] In an exemplary embodiment, after comparing the first angle and the third angle and obtaining a comparison result, the method further includes: when the absolute value of the first angle is less than the third angle, calculating, using the third angle and the first angle, an angle of a fan-shaped area formed by the earth blocking sunlight when the target operating device runs on the target orbit in the perspective of the target operating device, to obtain a fourth angle; and calculating a shadow coverage range of the target orbit using the fourth angle to obtain a target range.

[0010] In an exemplary embodiment, generating a trajectory change diagram of the solar vector in the first coordinate system within the target orbit period based on the comparison result and the trajectory change set includes one of the following: when the first angle is within a first preset range and the absolute value of the first angle is greater than or equal to the third angle, plotting the trajectory change of the solar vector in the first coordinate system within the target orbit period to obtain the trajectory change diagram; when the first angle is a first preset threshold, plotting the trajectory change of the solar vector in the first coordinate system within the target orbit period to obtain the trajectory change diagram; when the first angle is within a second preset range and the absolute value of the first angle is greater than or equal to the third angle, plotting the trajectory change of the solar vector in the first coordinate system within the target orbit period to obtain the trajectory change diagram; when the first angle is a second preset threshold, plotting the trajectory change of the solar vector in the first coordinate system within the target orbit period to obtain the trajectory change diagram; when the first angle is a third preset threshold, plotting the trajectory change of the solar vector in the first coordinate system within the target orbit period to obtain the trajectory change diagram.

[0011] In an exemplary embodiment, generating a solar radiation change set of the target operating device within the target orbit period based on the trajectory change set includes: respectively obtaining normal vectors of N outer surfaces of the target operating device in the first coordinate system to obtain N normal vectors, where N is a natural number greater than or equal to 1; and calculating solar radiation values of the target operating device within the target orbit period using the trajectory change set and the N normal vectors to obtain the solar radiation change values.

[0012] In an exemplary embodiment, after generating the solar radiation change set of the target operating device within the target orbit period based on the above trajectory change set, the method further includes: at a first angle, using the values in the solar radiation change set to plot the solar radiation change of the target operating device within the target orbit period, obtaining a solar radiation change diagram, where the first angle is used to represent the pitch angle between the solar vector and the orbital plane of the target orbit.

[0013] According to another embodiment of the present application, there is provided a device for generating a solar radiation change set, including a first memory, a first processor, and a first computer program stored on the first memory and executable on the first processor. When the first processor executes the first computer program, the following operations are implemented: obtaining the orbital parameters of the target operating device within the target orbit period, where the orbital parameters are used to represent the position and operating state of the target operating device running on the target orbit, and the target orbit period is the time for the target operating device to run one week on the target orbit; using the orbital parameters to generate a trajectory change set of the solar vector within the target orbit period in the first coordinate system of the target operating device, where the values in the trajectory change set are the coordinates of the solar vector in the first coordinate system; generating the solar radiation change set of the target operating device within the target orbit period based on the trajectory change set, where the values in the solar radiation change set are the radiation values of the solar radiation external heat flux received by the target operating device within the target orbit period.

[0014] According to still another embodiment of the present application, there is also provided a computer program product, including a computer program, where when the computer program is executed by a processor, the steps in any one of the above method embodiments are implemented.

[0015] According to still another embodiment of the present application, there is also provided a computer-readable storage medium, where a computer program is stored in the computer-readable storage medium, and the computer program is set to execute the steps in any one of the above method embodiments when running.

[0016] According to still another embodiment of the present application, there is also provided an electronic device, including a memory and a processor, where a computer program is stored in the memory, and the processor is set to run the computer program to execute the steps in any one of the above method embodiments.

[0017] Through this application, by using the orbital parameters of the target operating device within the target orbital period, a set of trajectory changes of the solar vector within the target orbital period in the first coordinate system of the target operating device is generated, and based on the set of trajectory changes, a set of changes in solar radiation within the orbital period is generated, that is, the radiation value of the external heat flux of solar radiation received by the target operating device. Therefore, the problem in the related art of being unable to determine the change law of sunlight irradiation in the first coordinate system of the target operating device can be solved, and further, the effect of being able to intuitively and quantitatively analyze the law of sunlight irradiation received by the target operating device is achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of the hardware environment of a method for generating a set of solar radiation changes according to an embodiment of the present application;

[0019] Figure 2 is a flowchart of a method for generating a set of solar radiation changes according to an embodiment of the present application;

[0020] Figure 3 is a schematic diagram of the direction of the solar vector and views A and B according to an embodiment of the present application;

[0021] Figure 4 is a schematic diagram of the second / third coordinate system and the geocentric inertial coordinate system according to an embodiment of the present application;

[0022] Figure 5 is a schematic diagram of the azimuth angle and elevation angle of the solar vector according to an embodiment of the present application;

[0023] Figure 6 is a schematic diagram of the overlapping of the plane projections of two views according to an embodiment of the present application;

[0024] Figure 7 is a schematic diagram of the geometric model of a target operating device according to an embodiment of the present application;

[0025] Figure 8 is a schematic diagram of the solar vector in the first coordinate system of the satellite according to an embodiment of the present application;

[0026] Figure 9 is the trajectory change of the solar vector according to an embodiment of the present application Figure 1 ;

[0027] Figure 10 is the trajectory change of the solar vector according to an embodiment of the present application Figure 2 ;

[0028] Figure 11 is the trajectory change of the solar vector according to an embodiment of the present application Figure 3 ;

[0029] Figure 12 is the change of the solar vector trajectory according to the embodiments of the present application Figure 4 ;

[0030] Figure 13 is the change of the solar vector trajectory according to the embodiments of the present application Figure 5 ;

[0031] Figure 14 is a flowchart of a method for generating a set of solar radiation changes on each outer surface of a satellite according to the embodiments of the present application;

[0032] Figure 15 is the change of the solar vector trajectory in the first coordinate system of the satellite according to the embodiments of the present application Figure 1 ;

[0033] Figure 16 is the change of the solar vector trajectory in the first coordinate system of the satellite according to the embodiments of the present application Figure 2 ;

[0034] Figure 17 is the change of the solar vector trajectory in the first coordinate system of the satellite according to the embodiments of the present application Figure 3 ;

[0035] Figure 18 is the TD simulation of solar radiation change in the related art Figure 1 ;

[0036] Figure 19 is the solar radiation change on each outer surface of a satellite according to the embodiments of the present application Figure 1 ;

[0037] Figure 20 is the TD simulation of solar radiation change in the related art Figure 2 ;

[0038] Figure 21 is the solar radiation change on each outer surface of a satellite according to the embodiments of the present application Figure 2 ;

[0039] Figure 22 is the TD simulation of solar radiation change in the related art Figure 3 ;

[0040] Figure 23 is the solar radiation change on each outer surface of a satellite according to the embodiments of the present application Figure 3 ;

[0041] Figure 24 is a structural block diagram of a device for generating a set of solar radiation changes according to the embodiments of the present application. Detailed implementation manners

[0042] In the following, embodiments of the present application will be described in detail with reference to the accompanying drawings and in conjunction with the embodiments.

[0043] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and do not necessarily need to describe a specific order or sequence.

[0044] The method embodiments provided in the embodiments of the present application can be executed on a server device or a similar computing device. Taking the operation on a server device as an example, Figure 1 is a schematic diagram of the hardware environment of a method for generating a set of solar radiation changes according to an embodiment of the present application. As Figure 1 shown, the server device may include one or more ( Figure 1 only one is shown in the figure) processors 102 (the processor 102 may include, but is not limited to, a processing device such as a microprocessor MCU or a programmable logic device FPGA) and a memory 104 for storing data. Among them, the above-mentioned server device may further include a transmission device 106 for communication functions and an input / output device 108. Those of ordinary skill in the art can understand that Figure 1 the structure shown is only schematic and does not limit the structure of the above-mentioned server device. For example, the server device may further include more or fewer components than Figure 1 shown in the figure, or have a different configuration from Figure 1 shown in the figure.

[0045] The memory 104 can be used to store computer programs. For example, software programs and modules of application software, such as the computer program corresponding to a method for generating a set of solar radiation changes in the embodiments of the present application. The processor 102 executes various functional applications and data processing by running the computer program stored in the memory 104, that is, implements the above-mentioned method. The memory 104 may include a high-speed random access memory, and may also include a non-volatile memory, such as one or more magnetic storage devices, flash memories, or other non-volatile solid-state memories. In some instances, the memory 104 may further include a memory remotely provided with respect to the processor 102, and these remote memories can be connected to the server device through a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an enterprise intranet, a local area network, a mobile communication network, and their combinations.

[0046] The transmission device 106 is used to receive or send data via a network. Specific examples of the above network may include a wireless network provided by a communication provider of a server device. In one example, the transmission device 106 includes a network adapter (Network Interface Controller, abbreviated as NIC), which can be connected to other network devices through a base station so as to communicate with the Internet. In one example, the transmission device 106 can be a Radio Frequency (RF) module, which is used to communicate with the Internet wirelessly.

[0047] In this embodiment, a method for generating a set of solar radiation changes is provided. Figure 2 It is a flowchart of a method for generating a set of solar radiation changes according to an embodiment of the present application, as Figure 2 shown, and the process includes the following steps:

[0048] Step S202, obtain the orbital parameters of the target operating device within the target orbital period, where the orbital parameters are used to represent the position and operating state of the target operating device on the target orbit, and the target orbital period is the time for the target operating device to orbit once on the target orbit;

[0049] Optionally, the target operating device in this embodiment is a device orbiting the Earth, including but not limited to satellites, spacecrafts, and detectors, which orbit on the orbit and perform specific tasks such as communication, remote sensing, and navigation.

[0050] Optionally, the target orbital period in this embodiment is the time for the target operating device to orbit once on the target orbit. For example: when the target operating device is a satellite, the target orbital period T is the time for the satellite to move once on the orbital plane, and this period depends on the height and shape of the orbit.

[0051] For example, when the target operating device is a communication satellite in a geosynchronous orbit, its orbital period can be 24 hours. The orbital parameters can be: orbital height h = 35,786 kilometers (standard geostationary orbit height), orbital inclination β = 0° (inclination of the geosynchronous orbit), and other orbital parameters such as the right ascension of the ascending node and the argument of perigee, which are determined according to specific tasks and orbital design requirements.

[0052] Step S204, generate a set of trajectory changes of the solar vector within the target orbital period in the first coordinate system of the target operating device by using the above orbital parameters, where the values in the set of trajectory changes are the coordinates of the solar vector in the first coordinate system;

[0053] Optionally, the first coordinate system in this embodiment is a coordinate system generated based on the operating attitude of the target operating device, and can also be referred to as the body coordinate system. For example, when the target operating device is a satellite, the first coordinate system is the satellite body coordinate system. The coordinate origin O of the satellite body coordinate system is located at the centroid of the satellite. The X-axis is in the orbital plane of the satellite, perpendicular to the satellite position vector r, and points in the direction of the satellite's motion velocity. The Z-axis is in the orbital plane of the satellite and points towards the center of the earth. The Y-axis is perpendicular to the orbital plane of the satellite and satisfies the right-hand screw rule to describe the attitude and motion of the satellite itself.

[0054] Optionally, the solar vector in this embodiment is a unit vector used to represent the direction from the geometric center of the target operating device to the geometric center of the sun. For example, when the target operating device is a satellite, in the satellite body coordinate system (i.e., the above-mentioned first coordinate system), the solar vector is a unit vector pointing from the geometric center of the satellite to the geometric center of the sun, and is used to describe the direction of the sun relative to the satellite. The solar vector can be decomposed into the coordinate values of the X, Y, and Z axes in the satellite body coordinate system, and these coordinate values change with the position of the satellite in the orbit.

[0055] Optionally, the trajectory change set in this embodiment is a set of changes of the solar vector over time in the first coordinate system, including the changes of the coordinate values of the solar vector in the X, Y, and Z axis directions over time at each time.

[0056] For example, when the target operating device is a satellite, based on the orbital parameters, methods such as Kepler's equation or Newton's iterative method can be used to calculate the position and velocity of the satellite at any moment within the orbital period. The azimuth and elevation angles of the sun relative to the satellite can be calculated from the unit vector pointing from the centroid of the satellite to the center of the sun, and these angles change with the position of the satellite in the orbit. The solar vector can be transformed from the geocentric inertial coordinate system to the first coordinate system of the satellite to facilitate further analysis of the impact of solar radiation on the satellite.

[0057] Step S206, generate the solar radiation change set of the target operating device within the target orbital period based on the above trajectory change set, where the values in the solar radiation change set are the radiation values of the solar radiation external heat flux received by the target operating device within the target orbital period.

[0058] Optionally, the solar radiation change set in this embodiment is based on the solar vector trajectory change set, including the radiation values of the solar radiation external heat flux received by each outer surface of the target operating device at each moment. For example, it can be the set of solar radiation external heat fluxes received by each surface of the satellite calculated within the orbital period, reflecting the change of the satellite's thermal environment over time.

[0059] Through the above steps, using the orbital parameters of the target operating device within the target orbital period, a set of trajectory changes of the solar vector within the target orbital period in the first coordinate system of the target operating device is generated, and based on the set of trajectory changes, a set of changes in solar radiation within the orbital period is generated, that is, the external heat flux radiation value of the sun received by the target operating device. Therefore, the problem in the related art of being unable to determine the change law of sunlight irradiation in the first coordinate system of the target operating device can be solved, and further, the effect of being able to intuitively and quantitatively analyze the law of sunlight irradiation received by the target operating device is achieved.

[0060] In an exemplary embodiment, obtaining the orbital parameters of the target operating device within the target orbital period includes: obtaining a first angle and the orbital altitude of the target orbit, where the first angle is used to represent the pitch angle between the solar vector and the orbital plane of the target orbit; obtaining a set of angles of a second angle within the target orbital period, where the second angle is used to represent the azimuth angle of the solar vector; and determining the first angle, the orbital altitude, and the set of angles of the second angle as the orbital parameters.

[0061] Optionally, the first angle in this embodiment is used to represent the pitch angle between the solar vector and the orbital plane of the target orbit where the target operating device is located, and the range is from -90° to +90°. This angle determines the directness of the solar radiation received on the surface of the target operating device. The second angle is the angle between the solar vector in the orbital plane of the target operating device and a certain fixed reference direction (for example, the positive X-axis direction of the target orbit), and the range is from 0° to 360°. The change in the azimuth angle describes the periodic rotation of the solar vector relative to the horizontal direction of the target operating device.

[0062] Optionally, as Figure 3 shown, it is a schematic diagram of the direction of the solar vector according to an embodiment of the present application. Among them, the B-direction orbital view is perpendicular to the orbital plane, and in the B-direction view, the target operating device flies counterclockwise around the earth, and the A-direction orbital view is the solar irradiation direction. In both views, the earth is a sphere with a radius of R, represents the orbital plane of the target orbit. The first angle can be calculated by subtracting the angle between the direction of solar irradiation and the normal of the orbital plane of the target operating device from 90°, Figure 3 where the vector n in represents the normal of the orbital plane of the target operating device, represents the angle between the direction of solar irradiation and the normal of the orbital plane of the target operating device,

[0063] Through the above steps, by obtaining the variation sets of the first angle (pitch angle), orbital altitude, and the second angle (azimuth angle) within the orbital period, and then combining the first angle, orbital altitude, and the variation set of the second angle, the complete orbital parameters are determined. The angular relationship between the solar vector and the orbital plane can be accurately described, providing a key input for subsequent analysis. Through the angle sets, the variation of the solar vector over time can be comprehensively reflected, enhancing the accuracy and reliability of the analysis.

[0064] In an exemplary embodiment, the trajectory variation set of the solar vector within the target orbital period is generated in the first coordinate system of the target operating device by using the above orbital parameters, including: generating a first trajectory variation set of the solar vector in the second coordinate system within the target orbital period by using the angle sets of the first angle and the second angle, where the second coordinate system is a coordinate system generated based on the Earth, and the values in the first trajectory variation set are the coordinates of the solar vector in the second coordinate system; converting the first trajectory variation set into a second trajectory variation set in the third coordinate system by using a coordinate transformation matrix, where the coordinate transformation matrix is a matrix for coordinate transformation between the second coordinate system and the third coordinate system, and the values in the second trajectory variation set are the coordinates of the solar vector in the third coordinate system, and the third coordinate system is a coordinate system generated based on the target operating device; when the first coordinate system coincides with the third coordinate system, determining the second trajectory variation set as the trajectory variation set.

[0065] Optionally, in this embodiment, the second coordinate system is a coordinate system generated based on the Earth, and the origin of the second coordinate system is the geocenter.

[0066] Optionally, in this embodiment, the third coordinate system is a coordinate system generated based on the target operating device, and the origin of the third coordinate system is the center of mass of the target operating device.

[0067] Optionally, in this embodiment, the Geocentric Inertial Coordinate System (abbreviated as GCI) is also used. The origin of the geocentric inertial coordinate system is at the center of mass of the Earth, fixed in space, and does not change with the rotation of the Earth or the orbital motion of the target operating device. Based on the geocentric inertial coordinate system, the parameters of the operating orbit of the target operating device (such as orbital altitude, orbital period, etc.) and the orbital position can be quantitatively described, which are used for subsequent calculation of the orbital motion of the satellite.

[0068] Optionally, as Figure 4 shown, is a schematic diagram of the coordinate system in this embodiment, as Figure 4As shown, when the target operating device is a satellite, the second coordinate system (also known as the perifocal coordinate system, abbreviated as PCS) has its origin O at the center of the earth, the axis points from the center of the earth to the satellite, that is, along the direction of the satellite position vector r, the axis is in the orbital plane of the satellite and is perpendicular to r and points in the forward direction of motion, the axis is perpendicular to the orbital plane and points in the direction of the orbital angular momentum, where the satellite position vector r is the vector in the orbital plane from the center of the earth to the current position of the satellite; the third coordinate system (Local-Vertical Local-Horizontal Coordinate System, abbreviated as LVLHS) has its origin located at the center of mass of the satellite, the axis is in the orbital plane, perpendicular to the satellite position vector r, and points in the forward direction of motion, the axis is in the orbital plane and points towards the center of the earth, the axis is perpendicular to the orbital plane and satisfies the right-hand screw rule; the geocentric inertial coordinate system has its origin O at the center of mass of the earth, and the plane coincides with the earth's equatorial plane, the axis is the earth's axis of rotation and points towards the north pole of the earth, the axis points towards the vernal equinox, the axis is determined according to the right-hand rule.

[0069] Optionally, the coordinate transformation matrix P from the second coordinate system to the third coordinate system can be expressed as: .

[0070] Optionally, the second angle in this embodiment is used to represent the azimuth angle of the solar vector. As Figure 5 shown, when the target operating device is a satellite, the axis represents the + axis of the second coordinate system, the vector H represents the + axis of the second coordinate system, the projection of the solar vector S on the orbital plane and the included angle is φ angle (i.e., the above-mentioned second angle, the azimuth angle of the solar vector S), the included angle between the solar vector S and the orbital plane is β angle (i.e., the above-mentioned first angle, the elevation angle of the solar vector S), where the change range of the second angle is [0°, 360°], and the satellite orbiting once on the operating orbit is equivalent to the second coordinate system orbiting once around the vector H.

[0071] Optionally, Figure 5 in the axis, the axis, The axes are the X, Y, and Z axes of the third coordinate system. The cube in the figure represents the satellite, and the elliptical dashed line represents the trajectory of the solar vector in the second coordinate system when the satellite orbits once.

[0072] Optionally, in this embodiment, when the first coordinate system coincides with the above-mentioned third coordinate system and the coordinate transformation matrix is P, in the first coordinate system, the solar vector can be expressed as , and the solar vector can be transformed to be expressed in the third coordinate system by using the coordinate transformation matrix P: , since the first coordinate system coincides with the third coordinate system, the solar vector in the first coordinate system = .

[0073] Through the above steps, when the first angle is greater than the preset threshold, a first trajectory change set of the solar vector is generated in the second coordinate system, and then the first trajectory change set is converted to the third coordinate system by using the coordinate transformation matrix to generate a second trajectory change set. If the first coordinate system coincides with the third coordinate system, the second trajectory change set is the final trajectory change set. Through coordinate transformation, the conversion of solar radiation analysis from the Earth's perspective to the device body perspective is realized.

[0074] In an exemplary embodiment, after generating a trajectory change set of the solar vector in the first coordinate system of the above-mentioned target operating device within the above-mentioned target orbit period by using the above-mentioned orbital parameters, the method further includes: calculating, by using the average radius of the Earth and the above-mentioned orbital altitude, the angle of the visible range of the Earth's surface when the above-mentioned target operating device operates on the above-mentioned target orbit in the perspective of the above-mentioned target operating device to obtain a third angle; comparing the above-mentioned first angle with the above-mentioned third angle to obtain a comparison result; and generating a trajectory change diagram of the above-mentioned solar vector in the first coordinate system within the above-mentioned target orbit period based on the above-mentioned comparison result and the above-mentioned trajectory change set.

[0075] Optionally, in this embodiment, the average radius of the Earth is approximately 6378.137 km, and in Figure 3 , R represents the average radius of the Earth.

[0076] Optionally, the orbital altitude is the average altitude of the target orbit from the Earth's surface. It affects the perspective of the target operating device relative to the Earth and whether it can continuously receive solar radiation.

[0077] Optionally, in this embodiment, the third angle represents the angle of the visible range of the Earth's surface when the above-mentioned target operating device operates on the above-mentioned target orbit in the perspective of the above-mentioned target operating device. In Figure 3 , represents the semi-angle of the Earth (i.e., the above-mentioned third angle), and the third angle can be determined by the following formula: , where R represents the average radius of the Earth and h represents the orbital altitude of the target operating device.

[0078] Optionally, in this embodiment, by comparing the first angle and the third angle, it can be determined whether the satellite will enter the Earth's shadow area within the orbital period.

[0079] For example, Figure 6 is a schematic diagram of the overlapping of the planar projections of two views according to an embodiment of the present application. As Figure 6 shown, when the target operating device is a satellite, the large black circle represents the operating orbit of the satellite (i.e., the above-mentioned target orbit) from the B-direction perspective (the B-direction perspective in the above Figure 3 ), that is, the orbital contour of the satellite orbit observed from the satellite's perspective, and the center point O is the centroid of the Earth; the small black circle shows the projection of the Earth from the B-direction perspective, providing an intuitive framework for the shape and size of the Earth for the satellite; the elliptical dashed line represents the orbit from the A-direction perspective (the A-direction perspective in the above Figure 3 ), expressing the geometric relationship between the critical orbit and the Earth; the solid-line ellipse represents the shadow orbit when the β angle continues to decrease to the critical β angle and there is a shadow area in the satellite orbit during the operation of the satellite orbit, indicating the geometric position relationship between the satellite orbit and the Earth, which is the visual projection of the position of the satellite on its target orbit relative to the Earth. The size and position of the ellipse depend on the orbital altitude h of the satellite. The ellipse is used to visually represent the boundary of the satellite orbit in the Earth's shadow area, that is, when the satellite orbit enters the Earth's shadow area and when it returns to the full-light state; when the elliptical part is within the large black circle, the satellite is in the Earth's shadow area and solar radiation will disappear, and when the ellipse is completely outside the large black circle, the satellite is in the full-light state; the shadow orbit is the orbit when the satellite enters the Earth's shadow range during its operation around the Earth; the gray dashed-line ellipse represents the critical orbit, that is, the orbital condition defined by the demarcation point between solar illumination and entry into the Earth's shadow in the satellite orbit. The β angle (i.e., the above-mentioned first angle) of the critical orbit is the critical β angle, which is the demarcation line between the orbital shadow area and the full-light area. For a circular orbit, the critical β angle is only related to the orbital altitude. When the β angle of the satellite orbit is greater than the critical β angle, the satellite will be in the full-light state and will not enter the Earth's shadow area; when the β angle is less than the critical β angle, there will be a shadow area in the satellite orbit; the line segment NC represents the orbital altitude h of the target operating device, and the line segment represents the average radius of the Earth, and the point H / N / C is the heliocentric point, that is, the point on the orbital plane where the target operating device is closest to the sun.

[0080] Optionally, the trajectory change diagram in this embodiment can be obtained by analyzing using the geometric analysis software GeoGebra.

[0081] Through the above steps, calculate the visible angle of the Earth's surface from the perspective of the target operating device (the third angle). Then, based on the comparison result between the first angle and the third angle and the set of trajectory changes, generate a trajectory change diagram of the solar vector in the first coordinate system. Through the trajectory change diagram, the change trajectory of the solar vector can be intuitively displayed, and the shadow and illumination states of the target operating device within the orbital period can be clearly identified.

[0082] In an exemplary embodiment, after comparing the above first angle and the above third angle to obtain a comparison result, the method further includes: when the absolute value of the first angle is less than the third angle, use the third angle and the first angle to calculate the angle of the fan-shaped area formed by the Earth blocking sunlight when the target operating device operates on the target orbit from the perspective of the target operating device, obtaining a fourth angle; use the fourth angle to calculate the shadow coverage range of the target orbit, obtaining a target range.

[0083] Optionally, in this embodiment, the absolute value of the first angle being less than the third angle indicates that there is a shadow area in the target orbit; the absolute value of the first angle being greater than or equal to the third angle indicates that the target orbit is a fully illuminated orbit without a shadow area. When the third angle is represented by and the first angle is represented by the β angle, when , it indicates that there is a shadow area in the target orbit; when , it indicates that the target orbit is a fully illuminated orbit without a shadow area.

[0084] Optionally, in this embodiment, the fourth angle represents the angle of the fan-shaped area formed by the Earth blocking sunlight when the target operating device operates on the target orbit from the perspective of the target operating device. In Figure 6 , represents the half angle η of the shadow area (i.e., the above fourth angle). The half angle of the shadow area is related to the β angle (i.e., the above first angle). As the β angle decreases to 0°, the perpendicular line moves to the right and becomes . is tangent to the projection of the Earth's plane. At this time, the half angle of the shadow area is the largest. The range of the half angle of the shadow area is [0°, , where Figure 6 in , and the intersection point of the shadow orbit and the projection of the Earth's plane is .

[0085] Optionally, in this embodiment, the fourth angle η can be calculated according to the third angle (or the orbital height h and the average radius R of the Earth) and the first angle β through the following formula: , according to the fourth angle, the duration of the shadow area that appears due to the earth blocking the sun when the target operating device operates on the target orbit can be calculated through the following formula , where T represents the above-mentioned target orbit period, that is, the time for the target operating device to complete one orbit on the target orbit.

[0086] Optionally, the target range in this embodiment represents the shadow coverage range of the target orbit. When the fourth angle is represented by η, the target range is .

[0087] Through the above steps, if the absolute value of the first angle is less than the third angle, calculate the angle of the fan-shaped area formed by the earth's occlusion (i.e., the above-mentioned fourth angle), and then use the fourth angle to calculate the shadow coverage range of the target orbit to obtain the target range. The specific angle range where the target operating device encounters shadow occlusion on the orbit is provided, which is convenient for subsequent determination of the occlusion area and non-occlusion area of the target operating device within the orbit period.

[0088] In an exemplary embodiment, based on the above comparison result and the above trajectory change set, a trajectory change diagram of the above solar vector in the above first coordinate system within the above target orbit period is generated, including one of the following: when the above first angle is within the first preset range and the absolute value of the above first angle is greater than or equal to the above third angle, draw the trajectory change of the above solar vector in the above first coordinate system within the above target orbit period to obtain the above trajectory change diagram; when the above first angle is the first preset threshold, draw the trajectory change of the above solar vector in the above first coordinate system within the above target orbit period to obtain the above trajectory change diagram; when the above first angle is within the second preset range and the absolute value of the above first angle is greater than or equal to the above third angle, draw the trajectory change of the above solar vector in the above first coordinate system within the above target orbit period to obtain the above trajectory change diagram; when the above first angle is the second preset threshold, draw the trajectory change of the above solar vector in the above first coordinate system within the above target orbit period to obtain the above trajectory change diagram; when the above first angle is the third preset threshold, draw the trajectory change of the above solar vector in the above first coordinate system within the above target orbit period to obtain the above trajectory change diagram.

[0089] Optionally, the first preset range, the first preset threshold, the second preset range, the second preset threshold, and the third preset threshold in this embodiment are all specific ranges or thresholds of the β angle (the angle between the solar vector and the orbital plane) defined in the orbital analysis of the target operating device. They are used to distinguish different thermal environment conditions of the target orbit, such as full sunlight state, shadow state, and critical conditions.

[0090] Optionally, the trajectory change diagram in this embodiment can be obtained by analyzing using the geometric analysis software GeoGebra.

[0091] Optionally, in this embodiment, the first preset range can be (0°, 90°), and the first angle is within the first preset range, that is, 0° < β < 90°; the second preset range can be (-90°, 0°), and the first angle is within the first preset range, that is, 0° < β < 90°; the first preset threshold can be 0°; the second preset threshold can be 90°; the third preset threshold can be -90°.

[0092] Optionally, as Figure 7 shown, it is a schematic diagram of the geometric model of a target operating device according to an embodiment of the present application. The positive X, Y, and Z planes of the geometric model of the target operating device are black, and the negative X, Y, and Z planes are gray. The operating attitude of the target operating device is that the three axes (i.e., the X-axis, Y-axis, and Z-axis) of the target operating device are all stable relative to the earth. Among them, the X-axis of the target operating device points to the flight direction of the target operating device, and the Z-axis points to the center of the earth. Within one target orbit period, it is assumed that the first angle remains fixed.

[0093] Optionally, as Figure 8 shown, it is a schematic diagram of the solar vector in the first coordinate system of the satellite according to an embodiment of the present application, and it is a schematic diagram of the solar vector S on a certain outer surface of the satellite at a certain moment in the first coordinate system of the satellite.

[0094] Optionally, Figure 9 is the solar vector trajectory change according to an embodiment of the present application Figure 1 , as Figure 9 shown, when the target operating device is a satellite and the first angle is represented by β, when 0° < β < 90° and there is no shadow area, the sunlight irradiates the satellite from the -Y side of the first coordinate system of the satellite, and the change of the solar vector forms a cone.

[0095] Optionally, Figure 10 is the solar vector trajectory change according to an embodiment of the present application Figure 2 , as Figure 10 shown, when the target operating device is a satellite and the first angle is represented by β, when β = 0°, the change of the solar vector forms a sector, and the notch of the sector is the shadow area.

[0096] Optionally, Figure 11 is the solar vector trajectory change according to an embodiment of the present application Figure 3 , as Figure 11 shown, when the target operating device is a satellite and the first angle is represented by β, when -90° < β < 0° and there is no shadow area, the sunlight irradiates the satellite from the +Y side of the first coordinate system of the satellite, and the change of the solar vector forms a cone.

[0097] Optionally, Figure 12 is the change of the solar vector trajectory according to the embodiments of the present application Figure 4 , as Figure 12 shown, when the target operating device is a satellite and the first angle is represented by β, when the β angle = 90°, the sunlight perpendicularly irradiates the -Y plane of the satellite body.

[0098] Optionally, Figure 13 is the change of the solar vector trajectory according to the embodiments of the present application Figure 5 , as Figure 13 shown, when the target operating device is a satellite and the first angle is represented by β, when the β angle = -90°, the sunlight perpendicularly irradiates the +Y plane of the satellite body.

[0099] For example, when the target operating device is a satellite, the specific implementation steps for generating the trajectory change diagram include:

[0100] Step S302, based on the comparison result of the first angle (β angle) and the third angle (the half-earth perspective ), select a suitable preset range or threshold to generate the trajectory change diagram.

[0101] Step S304, when the β angle is within the first preset range and the absolute value of the β angle is greater than or equal to the third angle (the half-earth perspective ), the satellite will not enter the earth's shadow area, and the direction of the solar vector shows a continuously changing trajectory in the first coordinate system, as Figure 12 , Figure 13 shown, the solar vector perpendicularly irradiates the Y plane of the satellite, and the satellite is in a fully illuminated state.

[0102] Step S306, when the β angle is equal to the first preset threshold, which usually corresponds to a critical condition, the trajectory change diagram of the solar vector will show the critical point where the satellite transitions from the fully illuminated state to the shadow state, as Figure 6 shown by the sector-shaped notch in, indicating the existence of the shadow area.

[0103] Step S308, when the β angle is within the second preset range and the absolute value of the β angle is greater than or equal to the third angle (the half-earth perspective ), the satellite is still in a fully illuminated state, and the trajectory change diagram will show the change of the solar vector direction in the first coordinate system of the satellite, similar to the situation in step S304.

[0104] Step S310, when the β angle is equal to the second preset threshold, which is usually also a critical condition, the trajectory change diagram will highlight the turning point where the satellite enters or leaves the earth's shadow area, helping to understand the change of the satellite's thermal environment.

[0105] Step S312, when the β angle is equal to the third preset threshold, the trajectory change diagram will focus on the change in the direction of the solar vector when the satellite is at the edge of the shadow area, which helps to more accurately evaluate the thermal environment and duration of the satellite in the shadow area.

[0106] Step S314, use geometric analysis software (such as GeoGebra) or custom programming tools (such as MATLAB, Python, etc.) to generate a trajectory change diagram of the solar vector in the first coordinate system of the satellite. This can be based on the first trajectory change set of the solar vector in the second coordinate system, transformed to the first coordinate system through a coordinate transformation matrix, and then identify and mark the shadow area according to the size relationship between the β angle and the size relationship.

[0107] Step S316, analyze the trajectory change diagram to determine the distribution and change of the external heat flux of solar radiation received by each surface of the satellite during the orbital period. This can be achieved by calculating the dot product of the solar vector and the normal vector of each surface of the satellite, and the magnitude of the dot product reflects the degree of direct solar radiation.

[0108] Step S318, compare and verify the trajectory change diagram with the actual satellite operation data or the simulation results of the thermal analysis software to ensure the accuracy and reliability of the analysis. This helps to optimize the thermal protection system and thermal management strategy during the satellite design phase to ensure the thermal stability and operation safety of the satellite under different orbital conditions.

[0109] Through the above steps, a trajectory change diagram of the solar vector in the first coordinate system of the satellite can be generated for a specific preset range or threshold, which is of great significance for deeply understanding the satellite thermal environment and evaluating its thermal protection requirements. In specific implementation, multiple data and analysis tools can be combined to generate more detailed and accurate thermal environment analysis results. For example, in Figures 8 to 13 it shows the trajectory change diagram of the solar vector and the change of the external heat flux of solar radiation under different β angle conditions, and this information is crucial for designing the satellite thermal protection system and optimizing its thermal management strategy.

[0110] In an exemplary embodiment, a solar radiation change set of the target operating device during the target orbital period is generated based on the above trajectory change set, including: respectively obtaining the normal vectors of N outer surfaces of the target operating device in the first coordinate system to obtain N normal vectors, where N is a natural number greater than or equal to 1; using the above trajectory change set and the N normal vectors to calculate the solar radiation value of the target operating device during the target orbital period to obtain the above solar radiation change value.

[0111] Optionally, in this embodiment, it is assumed that within a target orbital period, the first angle and the fourth angle remain fixed.

[0112] Optionally, in this embodiment, when the geometric model of the target operating device is as Figure 7 shown, it is possible to first determine whether the solar radiation value of each outer surface of the target operating device is 0 according to the coordinates of the solar vector; for the +Z and +Y planes of the target operating device, when the Z and Y axis coordinates of the solar vector S are less than or equal to 0, the solar radiation on the +Z and +Y planes is zero; for the -Z and -Y planes of the target operating device, when the Z and Y axis coordinates of the solar vector S are greater than or equal to 0, the solar radiation on the -Z and -Y planes is zero; for the -X and +X planes of the target operating device, since the rotation direction of the solar vector S in the first coordinate system of the target operating device (viewed from -Y to Y) is opposite to the movement direction of the target operating device in the geocentric inertial coordinate system (viewed from north to south), therefore, the azimuth angles of the solar vector S of the two differ by π.

[0113] Optionally, in this embodiment, Table 1 shows the solar radiation calculation conditions, that is, when the geometric model of the target operating device is as Figure 7 shown, the normal vectors of each outer surface of the target operating device and the conditions for zero solar radiation.

[0114] Table 1:

[0115]

[0116] Optionally, in this embodiment, in the first coordinate system of the target operating device, the change in the solar radiation external heat flux of each outer surface of the target operating device within a target orbit period can be calculated according to the projection of the solar vector S onto the normal vectors of each surface of the target operating device.

[0117] Optionally, when the geometric model of the target operating device is as Figure 7 shown, the target operating device is a satellite, and in the case of the second angle , , it means that there is a shadow area in the target orbit. The starting point of the second angle is the perihelion point, and the second angle ; the solar radiation values of each outer surface of the satellite can be calculated through the following formula: the solar radiation value of the +Z plane of the satellite ; the solar radiation value of the -Z plane of the satellite ; the solar radiation value of the +X plane of the satellite ; the solar radiation value of the -X plane of the satellite ; the solar radiation value of the +Y plane of the satellite ; the solar radiation value of the -Y plane of the satellite . The results calculated by the above formula are multiplied by the solar heat flux of 1414 W / m2 to obtain the solar radiation values of each outer surface of the target operating device in actual conditions. When , indicating that the target orbit is a full-illumination orbit with no shadow area. By setting η in the above formula to 0, the solar radiation values of each surface of the satellite can be obtained. Among them, represents the above first angle, represents the above second angle, represents the above third angle, η represents the above fourth angle, and S represents the solar vector.

[0118] Through the above steps, the normal vectors of the N outer surfaces of the target operating device are obtained, and combined with the trajectory change set, the solar radiation values of each outer surface within the orbit period are calculated to provide a quantitative evaluation of the solar radiation intensity for each outer surface.

[0119] In an exemplary embodiment, after generating the solar radiation change set of the target operating device within the target orbit period based on the above trajectory change set, the method further includes: at the first angle, using the values in the solar radiation change set, plotting the solar radiation change of the target operating device within the target orbit period to obtain a solar radiation change diagram, where the first angle is used to represent the pitch angle between the solar vector and the orbital plane of the target orbit.

[0120] Optionally, the solar radiation change diagram in this embodiment shows the solar radiation values of each outer surface of the target operating device under a target orbit period, including but not limited to being obtained through software analysis such as: COSMOS / MThermal Analysis, ESI Thermal Desktop (TD), ANSYS Fluent, SINDA / Gold, SABREThermal.

[0121] Optionally, the solar radiation change diagram in this embodiment includes but is not limited to being shown in the form of a line chart.

[0122] Through the above steps, at the first angle, using the solar radiation change set, a solar radiation change diagram is plotted. Through graphical display, the change trend of solar radiation within the orbit period is intuitively reflected, facilitating designers to understand the thermal environment of the target operating device and adjust the thermal control strategy.

[0123] The above method will be described below with a specific example. This embodiment takes a satellite as an example for illustration. The following is a specific embodiment involving the change of solar radiation external heat flux when a satellite operates in an inclined circular orbit:

[0124] This specific embodiment needs to define that the orbital altitude of the satellite's orbit is 500 km, the orbital inclination is 56.5°, the average radius of the earth is 6378.137 km, the range of β angle change within a year is -80° to 80°, and the critical β angle is ±68.02°.

[0125] In addition, the present specific embodiment needs to define a coordinate system: the second coordinate system: the origin O is the center of the earth, the axis points along the satellite position vector to the satellite position, the axis is perpendicular to the axis within the orbital plane, and the axis is perpendicular to the orbital plane and points to the direction of the orbital angular momentum. The third coordinate system (LVLHS): the origin is located at the center of mass of the spacecraft, the axis points in the forward direction of motion perpendicular to the position vector within the orbital plane, the axis points to the center of the earth within the orbital plane, and the axis is perpendicular to the orbital plane and satisfies the right-hand screw rule. The geocentric inertial coordinate system: the origin O is at the center of mass of the earth, and the plane coincides with the earth's equatorial plane, the axis is the earth's axis of rotation and points to the north pole, the axis points to the vernal equinox, and the axis is determined according to the right-hand rule. The satellite's first coordinate system: the origin O is located at the center of mass of the satellite, the X-axis points in the direction of the satellite's velocity perpendicular to the satellite position vector within the orbital plane, the Z-axis points to the center of the earth within the orbital plane, and the Y-axis is perpendicular to the orbital plane and satisfies the right-hand screw rule.

[0126] In this specific embodiment, Figure 14 is a flowchart of a method for generating a set of solar radiation changes on each outer surface of a satellite according to an embodiment of the present application. As Figure 14 shown, the process includes the following steps:

[0127] Step S1402: Obtain the orbital parameters of the satellite within the target orbital period. Here, the target orbital period is the time required for the satellite to orbit once on the satellite's operating orbit. The orbital parameters include the satellite's orbital altitude, orbital inclination, the range of pitch angle changes between the solar vector and the orbital plane of the target orbit within one year, and the critical β angle. The orbital parameters are shown in Table 2.

[0128] Table 2:

[0129]

[0130] Step S1404: Use the orbital parameters to generate a set of trajectory changes of the solar vector within the target orbital period in the satellite's first coordinate system, and draw a trajectory change diagram of the solar vector in the satellite's first coordinate system;

[0131] In this step, first calculate the earth view angle using the formula: According to the average radius of the earth and the orbital altitude, use the formula to calculate the half-earth view angle of the satellite, and determine whether the satellite's orbit enters the earth's shadow area based on this.

[0132] Secondly, generate a trajectory change diagram: When β = 0°, the satellite is in a critical condition, the solar vector trajectory is a sector, and there is a shaded area. Use GeoGebra software to draw the trajectory change diagram according to the change of the solar vector in the second coordinate system. When β = 30°, the satellite enters the earth's shadow area, and the solar vector trajectory is a truncated cone. Also use GeoGebra software to draw the trajectory change diagram. When β = 70°, the satellite is in a fully illuminated state, and the solar vector trajectory is a cone. Use GeoGebra software to generate the trajectory change diagram.

[0133] Among them, Figure 15 、 Figure 16 、 Figure 17 are respectively schematic diagrams of the trajectory change of a solar vector in the first coordinate system of the satellite according to an embodiment of the present application. Among them, Figure 15 is drawn under the condition that the first angle β = 0° and the half angle of the shaded area (i.e., the above-mentioned fourth angle) °. It is a schematic diagram of the set of trajectory changes of the solar vector within the target orbital period. In this case, the change of the solar vector forms a sector. Figure 16 is drawn under the condition that the first angle β = 30° and the half angle of the shaded area (i.e., the above-mentioned fourth angle) °. It is the set of trajectory changes of the solar vector within the target orbital period. Figure 17 is drawn under the condition that the first angle β = 70° and the half angle of the shaded area (i.e., the above-mentioned fourth angle) °. It is the set of trajectory changes of the solar vector within the target orbital period. In this case, the target orbit is a fully illuminated orbit, and the change of the solar vector forms a cone. Among them, Figure 15 、 Figure 16 and Figure 17 The cuboids in are all used to represent the geometric model of the satellite. The black surfaces represent the positive X, Y, and Z planes of the satellite, and the gray surfaces represent the negative X, Y, and Z planes of the satellite.

[0134] Step S1406, generate a solar radiation change set of the satellite within the target orbital period based on the trajectory change set, and draw a solar radiation change diagram of each outer surface of the satellite.

[0135] In this step, for each β-angle condition, use the formula to calculate the solar radiation external heat flux of each surface of the satellite at different β-angles. Assume that the β-angle of the satellite is fixed at 0°, 30°, and 70° to cover fully illuminated, shaded, and critical conditions.

[0136] The solar radiation variation graph is plotted using the values ​​in the solar radiation variation set. The horizontal axis represents time (different moments in the orbital period), and the vertical axis represents the solar radiation intensity (in W / m²). For the fully illuminated state (β =70°), the solar radiation intensity changes periodically during the orbital period, and there is no sudden drop to zero. For the shadowed state (β =30°), the solar radiation intensity variation graph will show the period when the solar radiation intensity is zero in the shadow area. For the critical state (β =0°), the solar radiation intensity variation graph will reflect the slight changes in solar radiation intensity when the satellite is at the edge of the shadow area.

[0137] Compare the results: Compare the solar radiation change graph with the simulation results of TD software (thermal analysis software) to verify the accuracy of the geometric visualization analysis method. Ensure that the trend of solar radiation intensity, the length and position of the shadow area, etc. are consistent with the simulation results of commercial software. Figure 18 It is the TD simulation solar radiation change of each outer surface of the satellite in the related technology Figure 1 , Figure 19 The solar radiation variation of each outer surface of the satellite according to the embodiment of the present application Figure 1 , Figure 18 and Figure 19 The solar radiation change diagrams of the satellite's various outer surfaces are drawn at the first angle β=0°. The horizontal axis represents time, and the vertical axis represents the solar radiation heat flow (i.e. the solar radiation value mentioned above). Figure 18 It is a map of solar radiation changes on the satellite's various outer surfaces drawn using software in related technologies. Figure 19 The solar radiation variation diagram of each outer surface of the satellite is drawn based on the solar radiation value calculated by the formula in the above method. Figure 18 NX.1 represents the solar radiation received by the -X surface of the satellite, NY.1 represents the solar radiation received by the -Y surface of the satellite, NZ.1 represents the solar radiation received by the -Z surface of the satellite, PX.1 represents the solar radiation received by the +X surface of the satellite, PY.1 represents the solar radiation received by the +Y surface of the satellite, and PZ.1 represents the solar radiation received by the +Z surface of the satellite. Figure 19 Geo_NX.1 represents the solar radiation received by the -X plane of the satellite, Geo_NY.1 represents the solar radiation received by the -Y plane of the satellite, Geo_NZ.1 represents the solar radiation received by the -Z plane of the satellite, Geo_PX.1 represents the solar radiation received by the +X plane of the satellite, Geo_PY.1 represents the solar radiation received by the +Y plane of the satellite, and Geo_PZ.1 represents the solar radiation received by the +Z plane of the satellite.

[0138] Optionally, Figure 20 It is the TD simulation solar radiation change of each outer surface of the satellite in the related technology Figure 2 , Figure 21is the solar radiation change on each outer surface of the satellite according to the embodiments of the present application Figure 2 , Figure 20 and Figure 21 are both solar radiation change diagrams of each outer surface of the satellite drawn under the condition that the first angle β = 30°. The abscissa represents time, and the ordinate represents the solar radiation heat flux (i.e., the above-mentioned solar radiation value). Figure 20 is a solar radiation change diagram of each outer surface of the satellite drawn using software in the related art Figure 21 is a solar radiation change diagram of each outer surface of the satellite drawn based on the solar radiation values calculated according to the formula in the above method Figure 20 In, NX.1 represents the solar radiation received by the -X surface of the satellite, NY.1 represents the solar radiation received by the -Y surface of the satellite, NZ.1 represents the solar radiation received by the -Z surface of the satellite, PX.1 represents the solar radiation received by the +X surface of the satellite, PY.1 represents the solar radiation received by the +Y surface of the satellite, and PZ.1 represents the solar radiation received by the +Z surface of the satellite Figure 21 In, Geo_NX.1 represents the solar radiation received by the -X surface of the satellite, Geo_NY.1 represents the solar radiation received by the -Y surface of the satellite, Geo_NZ.1 represents the solar radiation received by the -Z surface of the satellite, Geo_PX.1 represents the solar radiation received by the +X surface of the satellite, Geo_PY.1 represents the solar radiation received by the +Y surface of the satellite, and Geo_PZ.1 represents the solar radiation received by the +Z surface of the satellite

[0139] Optionally, Figure 22 is the TD simulation solar radiation change of each outer surface of the satellite in the related art Figure 3 , Figure 23 is the solar radiation change on each outer surface of the satellite according to the embodiments of the present application Figure 3 , Figure 22 and Figure 23 are both solar radiation change diagrams of each outer surface of the satellite drawn under the condition that the first angle β = 70°. The abscissa represents time, and the ordinate represents the solar radiation heat flux (i.e., the above-mentioned solar radiation value). Figure 22 is a solar radiation change diagram of each outer surface of the satellite drawn using software in the related art Figure 23 is a solar radiation change diagram of each outer surface of the satellite drawn based on the solar radiation values calculated according to the formula in the above method Figure 22 In, NX.1 represents the solar radiation received by the -X surface of the satellite, NY.1 represents the solar radiation received by the -Y surface of the satellite, NZ.1 represents the solar radiation received by the -Z surface of the satellite, PX.1 represents the solar radiation received by the +X surface of the satellite, PY.1 represents the solar radiation received by the +Y surface of the satellite, and PZ.1 represents the solar radiation received by the +Z surface of the satellite Figure 23Geo_NX.1 in it represents the solar radiation received by the -X plane of the satellite, Geo_NY.1 represents the solar radiation received by the -Y plane of the satellite, Geo_NZ.1 represents the solar radiation received by the -Z plane of the satellite, Geo_PX.1 represents the solar radiation received by the +X plane of the satellite, Geo_PY.1 represents the solar radiation received by the +Y plane of the satellite, and Geo_PZ.1 represents the solar radiation received by the +Z plane of the satellite.

[0140] By Figure 18 and Figure 19 , Figure 20 and Figure 21 , Figure 22 and Figure 23 Through comparison among them, it can be determined that the results calculated by the solar vector projection in the above method are basically the same as the TD simulation results, verifying the correctness of the formula calculation in the above method.

[0141] This embodiment also includes the step of data analysis, which is used to analyze the solar radiation variation map, determine the duration of the satellite in the shadow area and the full sunlight area, and evaluate the satellite's thermal protection and energy management requirements. For example, when the satellite enters the shadow area, it may be necessary to activate the thermal battery or use thermal insulation materials to maintain the equipment temperature.

[0142] Through the steps in the embodiment, it is possible to generate a solar vector trajectory variation map and a solar radiation variation map based on the orbital parameters and operating attitude of the satellite, which will help accurately predict the thermal environment in the satellite design and operation planning stages, thereby optimizing the thermal protection design and energy management strategy to ensure the stable operation and function realization of the satellite under different orbital conditions.

[0143] It should be noted that through the description of the above implementation manners, those skilled in the art can clearly understand that the method according to the above embodiments can be implemented by means of software plus a necessary general hardware platform. Of course, it can also be implemented by hardware, but in many cases the former is a better implementation manner. Based on such an understanding, the technical solution of the present application, in essence, or the part that makes contributions to the prior art, can be embodied in the form of a software product. This computer software product is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disc), including several instructions for causing a terminal device (which can be a mobile phone, computer, server, or network device, etc.) to execute the methods described in various embodiments of the present application.

[0144] In this embodiment, a generating device for a set of solar radiation changes is further provided. This device is used to implement the above-mentioned embodiments and preferred implementation manners, and those that have been described will not be repeated here. As used hereinafter, the term "module" can be a combination of software and / or hardware that can achieve a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, implementation in hardware, or a combination of software and hardware is also possible and contemplated.

[0145] Figure 24 is a structural block diagram of a generating device for a set of solar radiation changes according to an embodiment of the present application. As Figure 24 shown, the device includes: a first memory 242, a first processor 244, and a first computer program 24202 stored on the first memory 242 and executable on the first processor 244. It is characterized in that when the first processor 244 executes the first computer program 24202, the following operations are implemented: obtaining orbital parameters of a target operating device within a target orbital period, where the orbital parameters are used to represent the position and operating state of the target operating device running on the target orbit, and the target orbital period is the time for the target operating device to complete one revolution on the target orbit; generating a trajectory change set of the solar vector within the target orbital period in a first coordinate system of the target operating device by using the orbital parameters, where the values in the trajectory change set are the coordinates of the solar vector in the first coordinate system; generating a solar radiation change set of the target operating device within the target orbital period based on the trajectory change set, where the values in the solar radiation change set are the radiation values of the solar radiation external heat flux received by the target operating device within the target orbital period.

[0146] It should be noted that the above-mentioned respective modules can be implemented by software or hardware. For the latter, it can be achieved in the following ways, but not limited thereto: all the above-mentioned modules are located in the same processor; or, the above-mentioned respective modules are located in different processors in any combination form.

[0147] An embodiment of the present application further provides a computer-readable storage medium, in which a computer program is stored, and the computer program is configured to execute the steps in any one of the above method embodiments when running.

[0148] In an exemplary embodiment, the above computer-readable storage medium may include, but is not limited to: USB flash drives, read-only memories (ROM for short), random access memories (RAM for short), mobile hard disks, magnetic disks, or optical discs, and other various media that can store computer programs.

[0149] An embodiment of the present application further provides an electronic device, including a memory and a processor. A computer program is stored in the memory, and the processor is configured to run the computer program to execute the steps in any of the above method embodiments.

[0150] In an exemplary embodiment, the above electronic device may further include a transmission device and an input / output device. Among them, the transmission device is connected to the above processor, and the input / output device is connected to the above processor.

[0151] An embodiment of the present application further provides a computer program product. The above computer program product includes a computer program, and when the computer program is executed by a processor, it implements the steps in any of the above method embodiments.

[0152] An embodiment of the present application further provides another computer program product, including a non-volatile computer-readable storage medium. The non-volatile computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, it implements the steps in any of the above method embodiments.

[0153] An embodiment of the present application further provides a computer program. The computer program includes computer instructions, and the computer instructions are stored in a computer-readable storage medium; a processor of a computer device reads the computer instructions from the computer-readable storage medium, and the processor executes the computer instructions, so that the computer device executes the steps in any of the above method embodiments.

[0154] Specific examples in this embodiment may refer to the examples described in the above embodiments and exemplary embodiments, and will not be repeated here.

[0155] Obviously, those skilled in the art should understand that the above modules or steps of the present application can be implemented by a general-purpose computing device. They can be concentrated on a single computing device or distributed on a network composed of multiple computing devices. They can be implemented by program codes executable by the computing device, so that they can be stored in a storage device and executed by the computing device. And in some cases, the steps shown or described can be executed in a different order from here, or they can be separately made into individual integrated circuit modules, or multiple modules or steps among them can be made into a single integrated circuit module to implement. In this way, the present application is not limited to any specific combination of hardware and software.

[0156] The above are only the preferred embodiments of the present application and are not used to limit the present application. For those skilled in the art, the present application can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the principle of the present application shall be included in the protection scope of the present application.

Claims

1. A method for generating a solar radiation variation set, characterized in that: The method comprises: Acquire orbital parameters of a target running device within a target orbital period, wherein the orbital parameters are used to indicate the position and running state of the target running device on the target orbit, and the target orbital period is the time for the target running device to run one circle on the target orbit; Generate a trajectory change set of the sun vector within the target orbit period in the first coordinate system of the target operating device using the orbit parameters, wherein the values ​​in the trajectory change set are the coordinates of the sun vector in the first coordinate system; Generate a solar radiation change set for the target operating device within the target orbital period based on the trajectory change set, wherein the values ​​in the solar radiation change set are the radiation values ​​of the solar radiation external heat flux received by the target operating device within the target orbital period; Wherein, using the orbital parameters to generate a trajectory change set of the sun vector within the target orbital period in the first coordinate system of the target operating device includes: Generate a first trajectory change set of the sun vector in a second coordinate system within the target orbit period by using an angle set of a first angle and a second angle, wherein the second coordinate system is a coordinate system generated based on the earth, the values ​​in the first trajectory change set are coordinates of the sun vector in the second coordinate system, the first angle is used to represent a pitch angle between the sun vector and the orbital plane of the target orbit, and the second angle is used to represent an azimuth angle of the sun vector; The first trajectory change set is converted into a second trajectory change set in a third coordinate system by using a coordinate transformation matrix, wherein the coordinate transformation matrix is ​​a matrix for performing coordinate transformation between the second coordinate system and the third coordinate system, the values ​​in the second trajectory change set are the coordinates of the sun vector in the third coordinate system, and the third coordinate system is a coordinate system generated based on the target operating device; When the first coordinate system coincides with the third coordinate system, the second trajectory change set is determined as the trajectory change set.

2. The method according to claim 1, characterized in that Obtain the orbital parameters of the target operating device within the target orbital period, including: Acquire a first angle and a track height of the target track; Acquire an angle set of second angles within the target orbit period; An angle set of the first angle, the orbit height, and the second angle is determined as the orbit parameter.

3. The method according to claim 2, characterized in that After generating a set of trajectory changes of a sun vector within the target orbit period in the first coordinate system of the target operating device using the orbital parameters, the method further includes: Calculate the angle of the visible range of the earth's surface in the visual angle of the target operating device when the target operating device is operating on the target orbit by using the average radius of the earth and the orbital altitude to obtain a third angle; comparing the first angle and the third angle to obtain a comparison result; A trajectory change diagram of the sun vector in the first coordinate system within the target orbit period is generated based on the comparison result and the trajectory change set.

4. The method according to claim 3, characterized in that: After comparing the first angle and the third angle to obtain a comparison result, the method further includes: When the absolute value of the first angle is smaller than the third angle, the third angle and the first angle are used to calculate the angle of the fan-shaped area formed when the target operating device blocks sunlight in the viewing angle of the target operating device when the target operating device is operating on the target orbit, to obtain a fourth angle; The shadow coverage range of the target track is calculated using the fourth angle to obtain a target range.

5. The method according to claim 3, characterized in that: Generating a trajectory change diagram of the sun vector in the first coordinate system within the target orbit period based on the comparison result and the trajectory change set includes one of the following: When the first angle is within a first preset range and the absolute value of the first angle is greater than or equal to the third angle, plotting the trajectory change of the sun vector in the first coordinate system within the target orbit period to obtain the trajectory change graph; When the first angle is a first preset threshold, plotting the trajectory change of the sun vector in the first coordinate system within the target orbit period to obtain the trajectory change graph; When the first angle is within a second preset range and the absolute value of the first angle is greater than or equal to the third angle, plotting the trajectory change of the sun vector in the first coordinate system within the target orbit period to obtain the trajectory change graph; When the first angle is a second preset threshold, plotting the trajectory change of the sun vector in the first coordinate system within the target orbit period to obtain the trajectory change graph; When the first angle is a third preset threshold, the trajectory change of the solar vector in the first coordinate system within the target orbit period is plotted to obtain the trajectory change graph.

6. The method according to claim 1, characterized in that Generating a solar radiation change set of the target operating device within the target orbit period based on the trajectory change set includes: Respectively obtain normal vectors of N outer surfaces of the target operating device in the first coordinate system to obtain N normal vectors, where N is a natural number greater than or equal to 1; The trajectory change set and the N normal vectors are used to calculate the solar radiation value of the target running device within the target orbit period to obtain the solar radiation change set.

7. The method according to claim 1, characterized in that After generating the solar radiation change set of the target operating device within the target orbit period based on the trajectory change set, the method further includes: At a first angle, the solar radiation changes of the target operating equipment within the target orbit period are plotted using the values ​​in the solar radiation change set to obtain a solar radiation change graph, wherein the first angle is used to represent the pitch angle between the solar vector and the orbital plane of the target orbit.

8. A device for generating a solar radiation variation set, characterized in that: The system comprises a first memory, a first processor, and a first computer program stored in the first memory and executable on the first processor, wherein the first processor implements the following operations when executing the first computer program: Acquire orbital parameters of a target running device within a target orbital period, wherein the orbital parameters are used to indicate the position and running state of the target running device on the target orbit, and the target orbital period is the time for the target running device to run one circle on the target orbit; Generate a trajectory change set of the sun vector within the target orbit period in the first coordinate system of the target operating device using the orbit parameters, wherein the values ​​in the trajectory change set are the coordinates of the sun vector in the first coordinate system; Generate a solar radiation change set for the target operating device within the target orbital period based on the trajectory change set, wherein the values ​​in the solar radiation change set are the radiation values ​​of the solar radiation external heat flux received by the target operating device within the target orbital period; The device is also used to generate a first trajectory change set of the sun vector in the second coordinate system within the target orbit period using an angle set of a first angle and a second angle, wherein the second coordinate system is a coordinate system generated based on the earth, the values ​​in the first trajectory change set are the coordinates of the sun vector in the second coordinate system, the first angle is used to represent the pitch angle between the sun vector and the orbital plane of the target orbit, and the second angle is used to represent the azimuth angle of the sun vector; the first trajectory change set is converted into a second trajectory change set in a third coordinate system using a coordinate transformation matrix, wherein the coordinate transformation matrix is ​​a matrix for coordinate transformation between the second coordinate system and the third coordinate system, the values ​​in the second trajectory change set are the coordinates of the sun vector in the third coordinate system, and the third coordinate system is a coordinate system generated based on the target operating device; when the first coordinate system coincides with the third coordinate system, the second trajectory change set is determined as the trajectory change set.

9. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, wherein the computer program implements the steps of the method described in any one of claims 1 to 7 when executed by a processor.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the steps of the method described in any one of claims 1 to 7 are implemented.

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