Solar panel card stuck under the panel power supply calculation method, device and electronic equipment

Abstract

The application provides a solar panel card stagnation under panel energy supply calculation method, device and electronic equipment, and the method comprises the following steps: obtaining the corresponding card stagnation angle γ when the solar panel is in the card stagnation state, the card stagnation angle γ is the included angle between the plane where the solar panel is in the card stagnation state and the plane where the solar panel is in the electrical zero position; determining the interval where the solar incidence angle of the solar panel is located in a period according to the solar panel in the card stagnation state, the interval comprises an illumination period and a shadow period, wherein the solar incidence angle is the included angle between the solar vector direction and the normal direction of the solar panel; calculating the output energy of the solar panel in the illumination period in a period, and the output energy is an expression related to the card stagnation angle, wherein a period of the solar panel corresponds to an orbit period of the satellite. The application can accurately characterize the solar panel energy supply under different card stagnation angles, and provides effective support for subsequent satellite on-orbit practical application.

Description

TECHNICAL FIELD

[0001] The present application mainly relates to the field of satellite monitoring and control technology, and particularly relates to a solar array card sticking under-solar array power supply calculation method, device and electronic equipment. BACKGROUND

[0002] The solar array is a device for converting solar energy into electric energy, which converts solar energy into electric energy through photoelectric effect to provide continuous power for the satellite, or stores the electric energy in the battery to provide continuous power for the satellite. The solar array has power supply and charging functions, and is a key energy equipment for the on-orbit operation of the satellite. In the launch phase, the solar array is folded to reduce the volume, and is unfolded after entering the orbit, and the angle of the solar array is adjusted in real time to maximize the absorption of solar energy.

[0003] The SADA (Solar Array Drive Assembly) is one of the important components of the satellite energy system, and is composed of the SADE (controller line box), the SADM_A (+Y solar array drive mechanism), the SADM_B (-Y solar array drive mechanism) and the like. The main function of the SADA is to control and manage and ensure that the solar cell array points to the sun to realize maximum efficiency photoelectric conversion, thereby providing sufficient energy for the load and even the entire satellite.

[0004] According to the fault condition data of the satellite during on-orbit operation, it is found that the proportion of the energy system fault in each subsystem is high, and the solar cell array output abnormal fault accounts for about 25%, and most of them are SADA drive mechanism faults. About 45% of the energy system faults of the on-orbit spacecraft will lead to the failure of the entire task, and 80% of the energy system faults have a serious impact on the entire task. Therefore, the normal work of the SADA is of great significance to the satellite load business and the safety of the satellite platform, but there is no energy processing method for the case that the solar array of one wing cannot rotate due to the fault of the SADA of the wing in the current technology. SUMMARY

[0005] The technical problem to be solved by the present application is to provide a solar array card sticking under-solar array power supply calculation method, device and electronic equipment, which can accurately represent the solar array power supply under different card sticking angles, and provide effective support for subsequent on-orbit application of the satellite.

[0006] To solve the above technical problems, in a first aspect, the present application provides a solar panel carding under the panel energy calculation method, comprising: obtaining the corresponding carding angle γ when the solar panel is in the carding state, the carding angle γ is the angle between the plane of the solar panel in the carding state and the plane in the electrical zero position; according to the solar panel in the carding state, the solar incidence angle of the solar panel in a cycle is determined, the interval includes the illumination period and the eclipse period, wherein the solar incidence angle is the angle between the solar vector direction and the normal direction of the solar panel; calculate the output energy of the solar panel in the illumination period in a cycle, the output energy is related to the expression of the carding angle, wherein a cycle of the solar panel corresponds to the orbit period of the satellite.

[0007] Optionally, the method further comprises: after calculating the output energy of the solar panel in the illumination period in a cycle, according to the expression of the output energy, the target carding angle corresponding to the maximum value of the output energy is obtained.

[0008] Optionally, the method further comprises: calculating the output energy of the solar panel under the target carding angle.

[0009] Optionally, the method further comprises: judging whether the output energy of the solar panel under the target carding angle meets the energy supply and demand balance of the satellite, wherein the energy supply and demand balance is represented as the battery is not discharged in the illumination period, and the battery starts to supply power to the working load on the satellite in the full charge state in the eclipse period.

[0010] Optionally, the angle interval of the solar incidence angle is Wherein, β is the orbit solar angle, and γ is the carding angle.

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

[0012] Optionally, the calculation of the output energy of the solar panel in the illumination period in a cycle comprises: dividing the illumination period into each subinterval, and calculating the output energy of the solar panel in each subinterval.

[0013] In a second aspect, the present application provides a solar panel carding under the panel energy supply calculation device, comprising: an acquisition module configured to acquire the corresponding carding angle γ when the solar panel is in a carding state, the carding angle γ is the included angle between the plane where the solar panel is in the carding state and the plane where the solar panel is in the electrical zero position; a determination module configured to determine the interval of the solar incident angle of the solar panel in a cycle according to the solar panel in the carding state, the interval includes the illumination period and the eclipse period, wherein the solar incident angle is the included 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 in the illumination period in a cycle, the output energy is an expression related to the carding angle, wherein a cycle of the solar panel corresponds to an orbit period of the satellite.

[0014] In a third aspect, the present application provides an electronic device, comprising: a processor and a memory, the memory stores programs or instructions executable on the processor, and the programs or instructions are executed by the processor to implement the steps of the solar panel carding under the panel energy supply calculation method according to the first aspect.

[0015] In a fourth aspect, the present application provides a readable storage medium, the readable storage medium stores programs or instructions, and the programs or instructions are executed by the processor to implement the steps of the solar panel carding under the panel energy supply calculation method according to the first aspect.

[0016] Compared with the prior art, the present application has the following advantages: first, the corresponding carding angle γ when the solar panel is in a carding state is acquired, then the interval of the solar incident angle of the solar panel in a cycle is determined according to the solar panel in the carding state, the interval includes the illumination period and the eclipse period, finally the output energy of the solar panel in the illumination period in a cycle is calculated, the output energy is an expression related to the carding angle, and then the solar panel energy supply situation under different carding angles can be accurately characterized, which provides effective support for subsequent satellite on-orbit practical application. BRIEF DESCRIPTION OF DRAWINGS

[0017] The accompanying drawings are included to provide a further understanding of the present application, and they are collected and constitute a part of the present application, the drawings show the embodiments of the present application, and together with the present specification, they play a role in explaining the principles of the present application. In the drawings:

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

[0019] Figure 2 is a flowchart of a solar panel carding under the panel energy supply calculation method according to an embodiment of the present application;

[0020] Figure 3is a schematic diagram of a predicted ten-year variation of the satellite orbit solar angle;

[0021] Figure 4 is a schematic diagram of the annual variation of the solar incidence angle of the -Y sailboard in an embodiment of the present application (γ = 360°);

[0022] Figure 5 is a schematic diagram of the annual variation of the solar incidence angle of the -Y sailboard in an embodiment of the present application (γ = 270°);

[0023] Figure 6 is a schematic diagram of the energy analysis of different card angles in an embodiment of the present application (earth shadow period);

[0024] Figure 7 is a schematic diagram of the energy analysis of different card angles in an embodiment of the present application (light period);

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

[0026] Figure 9 is a schematic diagram of the analysis of the solar elevation angle variation of the actual satellite orbit;

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

[0028] Figure 11 is a graph of the voltage and discharge current variation curves of battery groups A and B during the earth shadow period;

[0029] Figure 12 is a graph of the voltage and discharge current variation curves of battery groups A and B during the summer solstice light period;

[0030] Figure 13 is a schematic diagram of the structure of the sailboard energy supply calculation device under the card of the sailboard in an embodiment of the present application;

[0031] Figure 14 is a schematic diagram of an electronic device according to an embodiment of the present application. DETAILED DESCRIPTION

[0032] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed in the embodiment description will be briefly introduced below. Obviously, the drawings in the following description are only some examples or embodiments of the present application, and for those skilled in the art, the present application can also be applied to other similar scenarios without creative labor. Unless it is obvious from the language environment or otherwise stated, the same reference numbers in the drawings represent the same structure or operation.

[0033] As indicated in this application and claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not specifically singular and may include plural forms. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0034] Flowcharts are used in this application to illustrate the operations performed by the system according to embodiments of this application. It should be understood that the preceding or following operations are not necessarily performed in exact order. Instead, various steps can be processed in reverse order or simultaneously. Furthermore, other operations may be added to these processes, or one or more steps may be removed from these processes.

[0035] Satellites experience shadow periods and illumination periods during their orbital operation. For example, if a satellite is operating in a MEO (Medium Earth Orbit) orbit at an altitude of 21,528 km with an orbital period T of 13 hours, the longest shadow period is 60 minutes. For instance, refer to... Figure 1 As shown, the solar array (or solar panels) on the satellite adopts a rigid, deployable solar array, consisting of two solar panels in the +Y and -Y directions, each with three panels. The output power meets the peak load requirement of 2KW and the constant load requirement of 1587W. The circuitry of each solar panel is collected on the back via wires, passing through isolation diodes to the cable connectors on the panel. The power and signals of each solar panel are input to the satellite power control unit via inter-panel cables and connectors through the SADA systems on both sides, and finally, the power control unit supplies power to the individual modules of the satellite subsystem. The rotating arrows in the figure indicate the rotation direction of the solar panels. The coordinate system is the satellite's own coordinate system, which is represented as follows: the origin is located at the satellite's center of mass (O), the X-axis is the roll axis, pointing in the direction of the satellite's movement, 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 Earth's center. In addition, the X, Y, and Z axes form a right-handed orthogonal coordinate system.

[0036] Satellite sets the working mode according to different task scenarios, including solar capture mode, minimum safety mode, uncontrolled mode, sun orientation mode, earth capture mode, stable earth mode and orbit control mode. The solar panel driving control is a full autonomous control strategy, and the working mode is switched autonomously during the switching process of different satellite operation modes. SADA has multiple working modes in orbit, such as cruise mode, emergency mode, incremental mode, maintenance mode and automatic zero mode. During the sun orientation of the solar panel, it is in cruise mode to track the sun at a fixed angular velocity. Due to the prediction orbit error, the actual rotation angle will lead or lag the target angle, and the energy cannot be optimized. Therefore, it is necessary to control the SADM to switch to the incremental working or maintenance mode to realize the stable sun orientation of the solar panel, and transmit the electric energy generated by the solar cell array to the satellite power controller to ensure the normal supply of satellite energy.

[0037] During the stable flight of the satellite in orbit, the working mode is stable earth. The yaw attitude and sun vector can be obtained in both light period and shadow period, so the satellite yaw control is performed according to the sun vector in both light period and shadow period. When SADA appears stuck fault, it is often manifested as single / double wing cannot rotate freely and is stuck at a certain angle. For example, if the -Y wing SADA of the solar panel is stuck, the -Y solar panel cannot normally sun during the shadow season, and the output current of the -Y wing array is abnormal, and the power output is abnormal. Since the output power of a single wing generally cannot meet the load demand of the satellite, the battery group is in a discharging state, and the bus voltage is normally and stably at 42.2±0.2V. After the stuck of the SADA motor in orbit, the double-winding power can restore operation, but the stuck will still occur at random.

[0038] During the initial launch stage of the satellite, the electrical zero of SADA coincides with the mechanical zero, which is in the horizontal direction (such as Figure 1 the middle Z-axis direction). After the solar panel is deployed in place and the effective deployment locking signal is given, the satellite computer issues relevant program control instructions, executes the emergency mode, and returns to the electrical zero at an angular velocity of about 0.3° / s, so as to accurately calculate the absolute rotation angle and know the pointing position of the solar cell array based on the given zero indication signal when SADA executes other modes. According to the satellite attitude operation state diagram in orbit, the orbit coordinate system sun vector is S ox S oy S oz ] T When the satellite operates in the yaw maneuver mode, the target yaw angle is ψ m =a tan2(S oy ,S ox ). Wherein, S ox / S oy / S ozare respectively the x / y / z direction projections of the orbit system sun vector, and the satellite body coordinate system sun vector is:

[0039]

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

[0041]

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

[0043]

[0044] S bx / S by / S bz are respectively the x / y / z direction projections of the satellite body coordinate system sun vector S b . The corresponding deviation angle is calculated through the target rotation angle (at this time, the included angle between the solar panel normal and the sun vector is deviated from the target rotation angle ψ m ), different deviation angles set different working modes of the SADA, so as to drive and control the solar panel to track the sun. When the satellite is switched from the sun tracking orientation to the stable earth orientation, the stable earth orientation is switched to the yaw maneuver or the orbit control, and the yaw maneuver is switched to the yaw maneuver after the attitude adjustment, the solar panel is tracked by the SADA large angle rotation incremental mode at an angular velocity of about 0.3° / s, and this mode is the satellite stable operation mode. When the satellite works in the stable earth orientation or the yaw maneuver, the solar panel is synchronously tracked according to the sun vector angle through the SADA, and the SADA is operated in the cruising angular velocity mode of about 0.0042° / s.

[0045] Reference Figure 2 is shown, the solar panel card jammed energy supply calculation method 200 mainly includes: S210, acquiring the card jammed angle γ corresponding to the solar panel in the card jammed state, the card jammed angle γ is the included angle between the plane where the solar panel is located in the card jammed state and the plane where the solar panel is located in the electrical zero position; S220, determining the sun incidence angle interval of the solar panel in a period according to the solar panel in the card jammed state, the interval includes the illumination period and the eclipse period, wherein the sun incidence angle is the included angle between the sun vector direction and the normal direction of the solar panel; S230, calculating the output energy of the solar panel in the illumination period in a period, the output energy is an expression related to the card jammed angle, wherein one period of the solar panel corresponds to the orbit period of the satellite.

[0046] Exemplarily, the orbit sun angle of the on-orbit satellite is The orbit sun angle β is the included angle between the orbit plane of the satellite revolving around the earth and the vector of the satellite pointing to the sun, the target rotation angle of the +Y wing solar panel is between ∣β∣~(π-∣β∣), the target rotation angle of the -Y wing SADM is between (π+∣β∣)~(2π-∣β∣). When the solar panel is stuck at the γ angle, the sun incidence angle θ of the solar panel changes in the range of:

[0047]

[0048] wherein, When the sun incidence angle θ exceeds the range, the solar panel is not irradiated by the light, and the current is 0 A. The stuck angle γ is in the range of [π+∣β∣~2π-∣β∣]. The angular velocity ω of the change of the sun incidence angle θ is about 0.0042° / s, and the specific value is related to the sun incidence angle. The principle is to keep the solar panel rotating one circle in one orbit period. The average value of the angular velocity is calculated by the following formula:

[0049]

[0050] wherein, T represents the time of one period, and W represents the output energy of the solar panel N The output energy W is positively correlated with cosθ, as shown below:

[0051]

[0052] wherein, W N represents the output energy, V bus represents the bus voltage, i N represents the output current of the solar panel in the Nth year of the satellite in orbit under normal sun alignment (i.e., without blocking), ω represents the angular velocity of the change of the sun incidence angle, ωt is related to the stuck angle γ, t0 represents the starting time of the current period, t represents the ending time of the current period, and the RELU expression indicates the calculation result of RELU(p) under different p values. Let-(γ-π-∣β∣)=θ1; 2π-γ+∣β∣=θ2.

[0053] In some embodiments, the light period is divided into subintervals, and the output energy of the solar panel is calculated in each subinterval. For example, since the target rotation angle of the -Y wing SADM is in (π+∣β∣)~(2π-∣β∣), the interval span is [π-2∣β∣]. When , the interval span exceeds For the stuck γ angle in this interval, the case that θ exceeds may occur. Therefore, for the energy case of , the interval calculation is required.

[0054]

[0055] The calculation result is

[0056]

[0057]

[0058] In order to obtain the maximum output energy, the solar panel card angle is obtained by setting W N ′ = 0, and the calculation result is

[0059]

[0060] When , the maximum output energy in the three γ intervals is as follows:

[0061]

[0062] When , 2cosβ≥1+cos(2∣β∝), in this case, when , the output energy is maximum, and the maximum output energy is

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

[0064]

[0065] The calculation result is

[0066]

[0067] Setting W N ′ = 0, the calculation result is At this time,

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

[0069] Referring to Figure 3 , according to the satellite orbit, the trend of the orbit sun angle in the next 10 years is fitted, when the absolute value of the orbit sun angle β is less than 13 degrees, the satellite enters the eclipse season, when β is 0, the satellite enters the deepest eclipse, and the longest eclipse time is 1 hour. The simulation result of the card angle in the 2π angle is that the change trend of the solar panel solar incidence angle θ in the next year is shown in Figure 4 and Figure 5 .

[0070] In some embodiments, it is determined whether the output energy of the solar panel at the target slack angle meets the energy supply and demand balance of the satellite. Energy supply and demand balance means that the battery does not discharge during the sunlight period and starts supplying power to the satellite's payload while fully charged during the shadow period. The most energy-critical situation is during the shadow period; if the energy is balanced during the shadow period, the energy is also balanced during the sunlight period. Only the energy balance under the shadow condition is analyzed; during the sunlight period, it is necessary to analyze whether the battery will experience additional discharge to avoid affecting battery life. When β is 0 degrees, the energy and load conditions and the solar panel current output conditions corresponding to different slack angles of the solar panel are as follows: Figure 6 As shown.

[0071] Table 1 shows the energy available for battery charging and discharging per orbital cycle under different stall angles. It can be seen that the energy is optimal at a stall angle of 270°, achieving a balance at the end of the battery's lifespan. When stalled at 270°, in addition to battery discharge during the ground shadow period, shallow battery discharge also occurs when the solar panel current drops to its minimum, resulting in insufficient solar panel energy to meet the load. The battery experiences two discharges per orbital cycle: one deep discharge (approximately 33% depth due to ground shadow) and one shallow discharge (approximately 4% depth).

[0072] Table 1

[0073]

[0074] W in Table 1 ec W is the energy available for charging the battery during one orbital cycle. edc This refers to the energy discharged by the battery during one orbital cycle. If W... ec >W edc If the energy balance is achieved, then energy is balanced; otherwise, it is unbalanced. During the solar term, the Earth-Sun distance factor is smallest at the summer solstice, and the energy situation is most strained. The SADA system is stuck at different angles, affecting the current of the sails and the load conditions as follows: Figure 7 As shown, it can be seen that when γ=270°, the battery does not experience any problems. Regardless of the angle at which it is stuck, the energy is balanced at the summer solstice point during the end of its lifespan.

[0075] The following specific example illustrates the method and its beneficial effects. In the fifth year of operation, a MEO-orbiting satellite experienced a stall in its -Y-wing SADA (Satellite Assisted Array) mechanism. Powering the dual windings caused it to become stuck at 270°. The summer solstice of 2024 coincides with the satellite's solar radiation season, during which the solar panel output current is minimized due to the Earth-Sun distance. The SADA target rotation angle tracking performance at this time is analyzed as follows: Figure 8As shown in the figure, the target rotation angle of the +Y wing sailboard SADA varies between ∣β∣~(π-∣β∣), and the target rotation angle of the -Y wing SADM varies between (π+∣β∣)~(2π-∣β∣). The actual in-orbit satellite sun angle is as shown in the figure Figure 9 As shown in the figure, the sun sailboard output current and the load condition are as shown in the figure Figure 10 As shown in the figure, the satellite battery discharge conditions are as shown in the figure Figure 11 、 Figure 12 As can be seen, when the -Y wing sailboard is stuck at 270°, the satellite does not discharge the battery in the light season, and the energy balance is achieved in the eclipse period. The battery is discharged twice in one orbit period, once for the discharge caused by entering the eclipse, and the maximum discharge depth is about 34%, and once for the shallow discharge caused by the inability of the double-wing sailboard current to meet the load demand when the -Y wing sailboard deviates from the target angle, and the discharge depth is about 4%. The in-orbit performance of the satellite is consistent with the simulation analysis results, and the -Y wing SADA is stuck at 270°, and the satellite is in good condition.

[0076] The sailboard energy supply calculation method under the sun sailboard sticking of the embodiment first acquires the sticking angle γ corresponding to the sticking state of the sun sailboard, and then determines the interval of the sun incidence angle of the sun sailboard in a period according to the sticking state of the sun sailboard, the interval including the light period and the eclipse period, and finally calculates the output energy of the sun sailboard in the light period in a period, the output energy being an expression related to the sticking angle, so as to accurately represent the sun sailboard energy supply under different sticking angles, and provide effective support for subsequent satellite in-orbit practical application.

[0077] Another embodiment of the present application provides a sun sailboard sticking sailboard energy supply calculation device, the device 1300 mainly comprises: an acquisition module 1301 configured to acquire the sticking angle γ corresponding to the sticking state of the sun sailboard, the sticking angle γ being the included angle between the plane of the sun sailboard in the sticking state and the plane in the electrical zero position; a determination module 1302 configured to determine the interval of the sun incidence angle of the sun sailboard in a period according to the sticking state of the sun sailboard, the interval including the light period and the eclipse period, wherein the sun incidence angle is the included angle between the sun vector direction and the normal direction of the sun sailboard; and a calculation module 1303 configured to calculate the output energy of the sun sailboard in the light period in a period, the output energy being an expression related to the sticking angle, wherein one period of the sun sailboard corresponds to the orbit period of the satellite.

[0078] In some embodiments, the device 1300 further comprises a solving module configured to solve the target sticking angle corresponding to the maximum value of the output energy according to the expression of the output energy after calculating the output energy of the sun sailboard in the light period in a period.

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

[0080] In some embodiments, the device 1300 further includes a judgment module configured to determine whether the output energy of the solar panel at the target jamming angle meets the energy supply and demand balance of the satellite, wherein the energy supply and demand balance means that the battery does not discharge during the sunshine period and the battery starts to supply power to the working payload on the satellite in a fully charged state during the shadow period.

[0081] In some embodiments, the angle range of the solar incidence angle is as follows: Where β is the orbital solar angle and γ is the lag angle.

[0082] In some embodiments, the output energy expression of a solar panel is: In the formula, W N To output energy, V bus For the bus voltage, i N ω represents the normal solar panel output current to the sun in the Nth year of the satellite's operation in orbit, ω represents the angular velocity of the change in the solar incident angle, ωt is related to the lag angle γ, t0 is the start time of the current cycle, t is the end time of the current cycle, and the RELU expression indicates the calculation result of RELU(p) under different p values.

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

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

[0085] This embodiment of the solar panel power supply calculation device under solar panel jamming first obtains the jamming angle γ corresponding to the solar panel being in a jamming state. Then, based on the solar panel being in a jamming state, it determines the interval of the solar incidence angle of the solar panel within one cycle, including the sunshine period and the shadow period. Finally, it calculates the output energy of the solar panel during the sunshine period in one cycle. The output energy is an expression related to the jamming angle, which can accurately characterize the solar panel power supply under different jamming angles, providing effective support for subsequent satellite on-orbit practical applications.

[0086] The solar panel card stuck under the panel power supply computing device in the embodiment of the present application can be a device, a component in a terminal, an integrated circuit, or a chip. The solar panel card stuck under the panel power supply computing device in the embodiment of the present application can be a device with an operating system. The operating system can be an Android operating system, an iOS operating system, or other possible operating systems, and the embodiment of the present application does not make specific limitations.

[0087] The present application also provides an electronic device, comprising a memory for storing programs or instructions executable by a processor, and a processor for executing the above-mentioned programs or instructions to realize the various processes of the above-mentioned solar panel card stuck under the panel power supply computing method embodiments and achieve the same technical effects. To avoid repetition, details are not repeated here.

[0088] Figure 14 is a schematic diagram of an electronic device according to an embodiment of the present application. The electronic device 1400 can include an internal communication bus 1401, a processor (Processor) 1402, a read-only memory (ROM) 1403, a random access memory (RAM) 1404, and a communication port 1405. When applied to a personal computer, the electronic device 1400 can also include a hard disk 1406. The internal communication bus 1401 can enable data communication between the components of the electronic device 1400. The processor 1402 can make judgments and issue prompts. In some embodiments, the processor 1402 can 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 can 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 by the computer processing and / or communication, and possible programs or instructions executed by the processor 1402. The results processed by the processor 1402 are transmitted to the user device through the communication port 1405 and displayed on the user interface.

[0089] The above-mentioned solar panel card stuck under the panel power supply computing method can be implemented as a computer program, saved in the hard disk 1406, and executed in the processor 1402 to implement any of the solar panel card stuck under the panel power supply computing methods in the present application.

[0090] The embodiment of the present application also provides a readable storage medium, which stores programs or instructions, and the programs or instructions are executed by a processor to realize the various processes of the above-mentioned solar panel card stuck under the panel power supply computing method embodiments and achieve the same technical effects. To avoid repetition, details are not repeated here.

[0091] The above-described application is merely an example for those skilled in the art and does not constitute a limitation on the present application. Although not explicitly described herein, those skilled in the art can make various modifications, improvements and corrections to the present application. Such modifications, improvements and corrections are suggested in the present application, and thus still fall within the spirit and scope of the exemplary embodiments of the present application.

[0092] Some embodiments use numerical values to describe components, quantities of attributes, and it should be understood that such numerical values used in the description of the embodiments are, in some examples, modified by the words "about," "approximately," or "generally." Unless otherwise stated, "about," "approximately," or "generally" indicate that the stated numerical value allows for a variation of ±20%. Accordingly, numerical values used in the specification and claims of some embodiments are approximations. The

[0093] Although the present application has been described with reference to the current exemplary embodiments, it will be recognized that the above-described embodiments are merely intended to illustrate the present application and that changes to or modifications of the above-described embodiments can be made by those skilled in the art without departing from the spirit of the present application. Accordingly, any changes, modifications, or alterations to the above-described embodiments that do not depart from the spirit of the present application will be recognized as falling within the scope of the appended claims.

Claims

1. A method for calculating the energy supply of a solar panel under conditions of solar panel jamming, characterized in that, include: Obtain the jamming angle γ corresponding to the solar panel being in a jammed state. The jamming angle γ is the angle between the plane where the solar panel is in the jammed state and the plane where it is in the electrical zero position. The solar panel is in a fixed state, and the solar incidence angle within a cycle is determined. The interval includes the sunshine period and the shadow period. The solar incidence angle is the angle between the solar vector direction and the normal of the solar panel. Calculate the output energy of the solar panel during the illumination period in one cycle. The output energy is an expression related to the hang angle, where one cycle of the solar panel corresponds to the orbital period of the satellite. The expression for the output energy of the solar panel is: In the formula, W N To output energy, V bus For the bus voltage, i N ω represents the normal solar panel output current to the sun in the Nth year of the satellite's operation in orbit, ω represents the angular velocity of the change in the solar incident angle, ωt is related to the lag angle γ, t0 is the start time of the current cycle, t is the end time of the current cycle, and the RELU expression indicates the calculation result of RELU(p) under different p values.

2. The method for calculating the energy supply of a solar panel under jamming conditions as described in claim 1, characterized in that, The method further includes: after calculating the output energy of the solar panel during the illumination period in a cycle, determining the target slack angle corresponding to the maximum value of the output energy based on the expression of the output energy.

3. The method for calculating the energy supply of a solar panel under jamming conditions as described in claim 2, further comprising: Calculate the output energy of the solar panel at the target hang angle.

4. The method for calculating the energy supply of a solar panel under jamming conditions as described in claim 3, characterized in that, The method further includes: determining whether the output energy of the solar panel at the target jamming angle meets the energy supply and demand balance of the satellite, wherein the energy supply and demand balance means that the battery does not discharge during the sunshine period and the battery starts to supply power to the working payload on the satellite in a fully charged state during the shadow period.

5. The method for calculating the energy supply of a solar panel under jamming conditions as described in claim 1, characterized in that, The angle range in which the solar incidence angle is located is: Where β is the orbital solar angle and γ is the lag angle.

6. The method for calculating the energy supply of a solar panel under jamming conditions as described in claim 1, characterized in that, The calculation of the output energy of the solar panel during the sunshine period in one cycle includes: dividing the sunshine period into sub-intervals, and calculating the output energy of the solar panel in each sub-interval.

7. A solar panel power supply calculation device under solar panel jamming, characterized in that, include: The acquisition module is configured to acquire the jamming angle γ corresponding to the solar panel being in a jammed state, wherein the jamming angle γ is the angle between the plane in which the solar panel is located when it is in a jammed state and the plane in which it is located when it is in an electrical zero position. The determination module is configured to determine the interval of the solar incidence angle of the solar panel in one cycle based on the solar panel being in a stuck state. The interval includes the sunshine period and the shadow period, wherein the solar incidence angle is the angle between the solar vector direction and the normal of the solar panel. The calculation module is configured to calculate the output energy of the solar panel during the illumination period in one cycle, the output energy being an expression related to the hangar angle, wherein one cycle of the solar panel corresponds to the orbital period of the satellite; the expression for the output energy of the solar panel is: In the formula, W N To output energy, V bus For the bus voltage, i N ω represents the normal solar panel output current to the sun in the Nth year of the satellite's operation in orbit, ω represents the angular velocity of the change in the solar incident angle, ωt is related to the lag angle γ, t0 is the start time of the current cycle, t is the end time of the current cycle, and the RELU expression indicates the calculation result of RELU(p) under different p values.

8. An electronic device, characterized in that, include: A processor and a memory, the memory storing a program or instructions executable on the processor, the program or instructions being executed by the processor to implement the steps of the solar panel power supply calculation method under solar panel jamming as described in any one of claims 1-6.

9. A readable storage medium, characterized in that, The readable storage medium stores a program or instructions, which, when executed by a processor, implement the steps of the solar panel power supply calculation method under solar panel jamming as described in any one of claims 1-6.

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