Solar radiation change set generation method and device, and storage medium

Abstract

The embodiment of the invention provides a solar radiation change set generation method and device and a storage medium, and the method comprises the steps: obtaining the orbit parameters of target operation equipment in a target orbit period; generating a trajectory change set of the sun vector in the target orbit period in a first coordinate system of the target operation equipment by using the orbit parameters; and generating a solar radiation change set of the target operation equipment in the target orbit period based on the trajectory change set. According to the method and the device, the problem that the change rule of sunlight irradiation under the first coordinate system of the target operation equipment cannot be determined in the prior art is solved, and the effect of intuitively and quantitatively analyzing the rule of sunlight irradiation on the target operation equipment can be achieved.

Description

Technical Field

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

[0002] In the relevant technology, the external heat flux of equipment orbiting the earth (for example, satellites, transmitters, etc.) is basically analyzed through the following methods: Method 1 relies on commercial software to obtain the relationship between the external heat flux of each surface of the equipment and time, and analyzes the change law of the external heat flux on the surface of the equipment; Method 2 is based on secondary development of commercial software to reduce the data processing amount of Method 1 and improve convenience.

[0003] The device moves around the earth, and the earth moves the device around the sun. In this case, it is more complicated to analyze the sunlight exposure of the device. When modeling sunlight exposure in existing commercial software, the device, the earth, and the sun are generally put in a three-dimensional view, which can intuitively view the shadow area and sun-illuminated area of ​​the device moving around the earth. However, it is impossible to intuitively give the changes in sunlight exposure from the perspective of the device's first coordinate system. Summary of the invention

[0004] The embodiments of the present application provide a method and device for generating a solar radiation change set, and a storage medium, so as to at least solve the problem in the related art that it is impossible to determine the changing pattern of solar radiation in the first coordinate system of the target operating device.

[0005] According to one embodiment of the present application, a method for generating a solar radiation change set is provided, including: obtaining orbital parameters of a target operating device within a target orbital period, wherein the orbital parameters are used to indicate the position and operating status of the target operating device on the target orbit, and the target orbital period is the time for the target operating device to operate for one cycle on the target orbit; generating a trajectory change set of a solar vector within the target orbital period in a first coordinate system of the target operating device using the orbital parameters, wherein 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, 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.

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

[0007] In an exemplary embodiment, the orbital parameters are used to generate a trajectory change set of the solar vector within the target orbital period in the first coordinate system of the target operating device, including: using the angle set of the first angle and the second angle to generate a first trajectory change set of the solar vector in the second coordinate system within the target orbital period, wherein the second coordinate system is a coordinate system generated based on the earth, and the values ​​in the first trajectory change set are the coordinates of the solar vector in the second coordinate system; using a coordinate transformation matrix to convert the first trajectory change set into a second trajectory change set in a third coordinate system, wherein 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 change 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; in a case where the first coordinate system coincides with the third coordinate system, the second trajectory change set is determined as the trajectory change set.

[0008] In an exemplary embodiment, after generating a trajectory change set of the sun vector within the target orbital period in the first coordinate system of the target operating device using the orbital parameters, the method further includes: calculating the angle of the visible range of the earth's surface from the perspective of the target operating device when the target operating device is operating on the target orbit using the average radius of the earth and the orbital altitude 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 sun vector in the first coordinate system within the target orbital period based on the comparison result and the trajectory change set.

[0009] In an exemplary embodiment, 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, using the third angle and the first angle 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; using the fourth angle to calculate the shadow coverage range of the target orbit to obtain the target range.

[0010] In an exemplary embodiment, a trajectory change diagram of the solar vector in the first coordinate system within the target orbital period is generated based on the comparison result and the trajectory change set, including 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, the trajectory change of the solar vector in the first coordinate system within the target orbital period is plotted to obtain the trajectory change diagram; when the first angle is a first preset threshold, the trajectory change of the solar vector in the first coordinate system within the target orbital period is plotted 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, the trajectory change of the solar vector in the first coordinate system within the target orbital period is plotted to obtain the trajectory change diagram; when the first angle is a second preset threshold, the trajectory change of the solar vector in the first coordinate system within the target orbital period is plotted to obtain the trajectory change diagram; when the first angle is a third preset threshold, the trajectory change of the solar vector in the first coordinate system within the target orbital period is plotted to obtain the trajectory change diagram.

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

[0012] In an exemplary embodiment, after generating a solar radiation change set of the target operating equipment within the target orbital period based on the trajectory change set, the method further includes: at a first angle, using the numerical values ​​in the solar radiation change set to plot the solar radiation changes of the target operating equipment within the target orbital period 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.

[0013] According to another embodiment of the present application, a device for generating a solar radiation change set is provided, comprising 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: obtaining orbital parameters of a target operating device within a target orbital period, wherein 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 operate for one cycle on the target orbit; generating a trajectory change set of a solar vector within the target orbital period in a first coordinate system of the target operating device using the orbital parameters, wherein 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, wherein the values ​​in the solar radiation change set are the radiation values ​​of the external heat flux of solar radiation received by the target operating device within the target orbital period.

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

[0015] According to another embodiment of the present application, a computer-readable storage medium is provided, in which a computer program is stored, wherein the computer program is configured to execute the steps of any one of the above method embodiments when running.

[0016] According to another embodiment of the present application, an electronic device is provided, including a memory and a processor, wherein the memory stores a computer program, and the processor is configured to run the computer program to execute the steps in any one of the above method embodiments.

[0017] Through the present application, the orbital parameters of the target operating device in the target orbital period are used to generate a set of trajectory changes of the sun vector in the target orbital period in the first coordinate system of the target operating device, and based on the set of trajectory changes, a set of changes of solar radiation in the orbital period is generated, that is, the radiation value of the solar radiation external heat flow received by the target operating device. Therefore, the problem that the change law of solar radiation in the first coordinate system of the target operating device cannot be determined in the related art can be solved, thereby achieving the effect of intuitively and quantitatively analyzing the law of solar radiation received by the target operating device. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

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

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

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

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

[0026] Fig. 9 The sun vector trajectory changes according to the embodiment of the present application Figure 1 ;

[0027] Fig.10 The sun vector trajectory changes according to the embodiment of the present application Figure 2 ;

[0028] Fig.11 The sun vector trajectory changes according to the embodiment of the present application Figure 3 ;

[0029] Fig.12 The sun vector trajectory changes according to the embodiment of the present application Figure 4 ;

[0030] Fig.13 The sun vector trajectory changes according to the embodiment of the present application Figure 5 ;

[0031] Fig.14 is a flow chart of a method for generating a set of solar radiation changes of each outer surface of a satellite according to an embodiment of the present application;

[0032] Fig.15 The trajectory change of the sun vector in the first coordinate system of the satellite according to an embodiment of the present application is Figure 1 ;

[0033] Fig.16 The trajectory change of the sun vector in the first coordinate system of the satellite according to an embodiment of the present application is Figure 2 ;

[0034] Fig.17 The trajectory change of the sun vector in the first coordinate system of the satellite according to an embodiment of the present application is Figure 3 ;

[0035] Fig.18 It is the TD simulation of solar radiation changes in related technologies Figure 1 ;

[0036] Fig.19 The solar radiation variation of each outer surface of a satellite according to an embodiment of the present application is Figure 1 ;

[0037] Fig. 20 It is the TD simulation of solar radiation changes in related technologies Figure 2 ;

[0038] Fig.21 The solar radiation variation of each outer surface of a satellite according to an embodiment of the present application is Figure 2 ;

[0039] Fig. 22 It is the TD simulation of solar radiation changes in related technologies Figure 3 ;

[0040] Fig.23 The solar radiation variation of each outer surface of a satellite according to an embodiment of the present application is Figure 3 ;

[0041] Fig.24 It is a structural block diagram of a device for generating a solar radiation variation set according to an embodiment of the present application. DETAILED DESCRIPTION

[0042] The embodiments of the present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

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

[0044] The method embodiments provided in the embodiments of the present application can be executed in a server device or a similar computing device. Taking running on a server device as an example, Figure 1 Schematic diagram of the hardware environment of a method for generating a solar radiation variation set in an embodiment of the present application. Figure 1 As shown, the server device may include one or more ( Figure 1 Only one is shown in the figure) a processor 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, wherein the above-mentioned server device may also include a transmission device 106 and an input / output device 108 for communication functions. It can be understood by those skilled in the art that Figure 1 The structure shown is only for illustration and does not limit the structure of the above server device. Figure 1 More or fewer components as shown, or with Figure 1 Different configurations are shown.

[0045] The memory 104 can be used to store computer programs, for example, software programs and modules of application software, such as a computer program corresponding to a method for generating a solar radiation change set in an embodiment 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, to implement the above 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 memory, or other non-volatile solid-state memory. In some examples, the memory 104 may further include a memory remotely arranged relative to the processor 102, and these remote memories may be connected to the server device via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0046] The transmission device 106 is used to receive or send data via a network. The specific example of the above network may include a wireless network provided by a communication provider of the server device. In one example, the transmission device 106 includes a network adapter (Network Interface Controller, referred to 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 solar radiation variation set is provided. Figure 2 is a flow chart of a method for generating a solar radiation variation set according to an embodiment of the present application, such as Figure 2 As shown, the process includes the following steps:

[0048] Step S202, obtaining orbital parameters of the 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;

[0049] Optionally, the target operating device in this embodiment is a device orbiting the earth, including but not limited to satellites, spacecraft, and probes, which operate in orbit and perform specific tasks such as communication, remote sensing, navigation, etc.

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

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

[0052] Step S204, 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, wherein the values ​​in the trajectory change set are the coordinates of the sun 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 may also be referred to as a 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 center of mass 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 speed. The Z-axis is in the orbital plane of the satellite, pointing to the center of the earth, and the Y-axis is perpendicular to the orbital plane of the satellite, and satisfies the right-hand screw rule to describe the satellite's own attitude and motion.

[0054] Optionally, the sun vector in this embodiment is used to represent a unit vector 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 first coordinate system mentioned above), the sun vector is a unit vector from the satellite geometric center to the sun geometric center, and is used to describe the direction of the sun relative to the satellite. The sun vector can be decomposed into coordinate values ​​of the X, Y, and Z axes in the satellite body coordinate system, and these coordinate values ​​vary with the position of the satellite in orbit.

[0055] Optionally, the trajectory change set in this embodiment is a set of changes of the sun vector in the first coordinate system over time, including changes of coordinate values ​​of the sun vector in the three axes directions of X, Y, and Z in the first coordinate system over time at various times.

[0056] For example, in the case where the target operating device is a satellite, the position and velocity of the satellite at any time in the orbital period can be calculated based on the orbital parameters using methods such as Kepler's equations or Newton's iteration method. The azimuth and pitch angles of the sun relative to the satellite can be calculated from the unit vector pointing from the satellite's center of mass to the center of the sun, and these angles vary with the position of the satellite in orbit. The sun vector can be transformed from the geocentric inertial coordinate system to the satellite's first coordinate system to facilitate further analysis of the impact of solar radiation on the satellite.

[0057] Step S206, generating a solar radiation change set of the target operating device within the target orbit period based on the trajectory change set, wherein the numerical value in the solar radiation change set is the radiation value of the solar radiation external heat flux received by the target operating device within the target orbit period.

[0058] Optionally, the solar radiation change set in this embodiment is based on the solar vector trajectory change set, including the radiation value of the solar radiation external heat flux received by each external surface of the target operating device at each time. For example, the calculated value may be the set of solar radiation external heat flux received by each surface of the satellite during the orbital period, reflecting the change of the satellite thermal environment over time.

[0059] Through the above steps, the orbital parameters of the target operating device in the target orbital period are obtained to generate a set of trajectory changes of the sun vector in the target orbital period in the first coordinate system of the target operating device, and based on the set of trajectory changes, a set of changes of solar radiation in 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 that the change law of solar radiation in the first coordinate system of the target operating device cannot be determined in the related art can be solved, thereby achieving the effect of intuitively and quantitatively analyzing the law of solar radiation received by the target operating device.

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

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

[0062] Alternatively, if Figure 3 , which is a schematic diagram of the sun vector direction according to an embodiment of the present application, wherein the B-direction orbit view is perpendicular to the orbit plane, and in the B-direction view the target running device flies around the earth in a counterclockwise direction, and the A-direction orbit view is the sun's irradiation direction. In both views, the earth is a sphere with a radius of R, The first angle is calculated by subtracting the angle between the normal line of the target orbital plane and the sun's direction from 90°. Figure 3 The vector n represents the normal of the orbital surface of the target running equipment. It represents the angle between the sun's radiation direction and the normal of the orbital plane of the target running equipment. Angle represents the above-mentioned first angle, h represents the orbital height of the target orbit, wherein the orbital surface normal is determined according to the running direction of the target running device using the right-hand rule, and the range of the first angle is [-90°, 90°].

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

[0064] In an exemplary embodiment, the orbital parameters are used to generate a trajectory change set of the solar vector within the target orbital period in the first coordinate system of the target operating device, including: using the angle set of the first angle and the second angle to generate a first trajectory change set of the solar vector in the second coordinate system within the target orbital period, wherein the second coordinate system is a coordinate system generated based on the earth, and the values ​​in the first trajectory change set are the coordinates of the solar vector in the second coordinate system; using a coordinate transformation matrix to convert the first trajectory change set into a second trajectory change set in a third coordinate system, wherein 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 change 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; in a case where the first coordinate system coincides with the third coordinate system, the second trajectory change set is determined as the trajectory change set.

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

[0066] Optionally, in this embodiment, the third coordinate system is a coordinate system generated based on the target operating device, and the coordinate 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 (Geocentric Inertial Coordinate System, referred to as GCI) is also used. The coordinate 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 (such as orbital altitude, orbital period, etc.) and orbital position of the operating orbit of the target operating device can be quantitatively described for the subsequent calculation of the orbital motion of the satellite.

[0068] Alternatively, if Figure 4 As shown in FIG. 1 , it is a schematic diagram of the coordinate system in this embodiment. Figure 4As shown, when the target operating device is a satellite, the second coordinate system (also known as the pericentric orbit coordinate system, Perifocal Coordinate System, referred to as PCS) The origin of coordinates O is at the center of the earth. The axis points to the satellite, that is, along the direction of the satellite position vector r. The axis is in the orbital plane of the satellite, perpendicular to r and pointing forward. The axis is perpendicular to the orbital plane and points in the direction of orbital angular momentum. The satellite position vector r is the vector pointing from the center of the earth to the current position of the satellite in the orbital plane. The third coordinate system (Local-Vertical Local-Horizontal Coordinate System, referred to as LVLHS) The origin of the coordinates Located at the satellite's centroid, The axis is in the orbital plane, perpendicular to the satellite position vector r, and points forward. The axis is in the orbital plane and points to the center of the Earth. The axis is perpendicular to the orbital plane, satisfying the right-hand screw rule; geocentric inertial coordinate system The origin O of the coordinate system is the center of mass of the Earth. coincides with the Earth's equatorial plane, The axis is the Earth's rotation axis and points to the Earth's North Pole. The axis points to the vernal equinox, The axes are 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 of the sun vector, such as Figure 5 As shown, when the target operating device is a satellite, Axis represents the + of the second coordinate system axis, vector H represents the + axis, the projection of the sun vector S on the orbital plane and The included angle is φ (i.e. the second angle mentioned above, the azimuth angle of the solar vector S), and the included angle between the solar vector S and the orbital plane is β (i.e. the first angle mentioned above, the pitch angle of the solar vector S). The second angle has a variation range of [0°, 360°]. One orbit of the satellite is equivalent to one orbit of the vector H in the second coordinate system.

[0071] Optionally, Figure 5 In axis, 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 dotted line represents the changing trajectory of the sun vector in the second coordinate system when the satellite orbits once.

[0072] Optionally, in this embodiment, the first coordinate system coincides with the third coordinate system, and when the coordinate change matrix is ​​P, in the first coordinate system, the sun vector can be expressed as , the coordinate transformation matrix P can be used to transform the sun vector into the third coordinate system: , since the first coordinate system coincides with the third coordinate system, the sun vector in the first coordinate system is = .

[0073] Through the above steps, when the first angle is greater than the preset threshold, a first trajectory change set of the sun vector is generated in the second coordinate system, and then the first trajectory change set is converted to the third coordinate system 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's perspective is realized.

[0074] In an exemplary embodiment, after generating a trajectory change set of the sun vector within the target orbital period in the first coordinate system of the target operating device using the orbital parameters, the method further includes: calculating the angle of the visible range of the earth's surface from the perspective of the target operating device when the target operating device is operating on the target orbit using the average radius of the earth and the orbital altitude 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 sun vector in the first coordinate system within the target orbital period based on the comparison result and the trajectory change set.

[0075] Optionally, in this embodiment, the average radius of the earth is about 6378.137 km. Figure 3 In the equation, R represents the average radius of the Earth.

[0076] Optionally, the orbit altitude is the average altitude of the target orbit from the earth's surface, which affects the viewing angle 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 from the perspective of the target running device when the target running device is running on the target orbit. Figure 3 middle, represents the half-angle of the earth (i.e. the third angle mentioned above), which 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, this embodiment can determine whether the satellite will enter the earth's shadow area within the orbital period by comparing the first angle and the third angle.

[0079] For example, Figure 6 is a schematic diagram of the plane projection overlap of two views according to an embodiment of the present application, such as Figure 6 As shown, when the target operating device is a satellite, the black circle represents the B-direction viewing angle (the above Figure 3 The orbit of the satellite under the B-direction perspective (i.e., the target orbit mentioned above), that is, the orbital profile of the satellite orbit observed from the satellite's perspective, with the center point O being the center of mass of the earth; the black circle shows the projection of the earth under the B-direction perspective, providing the satellite with an intuitive framework of the shape and size of the earth; the dotted ellipse indicates the projection of the earth under the A-direction perspective (i.e., the target orbit mentioned above). Figure 3 The solid ellipse expresses the geometric relationship between the critical orbit and the earth when the β angle continues to decrease to the critical β angle during the operation of the satellite orbit and the shadow orbit when the satellite orbit has a shadow area. It represents the geometric position relationship between the satellite orbit and the earth and 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 shadow area of ​​the earth, that is, when the satellite orbit enters the shadow area of ​​the earth and when it returns to the full illumination state. When part of the ellipse is within the black circle, the satellite is in the shadow area of ​​the earth and the solar radiation disappears. When the ellipse is completely outside the black circle, the satellite is in the full illumination state. The shadow orbit is the orbit of the satellite entering the shadow range of the earth when orbiting the earth. The gray dotted ellipse represents the critical orbit, that is, the orbit condition defined by the dividing point between solar illumination and entering the shadow of the earth in the satellite orbit. The β angle of the critical orbit (that is, the first angle mentioned above) is the critical β angle, which is the dividing line between the shadow area of ​​the orbit and the full illumination area. For circular orbits, 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 full illumination and will not enter the shadow area of ​​the earth. 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. The line segment It represents the average radius of the earth. The H / N / C point is the heliocentric point, i.e. the point where the target operating equipment is closest to the sun on the orbital plane.

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

[0081] Through the above steps, the visible angle (third angle) of the earth's surface from the perspective of the target operating device is calculated, and then based on the comparison results of the first angle and the third angle and the trajectory change set, a trajectory change graph of the sun vector in the first coordinate system is generated. Through the trajectory change graph, the changing trajectory of the sun vector can be intuitively displayed, and the shadow and lighting status of the target operating device within the orbital period can be clearly identified.

[0082] In an exemplary embodiment, 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, using the third angle and the first angle 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; using the fourth angle to calculate the shadow coverage range of the target orbit to obtain the target range.

[0083] Optionally, in this embodiment, if the absolute value of the first angle is less than the third angle, it indicates that there is a shadow area in the target track; if the absolute value of the first angle is greater than or equal to the third angle, it indicates that the target track is a fully illuminated track and there is no shadow area. In the case where the first angle is expressed as β angle, when , indicating that there is a shadow area in the target track; when , indicating that the target track is a fully illuminated track and there is no shadow area.

[0084] Optionally, the fourth angle in this embodiment represents the angle of the fan-shaped area formed when the target running device blocks the sunlight when the target running device is running on the target orbit, in the perspective of the target running device. Figure 6 middle, represents the half angle η of the shadow area (i.e., the fourth angle mentioned above), which is related to the angle β (i.e., the first angle mentioned above). As the angle β decreases to 0°, the vertical line Moving right becomes , Tangent to the projection of the earth plane, the shadow area has the largest half angle at this time, and the range of the shadow area half angle is [0°, ],in, Figure 6 In , and the intersection of the shadow track and the projection of the earth plane is .

[0085] Optionally, in this embodiment, the third angle (or orbital height h and the average radius of the earth R) and the first angle β are calculated by the following formula to obtain the fourth angle η: According to the fourth angle, the following formula can be used to calculate the duration of the shadow area when the target operating device is operating on the target orbit due to the earth blocking the sunlight in the perspective of the target operating device: , where T represents the target orbit period, i.e., the time it takes for the target operating device to run one cycle on the target orbit.

[0086] Optionally, the target range in this embodiment represents the shadow coverage of the target track. 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, the angle of the fan-shaped area formed by the earth's occlusion (that is, the fourth angle mentioned above) is calculated, and then the shadow coverage range of the target orbit is calculated using the fourth angle to obtain the target range. The specific angle range of the target running device encountering shadow occlusion on the orbit is provided, which facilitates the subsequent determination of the occluded area and non-occluded area of ​​the target running device within the orbital period.

[0088] In an exemplary embodiment, a trajectory change diagram of the solar vector in the first coordinate system within the target orbital period is generated based on the comparison result and the trajectory change set, including 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, the trajectory change of the solar vector in the first coordinate system within the target orbital period is plotted to obtain the trajectory change diagram; when the first angle is a first preset threshold, the trajectory change of the solar vector in the first coordinate system within the target orbital period is plotted 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, the trajectory change of the solar vector in the first coordinate system within the target orbital period is plotted to obtain the trajectory change diagram; when the first angle is a second preset threshold, the trajectory change of the solar vector in the first coordinate system within the target orbital period is plotted to obtain the trajectory change diagram; when the first angle is a third preset threshold, the trajectory change of the solar vector in the first coordinate system within the target orbital period is plotted to obtain the 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 sun vector and the orbital plane) defined in the operation orbit analysis of the target operation device. They are used to distinguish different thermal environment conditions of the target orbit, such as full illumination state, shadow state, and critical condition.

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

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

[0092] Alternatively, if Figure 7 As shown, it is a schematic diagram of a 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 posture of the target operating device is that the three axes of the target operating device (i.e., the X-axis, Y-axis, and Z-axis) are all stable relative to the earth, wherein 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 a target orbit period, it is assumed that the first angle is fixed.

[0093] Alternatively, if Figure 8 , which 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 is a schematic diagram of the solar vector S on a certain outer surface of the satellite in the first coordinate system of the satellite at a certain moment.

[0094] Optionally, Fig. 9 The sun vector trajectory changes according to the embodiment of the present application Figure 1 ,like Fig. 9 As 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 illuminates the satellite from the -Y side of the satellite's first coordinate system, and the change of the sun vector forms a cone.

[0095] Optionally, Fig.10 The sun vector trajectory changes according to the embodiment of the present application Figure 2 ,like Fig.10 As shown, when the target operating device is a satellite and the first angle is represented by β, when the β angle = 0°, the change of the sun vector forms a sector, and the sector gap is the shadow area.

[0096] Optionally, Fig.11 The sun vector trajectory changes according to the embodiment of the present application Figure 3 ,like Fig.11 As 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 illuminates the satellite from the +Y side of the satellite's first coordinate system, and the change of the sun vector forms a cone.

[0097] Optionally, Fig.12 The sun vector trajectory changes according to the embodiment of the present application Figure 4 ,like Fig.12 As shown, when the target operating device is a satellite and the first angle is represented by β, when the β angle = 90°, the sunlight vertically illuminates the -Y plane of the satellite body.

[0098] Optionally, Fig.13 The sun vector trajectory changes according to the embodiment of the present application Figure 5 ,like Fig.13 As shown, when the target operating device is a satellite and the first angle is represented by β, when the β angle = -90°, the sunlight vertically illuminates the +Y plane of the satellite body.

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

[0100] Step S302, based on the first angle (angle β) and the third angle (half angle of the earth ) comparison results, select the appropriate preset range or threshold to generate the trajectory change map.

[0101] Step S304: when the angle β is within the first preset range and the absolute value of the angle β is greater than or equal to the third angle (the half angle of the earth), ), the satellite will not enter the Earth's shadow area, and the direction of the sun vector in the first coordinate system appears as a continuously changing trajectory, such as Fig.12 , Fig.13 As shown, the sun vector vertically illuminates the Y surface of the satellite, and the satellite is in a fully illuminated state.

[0102] Step S306, when the angle β is equal to the first preset threshold, which usually corresponds to a critical condition, the trajectory change diagram of the sun vector will show the critical point where the satellite transitions from the full illumination state to the shadow state, such as Figure 6 The fan-shaped gap in the figure indicates the existence of the shadow area.

[0103] Step S308: When the angle β is within the second preset range and the absolute value of the angle β is greater than or equal to the third angle (the half angle of the earth), ), the satellite is still in full illumination, and the trajectory change diagram will show the change of the sun vector direction in the first coordinate system of the satellite, similar to the situation in step S304.

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

[0105] Step S312, when the angle β is equal to the third preset threshold, the trajectory change diagram will focus on the change in the direction of the sun 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 sun vector in the first coordinate system of the satellite. This can be based on the first trajectory change set of the sun vector in the second coordinate system, converted to the first coordinate system through the coordinate transformation matrix, and then according to the β angle and Identify and mark the shaded area based on the size relationship.

[0107] Step S316, analyzing the trajectory change graph to determine the distribution and change of the solar radiation heat flux received by each surface of the satellite during the orbital period. This can be achieved by calculating the dot product of the sun vector and the normal vector of each surface of the satellite. The size of the dot product reflects the degree of direct exposure to 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 operational safety of the satellite under different orbital conditions.

[0109] Through the above steps, a trajectory change diagram of the sun vector in the satellite's first coordinate system can be generated for a specific preset range or threshold, which is of great significance for in-depth understanding of the satellite's thermal environment and evaluation of its thermal protection needs. In specific implementation, a variety of data and analysis tools can be combined to generate more detailed and accurate thermal environment analysis results. For example, in Figures 8 to 13 In the figure, the change of solar vector trajectory and the change of solar radiation heat flux under different β angle conditions are shown. This information is crucial for designing the satellite's thermal protection system and optimizing its thermal management strategy.

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

[0111] Optionally, in this embodiment, it is assumed that within one target orbit period, the first angle and the fourth angle are fixed.

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

[0113] Optionally, in this embodiment, Table 1 is the solar radiation calculation condition, that is, when the geometric model of the target operating device is as follows Figure 7 As shown, the normal vectors of each external surface of the target operating equipment and the condition of 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 solar radiation external heat flux of each outer surface of the target operating device within a target orbit period can be calculated based on the projection of the solar vector S to the normal vectors of each surface of the target operating device.

[0117] Optionally, when the geometry of the target operating device is Figure 7 As shown, the target operating device is a satellite, and the second angle In the case of , indicating that there is a shadow area in the target orbit. The starting point of the second angle is the solar conjunction point. The solar radiation value of each outer surface of the satellite can be calculated by the following formula: The solar radiation value of the +Z surface of the satellite ; Solar radiation value of the -Z plane of the satellite ; Solar radiation value of the satellite's +X surface ; Solar radiation value of the -X side of the satellite ; Solar radiation value of the satellite's +Y surface ; Solar radiation value of the -Y surface of the satellite The result calculated by the above formula is multiplied by the solar heat flux 1414 W / m2 to obtain the solar radiation value of each external surface of the target operating equipment in actual conditions. , indicating that the target orbit is a fully illuminated orbit with no shadow area. Let η in the above formula be 0 to calculate the solar radiation value of each side of the satellite. represents the first angle mentioned above, represents the second angle mentioned above, represents the third angle mentioned above, η represents the fourth angle mentioned above, and S represents the sun vector.

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

[0119] In an exemplary embodiment, after generating a solar radiation change set of the target operating equipment within the target orbital period based on the trajectory change set, the method further includes: at a first angle, using the numerical values ​​in the solar radiation change set to plot the solar radiation changes of the target operating equipment within the target orbital period 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.

[0120] Optionally, the solar radiation variation diagram in this embodiment shows the solar radiation values ​​of each outer surface of the target operating equipment under a target orbital period, including but not limited to those obtained through the following software analysis: COSMOS / MThermal Analysis, ESI Thermal Desktop (TD), ANSYS Fluent, SINDA / Gold, and SABREThermal.

[0121] Optionally, the solar radiation variation graph in this embodiment includes but is not limited to being displayed in the form of a line graph.

[0122] Through the above steps, at the first angle, the solar radiation change set is used to draw a solar radiation change graph. Through the graphical display, the changing trend of solar radiation within the orbital period is intuitively reflected, which is convenient for designers to understand the thermal environment of the target operating equipment and adjust the thermal control strategy.

[0123] The above method is described below with a specific example, and this embodiment is described with a satellite as an example. The following is a specific embodiment involving the change of the external heat flux of solar radiation when the satellite is operating on an inclined circular orbit:

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

[0125] In addition, this specific embodiment needs to define a coordinate system: a second coordinate system: the origin O is the center of the earth, The axis points to the satellite position along the satellite position vector, The axis is perpendicular to the orbital plane axis, The axis is perpendicular to the orbital plane and points in the direction of orbital angular momentum. The third coordinate system (LVLHS): origin Located at the spacecraft center of mass, The axis points in the orbital plane perpendicular to the position vector and points forward of the motion. The axis points to the center of the Earth in the orbital plane. The axis is perpendicular to the orbital plane and satisfies the right-hand screw rule. Geocentric inertial coordinate system: the origin O is at the center of mass of the Earth, the plane coincides with the Earth's equatorial plane, The axis is the Earth's rotation axis pointing to the North Pole. The axis points to the vernal equinox, The axis is determined according to the right-hand rule. The first satellite coordinate system: the origin O is located at the satellite's center of mass, the X-axis is perpendicular to the satellite position vector in the orbital plane and points to the direction of the satellite's motion speed, the Z-axis points to the center of the earth in 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, Fig.14 is a flow chart 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, such as Fig.14 As shown, the process includes the following steps:

[0127] Step S1402, obtaining the orbital parameters of the satellite within the target orbital period, wherein the target orbital period is the time required for the satellite to orbit one circle in the satellite orbit, and the orbital parameters include the satellite orbital altitude, orbital inclination, the pitch angle variation range 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, generating a trajectory change set of the sun vector in the target orbit period in the first coordinate system of the satellite using the orbit parameters, and drawing a trajectory change diagram of the sun vector in the first coordinate system of the satellite;

[0131] In this step, the earth's viewing angle is first calculated using the formula: Based on the average radius of the earth and the orbital altitude, the satellite's half-viewing angle of the earth is calculated using the formula , and use this to determine whether the satellite orbit has entered the Earth's shadow.

[0132] Secondly, generate a trajectory change diagram: when β = 0 °, the satellite is in a critical condition, the sun vector trajectory is fan-shaped, and there is a shadow area. Use GeoGebra software to draw a trajectory change diagram according to the change of the sun vector in the second coordinate system. When β = 30 °, the satellite enters the earth's shadow area, and the sun vector trajectory is a missing corner cone. Use GeoGebra software to draw a trajectory change diagram. When β = 70 °, the satellite is in a full illumination state, and the sun vector trajectory is a cone. Use GeoGebra software to generate a trajectory change diagram.

[0133] in, Fig.15 , Fig.16 , Fig.17 They are schematic diagrams of trajectory changes of a sun vector in a first coordinate system of a satellite according to an embodiment of the present application, wherein: Fig.15 At the first angle β=0°, the half angle of the shadow area (i.e. the fourth angle mentioned above) ° is a schematic diagram of the trajectory change set of the solar vector within the target orbit period. In this case, the change of the solar vector forms a fan shape. Fig.16 At the first angle β=30°, the half angle of the shadow area (i.e. the fourth angle mentioned above) ° is the set of trajectory changes of the solar vector within the target orbit period, Fig.17 At the first angle β=70°, the half angle of the shadow area (i.e. the fourth angle mentioned above) ° is a set of trajectory changes of the sun vector in the target orbit period. In this case, the target orbit is a fully illuminated orbit, and the change of the sun vector forms a cone, where Fig.15 , Fig.16 and Fig.17 The rectangular blocks in the figure are used to represent the geometric model of the satellite. The black surface represents the positive X, Y, and Z surfaces of the satellite, and the gray surface represents the negative X, Y, and Z surfaces of the satellite.

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

[0135] In this step, for each β angle condition, the formula is used to calculate the external heat flux of solar radiation on each side of the satellite at different β angles. Assume that the β angle of the satellite is fixed at 0°, 30°, and 70° to cover full sunlight, shadow, 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. Fig.18 It is the TD simulation solar radiation change of each outer surface of the satellite in the related technology Figure 1 , Fig.19 The solar radiation variation of each outer surface of the satellite according to the embodiment of the present application Figure 1 , Fig.18 and Fig.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). Fig.18 It is a map of solar radiation changes on the satellite's various outer surfaces drawn using software in related technologies. Fig.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. Fig.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. Fig.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, Fig. 20 It is the TD simulation solar radiation change of each outer surface of the satellite in the related technology Figure 2 , Fig.21The solar radiation variation of each outer surface of the satellite according to the embodiment of the present application Figure 2 , Fig. 20 and Fig.21 The solar radiation variation diagrams of the satellite's various outer surfaces are drawn at the first angle β=30°. The horizontal axis represents time, and the vertical axis represents the solar radiation heat flow (i.e. the solar radiation value mentioned above). Fig. 20 It is a map of solar radiation changes on the satellite's various outer surfaces drawn using software in related technologies. Fig.21 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. Fig. 20 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. Fig.21 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.

[0139] Optionally, Fig. 22 It is the TD simulation solar radiation change of each outer surface of the satellite in the related technology Figure 3 , Fig.23 The solar radiation variation of each outer surface of the satellite according to the embodiment of the present application Figure 3 , Fig. 22 and Fig.23 The solar radiation variation diagrams of the satellite's various outer surfaces are drawn at the first angle β=70°. The horizontal axis represents time, and the vertical axis represents the solar radiation heat flow (i.e. the solar radiation value mentioned above). Fig. 22 It is a map of solar radiation changes on the satellite's various outer surfaces drawn using software in related technologies. Fig.23 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. Fig. 22 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. Fig.23Geo_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.

[0140] pass Fig.18 and Fig.19 , Fig. 20 and Fig.21 , Fig. 22 and Fig.23 By comparing the two, it can be determined that the results calculated according to the solar vector projection in the above method are basically the same as the TD simulation results, which verifies the correctness of the calculation formula in the above method.

[0141] This embodiment also includes a data analysis step for analyzing the solar radiation variation map, determining the duration of the satellite in the shadow area and the full light area, and evaluating the satellite thermal protection and energy management requirements. For example, when the satellite enters the shadow area, it may be necessary to activate thermal batteries or use insulation materials to maintain the temperature of the equipment.

[0142] Through the steps in the embodiment, it is possible to generate a solar vector trajectory change map and a solar radiation change map according to the orbital parameters and operating attitude of the satellite, which will help to accurately predict the thermal environment during the satellite design and operation planning stage, thereby optimizing the thermal protection design and energy management strategy, and ensuring 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 methods, those skilled in the art can clearly understand that the method according to the above embodiment can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware, but in many cases the former is a better implementation method. Based on such an understanding, the technical solution of the present application, or the part that contributes to the prior art, can be embodied in the form of a software product, which is stored in a storage medium (such as ROM / RAM, disk, CD), and includes a number of instructions for a terminal device (which can be a mobile phone, computer, server, or network device, etc.) to execute the methods described in each embodiment of the present application.

[0144] In this embodiment, a device for generating a solar radiation variation set is also provided, and the device is used to implement the above-mentioned embodiments and preferred implementation modes, and the descriptions that have been made will not be repeated. As used below, the term "module" can implement a combination of software and / or hardware of a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, the implementation of hardware, or a combination of software and hardware, is also possible and conceivable.

[0145] Fig.24 is a structural block diagram of a device for generating a solar radiation variation set according to an embodiment of the present application, such as Fig.24 As shown, the device includes: a first memory 242, a first processor 244, and a first computer program 24202 stored in the first memory 242 and executable on the first processor 244, characterized in that the first processor 244 implements the following operations when executing the first computer program 24202: obtaining orbital parameters of the target operating device within a target orbital period, wherein the orbital parameters are used to indicate 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 operate for one cycle on the target orbit; generating a trajectory change set of the solar vector within the target orbital period in the first coordinate system of the target operating device using the orbital parameters, wherein 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, 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.

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

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

[0148] In an exemplary embodiment, the computer-readable storage medium may include, but is not limited to, various media that can store computer programs, such as a USB flash drive, a read-only memory (ROM), a random access memory (RAM), a mobile hard disk, a magnetic disk or an optical disk.

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

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

[0151] An embodiment of the present application further provides a computer program product, which includes a computer program. When the computer program is executed by a processor, the steps in any one of the above method embodiments are implemented.

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

[0153] The embodiments of the present application also provide a computer program, which includes computer instructions, which 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 performs the steps of any one of the above method embodiments.

[0154] For specific examples in this embodiment, reference may be made to the examples described in the above embodiments and exemplary implementation modes, and this embodiment will not be described in detail herein.

[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 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 a program code executable by a 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 that herein, or they can be made into individual integrated circuit modules, or multiple modules or steps therein can be made into a single integrated circuit module for implementation. Thus, the present application is not limited to any specific combination of hardware and software.

[0156] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the principles 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; A solar radiation change set of the target operating device within the target orbital period is generated based on the trajectory change set, wherein the numerical 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.

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 an orbital altitude of the target orbit, wherein the first angle is used to represent a pitch angle between the sun vector and the orbital plane of the target orbit; Acquire an angle set of second angles within the target orbit period, wherein the second angle is used to represent the azimuth of the sun vector; 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 Generating a trajectory change set of a sun vector within the target orbit period in a first coordinate system of the target operating device using the orbital parameters 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 the first angle and the second angle, wherein the second coordinate system is a coordinate system generated based on the earth, and the values ​​in the first trajectory change set are the coordinates of the sun vector in the second coordinate system; 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.

4. 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.

5. The method according to claim 4, 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.

6. The method according to claim 4, 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.

7. 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 value.

8. 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.

9. 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; A solar radiation change set of the target operating device within the target orbital period is generated based on the trajectory change set, wherein the numerical 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.

10. 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 8 when executed by a processor.

11. 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 8 are implemented.

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