Solar panel energy supply calculation method and device under clamping stagnation of solar panel and electronic equipment

Abstract

The invention provides a solar panel energy supply calculation method and device under clamping stagnation of a solar panel and electronic equipment, and the method comprises the steps: obtaining a corresponding clamping stagnation angle gamma when the solar panel is in a clamping stagnation state, the clamping stagnation angle gamma being an included angle between a plane where the solar panel is located in the clamping stagnation state and a plane where the solar panel is located in an electrical zero position; the interval of the solar incident angle of the solar panel in one period is determined when the solar panel is in the clamping stagnation state, the interval comprises an illumination period and an earth shadow period, and the solar incident angle is the included angle between the solar vector direction and the normal direction of the solar panel; the output energy of the solar panel in the illumination period in one period is calculated, the output energy is an expression related to the clamping stagnation angle, and one period of the solar panel corresponds to the orbit period of satellite operation. According to the method, the energy supply condition of the solar panel at different clamping stagnation angles can be accurately represented, and effective support is provided for subsequent in-orbit practical application of satellites.

Description

Technical Field

[0001] The present invention mainly relates to the technical field of satellite monitoring and control, and particularly relates to a method, device and electronic device for calculating the energy supply of a solar panel under the condition of panel jamming. Background Art

[0002] A solar panel is a device that converts solar energy into electrical energy. It converts solar energy into electrical energy through the photovoltaic effect to provide continuous power for the satellite, or stores the electrical energy in a storage battery to provide continuous power for the satellite. The solar panel has the functions of power supply and charging, and is a key energy device for the satellite to operate in orbit. During the launch phase, the panel is folded to reduce the volume, and after entering the orbit, it is unfolded and the panel angle is adjusted in real time to maximize the absorption of solar energy.

[0003] SADA (Solar Array Drive Assembly) is one of the important components of the satellite energy system. SADA consists of SADE (controller line box), SADM_A (+Y solar panel drive mechanism), SADM_B (-Y solar panel drive mechanism), etc. Its main function is to control and manage and ensure that the solar cell array points to the sun to achieve the maximum efficiency of photovoltaic conversion, so as to provide sufficient energy for the payload and even the whole satellite.

[0004] According to the statistics of the failure situation data of the satellite during on-orbit operation, it is found that the failure of the energy system accounts for the second highest proportion among all subsystems. Among them, the abnormal output failure of the solar cell array accounts for about 25%, and most of them are SADA drive mechanism failures. About 45% of the energy system failures of on-orbit spacecraft will lead to the failure of the entire mission, and 80% of the energy system failures have a serious impact on the entire mission. Therefore, the normal operation of SADA is of great significance to the satellite payload service and the safety of the satellite platform. However, there is currently no energy processing method in the existing technology for the situation where a certain wing of SADA fails in orbit and the panel of that wing cannot rotate. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a method, device and electronic device for calculating the energy supply of a solar panel under the condition of panel jamming, which can accurately characterize the energy supply situation of the solar panel at different jamming angles and provide effective support for the subsequent actual application of the satellite in orbit.

[0006] To solve the above technical problems, in a first aspect, the present invention provides a method for calculating the energy supply of a solar panel during stalling, including: obtaining a stalling angle γ corresponding to the solar panel when it is in a stalling state, where the stalling angle γ is the angle between the plane where the solar panel is located in the stalling state and the plane where it is located in the electrical zero position; determining the interval of the solar incidence angle of the solar panel within one cycle when the solar panel is in a stalling state, and the interval includes a lighting period and an eclipse period, where the solar incidence angle is the angle between the solar vector direction and the normal direction of the solar panel; calculating the output energy of the solar panel during the lighting period within one cycle, and the output energy is an expression related to the stalling angle, where one cycle of the solar panel corresponds to the orbital period of the satellite operation.

[0007] Optionally, the method further includes: after calculating the output energy of the solar panel during the lighting period within one cycle, obtaining a target stalling angle corresponding to the maximum value of the output energy according to the expression of the output energy.

[0008] Optionally, the method further includes: calculating the output energy of the solar panel at the target stalling angle.

[0009] Optionally, the method further includes: determining whether the output energy of the solar panel at the target stalling angle meets the energy supply and demand balance of the satellite, where the energy supply and demand balance means that the battery does not discharge during the lighting period, and the battery starts to supply power to the working load on the satellite in a fully charged state during the eclipse period.

[0010] Optionally, the angle interval of the solar incidence angle is where β is the orbital solar angle and γ is the stalling angle.

[0011] Optionally, the expression of the output energy of the solar panel is: In the formula, W N is the output energy, V bus is the bus voltage, ω is the angular velocity of change of the solar incidence angle, i N is the normal output current of the solar panel of the satellite in the Nth year in orbit, ωt is related to the stalling angle γ, t0 is the starting moment of the current cycle, t is the ending moment of the current cycle, and the RELU expression indicates the calculation result of RELU(p) under different p values.

[0012] Optionally, calculating the output energy of the solar panel during the lighting period within one cycle includes: dividing the lighting period into each sub-interval, and respectively calculating the output energy of the solar panel within each sub-interval.

[0013] In a second aspect, the present invention provides a solar panel jamming under-panel power supply calculation device, including: an acquisition module configured to acquire a jamming angle γ corresponding to the solar panel when it is in a jammed state, where the jamming angle γ is the angle between the plane where the solar panel is located in the jammed state and the plane where it is located at the electrical zero position; a determination module configured to determine, according to the solar panel being in a jammed state, the interval where the solar incidence angle of the solar panel is located within one cycle, the interval including a light period and an earth shadow period, where the solar incidence angle is the angle between the solar vector direction and the normal direction of the solar panel; a calculation module configured to calculate the output energy of the solar panel during the light period within one cycle, the output energy being an expression related to the jamming angle, where one cycle of the solar panel corresponds to the orbital period of the satellite operation.

[0014] In a third aspect, the present invention provides an electronic device, including: a processor and a memory, where the memory stores a program or instruction that can run on the processor, and when the program or instruction is executed by the processor, it implements the steps of the solar panel jamming under-panel power supply calculation method as described in the first aspect.

[0015] In a fourth aspect, the present invention provides a readable storage medium, where a program or instruction is stored on the readable storage medium, and when the program or instruction is executed by a processor, it implements the steps of the solar panel jamming under-panel power supply calculation method as described in the first aspect.

[0016] Compared with the prior art, the present invention has the following advantages: First, acquire the jamming angle γ corresponding to the solar panel when it is in a jammed state, then determine the interval where the solar incidence angle of the solar panel is located within one cycle according to the solar panel being in a jammed state, the interval including a light period and an earth shadow period, and finally calculate the output energy of the solar panel during the light period within one cycle, the output energy being an expression related to the jamming angle, thereby accurately characterizing the power supply situation of the solar panel at different jamming angles and providing effective support for the subsequent actual in-orbit application of the satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Including the drawings is to provide a further understanding of the present application. They are incorporated and constitute a part of the present application. The drawings illustrate the embodiments of the present application and, together with this specification, serve to explain the principle of the present application. In the drawings:

[0018] Figure 1 is a schematic diagram of a satellite body structure;

[0019] Figure 2 is a flowchart of the solar panel jamming under-panel power supply calculation method according to an embodiment of the present invention;

[0020] Figure 3It is a schematic diagram of the predicted decadal change of the solar angle of the satellite orbit;

[0021] Figure 4 It is a schematic diagram of the annual change of the solar incidence angle of the -Y solar panel in the embodiment of the present invention (γ = 360°);

[0022] Figure 5 It is a schematic diagram of the annual change of the solar incidence angle of the -Y solar panel in the embodiment of the present invention (γ = 270°);

[0023] Figure 6 It is a schematic diagram of the energy analysis at different jamming angles in the embodiment of the present invention (during the earth shadow period);

[0024] Figure 7 It is a schematic diagram of the energy analysis at different jamming angles in the embodiment of the present invention (during the illumination period);

[0025] Figure 8 It is a tracking schematic diagram of the SADA target rotation angle during the earth shadow period and the summer solstice sunshine period;

[0026] Figure 9 It is a schematic diagram of the analysis of the change of the solar altitude angle of the actual on-orbit trajectory of the satellite;

[0027] Figure 10 It is a graph showing the relationship between the output current of the satellite solar panel and the load conditions;

[0028] Figure 11 It is a graph showing the change of the voltage and discharge current of battery packs A and B during the spherical shadow area;

[0029] Figure 12 It is a graph showing the change of the voltage and discharge current of battery packs A and B during the summer solstice illumination season;

[0030] Figure 13 It is a schematic diagram of the structure of the solar panel energy supply calculation device under jamming in an embodiment of the present invention;

[0031] Figure 14 It is a schematic diagram of an electronic device shown according to an embodiment of the present invention. Detailed implementation manners

[0032] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the accompanying drawings required for the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings in the following description are only some examples or embodiments of the present application. For those of ordinary skill in the art, without creative efforts, the present application can also be applied to other similar scenarios based on these drawings. Unless obvious from the language context or otherwise stated, the same reference numerals in the figures represent the same structure or operation.

[0033] As shown in this application and the claims, unless the context clearly indicates otherwise, words such as "a", "an", "one", and / or "the" are not specifically singular and may also include the plural. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0034] In this application, flowcharts are used to illustrate the operations performed by the system according to the embodiments of this application. It should be understood that the operations before or below do not necessarily need to be executed precisely in sequence. On the contrary, they can be executed in reverse order or simultaneously. At the same time, other operations can be added to these processes, or one or more steps can be removed from these processes.

[0035] During the on-orbit operation of the satellite, there are periods of eclipse and illumination. For example, if the satellite is operating in a MEO (Medium Earth Orbit) with an orbital altitude of 21,528 km and an orbital period T of 13 h, the longest eclipse time is 60 min. For example, refer to Figure 1 As shown, the satellite's solar array (or solar panel or panel) uses a rigid structure deployable solar wing, which consists of two solar wings in the +Y and -Y directions. Each wing has 3 panels, and the output power meets the requirements of a peak load of 2 KW and a constant load of 1587 W. The circuits of each solar panel are collected on the back through wires, and then pass through isolation diodes to the cable electrical connectors on the panel. The power and signals of each wing of solar panels are input to the satellite power control unit through the inter-panel cables and electrical connectors on both sides of the SADA, and finally, the power control unit supplies power to each module of the satellite subsystems. The rotating arrow in the figure indicates the rotation direction of the solar panel. The coordinate system is the satellite body coordinate system, and the coordinate system in the figure is represented as: the origin is located at the satellite's center of mass (represented by O), the X-axis is the roll axis, pointing in the forward direction of the satellite, the Y-axis is the pitch axis, pointing in the negative normal direction of the orbit, and the Z-axis is the yaw axis, pointing radially towards the center of the earth. In addition, the X, Y, and Z axes form a right-handed orthogonal coordinate system.

[0036] The satellite sets its working modes according to different mission scenarios, including solar capture mode, minimum safety mode, uncontrolled mode, sun-pointing mode, earth capture mode, stable earth-pointing mode, orbit control mode, and other working modes. The on-orbit drive control of the solar panels adopts a fully autonomous control strategy, and the working mode is automatically switched during the switching process of different satellite operation modes. The SADA has multiple working modes in orbit, such as cruise mode, emergency mode, incremental mode, hold mode, and automatic zeroing mode. During the sun-pointing process of the solar panels, it is in cruise mode, tracking the sun at a fixed angular velocity. Due to the predicted orbit error, the actual rotation angle will be ahead of or lag behind the target angle, and the energy cannot be optimized. Therefore, it is necessary to control the SADM to switch to incremental operation or hold mode to achieve stable sun-pointing of the solar panels, transmit the electric energy generated by the solar array to the satellite power controller, and ensure the normal supply of satellite energy.

[0037] During the steady-state flight of the satellite in orbit, the working mode is stable earth-pointing. Whether in the illumination period or the shadow period, the yaw attitude and the solar vector can be obtained, so the satellite conducts yaw control according to the solar vector both in the illumination period and the earth shadow period. When a stall fault occurs in the SADA, it often shows that one wing / two wings cannot rotate freely and gets stuck at a certain angle. For example, if the SADA of the -Y wing of the solar panel has a stall fault, it will cause the -Y solar panel to get stuck at a certain fixed angle during the earth shadow season, unable to face the sun normally, and the output current and power of the -Y wing array are abnormal. Since the output power of a single wing generally cannot meet the satellite load demand, the battery pack is in a discharging state, and the bus voltage is normally stable at 42.2±0.2V. After the SADA motor in orbit has a stall, it can be restored to operation by applying power to the double windings, but it will still get stuck at irregular intervals.

[0038] In the initial launch stage of the satellite, the electrical zero position of the SADA coincides with the mechanical zero position and is in the horizontal direction (such as Figure 1 the Z-axis direction in ox ). When the solar panels are fully deployed and an effective deployment locking signal is given, the on-board computer issues relevant programmed control instructions to execute the emergency mode, returning to the electrical zero position at an angular velocity of about 0.3° / s. Based on the given zero position indication signal, it is convenient for the SADA to accurately calculate the absolute rotation angle when executing other modes and obtain the pointing position of the solar array plane. According to the satellite's on-orbit attitude operation state diagram, the solar vector in the orbital coordinate system is S = [SS oy S oz T . When the satellite is operating in the yaw maneuver mode, the target yaw angle is ψ m = a tan2(S oy , S ox ). Among them, S ox / S oy / S ozare the projections of the orbital solar vector in the x / y / z directions respectively, and the satellite body coordinate system solar vector is:

[0039]

[0040] The target rotation angle is defined as the angle between the projection of the sun vector on the XOZ plane and the SADA electrical zero position (i.e., the +Z axis). The clockwise direction is positive and the range is [0,2π]. The -Y solar panel target rotation angle is:

[0041]

[0042] +Y solar panel target rotation angle is:

[0043]

[0044] S bx / S by / S bz They are the sun vector S in the satellite coordinate system b The corresponding deviation angle is calculated by the target rotation angle (the angle between the normal line of the solar panel and the sun vector is equal to the target rotation angle ψ m Different deviation angles set different working modes of SADA, thereby driving and controlling the solar panels to face the sun. When the satellite switches from facing the sun to stable facing the earth, from stable facing the earth to yaw maneuvering, or from attitude adjustment after orbit control to yaw maneuvering, the SADA large-angle rotation increment mode is used to achieve solar panel tracking at an angular velocity of about 0.3° / s. This mode is the steady-state operation mode of the satellite. When the satellite works in stable facing the earth or yaw maneuvering, the solar panels are controlled to synchronously track the sun through the rotation of SADA according to the solar vector angle, and SADA operates in a cruising angular velocity mode of about 0.0042° / s.

[0045] refer to Figure 2 As shown, the solar panel energy supply calculation method 200 of this embodiment when the solar panel is stuck mainly includes: S210, obtaining the stuck angle γ corresponding to the solar panel in the stuck state, the stuck angle γ is the angle between the plane where the solar panel is located in the stuck state and the plane where the solar panel is located in the electrical zero position; S220, determining the interval of the solar incident angle of the solar panel in one cycle when the solar panel is in the stuck state, the interval includes the illumination period and the earth shadow period, wherein the solar incident angle is the angle between the sun vector direction and the normal of the solar panel; S230, calculating the output energy of the solar panel in the illumination period in one cycle, the output energy is an expression related to the stuck angle, wherein one cycle of the solar panel corresponds to the orbital period of the satellite.

[0046] Exemplarily, the orbital solar angle of the on-orbit satellite is The orbital solar angle β is the angle between the orbital plane of the satellite orbiting the earth and the vector of the satellite pointing to the sun. Then, the target rotation angle of the +Y-wing solar panel varies between |β| and (π - |β|), and the target rotation angle of the -Y-wing SADM varies between (π + |β|) and (2π - |β|). When the solar panel is stuck at the γ angle, the variation range of the solar incidence angle θ of the solar panel is:

[0047]

[0048] Where When the solar panel is irradiated by no sunlight outside this interval, the current is 0A. The stuck angle γ ∈ [π + |β| to 2π - |β|]. The angular velocity ω of the change of the solar incidence angle θ is about 0.0042° / s. The specific value is related to the solar incidence angle. The principle is to keep the solar panel rotate one week in one orbital period. The calculation formula for the average value of the angular velocity is:

[0049]

[0050] Where T represents the time of one period, and the output energy W of the solar panel N Has a positive correlation with cosθ, as follows:

[0051]

[0052] In the formula, W N Is the output energy, V bus Is the bus voltage, i N Is the output current of the solar panel of the satellite in the Nth year on orbit when it is facing the sun normally (i.e., when there is no jamming), ω is the angular velocity of the change of the solar incidence angle, ωt is related to the stuck angle γ, t0 is the start time of the current period, t is the end time of the current period, and the RELU expression indicates the calculation result of RELU(p) in different p values. Let -(γ - π - |β|) = θ1; 2π - γ + |β| = θ2.

[0053] In some embodiments, the illumination period is divided into sub-intervals, and the output energy of the solar panel is calculated separately in each sub-interval. For example, since the target rotation angle of the -Y-wing SADM varies between (π + |β|) and (2π - |β|), the interval span is [π - 2|β|]. When When, the interval span exceeds Then for the γ angle stuck in this interval, θ may exceed Situation. Therefore, for The energy situation needs to be calculated by sub-intervals.

[0054]

[0055] Calculated

[0056]

[0057]

[0058] To obtain the stalling angle of the solar panel when the output energy takes the maximum value, we can set W N ′ = 0 and obtain

[0059]

[0060] When the maximum values of the output energy in the 3 γ intervals are as follows respectively:

[0061]

[0062] When 2cosβ ≥ 1 + cos(2∣β∣). In this case, when the output energy is the largest, and the maximum value of the output energy is

[0063] When the span of the rotation angle interval of the -Y-wing SADM target is less than

[0064]

[0065] Calculated

[0066]

[0067] Set W N ′ = 0 and obtain At this time,

[0068] It can be seen that regardless of the value of the β angle, when the stalling angle γ is the output energy of the solar panel is the maximum, and the maximum output energy is

[0069] Refer to Figure 3 As shown, according to the satellite orbit situation, the trend of the orbital solar angle in the next 10 years is fitted. When the absolute value of the orbital solar angle β is less than 13 degrees, the satellite enters the earth shadow season. When β is 0, the satellite enters the deepest shadow, and the longest earth shadow duration is 1 h. The change trend of the solar incidence angle θ of the solar panel in the next 1 year when it is stalled at 2π angles is referred to Figure 4 and Figure 5 as shown.

[0070] In some embodiments, it is determined whether the output energy of the solar panel at the target stuck angle meets the energy supply-demand balance of the satellite, where the energy supply-demand balance means that the battery does not discharge during the illumination period, and the battery starts to supply power to the payload on the satellite in the fully charged state during the eclipse period. The most energy-intensive situation is the eclipse period. If the energy balance is achieved during the eclipse period, the illumination period is also balanced. Only the energy balance situation during the eclipse period is analyzed. For the illumination period, it is necessary to analyze whether the battery will experience additional discharge to avoid affecting the battery life. When β is 0 degrees, corresponding to different stuck angles of the solar panel, the energy and load conditions, as well as the current output of the solar panel, are as Figure 6 shown.

[0071] The energy available for battery charging and the battery discharge energy in one orbital period at different stuck angles are calculated as shown in Table 1. It can be seen that when the stuck angle is 270°, the energy is optimal and can be balanced at the end of the life cycle. When the motor is blocked at 270°, in addition to the battery discharging during the eclipse period, when the current of the solar panel decreases to the minimum value, the energy of the solar panel cannot meet the load situation, resulting in a shallow discharge of the battery. The battery discharges twice in one orbital period: one deep discharge, with the discharge depth caused by the eclipse being approximately 33%; one shallow discharge, with the discharge depth being approximately 4%.

[0072] Table 1

[0073]

[0074] In Table 1, W ec is the energy available for battery charging in one orbital period, and W edc is the energy of the battery discharge in one orbital period. If, in one orbital period, W ec > W edc , then the energy is balanced; otherwise, it is unbalanced. During the illumination period, the sun-earth distance factor is the smallest at the summer solstice, and the energy situation is the most tense. The current and load conditions of the solar panel with SADA stuck at different angles are as Figure 7 shown. It can be seen that when γ = 270°, the battery does not discharge. Regardless of the stuck angle, the energy at the summer solstice during the illumination period at the end of the life cycle is balanced.

[0075] The following shows the method and its beneficial effects of this embodiment through a specific example. When a certain MEO orbit satellite is in orbit for the 5th year, the -Y wing SADA is blocked, and it is stuck at 270° by applying power to the double winding. The summer solstice in 2024 is the illumination season of the satellite. Affected by the sun-earth distance during the summer solstice, the output current of the solar panel is the smallest. Analyze the tracking situation of the target rotation angle of SADA at this time as Figure 8As shown, it can be seen that the target rotation angle of the +Y wing solar panel SADA varies between |β| and (π - |β|), and the target rotation angle of the -Y wing SADM varies between (π + |β|) and (2π - |β|). The actual solar angle of the on-orbit satellite is as Figure 9 shown, and the output current of the solar panel and the load condition are as Figure 10 shown, and the discharge conditions of the satellite battery are respectively as Figure 11 , Figure 12 shown. It can be seen that when the -Y wing solar panel is stuck at 270°, the satellite battery does not discharge during the illumination season, and the energy balance is maintained during the eclipse period. The battery discharges twice in one orbital period. One discharge occurs when entering the eclipse, with a maximum discharge depth of about 34%. The other is a shallow discharge when the -Y wing solar panel deviates from the target angle the most and the current of the double-wing solar panel cannot meet the load demand, with a discharge depth of about 4%. The on-orbit performance of the satellite is consistent with the previous simulation analysis results. It is proved that when the -Y wing SADA is stuck at 270°, the satellite is in good condition.

[0076] For the method for calculating the energy supply of the solar panel under the condition of solar panel jamming in this embodiment, first, the jamming angle γ corresponding to the solar panel in the jamming state is obtained, and then the interval of the solar incidence angle of the solar panel in one period is determined according to the solar panel in the jamming state. The interval includes the illumination period and the eclipse period. Finally, the output energy of the solar panel during the illumination period in one period is calculated. The output energy is an expression related to the jamming angle, and thus the energy supply situation of the solar panel under different jamming angles can be accurately characterized, providing effective support for the subsequent actual application of the satellite in orbit.

[0077] Another embodiment of the present invention provides a device for calculating the energy supply of a solar panel under the condition of solar panel jamming. The device 1300 mainly includes: an acquisition module 1301 configured to acquire the jamming angle γ corresponding to the solar panel in the jamming state, where the jamming angle γ is the angle between the plane where the solar panel is located in the jamming state and the plane where it is located at the electrical zero position; a determination module 1302 configured to determine the interval of the solar incidence angle of the solar panel in one period according to the solar panel in the jamming state, and the interval includes the illumination period and the eclipse period, where the solar incidence angle is the angle between the solar vector direction and the normal direction of the solar panel; a calculation module 1303 configured to calculate the output energy of the solar panel during the illumination period in one period, and the output energy is an expression related to the jamming angle, where one period of the solar panel corresponds to the orbital period of the satellite operation.

[0078] In some embodiments, the device 1300 further includes an obtaining module configured to, after calculating the output energy of the solar panel during the illumination period in one period, obtain the target jamming angle corresponding to the maximum value of the output energy according to the expression of the output energy.

[0079] In some embodiments, the calculation module 1303 further includes: calculating the output energy of the solar panel at the target stuck angle.

[0080] In some embodiments, the apparatus 1300 further includes a judgment module configured to judge whether the output energy of the solar panel at the target stuck angle meets the energy supply - demand balance of the satellite, where the energy supply - demand balance means that the battery does not discharge during the illumination period and the battery starts to supply power to the payload on the satellite in a fully - charged state during the eclipse period.

[0081] In some embodiments, the angle range of the solar incidence angle is where β is the orbital solar angle and γ is the stuck angle.

[0082] In some embodiments, the expression of the output energy of the solar panel is: In the formula, W N is the output energy, V bus is the bus voltage, i N is the normal solar - facing output current of the solar panel in the Nth year of the satellite in orbit, ω is the angular velocity of the change of the solar incidence angle, ωt is related to the stuck angle γ, t0 is the starting moment of the current period, t is the ending moment of the current period, and the RELU expression indicates the calculation result of RELU(p) under different p values.

[0083] In some embodiments, calculating the output energy of the solar panel during the illumination period in a cycle includes: dividing the illumination period into sub - intervals and calculating the output energy of the solar panel in each sub - interval respectively.

[0084] Details of other operations performed by each module in this embodiment can be referred to the foregoing embodiments and will not be elaborated here.

[0085] In this embodiment, the device for calculating the energy supply of the solar panel under stuck conditions first obtains the stuck angle γ corresponding to the solar panel in the stuck state, then determines the interval of the solar incidence angle of the solar panel in a cycle according to the stuck state of the solar panel, the interval includes the illumination period and the eclipse period, and finally calculates the output energy of the solar panel during the illumination period in a cycle. The output energy is an expression related to the stuck angle, and thus can accurately characterize the energy supply situation of the solar panel under different stuck angles, providing effective support for the subsequent actual application of the satellite in orbit.

[0086] A solar panel jamming lower panel power supply calculation device in an embodiment of the present application can be a device, or a component, integrated circuit, or chip in a terminal. A solar panel jamming lower panel power supply calculation device in an embodiment of the present application can be a device with an operating system. The operating system can be the Android operating system, the iOS operating system, or other possible operating systems, which are not specifically limited in the embodiments of the present application.

[0087] The present application also provides an electronic device, including: a memory for storing programs or instructions executable by a processor; and a processor for executing the above programs or instructions to implement each process of the above solar panel jamming lower panel power supply calculation method embodiment, and can achieve the same technical effect. To avoid repetition, it will not be elaborated here.

[0088] Figure 14 FIG. 7 is a schematic diagram of an electronic device shown according to an embodiment of the present invention. The electronic device 1400 may include an internal communication bus 1401, a processor 1402, a read-only memory (ROM) 1403, a random access memory (RAM) 1404, and a communication port 1405. When the application is on a personal computer, the electronic device 1400 may further include a hard disk 1406. The internal communication bus 1401 can enable data communication between components of the electronic device 1400. The processor 1402 can make judgments and issue prompts. In some embodiments, the processor 1402 may be composed of one or more processors. The communication port 1405 can enable data communication between the electronic device 1400 and the outside. In some embodiments, the electronic device 1400 can send and receive information and data from the network through the communication port 1405. The electronic device 1400 may also include different forms of program storage units and data storage units, such as the hard disk 1406, the read-only memory (ROM) 1403, and the random access memory (RAM) 1404, which can store various data files used for computer processing and / or communication, and possible programs or instructions executed by the processor 1402. The result processed by the processor 1402 is transmitted to the user device through the communication port 1405 and displayed on the user interface.

[0089] The above solar panel jamming lower panel power supply calculation method can be implemented as a computer program, stored in the hard disk 1406, and can be recorded in the processor 1402 for execution to implement any one of the solar panel jamming lower panel power supply calculation methods in the present application.

[0090] The embodiment of the present application also provides a readable storage medium, on which programs or instructions are stored. When the programs or instructions are executed by a processor, each process of the above solar panel jamming lower panel power supply calculation method embodiment is implemented, and the same technical effect can be achieved. To avoid repetition, it will not be elaborated here.

[0091] To those skilled in the art, the above invention disclosure is merely an example and does not constitute a limitation to this application. Although not explicitly stated here, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are proposed in this application, so such modifications, improvements, and corrections still fall within the spirit and scope of the exemplary embodiments of this application.

[0092] In some embodiments, numbers are used to describe components and attribute quantities. It should be understood that such numbers used for the description of embodiments are modified by the modifiers "about", "approximate", or "substantially" in some examples. Unless otherwise stated, "about", "approximate", or "substantially" indicate that the said numbers allow a variation of ±20%. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximate values, and such approximate values may change according to the characteristics required by individual embodiments. In some embodiments, the numerical parameters should consider the specified significant digits and adopt the method of retaining general digits. Although the numerical ranges and parameters used to confirm the breadth of the scope in some embodiments of this application are approximate values, in specific embodiments, the setting of such numerical values is as precise as possible within the feasible range.

[0093] Although this application has been described with reference to the current specific embodiments, those of ordinary skill in the art should recognize that the above embodiments are only used to illustrate this application, and various equivalent changes or substitutions can be made without departing from the spirit of this application. Therefore, as long as the changes and variations of the above embodiments are within the scope of the spirit of this application, they will fall within the scope of the claims of this application.

Claims

1. A calculation method for supplying energy to a solar panel under the condition of solar panel jamming, characterized in that including: obtaining a stuck angle γ corresponding to the solar panel when it is in a stuck state, where the stuck angle γ is the angle between the plane where the solar panel is located in the stuck state and the plane where it is located in the electrical zero position; determining an interval in which the solar incidence angle of the solar panel is located within one cycle according to the solar panel being in a stuck state, the interval including a light period and a shadow period, where the solar incidence angle is the angle between the direction of the solar vector and the normal direction of the solar panel; calculating the output energy of the solar panel during the light period within one cycle, the output energy being an expression related to the stuck angle, where one cycle of the solar panel corresponds to the orbital period of the satellite operation.

2. The method for calculating the energy supply of the lower solar panel in case of solar panel jamming according to claim 1, wherein, The method further includes: after calculating the output energy of the solar panel during the light period within one cycle, obtaining a target stuck angle corresponding to the maximum value of the output energy according to the expression of the output energy.

3. The method for calculating the energy supply of the lower solar panel under the condition of solar panel jamming according to claim 2, the method further comprising: calculating the output energy of the solar panel at the target stuck angle.

4. The solar panel jamming and lower panel energy supply calculation method according to claim 3, wherein The method further includes: determining whether the output energy of the solar panel at the target stuck angle satisfies the energy supply and demand balance of the satellite, where the energy supply and demand balance means that the battery does not discharge during the light period and the battery starts to supply power to the payload on the satellite in a fully charged state during the shadow period.

5. The method for calculating the energy supply of the lower solar panel in case of solar panel jamming according to claim 1, characterized in that, The angle range of the solar incident angle is where β is the orbital solar angle and γ is the jamming angle.

6. The method for calculating the energy supply of the lower solar panel under the condition of solar panel jamming according to claim 1, characterized in that, The output energy expression of the solar panel is as follows: In the formula, W N is the output energy, V bus is the bus voltage, i N is the normal solar panel output current to the sun in the Nth year of the satellite in orbit. ω is the angular velocity of the solar incidence angle change. ωt is related to the stuck angle γ. t0 is the starting time of the current period, t is the ending time of the current period. The RELU expression indicates the calculation result of RELU(p) under different p values.

7. The method for calculating the energy supply of the lower sailboard under the condition of solar sailboard jamming according to claim 1, wherein The calculating the output energy of the solar panel during the light period within one cycle includes: dividing the light period into sub-intervals and calculating the output energy of the solar panel in each sub-interval respectively.

8. A solar panel jamming energy supply calculation device for the solar panel, characterized in that, including: an obtaining module configured to obtain a stuck angle γ corresponding to the solar panel when it is in a stuck state, where the stuck angle γ is the angle between the plane where the solar panel is located in the stuck state and the plane where it is located in the electrical zero position; a determining module configured to determine an interval in which the solar incidence angle of the solar panel is located within one cycle according to the solar panel being in a stuck state, the interval including a light period and a shadow period, where the solar incidence angle is the angle between the direction of the solar vector and the normal direction of the solar panel; a calculating module configured to calculate the output energy of the solar panel during the light period within one cycle, the output energy being an expression related to the stuck angle, where one cycle of the solar panel corresponds to the orbital period of the satellite operation.

9. An electronic device, characterized in that, including: a processor and a memory, where the memory stores a program or instruction that can run on the processor, and when the program or instruction is executed by the processor, the steps of the method for calculating the energy supply of the solar panel under stuck conditions as described in any one of claims 1-7 are implemented.

10. A readable storage medium, characterized in that, A program or instruction is stored on the readable storage medium, and when the program or instruction is executed by a processor, the steps of the method for calculating the energy supply of the solar panel under stuck conditions as described in any one of claims 1-7 are implemented.

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