A simulation method based on real-time motion state of solar orientation satellite panel

Abstract

The application provides a simulation method for real-time motion state of a sun-oriented satellite battery panel, comprising the following steps: obtaining an installation position of a battery panel in a satellite and describing the installation position in a satellite body coordinate system; obtaining a sunray vector in a J2000 coordinate system at any time and transforming the sunray vector into a sunray vector in the satellite body coordinate system; projecting a normal vector of the battery panel and the sunray vector in the satellite body coordinate system onto a projection plane to obtain a battery panel normal vector projection and a sunray vector projection, respectively; and calculating an included angle between the battery panel normal vector projection and the sunray vector projection. The simulation method for real-time motion state of a sun-oriented satellite battery panel can obtain the real-time motion state of the sun-oriented satellite battery panel, has high calculation efficiency, accurate results, can improve the efficiency of the battery panel and prolong the service life.

Description

Technical Field

[0001] This invention relates to the field of aerospace engineering technology, and more specifically, to a simulation method based on the real-time motion state of solar panels on a sun-oriented satellite. Background Technology

[0002] With the development of aerospace technology, the power required by spacecraft is increasing, making the development of high-power, long-life, and low-cost space solar cells a key direction for aerospace technology development. Solar energy is a crucial energy source for spacecraft, and the acquisition of solar energy is closely related to the movement of solar panels. The energy provided per unit area of ​​a solar panel depends on the angle between its normal direction and the solar vector direction. There is an urgent need for a method to study the specific motion state of spacecraft solar panels and to understand the real-time status of solar panels on sun-oriented satellites. This would help improve the efficiency of solar cells and extend the lifespan of solar panels in the harsh space environment. Summary of the Invention

[0003] The problem addressed by this invention is how to provide a simulation method that can study the real-time motion state of satellite solar panels, which helps to improve the efficiency of solar cells and extend their lifespan in the space environment.

[0004] To address at least one of the aforementioned problems, this invention provides a simulation method based on the real-time motion state of solar panels on a solar-orienting satellite, comprising the following steps:

[0005] Step S1: Obtain the installation position of the solar panel in the satellite, and describe the installation position in the satellite body coordinate system to obtain the initial installation position of the solar panel in the satellite body coordinate system.

[0006] Step S2: Calculate the trajectory of the satellite and obtain the sun ray vector in the J2000 coordinate system at any time. Transform the sun ray vector in the J2000 coordinate system into the sun ray vector in the satellite body coordinate system.

[0007] Step S3: Project the normal vector of the solar panel and the solar ray vector of the satellite body coordinate system onto the projection plane to obtain the solar panel normal vector projection and the solar ray vector projection, respectively. The projection plane is a plane perpendicular to the axis of the initial installation position of the solar panel in the satellite body coordinate system.

[0008] Step S4: Calculate the angle between the normal vector projection of the solar panel and the vector projection of the sunlight, and adjust the motion state of the solar panel according to the angle.

[0009] Preferably, in step S1, the origin of the satellite body coordinate system is located at the centroid of the satellite.

[0010] Preferably, the satellite body coordinate system includes an X-axis, a Y-axis, and a Z-axis, wherein, when the satellite has no attitude deviation, the direction of the X-axis coincides with the direction of motion of the satellite, the Y-axis points to the negative normal direction of the satellite's orbital plane, and the Z-axis points to the Earth's center.

[0011] Preferably, the mounting position of the solar panel is located in the positive direction of the X-axis, the negative direction of the X-axis, the positive direction of the Y-axis, the negative direction of the Y-axis, the positive direction of the Z-axis, or the negative direction of the Z-axis.

[0012] Preferably, in step S2, the sunlight vector in the J2000 coordinate system is first transformed into the sunlight vector in the satellite orbit coordinate system, and then the sunlight vector in the satellite orbit coordinate system is transformed into the sunlight vector in the satellite body coordinate system.

[0013] Preferably, in step S2, the orbital trajectory of the satellite is calculated using the SGP4 orbital calculation model.

[0014] Preferably, in step S3, the normal vector of the solar panel is the normal vector of the sun-facing side of the solar panel.

[0015] Preferably, in step S4, the motion state of the solar panel is adjusted so that the normal vector projection of the solar panel is consistent with the vector projection of the sunlight, thereby improving the photoelectric conversion efficiency of the solar panel.

[0016] This invention obtains the installation position of solar panels in a satellite through simulation and describes the initial position of the panels in the satellite's coordinate system. By simulating the satellite's trajectory, it obtains the sunlight vector at any given moment. The sunlight vector is then transformed from the J2000 coordinate system to the satellite's coordinate system. The normal vector of the solar panel and the sunlight vector in the satellite's coordinate system are then projected onto a plane perpendicular to the axis of the initial installation position of the solar panel. The angle between the projected normal vector and the projected sunlight vector is measured. By rotating the solar panel by this angle, the installation position can be adjusted. By aligning the normal vector projection of the solar panel with the vector projection of sunlight, the photoelectric conversion efficiency of the solar panel is improved. Specifically, the simulation method provided by this invention, based on the real-time motion state of a solar panel for a sun-oriented satellite, can simulate the satellite's trajectory through computer simulation and obtain the installation position of the solar panel and the sunlight vector at any given time. After transforming to the same coordinate system, the angle between the normal projection of the solar panel and the vector projection of sunlight is calculated, and the solar panel's motion state is adjusted according to this angle. This yields the real-time motion state of the solar panel for a sun-oriented satellite, resulting in high computational efficiency, accurate results, improved panel efficiency, and extended service life. Attached Figure Description

[0017] Figure 1 This is a flowchart of a simulation method based on the real-time motion state of solar panels on a solar-orienting satellite, as described in an embodiment of the present invention.

[0018] Figure 2 This is a diagram showing the relationship between the J2000 coordinate system and the satellite body coordinate system in an embodiment of the present invention;

[0019] Figure 3 This is a schematic diagram of a simulation method based on the real-time motion state of solar panels on a solar-orienting satellite, as described in an embodiment of the present invention. Detailed Implementation

[0020] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below.

[0021] It should be noted that, unless otherwise specified, the features in the embodiments of this invention can be combined with each other. The terms "comprising," "including," "containing," and "having" are non-limiting, meaning that other steps and other components that do not affect the results can be added. The above terms cover the terms "composed of" and "substantially composed of." Unless otherwise specified, the materials, equipment, and reagents are commercially available.

[0022] This invention provides a simulation method based on the real-time motion state of solar panels on a solar-orienting satellite, such as... Figure 1 As shown, it includes the following steps:

[0023] Step S1: Obtain the installation position of the solar panel in the satellite, and describe the installation position in the satellite body coordinate system to obtain the initial installation position of the solar panel in the satellite body coordinate system.

[0024] Step S2: Calculate the trajectory of the satellite and obtain the sun ray vector in the J2000 coordinate system at any time. Transform the sun ray vector in the J2000 coordinate system into the sun ray vector in the satellite body coordinate system.

[0025] Step S3: Project the normal vector of the solar panel and the solar ray vector of the satellite body coordinate system onto the projection plane to obtain the solar panel normal vector projection and the solar ray vector projection, respectively. The projection plane is a plane perpendicular to the axis of the initial installation position of the solar panel in the satellite body coordinate system.

[0026] Step S4: Calculate the angle between the normal vector projection of the solar panel and the vector projection of the sunlight, and adjust the motion state of the solar panel according to the angle.

[0027] In step S1, the origin of the satellite's body coordinate system is located at the satellite's center of mass, and it includes the X-axis, Y-axis, and Z-axis. Under normal conditions, the three axes of the satellite's body coordinate system coincide with the satellite's orbital coordinate system. At this point, the Z-axis of the satellite's body coordinate system points towards the Earth's center, the X-axis coincides with the satellite's direction of motion, and the Y-axis points towards the negative normal to the satellite's orbit, forming a right-handed rectangular coordinate system with the Z-axis. The solar panels can be installed in six different directions: positive X-axis, negative X-axis, positive Y-axis, negative Y-axis, positive Z-axis, or negative Z-axis. The installation positions of the solar panels are described using the satellite's body coordinate system, resulting in the initial installation positions of the solar panels within this coordinate system.

[0028] In step S2, the satellite's trajectory at any given time is calculated using the SGP4 orbit calculation model, and the corresponding solar ray vector is obtained. The initially obtained solar ray vector is represented in the J2000 coordinate system. It is first transformed into a solar ray vector in the satellite orbit coordinate system, and then transformed into a solar ray vector in the satellite body coordinate system.

[0029] The J2000 coordinate system refers to the Earth's J2000 coordinate system, which is a celestial reference coordinate system defined using the celestial equator and equinoxes at the time J2000 (12:00 on January 1, 2000). For example... Figure 2 As shown, the origin of the J2000 coordinate system coincides with the Earth's center of mass. The X-axis points to the mean vernal equinox at the J2000 time, the Z-axis points to the North Pole, and the Y-axis, together with the X and Z axes, forms a right-handed rectangular coordinate system, which is an inertial coordinate system. Figure 2 The relationship between the J2000 coordinate system and the satellite body coordinate system is shown in the figure.

[0030] In this embodiment of the invention, the calculation of the solar ray vector is performed in the J2000 coordinate system. The motion of the Earth, Moon and Sun is determined by the input of the Julian Day and the ephemeris provided by JPL Laboratory. The solar ray vector is calculated from the position of the Sun and the Earth in the J2000 coordinate system.

[0031] The Julian Day definition method uses the number of days starting from 12:00 on January 1, 4573 BC. Converting the Gregorian calendar date to a Julian Day allows for a standardized description of the difference between two Gregorian calendar times, facilitating the determination of simulation step sizes. The Julian Day is calculated from the Gregorian calendar using the following formula:

[0032]

[0033] In the formula, INT() represents the integer part, Year represents the year, Month represents the month, Day represents the day, Hour represents the hour, Minute represents the minute, Second represents the second, and the Gregorian calendar year, month, day, hour, minute, and second are selected in UTC time.

[0034] In step S3, the normal vector of the solar panel facing the sun and the solar ray vector in the satellite body coordinate system are obtained. Both are projected onto a plane in the satellite body coordinate system that is perpendicular to the axis of the initial installation position of the solar panel, thus obtaining the solar panel normal vector projection and the solar ray vector projection.

[0035] In step S4, the angle between the projection of the solar panel's normal vector and the projection of the sunlight vector is calculated to guide the adjustment of the solar panel's motion state.

[0036] Specifically, the photoelectric conversion efficiency of the solar panel is highest when the normal vector projection of the solar panel is consistent with the vector projection of the sunlight. Therefore, by rotating the solar panel according to the calculated angle, the two can be made consistent, thereby improving the efficiency of the solar panel.

[0037] The present invention will be further illustrated below with reference to specific embodiments. It should be understood that these embodiments are for illustrative purposes only and are not intended to limit the scope of the invention. Experimental methods in the following embodiments, unless otherwise specified, are generally performed according to the conditions recommended by the manufacturer.

[0038] 1.1, such as Figure 3 As shown, the solar panel is installed in the positive Y-axis direction of the satellite body coordinate system. The installation position of the solar panel is described using the satellite body coordinate system.

[0039] 1.2. The satellite's orbit is simulated using the SGP4 orbit calculation model to calculate the satellite's trajectory at any given time and obtain the corresponding solar ray vector. The initially obtained solar ray vector is represented in the J2000 coordinate system. It is first transformed into the solar ray vector in the satellite orbit coordinate system, and then transformed into the solar ray vector in the satellite body coordinate system.

[0040] 1.3. Take the normal vector of the solar panel facing the sun and the sunlight vector in the satellite body coordinate system, and project both onto the plane perpendicular to the axis of the initial installation position of the solar panel in the satellite body coordinate system (i.e., the XOZ plane in the satellite body coordinate system) to obtain the solar panel normal vector projection and the sunlight vector projection.

[0041] 1.4 Calculate the angle between the solar panel normal vector projection and the sunlight vector projection to guide the adjustment of the solar panel's motion state, so that the solar panel normal projection and the sunlight vector projection are consistent, thereby improving the efficiency of the solar panel.

[0042] While the disclosure is as stated above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of this disclosure, and all such changes and modifications will fall within the protection scope of this invention.

Claims

1. A simulation method based on the real-time motion state of solar panels on a solar-orienting satellite, characterized in that, Includes the following steps: Step S1: Obtain the installation position of the solar panel in the satellite, and describe the installation position in the satellite body coordinate system to obtain the initial installation position of the solar panel in the satellite body coordinate system. Step S2: Calculate the trajectory of the satellite and obtain the sun ray vector in the J2000 coordinate system at any time. Transform the sun ray vector in the J2000 coordinate system into the sun ray vector in the satellite body coordinate system. Step S3: Project the normal vector of the solar panel and the sunlight vector of the satellite body coordinate system onto the projection plane to obtain the solar panel normal vector projection and the sunlight vector projection, respectively. The projection plane is a plane perpendicular to the axis of the initial installation position of the solar panel in the satellite body coordinate system. In step S3, the solar panel normal vector is the normal vector of the solar panel facing the sun. Step S4: Calculate the angle between the normal vector projection of the solar panel and the vector projection of the sunlight, and adjust the motion state of the solar panel according to the angle; In step S1, the origin of the satellite body coordinate system is located at the center of mass of the satellite. The satellite body coordinate system includes an X-axis, a Y-axis, and a Z-axis. When the satellite has no attitude deviation, the direction of the X-axis coincides with the direction of motion of the satellite, the Y-axis points to the negative normal direction of the satellite's orbital plane, and the Z-axis points to the Earth's center. The solar panel is installed in the positive direction of the X-axis, the negative direction of the X-axis, the positive direction of the Y-axis, the negative direction of the Y-axis, the positive direction of the Z-axis, or the negative direction of the Z-axis.

2. The simulation method based on the real-time motion state of solar panels on a solar-orienting satellite according to claim 1, characterized in that, In step S2, the sunlight vector in the J2000 coordinate system is first transformed into the sunlight vector in the satellite orbit coordinate system, and then the sunlight vector in the satellite orbit coordinate system is transformed into the sunlight vector in the satellite body coordinate system.

3. The simulation method based on the real-time motion state of solar panels on a solar-orienting satellite according to claim 1, characterized in that, In step S2, the orbital trajectory of the satellite is calculated using the SGP4 orbital calculation model.

4. The simulation method based on the real-time motion state of solar panels on a solar-orienting satellite according to claim 1, characterized in that, In step S4, the motion state of the solar panel is adjusted so that the normal vector projection of the solar panel is consistent with the vector projection of the sunlight, thereby improving the photoelectric conversion efficiency of the solar panel.

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