Rotation control method and device for spacecraft solar panel

Abstract

The invention provides a rotation control method and device for a spacecraft solar panel, and belongs to the technical field of universe navigation. According to the method, the generating capacity of the solar panel is obtained through analysis according to a solar vector, a solar panel vector, the area of the solar panel and the generating power of the solar panel; constructing a solar panel power generation efficiency evaluation model by adopting the power generation amount of the solar panel and the power consumption amount of the spacecraft, and adjusting the angle relation between the solar panel and the spacecraft body through the solar panel power generation efficiency evaluation model in the sailing process of the spacecraft, so that the power generation efficiency of the solar panel reaches the highest as far as possible. And the cruising ability of the spacecraft can be greatly improved.

Description

Technical Field

[0001] The present invention relates to the field of space navigation technology, and in particular to a rotation control method and device for a spacecraft solar sail panel. Background Art

[0002] Spacecraft (such as ultra-low-orbit satellites) serve as vehicles for space exploration, carrying out exploration missions by orbiting central celestial bodies (such as Earth). Meanwhile, solar panels (such as fixed-wing panels and single- or dual-degree-of-freedom directional panels) onboard spacecraft can convert the solar energy they receive into electrical energy during the spacecraft's exploration mission. This electrical energy is then converted into thrust by the spacecraft's electric propulsion system to maintain the spacecraft's orbital motion, thereby enhancing the spacecraft's endurance.

[0003] However, the power generation efficiency of existing solar panels is low and cannot meet the power requirements of the electric propulsion system on board the spacecraft, and the improvement of the spacecraft's endurance is small. Summary of the Invention

[0004] The present invention proposes a rotation control method and device for a spacecraft solar panel, which can adjust the angular relationship between the solar panel and the spacecraft body through a solar panel power generation efficiency evaluation model, so that the power generation efficiency of the solar panel can be maximized, thereby greatly improving the endurance of the spacecraft.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] In a first aspect, the present invention provides a method for controlling the rotation of a solar panel on a spacecraft. The spacecraft includes a spacecraft body and a solar panel connected to the spacecraft body. The method comprises: determining the power generation of the solar panel using a sun vector, a solar panel vector, the area of ​​the solar panel, and the power generation of the solar panel; wherein the sun vector is a vector pointing from the spacecraft to the sun, and the solar panel vector represents the angular relationship between the solar panel and the spacecraft body. A solar panel power generation efficiency evaluation model is then determined based on the power generation of the solar panel and the power consumption of the spacecraft; the power consumption of the solar panel indicates the resistance experienced by the spacecraft while maintaining orbital motion. Based on the solar panel power generation efficiency evaluation model, the angular relationship between the solar panel and the spacecraft body is adjusted to maximize the power generation efficiency of the solar panel.

[0007] In a rotation control method for a spacecraft solar panel provided by the present invention, the solar panel's power generation is first analyzed based on the sun vector, the solar panel vector, the panel's area, and the panel's power generation. A solar panel power generation efficiency evaluation model is then constructed using the solar panel's power generation and the spacecraft's power consumption. During the spacecraft's flight, the solar panel power generation efficiency evaluation model is used to adjust the angular relationship between the solar panel and the spacecraft body to maximize the panel's power generation efficiency, thereby significantly improving the spacecraft's endurance.

[0008] In one implementation of the first aspect, determining the power generation of the solar panel's light-receiving area includes: multiplying the product of a sun vector, a solar panel vector, and an area of ​​the solar panel as the solar panel's light-receiving area; and multiplying the power generation of the solar panel by the solar panel's light-receiving area as the solar panel's power generation.

[0009] In one implementation of the first aspect, adjusting the angle between the solar panel and the spacecraft to maximize the power generation efficiency of the solar panel according to a solar panel power generation efficiency evaluation model includes:

[0010] An extreme value analysis is performed on the evaluation model of the solar panel power generation efficiency of a spacecraft. When the angle β between the solar panel and the spacecraft body ranges from -90° to 90°:

[0011] When the position angle θ of the spacecraft on the orbit ranges from 0° to 90°, when p s When cosθ-A>0, adjust Solar panels have the highest power generation efficiency; when p s When cosθ-A<0, adjust β=90°, the power generation efficiency of the solar panel is the highest; when p s When cosθ-A=0, the value of β has nothing to do with the power generation efficiency of the solar panel;

[0012] When the position angle θ of the spacecraft on the orbit is in the range of 90° to 180° and the spacecraft is in the sunlight area, adjust Solar panels have the highest power generation efficiency;

[0013] When the position angle θ of the spacecraft on the orbit ranges from 180° to 360° and the spacecraft is in the sunlight area, adjust Solar panels have the highest power generation efficiency;

[0014] Among them, p s Indicates the power generation of solar panels per unit area, C d It represents the resistance per unit frontal area of ​​the spacecraft, P tIndicates the working power of the spacecraft's electric propulsion system, F t Indicates the thrust provided by the electric propulsion system.

[0015] In an implementation of the first aspect, the method further includes: adjusting a solar panel power generation efficiency evaluation model based on actual resistance encountered by the spacecraft in maintaining orbital motion.

[0016] In one implementation of the first aspect, in the adjusted solar panel power generation efficiency evaluation model, the resistance experienced by the spacecraft during orbital motion satisfies the following formula:

[0017]

[0018] Among them, C d Indicates the resistance per unit frontal area of ​​the spacecraft, F t represents the thrust provided by the electric propulsion system, t1 represents the actual orbit control time, t2 represents the ideal orbit control time, S represents the total frontal area of ​​the spacecraft, T represents the orbital period of the spacecraft, C d0 It represents the resistance per unit frontal area of ​​the spacecraft before adjustment.

[0019] In a second aspect, the present invention provides a rotation control device for a spacecraft solar panel. The spacecraft includes a spacecraft body and a solar panel connected to the spacecraft body. The device includes a power generation determination module, an evaluation model construction module, and a control module. The power generation determination module is configured to determine the power generation of the solar panel using a sun vector, a solar panel vector, the area of ​​the solar panel, and the power generated by the solar panel. The sun vector is a vector pointing from the spacecraft to the sun, and the solar panel vector represents the angular relationship between the solar panel and the spacecraft body. The evaluation model construction module is configured to determine a solar panel power generation efficiency evaluation model based on the power generation of the solar panel and the power consumption of the spacecraft. The power consumption of the solar panel indicates the resistance experienced by the spacecraft while maintaining orbital motion. The control module is configured to adjust the angular relationship between the solar panel and the spacecraft body based on the solar panel power generation efficiency evaluation model to maximize the power generation efficiency of the solar panel.

[0020] In an implementation of the first and second aspects, a solar panel power generation efficiency evaluation model for a spacecraft satisfies the following formula:

[0021]

[0022] Where Q represents the power generation efficiency of the solar panel; p s Indicates the power generation of solar panels per unit area; S p represents the area of ​​the solar sail; θ represents the position angle of the spacecraft on the orbit and represents the solar azimuth angle of the spacecraft; β represents the angle between the solar sail and the spacecraft body; S p cos(θ-β) represents the light receiving area of ​​the solar sail, p s S p cos(θ-β) represents the power generation of the solar panel; C d It represents the resistance per unit frontal area of ​​the spacecraft, S sat Represents the frontal area of ​​the spacecraft, P t Indicates the working power of the spacecraft's electric propulsion system, F t represents the thrust provided by the electric propulsion system, Indicates the power consumption of the solar panels.

[0023] In an implementation of the first and second aspects, the sun vector satisfies the following formula:

[0024]

[0025] Where S1 represents the sun vector, λ S represents the solar pitch angle of the spacecraft, represents the solar azimuth angle of the spacecraft;

[0026] The solar sail vector satisfies the following formula;

[0027]

[0028] Where S2 represents the solar panel vector, and β represents the angle between the solar panel and the spacecraft body.

[0029] In an implementation of the second aspect, the apparatus further includes an adjustment module configured to adjust the solar panel power generation efficiency evaluation model based on actual resistance experienced by the spacecraft while maintaining orbital motion.

[0030] In a third aspect, the present invention provides an electronic device comprising a processor and a memory coupled to the processor; the memory is used to store computer instructions, and when the electronic device is running, the processor executes the computer instructions stored in the memory, so that the electronic device performs the method described in the first aspect or any one of its implementations.

[0031] In a fourth aspect, the present invention provides a computer-readable storage medium comprising computer program instructions, which, when executed by a computer, enable the computer to execute the method as described in the first aspect or any one of its implementations.

[0032] In a fifth aspect, the present invention provides a computer program product, comprising computer program instructions, which, when executed on a computer, enable the computer to execute the method as described in the first aspect or any one of its implementations.

[0033] The technical effects corresponding to the above-mentioned second to fifth aspects and their possible implementation methods can refer to the above-mentioned description of the technical effects of the first aspect and its possible implementation methods, and will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 is a schematic structural diagram of a spacecraft provided in an embodiment of the present application;

[0035] Figure 2 This is one of the schematic diagrams of a rotation control method for a spacecraft solar panel provided in an embodiment of the present application;

[0036] Figure 3 This is a second schematic diagram of a rotation control method for a spacecraft solar panel provided in an embodiment of the present application;

[0037] Figure 4 Schematic diagram of the orbital coordinate system and the body coordinate system provided in the embodiment of the present application;

[0038] Figure 5 is the solar azimuth provided in the embodiment of this application and the solar pitch angle λ s Schematic diagram;

[0039] Figure 6 It is a schematic diagram of the change of the angle β between the solar sail and the spacecraft body during an orbital period;

[0040] Figure 7 This is a third schematic diagram of a rotation control method for a spacecraft solar panel provided in an embodiment of the present application;

[0041] Figure 8 This is a structural schematic diagram of a rotation control device for a spacecraft solar panel provided in an embodiment of the present application. DETAILED DESCRIPTION

[0042] In the description and claims of the present invention, the terms "first" and "second" are used to distinguish different objects rather than to describe a specific order of objects.

[0043] In the embodiments of the present application, “and / or” represents the relationship between objects. For example, A and / or B can represent the following three situations: A exists alone, B exists alone, and A and B exist at the same time.

[0044] In the embodiments of this application, words such as "exemplary" or "for example" are used to indicate examples, illustrations, or descriptions. Any embodiment or design described as "exemplary" or "for example" in the embodiments of this application should not be interpreted as being preferred or advantageous over other embodiments or designs. Rather, the use of words such as "exemplary" or "for example" is intended to present the relevant concepts in a concrete manner.

[0045] The method and apparatus provided in the embodiments of the present application relate to space navigation and can be used to adjust the solar panels of a spacecraft to maximize the power generation efficiency of the solar panels while the spacecraft is performing a detection mission.

[0046] Understandably, Figure 1 As shown, a spacecraft (such as an ultra-low-orbit satellite) includes a spacecraft body and a solar panel connected to the spacecraft body. The spacecraft body has a built-in electric thrust system and energy storage batteries, and the solar panel has built-in solar cells. During the spacecraft's exploration mission, the solar panel can convert the received solar energy into electrical energy and store it in the solar cells. The electric thrust system can convert the electrical energy stored in the energy storage battery or solar cell into thrust to maintain the orbital motion of the spacecraft. It can be seen that the electrical energy converted by the solar panel can increase the power reserve of the spacecraft, thereby improving the endurance of the spacecraft. The higher the power generation efficiency of the solar panel, the more electrical energy converted by the solar panel, and the higher the endurance of the spacecraft.

[0047] However, since solar panels are often fixed flat on spacecraft, as the position of the spacecraft changes on its orbit, the angle between the projection of sunlight on the orbital plane and the normal of the solar panel will change between 0° and 360°, making it impossible to maintain the maximum light-receiving area of ​​the solar panel, which in turn leads to lower power generation efficiency of the solar panel.

[0048] To address the low power generation efficiency of horizontal solar panels, existing technologies have installed dual-degree-of-freedom solar-oriented panels on the spacecraft body. These panels have a swing axis in addition to the rotation axis, thereby compensating for the loss of power generation efficiency caused by the angle between sunlight and the orbital plane. However, while single- and dual-degree-of-freedom solar-oriented panels can maximize the use of solar power for spacecraft (such as ultra-low-orbit satellites), the resistance generated by the panels during spacecraft operation is relatively high. For ultra-low-orbit satellites using electric propulsion, the high atmospheric density results in significant resistance, and the amount of electricity required to maintain the orbit is higher. This may result in the power generated by the solar-oriented panels being insufficient to meet the power consumption required to maintain the satellite's orbit.

[0049] To address the aforementioned issues, embodiments of the present application provide a method and device for controlling the rotation of a spacecraft solar panel. The method first analyzes the solar panel's power generation based on the sun vector, the solar panel vector, the panel's area, and the panel's power generation. A solar panel power generation efficiency evaluation model is then constructed using the panel's power generation and the spacecraft's power consumption. This model is then used to adjust the angle between the solar panel and the spacecraft during navigation, maximizing the panel's power generation efficiency and significantly improving the spacecraft's endurance.

[0050] For example, the rotation control method for a spacecraft solar panel provided in an embodiment of the present invention can be performed by an electronic device with processing capabilities, such as a computer or server. For example, if the electronic device is a computer, the hardware components of the computer may include a processor, memory, a network interface, a user interface, a communication bus, and the like.

[0051] The processor is used to control the electronic device to perform related processing and computing tasks, such as determining the power generation of the solar panels, determining a solar panel power generation efficiency evaluation model, adjusting the angular relationship between the solar panels and the spacecraft body, etc. The processor may include a central processing unit (CPU) or other processors. The processor may be single-core or multi-core, for example, the processor may include multiple CPUs.

[0052] Memory is used to store computer instructions and related data, such as the power generation of solar panels, the power consumption of spacecraft, and solar panel power generation efficiency evaluation models. Memory can be random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM), flash memory, optical storage, magnetic disk storage media or other magnetic storage devices, or any other medium capable of storing program code or data accessible by a computer. Optionally, memory can be integrated into the processor or independent of the processor.

[0053] The network interface is used for the computer to communicate with other devices or communication networks. The network interface can be a transceiver with transceiver functions. Optionally, the network interface can include a standard wired interface or a wireless interface (such as a Wi-Fi interface, a Bluetooth interface, or a 5G interface).

[0054] The communication bus is used to achieve connection and communication between different components. For example, the processor, memory, network interface, and user interface mentioned above can be interconnected through the communication bus.

[0055] The user interface may include a display screen and an input unit (such as a keyboard). Optionally, the user interface may also include a standard wired interface and a wireless interface.

[0056] Those skilled in the art will appreciate that the above-mentioned computer may also include more or fewer components, or a combination of certain components, or different arrangements of components, which is not limited in the embodiments of the present application.

[0057] The following describes in detail a method for controlling the rotation of a spacecraft solar sail panel provided in an embodiment of the present application, taking the case where the spacecraft is an ultra-low-orbit satellite (a satellite with an orbital altitude of less than 300 km), the solar sail panel on the spacecraft is a single-degree-of-freedom sun-oriented sail panel, and the solar sail panel can generate electricity on both sides with the same power generation efficiency. Figure 2 As shown, the above-mentioned rotation control method of the spacecraft solar panel includes S101-S103.

[0058] S101 , determining the power generation of the solar panel using the sun vector, the solar panel vector, the area of ​​the solar panel, and the power generation of the solar panel.

[0059] The sun vector is a vector pointing from the spacecraft to the sun. The solar panel vector represents the angular relationship between the solar panel and the spacecraft. The solar panel power generation capacity describes the power generation capacity of the solar panel corresponding to various angular relationships (also called included angles or rotation angles) between the spacecraft and the solar panel.

[0060] Optionally, combined Figure 2 ,like Figure 3 As shown, the above S101 includes S1011-S1012.

[0061] S1011. The product of the sun vector, the solar panel vector, and the area of ​​the solar panel is used as the light receiving area of ​​the solar panel.

[0062] It should be understood that the area of ​​the solar panel mentioned above refers to the total area of ​​the solar panel, and the light-receiving area of ​​the solar panel mentioned above refers to the area of ​​the portion of the solar panel that is illuminated by sunlight.

[0063] In one application scenario, the solar vector is determined by the solar azimuth and solar pitch angle of the spacecraft; and the solar sail panel vector is determined by the angle between the solar sail panel and the spacecraft body.

[0064] Then the above solar vector satisfies the following formula (1).

[0065]

[0066] Where S1 represents the sun vector, λ S represents the solar pitch angle of the spacecraft, Represents the solar azimuth of the spacecraft.

[0067] The above solar panel vector satisfies the following formula (2).

[0068]

[0069] Where S2 represents the solar panel vector, and β represents the angle between the solar panel and the spacecraft body.

[0070] Then the light receiving area S of the solar sail panel is n satisfy: Among them, S p Represents the area of ​​the solar panel.

[0071] Since only the single-degree-of-freedom rotation of the solar sail panel is considered, the influence of the solar pitch angle can be temporarily ignored when designing the rotation method. The above formula can be simplified to the following formula (3).

[0072]

[0073] Where θ represents the position angle of the spacecraft on the orbit and

[0074] The following describes the process of solving the above-mentioned sun vector S1 and solar sail panel vector S2.

[0075] Step 1: Establish the orbital coordinate system and the body coordinate system

[0076] Establish the orbital coordinate system x0y0z0, such as Figure 4 As shown, the origin O of the orbital coordinate system is located at the center of mass of the spacecraft, the positive direction of the z0 axis points to the center of mass of the central celestial body, the positive direction of the x0 axis points to the forward direction of the spacecraft in the orbital plane, and the positive direction of the y0 axis is perpendicular to the orbital plane of the spacecraft.

[0077] Establish the body coordinate system x b y b z b , continue to refer to Figure 4 , the origin O of the body coordinate system is located at the center of mass of the spacecraft, x b The positive direction of the axis is in the same direction as the longitudinal axis of the spacecraft body, b The positive direction of the axis is perpendicular to the longitudinal axis of the spacecraft body and is located in the symmetry plane of the spacecraft body. bThe positive direction of the axis is perpendicular to the symmetry plane of the spacecraft body. In the embodiment of the present application, assuming that the spacecraft body is a cube, the longitudinal axis is the main structural axis of the spacecraft body. The longitudinal axis is an imaginary axis passing through the center of mass of the spacecraft and perpendicular to the front and rear surfaces of the spacecraft; the symmetry plane of the spacecraft body is an imaginary plane containing the longitudinal axis and parallel to the side of the spacecraft body.

[0078] Step 2: Calculate the sun vector based on the satellite orbit coordinate system and the satellite body coordinate system

[0079] refer to Figure 5 Under the assumption that the orbit of the spacecraft is a circular orbit and the line between the spacecraft and the sun is parallel to the line between the central celestial body (such as the earth) and the sun, the relationship between the sun's rays and the orbital coordinate system can be expressed as the solar azimuth angle. and the solar pitch angle λ s It means that the relationship between the sun's rays and the orbital coordinate system satisfies the following formulas (4) and (5).

[0080]

[0081] Where s represents the angle between the line connecting the earth and the sun and the line connecting the earth and the vernal equinox, i Q represents the angle between the spacecraft orbital plane and the ecliptic plane, Ω Q represents the angle between the line connecting the center of the Earth and the ascending node of the spacecraft's orbit on the ecliptic plane and the line connecting the spacecraft and the vernal equinox, ω Q It represents the angle between the perigee of the spacecraft orbit and the ascending node of the ecliptic plane with the Earth as the center, f Q It represents the angle between the spacecraft position and perigee with the Earth as the center.

[0082] According to the above formulas (4) and (5), the expression of the sun vector in the satellite orbit coordinate system can be obtained, which is the above formula (1).

[0083] Step 3: Calculate the solar panel vector based on the satellite orbit coordinate system and the satellite body coordinate system

[0084] Since the solar sailboard in the embodiment of the present application is a single-degree-of-freedom sun-oriented sailboard, the solar sailboard is set to be installed in the body coordinate system y b The angle β between the solar sail and the spacecraft body is defined as the angle between the normal of the solar sail and the body coordinate system x b The angle between the axes can be obtained by the above formula (2) which expresses the solar sail vector in the orbital coordinate system.

[0085] S1012: The product of the power generation power of the solar panel and the light receiving area of ​​the solar panel is used as the power generation amount of the solar panel.

[0086] In one implementation, the power generation of the solar panel is the product of the power generation of the solar panel and the light receiving area of ​​the solar panel. Combining the above formula (3) can be used to calculate the power generation of the solar panel. The calculation formula for the power generation Eg of the solar panel is shown in the following formula (6).

[0087] Eg=p s cos(θ-β) Formula (6)

[0088] Among them, p s Indicates the power generation of solar panels per unit area.

[0089] S102: Determine a solar panel power generation efficiency evaluation model based on the power generation of the solar panel and the power consumption of the spacecraft.

[0090] In the embodiment of the present application, the difference between the power generation of the solar panel and the power consumption of the spacecraft is used as a solar panel power generation efficiency evaluation model to evaluate the power generation efficiency of the solar panel.

[0091] The power generation of the solar panels is obtained by the above formula (6). The power consumption of the solar panels indicates the resistance encountered by the spacecraft in the process of maintaining orbital motion. Specifically, the power consumption of the solar panels refers to the power consumed by the electric propulsion system to maintain the orbital motion of the spacecraft after the windward area of ​​the spacecraft body and the windward area of ​​the solar panels are jointly subjected to resistance during the navigation process. Therefore, the difference between the power generation of the solar panels and the power consumption of the spacecraft is the power that can be stored in the solar cells from the power converted by the solar panels.

[0092] In one implementation, the solar panel power generation efficiency evaluation model of the spacecraft satisfies the following formula (7).

[0093]

[0094] Where Q represents the power generation efficiency of the solar panel; p s Indicates the power generation of solar panels per unit area; S p represents the area of ​​the solar sail; θ represents the position angle of the spacecraft on the orbit and represents the solar azimuth angle of the spacecraft; β represents the angle between the solar sail and the spacecraft body; S p cos(θ-β) represents the light receiving area of ​​the solar sail, p s S p cos(θ-β) represents the power generation of the solar panel; C d It represents the resistance per unit frontal area of ​​the spacecraft, S sat Represents the frontal area of ​​the spacecraft, P tIndicates the working power of the spacecraft's electric propulsion system, F t represents the thrust provided by the electric propulsion system, Indicates the power consumption of the solar panels.

[0095] It should be noted that the resistance C per unit frontal area of ​​the spacecraft is d The working power of the spacecraft's electric propulsion system P is calculated based on the spacecraft's orbital altitude and the existing atmospheric density model. t and the thrust F provided by the electric propulsion system t It can be directly obtained through the electric propulsion system, and the specific solution and acquisition process of the above parameters will not be described in detail in the embodiment of the present application.

[0096] S103. According to the solar panel power generation efficiency evaluation model, adjust the angle between the solar panel and the spacecraft body to maximize the power generation efficiency of the solar panel.

[0097] In one application scenario, the implementation process of the above S103 is as follows.

[0098] Perform extreme value analysis on the evaluation model of spacecraft solar panels power generation efficiency.

[0099] For example, the extreme value analysis of the above formula (7) is performed on the premise that the range of θ and β is 0° to 90°, and β equal to 90° indicates that the solar panel is installed horizontally and does not generate additional resistance.

[0100] The first-order derivative Q' of the above formula (7) is: Q'=p s S p sin(θ-β)+AS p sinβ, where

[0101] Let the first-order derivative Q'=0, we can get:

[0102] The second-order derivative Q" of the above formula (7) is: Q" = -p s S p sin(θ-β)+AS p cosβ.

[0103] Analyzing the above second-order derivative, we can see that when p s cosθ-A>0, that is When Q The windsurfing board can obtain the highest power generation efficiency when p takes the maximum value. s cosθ-A<0, that is and When , Q takes the minimum value at β0 and increases in the range of β0~90°, and Q(0)<Q(90), so β ​​takes 90°, that is, the highest power generation efficiency can be obtained when the solar sail panel is placed horizontally; at the same time, since the value of cosθ has an upper limit of 1, and When Q has no maximum value, β takes 90°, that is, the highest power generation efficiency can be obtained when the solar panels are placed flat. s If cosθ-A=0, then β0 has no solution, and the value of β no longer affects the power generation efficiency of the spacecraft's solar panels.

[0104] It should be noted that due to Among them C d Related to the spacecraft orbit altitude, P t 、F t and p s It is related to the energy and power system capabilities of the spacecraft. Therefore, in order to maximize the power generation efficiency, the above factors should be considered simultaneously.

[0105] Based on the above extreme value analysis, refer to Figure 6 (The change of the angle β between the solar panel and the spacecraft body within one orbital period) It can be concluded that when the angle β between the solar panel and the spacecraft body ranges from -90° to 90°:

[0106] When the position angle θ of the spacecraft on the orbit ranges from 0° to 90°, when p s When cosθ-A>0, adjust Solar panels have the highest power generation efficiency; when p s When cosθ-A<0, adjust β=90° (that is, the solar sail panel is placed horizontally), the power generation efficiency of the solar sail panel is the highest; when p s When cosθ-A=0, the value of β has nothing to do with the power generation efficiency of the solar panel;

[0107] When the position angle θ of the spacecraft on the orbit is in the range of 90° to 180° and the spacecraft is in the sunlight area, adjust Solar panels have the highest efficiency in generating electricity.

[0108] When the position angle θ of the spacecraft on the orbit ranges from 180° to 360° and the spacecraft is in the sunlight area, adjust Solar panels have the highest efficiency in generating electricity.

[0109] When the spacecraft is in the earth's shadow, adjust β=90°, that is, the solar sail panel is placed horizontally. At this time, the windward area of ​​the solar sail panel is the smallest, and the resistance encountered by the solar sail panel is also the smallest.

[0110] Exemplary, reference Figure 6 Provides the change of the angle β between the solar sail and the spacecraft body during one orbital period

[0111] The following describes in detail the method for determining whether the above-mentioned spacecraft is in the sun's illumination area or the earth's shadow area.

[0112] Assume that the solar azimuth angle corresponding to the spacecraft entering the earth's shadow is The solar azimuth angle corresponding to the spacecraft leaving the earth's shadow is According to spherical geometry, the following formulas (8) and (9) are obtained.

[0113]

[0114] Where ψ is the angular radius of the Earth observed with the spacecraft as the center, and ψ satisfies: R e represents the average radius of the Earth, and r represents the orbital radius of the spacecraft.

[0115] So far, we have obtained the range of the earth shadow area When the solar azimuth angle corresponding to the spacecraft is If the spacecraft is within the Earth's shadow, it is judged that the spacecraft is in the Earth's shadow; otherwise, the spacecraft is in the Sun's illumination area.

[0116] For example, combined Figure 3 ,like Figure 7 As shown, the above-mentioned rotation control method of the spacecraft solar panel also includes S104.

[0117] S104. Adjust the solar panel power generation efficiency evaluation model based on the actual resistance encountered by the spacecraft in the process of maintaining orbital motion.

[0118] It should be noted that during the actual operation of the spacecraft, due to factors such as orbit adjustment, changes in the sun's position, and deviations between the existing atmospheric model and the actual atmospheric density, the actual rotation strategy with the highest solar panel power generation efficiency may deviate from the solution given by the solar panel power generation efficiency evaluation model. Therefore, during the navigation of the spacecraft, the resistance C per unit windward area of ​​the spacecraft in the solar panel power generation efficiency evaluation model must be calculated. d Make adjustments.

[0119] In the above-mentioned adjusted solar panel power generation efficiency evaluation model, the resistance encountered by the spacecraft during the process of maintaining orbital motion satisfies the following formula:

[0120]

[0121] Among them, C d Indicates the resistance per unit frontal area of ​​the spacecraft, F trepresents the thrust provided by the electric propulsion system, t1 represents the actual orbit control time, t2 represents the ideal orbit control time, S represents the total frontal area of ​​the spacecraft, T represents the orbital period of the spacecraft, C d0 It represents the resistance per unit frontal area of ​​the spacecraft before adjustment.

[0122] In summary, in the rotation control method for a spacecraft solar panel provided in the embodiments of the present application, the solar panel's power generation is first analyzed based on the sun vector, the solar panel vector, the area of ​​the solar panel, and the power generation of the solar panel. A solar panel power generation efficiency evaluation model is then constructed using the solar panel's power generation and the spacecraft's power consumption. During the spacecraft's navigation, the solar panel power generation efficiency evaluation model is used to adjust the angular relationship between the solar panel and the spacecraft body to maximize the solar panel's power generation efficiency, thereby significantly improving the spacecraft's endurance.

[0123] Accordingly, an embodiment of the present application provides a rotation control device for a spacecraft solar sail panel, wherein the spacecraft includes a spacecraft body and a solar sail panel connected to the spacecraft body, such as Figure 8 As shown, the device includes a power generation determination module 501 , an evaluation model construction module 502 and a control module 503 .

[0124] The power generation determination module 501 is configured to determine the power generation of the solar panel using the sun vector, the solar panel vector, the area of ​​the solar panel, and the power generation of the solar panel. The sun vector is a vector pointing from the spacecraft to the sun, and the solar panel vector represents the angular relationship between the solar panel and the spacecraft. For example, the power generation determination module 501 is configured to implement S101 of the aforementioned spacecraft solar panel rotation control method.

[0125] Evaluation model construction module 502 is configured to determine a solar panel power generation efficiency evaluation model based on the solar panel's power generation and the spacecraft's power consumption. The solar panel's power consumption indicates the drag experienced by the spacecraft while maintaining orbital motion. For example, evaluation model construction module 502 is configured to implement S102 of the aforementioned spacecraft solar panel rotation control method.

[0126] The control module 503 is configured to adjust the angle between the solar panel and the spacecraft body according to the solar panel power generation efficiency evaluation model to maximize the power generation efficiency of the solar panel. For example, the control module 503 is configured to implement S103 of the above-mentioned spacecraft solar panel rotation control method.

[0127] Optionally, the power generation determination module 501 is specifically configured to: multiply the sun vector, the solar panel vector, and the area of ​​the solar panel as the light-receiving area of ​​the solar panel. And multiply the power generated by the solar panel by the light-receiving area of ​​the solar panel as the power generation of the solar panel. For example, the power generation determination module 501 is specifically configured to implement S1011-S1012 of the aforementioned spacecraft solar panel rotation control method.

[0128] Optionally, the above device further includes an adjustment module 504 .

[0129] The adjustment module 504 is used to adjust the solar panel power generation efficiency evaluation model based on the actual resistance encountered by the spacecraft in the process of maintaining orbital motion.

[0130] The various modules of the above-mentioned spacecraft solar panel rotation control device can also be used to execute other steps in the above-mentioned method embodiment. All relevant contents involved in the above-mentioned method embodiment can be referred to the functional description of the corresponding functional module and will not be repeated here.

[0131] The present application also provides an electronic device comprising: a processor and a memory coupled to the processor; the memory is configured to store computer instructions, and when the electronic device is in operation, the processor executes the computer instructions stored in the memory, causing the electronic device to perform the method described in the above embodiment. The processor can implement the aforementioned power generation determination module 501, evaluation model construction module 502, and control module 503; the memory can also store the power generation of solar panels, the power consumption of spacecraft, and a solar panel power generation efficiency evaluation model.

[0132] An embodiment of the present application further provides a computer-readable storage medium, which includes a computer program. When the computer program runs on a computer, the method described in the above embodiment is executed.

[0133] An embodiment of the present application further provides a computer program product, which includes computer program instructions. When the computer program instructions are run on a computer, the method described in the above embodiment is executed.

[0134] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referred to each other. Each embodiment focuses on the differences from other embodiments.

[0135] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of this application.

Claims

1. A method for controlling the rotation of a solar panel on a spacecraft, wherein the spacecraft comprises a spacecraft body and a solar panel connected to the spacecraft body, characterized in that: The method comprises: Determining the power generation of the solar panel using a sun vector, a solar panel vector, an area of ​​the solar panel, and a power generation power of the solar panel; wherein the sun vector is a vector pointing from the spacecraft to the sun, and the solar panel vector represents an angular relationship between the solar panel and the spacecraft body; determining a solar panel power generation efficiency evaluation model based on the power generation of the solar panel and the power consumption of the spacecraft; the power consumption of the solar panel indicates the resistance encountered by the spacecraft in maintaining orbital motion; According to the solar panel power generation efficiency evaluation model, the angular relationship between the solar panel and the spacecraft body is adjusted to maximize the power generation efficiency of the solar panel.

2. The method according to claim 1, wherein The solar panel power generation efficiency evaluation model of the spacecraft satisfies the following formula: Wherein, Q represents the power generation efficiency of the solar panel; p s Indicates the power generation of solar panels per unit area; S p represents the area of ​​the solar sail panel; θ represents the position angle of the spacecraft on the orbit; represents the solar azimuth angle of the spacecraft; β represents the angle between the solar sail panel and the spacecraft body; S p cos(θ-β) represents the light receiving area of ​​the solar sail panel, p s S p cos(θ-β) represents the power generation of the solar panel; C d It represents the resistance per unit frontal area of ​​the spacecraft, S sat represents the frontal area of ​​the spacecraft body, P t represents the working power of the electric propulsion system of the spacecraft, F t represents the thrust provided by the electric propulsion system, Indicates the power consumption of the solar panel.

3. The method according to claim 1, wherein Determining the power generation of the light-receiving area of ​​the solar panel includes: The product of the sun vector, the solar sail panel vector and the area of ​​the solar sail panel is used as the light receiving area of ​​the solar sail panel; The product of the power generation power of the solar panel and the light receiving area of ​​the solar panel is used as the power generation amount of the solar panel.

4. The method according to claim 1 or 3, wherein: The sun vector satisfies the following formula: Wherein, S1 represents the sun vector, λ S represents the solar pitch angle of the spacecraft, represents the solar azimuth angle of the spacecraft; The solar sail panel vector satisfies the following formula: Wherein, S2 represents the solar panel vector, and β represents the angle between the solar panel and the spacecraft body.

5. The method according to claim 1, wherein The adjusting the angular relationship between the solar panel and the spacecraft body according to the solar panel power generation efficiency evaluation model to maximize the power generation efficiency of the solar panel includes: An extreme value analysis is performed on the solar panel power generation efficiency evaluation model of the spacecraft. When the angle β between the solar panel and the spacecraft body ranges from -90° to 90°: When the position angle θ of the spacecraft on the orbit ranges from 0° to 90°, when p s When cosθ-A>0, adjust The solar panels have the highest power generation efficiency; when p s When cosθ-A<0, adjust β=90°, the power generation efficiency of the solar panel is the highest; when p s When cosθ-A=0, the value of β has nothing to do with the power generation efficiency of the solar panel; When the position angle θ of the spacecraft on the orbit is in the range of 90° to 180° and the spacecraft is in the sunlight area, adjust The solar panels have the highest power generation efficiency; When the position angle θ of the spacecraft on the orbit is in the range of 180° to 360° and the spacecraft is in the sunlight area, adjust The solar panels have the highest power generation efficiency; Among them, p s Indicates the power generation of solar panels per unit area, C d It represents the resistance per unit frontal area of ​​the spacecraft, P t represents the working power of the electric propulsion system of the spacecraft, F t represents the thrust provided by the electric propulsion system.

6. The method according to claim 1, wherein The method further comprises: The solar panel power generation efficiency evaluation model is adjusted based on the actual resistance encountered by the spacecraft in the process of maintaining orbital motion.

7. The method according to claim 6, wherein In the adjusted solar panel power generation efficiency evaluation model, the resistance experienced by the spacecraft during orbital motion satisfies the following formula: Among them, C d It represents the resistance per unit frontal area of ​​the spacecraft, F t represents the thrust provided by the electric propulsion system, t1 represents the actual orbit control time, t2 represents the ideal orbit control time, S represents the total frontal area of ​​the spacecraft, T represents the orbital period of the spacecraft, C d0 It represents the resistance per unit frontal area of ​​the spacecraft before adjustment.

8. A rotation control device for a spacecraft solar sail panel, characterized in that: The spacecraft includes a spacecraft body and a solar sail panel connected to the spacecraft body, and the device includes a power generation determination module, an evaluation model construction module, and a control module; The power generation determination module is configured to determine the power generation of the solar panel using a sun vector, a solar panel vector, an area of ​​the solar panel, and a power generation power of the solar panel; wherein the sun vector is a vector pointing from the spacecraft to the sun, and the solar panel vector represents an angular relationship between the solar panel and the spacecraft body; The evaluation model building module is used to determine a solar panel power generation efficiency evaluation model based on the power generation of the solar panel and the power consumption of the spacecraft; the power consumption of the solar panel indicates the resistance encountered by the spacecraft in maintaining orbital motion; The control module is used to adjust the angular relationship between the solar panel and the spacecraft body according to the solar panel power generation efficiency evaluation model to maximize the power generation efficiency of the solar panel.

9. An electronic device, characterized in that: The electronic device comprises a processor and a memory coupled to the processor; the memory is used to store computer instructions, and when the electronic device is running, the processor executes the computer instructions stored in the memory, so that the electronic device executes the method according to any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that The method comprises computer program instructions, which, when executed by a computer, cause the computer to perform the method according to any one of claims 1 to 7.

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