Spherical satellite, energy balance analysis method, device and equipment

Abstract

The application provides a spherical satellite, an energy balance analysis method, device and equipment. The spherical satellite comprises a spherical frame, M arc-shaped bottom plates spliced on the spherical frame, M being an integer greater than 1, and a solar cell array distributed on the outer surfaces of at least K first arc-shaped bottom plates in the M arc-shaped bottom plates, K being an integer greater than 1 and less than or equal to M, wherein the outer surface of each first arc-shaped bottom plate is provided with a plurality of first solar cell pieces in a multi-string and multi-parallel manner, the number of the first solar cell pieces in series on each first arc-shaped bottom plate is equal, and the plurality of first solar cell pieces of the K first arc-shaped bottom plates form the solar cell array. According to the embodiment of the application, the solar cell array of the spherical satellite is composed of the plurality of first solar cell pieces of the K first arc-shaped bottom plates, the photoelectric conversion efficiency of the solar cell array is improved, and the energy demand of the spherical satellite can be considered while meeting the spherical configuration demand.

Description

Technical Field

[0001] This application belongs to the field of aerospace technology, and in particular relates to a spherical satellite, an energy balance analysis method, a device and equipment. Background Technology

[0002] To ensure the accuracy requirements of satellite exploration missions, precise attitude control is often needed to maintain a constant mass-to-weight ratio on the satellite's windward side. Based on this, the satellite's shape can be designed as spherical to meet these requirements. Ensuring that the solar array on the satellite's outer surface presents a spherical shape is one of the key aspects of developing spherical satellites. Related technologies can utilize thin-film solar arrays, which offer good shape adaptability; however, thin-film solar arrays suffer from drawbacks such as low photoelectric conversion efficiency and difficulty in achieving energy balance. Summary of the Invention

[0003] This application provides a spherical satellite, an energy balance analysis method, an apparatus, and equipment to solve the technical problems of low photoelectric conversion efficiency and difficulty in achieving energy balance.

[0004] In a first aspect, embodiments of this application provide a spherical satellite, the spherical satellite comprising:

[0005] Spherical frame;

[0006] M arc-shaped base plates are spliced ​​onto the spherical frame, where M is an integer greater than 1;

[0007] A solar cell array, wherein the solar cell array is distributed on the outer surface of at least K first arc-shaped base plates among the M arc-shaped base plates, wherein K is an integer greater than 1 and K is less than or equal to M.

[0008] In this configuration, the outer surface of each of the first arc-shaped base plates is provided with multiple first solar cells in a series-parallel manner, and the number of first solar cells connected in series on each of the first arc-shaped base plates is equal. The multiple first solar cells of the K first arc-shaped base plates form the solar cell array.

[0009] Secondly, embodiments of this application provide an energy balance analysis method, the method comprising:

[0010] The effective illumination area, solar radiation flux, and photoelectric conversion efficiency of the solar cell array of the spherical satellite are obtained, as well as the illumination status information, first output power, and performance parameters of the power system of the spherical satellite are obtained, wherein the first output power is the output power required corresponding to the illumination status information.

[0011] The second output power is calculated based on the effective illuminated area, the solar radiation flux, and the photoelectric conversion efficiency. The second output power is the actual output power of the solar cell array.

[0012] Based on the illumination status information, the first output power, and the performance parameters, calculate the third output power required for the solar array of the spherical satellite;

[0013] Based on the second output power and the third output power, it is determined whether the energy of the spherical satellite is in a balanced state.

[0014] Thirdly, embodiments of this application provide an energy balance analysis device, the device comprising:

[0015] The acquisition module is used to acquire the effective illumination area, solar radiation flux and photoelectric conversion efficiency of the solar cell array of the spherical satellite, and to acquire the illumination status information, first output power and performance parameters of the power system of the spherical satellite, wherein the first output power is the output power required corresponding to the illumination status information;

[0016] The first calculation module is used to calculate the second output power based on the effective illuminated area, the solar radiation flux and the photoelectric conversion efficiency, wherein the second output power is the actual output power of the solar cell array;

[0017] The second calculation module is used to calculate the third output power required by the solar array of the spherical satellite based on the illumination status information, the first output power and the performance parameters.

[0018] The determining module is used to determine whether the energy of the spherical satellite is in a balanced state based on the second output power and the third output power.

[0019] Fourthly, embodiments of this application provide an electronic device, the device comprising:

[0020] Processor and memory storing programs or instructions;

[0021] The processor implements the above-described method when executing the program or instructions.

[0022] Fifthly, embodiments of this application provide a storage medium storing a program or instructions that, when executed by a processor, implement the method described above.

[0023] Sixthly, embodiments of this application provide a computer program product, wherein instructions in the computer program product, when executed by a processor of an electronic device, cause the electronic device to perform the above-described method.

[0024] The spherical satellite, energy balance analysis method, apparatus, and equipment described in this application include a spherical satellite comprising a spherical frame, M arc-shaped base plates, and a solar cell array. The M arc-shaped base plates are spliced ​​onto the spherical frame, where M is an integer greater than 1. The solar cell array is distributed on the outer surfaces of at least K first arc-shaped base plates among the M arc-shaped base plates, where K is an integer greater than 1 and K is less than or equal to M. Each first arc-shaped base plate has multiple first solar cells arranged in a multi-series, multi-parallel configuration on its outer surface, with an equal number of first solar cells connected in series on each first arc-shaped base plate. The multiple first solar cells on the K first arc-shaped base plates form a solar cell array. Thus, the solar cell array of the spherical satellite is composed of multiple first solar cells on K first arc-shaped base plates, improving the photoelectric conversion efficiency of the solar cell array and meeting the energy requirements of the spherical satellite while satisfying the spherical configuration requirements. Attached Figure Description

[0025] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments of this application will be briefly introduced below. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0026] Figure 1 This is a schematic diagram of the structure of a spherical satellite provided in one embodiment of this application;

[0027] Figure 2a This is one of the structural schematic diagrams of the arc-shaped base plate in the spherical satellite provided in the embodiments of this application;

[0028] Figure 2b This is the second schematic diagram of the arc-shaped base plate in the spherical satellite provided in the embodiments of this application;

[0029] Figure 2c This is the third schematic diagram of the arc-shaped base plate in the spherical satellite provided in the embodiments of this application;

[0030] Figure 2d This is the fourth schematic diagram of the arc-shaped base plate in the spherical satellite provided in the embodiments of this application;

[0031] Figure 2e This is the fifth schematic diagram of the arc-shaped base plate in the spherical satellite provided in the embodiments of this application;

[0032] Figure 2f This is the sixth schematic diagram of the arc-shaped base plate in the spherical satellite provided in the embodiments of this application;

[0033] Figure 3a This is a schematic diagram of the solar cell array distribution in the upper hemisphere of a spherical satellite provided in an embodiment of this application;

[0034] Figure 3bThis is a schematic diagram of the solar cell array distribution in the lower hemisphere of a spherical satellite provided in an embodiment of this application;

[0035] Figure 4 This is a flowchart illustrating an energy balance analysis method provided in one embodiment of this application;

[0036] Figure 5 This is a schematic diagram of the structure of an energy balance analysis device provided in another embodiment of this application;

[0037] Figure 6 This is a schematic diagram of the structure of an electronic device provided in another embodiment of this application. Detailed Implementation

[0038] The features and exemplary embodiments of various aspects of this application will be described in detail below. To make the objectives, technical solutions, and advantages of this application clearer, the application will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only intended to explain this application and not to limit it. For those skilled in the art, this application can be implemented without some of these specific details. The following description of the embodiments is merely to provide a better understanding of this application by illustrating examples.

[0039] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of additional identical elements in the process, method, article, or apparatus that includes said element.

[0040] To address the problems of the prior art, this application provides a spherical satellite, an energy balance analysis method, an apparatus, and equipment. The spherical satellite provided in this application is described below.

[0041] like Figure 1 As shown, the spherical satellite provided in this application embodiment may include:

[0042] Spherical frame;

[0043] M curved base plates are spliced ​​onto a spherical frame, where M is an integer greater than 1;

[0044] A solar cell array is formed by distributing solar cells on the outer surfaces of at least K of the M curved base plates, where K is an integer greater than 1 and less than or equal to M.

[0045] In this configuration, the outer surface of each first arc-shaped base plate is equipped with multiple first solar cells in a series-parallel manner, and the number of first solar cells connected in series on each first arc-shaped base plate is equal. The multiple first solar cells of K first arc-shaped base plates form a solar cell array.

[0046] In this embodiment of the application, the spherical satellite can be formed by splicing M arc-shaped base plates 101 onto a spherical frame. For example, such as... Figure 1 As shown, the spherical satellite may also include a central support ring 102, which can divide the spherical satellite into an upper hemisphere and a lower hemisphere.

[0047] like Figures 2a to 2f As shown, the M curved base plates 201 can be divided into several different types according to their different shapes. For example, the curved base plate 201 may include a type A hexagonal curved base plate (such as...). Figure 2a ), Class B hexagonal curved base plate (such as Figure 2b ), Class C hexagonal curved base plate (such as Figure 2c ), Class A pentagonal curved base plate (such as Figure 2d ), Type B pentagonal curved base plate (such as Figure 2e ) and Class C pentagonal curved base plate (such as Figure 2f A spherical satellite can be constructed by assembling these six types of curved base plates 201. The layout design of each curved base plate 201 in the upper and lower hemispheres can be as follows: Figure 3a and Figure 3b As shown, the specific splicing structure is similar to that of a soccer ball, which will not be elaborated here.

[0048] After M arc-shaped base plates 201 are spliced ​​into a spherical satellite, a first solar cell 202 can be attached to the outer surface of the arc-shaped base plate 201. Theoretically, a first solar cell 202 can be attached to the outer surface of each arc-shaped base plate 201. However, in practical applications, based on the need to install antennas, electrical connectors and other components on the spherical satellite, an arc-shaped base plate 201 without antennas, electrical connectors and other components can be used as the first arc-shaped base plate, and the first solar cell 202 can be attached to the first arc-shaped base plate.

[0049] It is understandable that, such as Figures 2a to 2fAs shown, since the Class A hexagonal arc base plate, Class B hexagonal arc base plate, Class C hexagonal arc base plate, Class A pentagonal arc base plate and Class B pentagonal arc base plate can all be used as the first arc base plate, and the first solar cell 202 is attached to its outer surface, while the Class C pentagonal arc base plate, due to its smaller area and distribution at the junction of the upper and lower hemispheres, has a weaker light intensity, the Class C pentagonal arc base plate does not need to be attached to the first solar cell and is used to install components such as electrical connector plugs.

[0050] In this embodiment of the application, multiple first solar cells 202 can be attached to the outer surface of each first arc-shaped base plate, and the multiple first solar cells 202 can be arranged in a series-parallel manner.

[0051] The number of first solar cells 202 connected in series on each first arc-shaped base plate can be determined based on the bus voltage of the spherical satellite's power system and the open-circuit voltage of each first solar cell 202. No specific limitation is made here. Since the bus voltage of the power system is a uniform value, it is sufficient that the number of first solar cells 202 connected in series on each first arc-shaped base plate is equal. For example, the bus voltage of the power system can be 14V, and the first solar cell 202 can be a triple-junction gallium arsenide solar cell with an open-circuit voltage of 2.7V. Therefore, the multiple first solar cells 202 on each first arc-shaped base plate can be connected in a "five-series, multiple-parallel" configuration, where the "five-series" configuration is to provide approximately 14V of bus voltage to the power system.

[0052] Furthermore, the number of first solar cells 202 connected in parallel on each first arc-shaped base plate can be determined based on the area of ​​the first arc-shaped base plate; therefore, the number of first solar cells 202 connected in parallel on each first arc-shaped base plate can be unequal. For example... Figures 2a to 2f As shown, multiple first solar cells 202 of a type A hexagonal arc-shaped base plate can be connected in a "five-series, eight-parallel" configuration; multiple first solar cells 202 of a type B hexagonal arc-shaped base plate can be connected in a "five-series, nine-parallel" configuration; multiple first solar cells 202 of a type C hexagonal arc-shaped base plate can be connected in a "five-series, eight-parallel" configuration; multiple first solar cells 202 of a type A pentagonal arc-shaped base plate can be connected in a "five-series, five-parallel" configuration; and multiple first solar cells 202 of a type B pentagonal arc-shaped base plate can be connected in a "five-series, three-parallel" configuration.

[0053] In one possible example, please see Figures 2a to 3b The spherical satellite can be composed of 40 arc-shaped base plates, of which 31 may include the first arc-shaped base plates on which the first solar cells are mounted (e.g., ...). Figure 3a and Figure 3bAs shown, after removing the eight Class C pentagonal arc base plates, one Class A pentagonal arc base plate used for antenna mounting can also be removed, leaving the first arc base plate. At this point, based on the number of first solar cells installed on each first arc base plate, it can be determined that the entire spherical satellite's solar array can be composed of five strings of 195 parallel first solar cells.

[0054] In this embodiment, the solar cell array of the spherical satellite can be composed of multiple first solar cells on K first arc-shaped base plates. In other words, multiple first solar cells are attached to the outer surface of the first arc-shaped base plates, so that the solar cell array can meet the spherical configuration requirements of the spherical satellite. At the same time, it is not necessary to select a thin-film solar cell array with poor photoelectric conversion efficiency for the sake of the spherical configuration, thereby improving the photoelectric conversion efficiency of the solar cell array and taking into account the energy requirements of the spherical satellite.

[0055] In some embodiments, the solar array may further include second solar cells disposed on the outer surfaces of at least P first arc-shaped base plates, where P is a positive integer and P is less than or equal to K.

[0056] The second solar cell is used to detect the attitude information between the spherical satellite and the sun, while the first solar cell is used to output electrical energy.

[0057] In this embodiment, the solar array may include a first solar cell and a second solar cell, wherein the first solar cell can be used to provide power for the operation of the spherical satellite, and the second solar cell can be used to detect the attitude information between the spherical satellite and the sun. For example, as... Figures 2a to 2d As shown, the second solar cell 203 can be disposed on the outer surface of each of the first arc-shaped base plates, or on the outer surface of a portion of the first arc-shaped base plates. For example, as... Figure 2e As shown, the type B pentagonal arc base plate serves as the first arc base plate. Although it has the first solar cell 202 installed, its area is smaller than that of other types of first arc base plates. Moreover, it is located at the junction of the upper and lower hemispheres, where the intensity of sunlight is relatively weak. Therefore, the type B pentagonal arc base plate does not need to be fitted with a second solar cell.

[0058] Each second solar cell 203 carries a fixed position information. During the operation of the spherical satellite, the second solar cell will generate a change in current after being exposed to light. At this time, the position information of the second solar cell with the change in current can be obtained, and then the attitude information between the spherical satellite and the sun can be determined based on the position information.

[0059] Based on the spherical satellite provided above, in order to accurately detect whether the energy of the spherical satellite is in a balanced state, an embodiment of this application also provides a specific implementation of an energy balance analysis method. Figure 4 A flowchart illustrating an energy balance analysis method according to an embodiment of this application is shown. Figure 4 As shown, a spherical satellite may also include a power system, and the energy balance analysis method may include the following steps:

[0060] Step 401: Obtain the effective illumination area, solar radiation flux and photoelectric conversion efficiency of the solar cell array of the spherical satellite, and obtain the illumination status information, first output power and power system performance parameters of the spherical satellite, wherein the first output power is the output power required corresponding to the illumination status information;

[0061] Step 402: Calculate the second output power based on the effective illuminated area, solar radiation flux, and photoelectric conversion efficiency. The second output power is the actual output power of the solar cell array.

[0062] Step 403: Calculate the third output power required by the solar array of the spherical satellite based on the illumination status information, the first output power, and the performance parameters;

[0063] Step 404: Determine whether the energy of the spherical satellite is in a balanced state based on the second output power and the third output power.

[0064] The specific implementation methods of each of the above steps will be described in detail below.

[0065] In this embodiment, the energy balance analysis method can obtain the effective illuminated area, solar radiation flux, and photoelectric conversion efficiency of the solar array of a spherical satellite, and obtain the illumination status information, first output power, and power system performance parameters of the spherical satellite, wherein the first output power is the output power required corresponding to the illumination status information; then, based on the effective illuminated area, solar radiation flux, and photoelectric conversion efficiency, the second output power is calculated, which is the actual output power of the solar array; based on the illumination status information, the first output power, and performance parameters, the third output power required by the solar array of the spherical satellite is calculated; and then, based on the third output power and the second output power, it is determined whether the energy of the spherical satellite is in a balanced state. In this way, the output power requirement of the solar array can be calculated based on the energy demand of the spherical satellite during operation, and then compared with the actual output power of the solar array, thereby more accurately determining the energy balance state of the spherical satellite.

[0066] The specific implementation methods for each of the above steps are described below.

[0067] In step 401, the effective illumination area, solar radiation flux, and photoelectric conversion efficiency of the solar array of the spherical satellite can be obtained based on the relevant parameters of the first solar cell. For example, the first solar cell can be a triple-junction gallium arsenide solar cell with a solar radiation flux of 1353 W / m² at a temperature of 25°C. 2 Under these conditions, the area of ​​the first solar cell is 20×20mm. 2 The open-circuit voltage is 2.7V, and the photoelectric conversion efficiency is 29.5%. To obtain the effective illuminated area of ​​the solar array, the number of first solar cells receiving illumination at different illumination angles can be determined first. Then, based on the number of first solar cells and the area of ​​a single first solar cell, the effective illuminated area of ​​the solar array can be calculated.

[0068] This application embodiment can simulate and analyze the sunlight conditions of a spherical satellite within its effective lifespan based on its orbital operating parameters, thereby obtaining the illumination status information of the spherical satellite. This illumination status information may include the shortest illumination time T for a single orbit of the spherical satellite within its lifespan. s And the longest shadow time T w Then, based on the mission requirements, payload operating mode, and data transmission and telemetry requirements of the spherical satellite, the required first output power corresponding to the illumination status information can be determined. This first output power may include the first sub-output power W required by the spherical satellite for illumination time. s The second sub-output power W required for spherical satellites with Earth shadow time w Based on the performance of the battery system and the power controller system, the performance parameters of the spherical satellite's power system are determined. These parameters are shown in the table below.

[0069]

[0070] In step 402, after obtaining the effective illuminated area, solar radiation flux, and photoelectric conversion efficiency of the solar cell array of the spherical satellite, the actual second output power of the solar cell array can be calculated based on the effective illuminated area, solar radiation flux, and photoelectric conversion efficiency. For example, the second output power can be equal to the product of the effective illuminated area, solar radiation flux, and photoelectric conversion efficiency.

[0071] In step 403, after obtaining the illumination status information, first output power, and power system performance parameters of the spherical satellite, the third output power required by the solar array of the spherical satellite can be calculated based on the illumination status information, first output power, and performance parameters. It can be understood that the third output power can be the minimum output power required for the spherical satellite to maintain its operational status.

[0072] In step 404, after obtaining the second output power actually output by the solar cell array and the third output power required for the spherical satellite to maintain its operational state, it can be determined whether the spherical satellite's energy is in a balanced state based on the second and third output powers. For example, the spherical satellite's energy can be considered balanced if the second output power is greater than or equal to the third output power. Alternatively, to further ensure the spherical satellite's operational state, the spherical satellite's energy can be considered balanced if the difference between the second and third output powers is greater than or equal to a preset power threshold. The preset power threshold can be set based on empirical values ​​and is not specifically limited here.

[0073] In some embodiments, obtaining the effective illuminated area of ​​the solar array of the spherical satellite can be achieved by performing the following steps:

[0074] Determine the incident direction of illumination parallel to the direction vector of each arc-shaped base plate of the spherical satellite. The direction vector of the arc-shaped base plate is used to indicate the direction of the line connecting the center of the spherical satellite and the center of the arc-shaped base plate.

[0075] Based on each incident light direction, determine the angle between each curved base plate and the incident light direction under each incident light direction;

[0076] Based on the angle between each arc-shaped base plate and the incident direction of light, the target arc-shaped base plate is determined from the M arc-shaped base plates;

[0077] Based on the target curved base plate, determine the initial illumination area corresponding to each incident light direction;

[0078] Based on M initial illumination areas, determine the effective illumination area of ​​the solar array of the spherical satellite.

[0079] In this embodiment of the application, when determining the effective illumination area of ​​the solar cell array, the initial illumination area of ​​the solar cell array can be calculated by comparing different incident light directions. Specifically, the following steps can be performed:

[0080] We can define the line connecting the center of each arc-shaped base plate to the center of the spherical satellite as the direction vector of each arc-shaped base plate. Then, the direction vector of each arc-shaped base plate can be expressed as n. j , where j = 1, 2, ..., M.

[0081] Then, the incident light direction is determined, which can be divided into M types, each parallel to the direction vector of each curved base plate. Each incident light direction vector can then be expressed as s. i , where i = 1, 2, ..., M.

[0082] It is possible to obtain the angle between each curved base plate and the incident light direction under different incident light directions, where the angle θ ij The expression for can be shown in formula (1):

[0083] θ ij =arccos(s i ·n j ), θ ij ∈[0°, 180°] (1)

[0084] Understandably, when i = j, the angle between the curved base plate and the incident light direction is 0°. When the angle between the curved base plate and the incident light direction is greater than 90°, it indicates that the curved base plate is blocked and not exposed to sunlight. In other words, if this curved base plate is the first curved base plate, then the first solar cell set on this curved base plate is not exposed to sunlight and cannot be used to calculate the initial illuminated area of ​​the solar array. If the angle between the incident light direction and the curved base plate is too large, for example, greater than 75°, it may cause the output current of the first solar cell to not satisfy the cosine relationship, that is, the effective output power will be reduced. Based on this, in some examples, in order to obtain a more accurate initial illuminated area of ​​the solar array, this part of the curved base plate can also be ignored when calculating the initial illuminated area of ​​the solar array. In other words, the target curved base plate can be the first curved base plate with an angle less than or equal to a preset angle threshold, for example, the preset angle threshold can be 75°.

[0085] For example, based on the solar array layout design of a spherical satellite, the area of ​​the solar array on each curved base plate can be defined as r. j Where j = 1, 2, ..., M, then the initial illuminated area R of the solar array under different incident light directions is... i The calculation formula can be shown in formula (2):

[0086]

[0087] Among them, R i Let n be the initial illuminated area of ​​the solar array. j Let r be the direction vector of each curved base plate. j Let s be the area of ​​the solar cell array on each curved base plate. i Let be the incident direction vector for each light source.

[0088] It is understandable that when calculating the initial illumination area of ​​the solar cell array, the solar cell array area of ​​the M curved base plates, except for the target curved base plate, can be considered equal to 0.

[0089] After calculating the initial illumination area corresponding to each incident light direction, the initial illumination area of ​​the solar cell array with the smallest illumination area under M different incident light directions can be selected as the effective illumination area R of the solar cell array of the spherical satellite.

[0090] In this embodiment, the initial illumination area of ​​the solar cell array under the incident light direction with parallel direction vectors of the M arc-shaped base plates can be calculated respectively. Then, the minimum area value is taken as the effective illumination area of ​​the solar cell array, which can make the value of the effective illumination area more accurate, thereby enabling a more accurate determination of the energy balance state of the spherical satellite.

[0091] In some embodiments, step 403 above may specifically perform the following steps:

[0092] Based on the illumination status information, the first output power, and performance parameters, determine the input power required for the spherical satellite;

[0093] Based on the input power and performance parameters, determine the third output power required for the solar array of the spherical satellite.

[0094] As mentioned above, illumination status information can include the shortest illumination time T for a single orbit of a spherical satellite within its lifespan. s And the longest shadow time T w The first output power may include the first sub-output power W required by the spherical satellite for illumination time. s The second sub-output power W required for spherical satellites with Earth shadow time w The performance parameters may include the power controller efficiency η1, the secondary power supply efficiency η2, the first battery efficiency η3, and the second battery efficiency η4.

[0095] You can first determine the shortest illumination time T. s Longest Earth Shadow Time T w First sub-output power W s Second sub-output power W w Based on the secondary power supply efficiency η2, the first battery efficiency η3, and the second battery efficiency η4, determine the required input power W for the spherical satellite. i Then, based on the input power W i The third output power W required for the solar array of the spherical satellite is determined by the power controller efficiency η1. The formula for calculating the third output power W can be shown in formula (3):

[0096]

[0097] In some embodiments, illumination status information may include the shortest illumination time and the longest shadow time, and the first output power may include a first sub-output power required for the illumination time spherical satellite and a second sub-output power required for the shadow time spherical satellite.

[0098] Based on the illumination status information, the initial output power, and performance parameters, determine the required input power for the spherical satellite. Specifically, the following steps can be performed:

[0099] Calculate the first power consumption of the spherical satellite based on the shortest illumination time, the first sub-output power, and performance parameters.

[0100] Calculate the second power consumption of the shadow-time spherical satellite based on the longest shadow time, the second sub-output power, and performance parameters;

[0101] Calculate the input power required for the spherical satellite based on the first power consumption, the second power consumption, and the shortest illumination time.

[0102] In this embodiment of the application, the shortest illumination time T can be used as a basis first. s First sub-output power W s And the secondary power efficiency η2, calculate the first power consumption E of the spherical satellite during illumination time. s First power consumption E s The calculation formula can be shown in formula (4):

[0103]

[0104] Based on the longest shadow time T w Second sub-output power W w Calculate the second power consumption E of the Earth-shadow time spherical satellite based on the secondary power supply efficiency η2, the first battery efficiency η3, and the second battery efficiency η4. w Second power consumption E w The calculation formula can be shown in formula (5):

[0105]

[0106] Then the first power consumption E can be calculated. s With the second power consumption E w The sum of these values ​​represents the total system power consumption E during the single orbit of the spherical satellite. Then, based on the total system power consumption E and the shortest illumination time T... s Calculate the input power W required for a spherical satellite. i Input power W i The calculation formula can be shown in formula (6):

[0107]

[0108] In some embodiments, step 404 above may specifically perform the following steps:

[0109] Calculate the power margin of the power supply system based on the second and third output powers;

[0110] Under the condition that the power margin meets the preset margin conditions, it is determined that the energy of the spherical satellite is in a balanced state.

[0111] In this embodiment, to ensure the operational status of the spherical satellite, the actual output power of the solar array should have a certain margin compared to the required output power of the solar array, so as to ensure that the spherical satellite can cope with some emergencies. Based on this, when analyzing whether the energy of the spherical satellite is balanced, the power margin of the power system can be calculated first based on the second output power and the third output power. The formula for calculating the power margin of the power system can be shown in formula (7):

[0112]

[0113] Where p is the power margin of the power supply system, W All W is the second output power, and W is the third output power.

[0114] If the power margin meets the preset margin conditions, it can be determined that the energy of the spherical satellite is in a balanced state. For example, if the power margin of the power system meets 10%, the spherical satellite can be considered to meet the energy balance requirements.

[0115] Based on the energy balance analysis method provided in the above embodiments, this application also provides an embodiment of an energy balance analysis device.

[0116] Figure 5 A schematic diagram of the structure of an energy balance analysis device provided in another embodiment of this application is shown. For ease of explanation, only the parts related to the embodiments of this application are shown.

[0117] Reference Figure 5 The energy balance analysis device 500 can be applied to the aforementioned spherical satellite, wherein the spherical satellite may include a power system, and the energy balance analysis device 500 may include:

[0118] The acquisition module 501 is used to acquire the effective illumination area, solar radiation flux and photoelectric conversion efficiency of the solar cell array of the spherical satellite, and to acquire the illumination status information, first output power and power system performance parameters of the spherical satellite, wherein the first output power is the output power required corresponding to the illumination status information.

[0119] The first calculation module 502 is used to calculate the second output power based on the effective illuminated area, solar radiation flux and photoelectric conversion efficiency. The second output power is the actual output power of the solar cell array.

[0120] The second calculation module 503 is used to calculate the third output power required by the solar cell array of the spherical satellite based on the illumination status information, the first output power and performance parameters.

[0121] The determination module 504 is used to determine whether the energy of the spherical satellite is in a balanced state based on the second output power and the third output power.

[0122] In some embodiments, the second computing module 503 may include:

[0123] The first determining unit is used to determine the input power required by the spherical satellite based on the illumination status information, the first output power, and performance parameters.

[0124] The second determining unit is used to determine the third output power required by the solar array of the spherical satellite based on the input power and performance parameters.

[0125] In some embodiments, illumination state information may include the shortest illumination time and the longest shadow time, the first output power may include the first sub-output power required by the illumination time spherical satellite and the second sub-output power required by the shadow time spherical satellite, and the first determining unit may specifically be used for:

[0126] Calculate the first power consumption of the spherical satellite based on the shortest illumination time, the first sub-output power, and performance parameters.

[0127] Calculate the second power consumption of the shadow-time spherical satellite based on the longest shadow time, the second sub-output power, and performance parameters;

[0128] Calculate the input power required for the spherical satellite based on the first power consumption, the second power consumption, and the shortest illumination time.

[0129] In some embodiments, the determining module 504 may specifically be used for:

[0130] Calculate the power margin of the power supply system based on the second and third output powers;

[0131] Under the condition that the power margin meets the preset margin conditions, it is determined that the energy of the spherical satellite is in a balanced state.

[0132] In some embodiments, the acquisition module 501 can also be used for:

[0133] Determine the incident direction of illumination parallel to the direction vector of each arc-shaped base plate of the spherical satellite. The direction vector of the arc-shaped base plate is used to indicate the direction of the line connecting the center of the spherical satellite and the center of the arc-shaped base plate.

[0134] Based on each incident light direction, determine the angle between each curved base plate and the incident light direction under each incident light direction;

[0135] Based on the angle between each arc-shaped base plate and the incident direction of light, the target arc-shaped base plate is determined from the M arc-shaped base plates;

[0136] Based on the target curved base plate, determine the initial illumination area corresponding to each incident light direction;

[0137] Based on M initial illumination areas, determine the effective illumination area of ​​the solar array of the spherical satellite.

[0138] It should be noted that the information interaction and execution process between the above-mentioned devices / units are based on the same concept as the method embodiments of this application. They are devices corresponding to the above-mentioned energy balance analysis method. All implementation methods in the above-mentioned method embodiments are applicable to the embodiments of this device. For details on its specific functions and the resulting technical effects, please refer to the method embodiment section. It will not be repeated here.

[0139] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the above-described division of functional units and modules is merely an example. In practical applications, the above functions can be assigned to different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiments can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit. Furthermore, the specific names of the functional units and modules are only for easy differentiation and are not intended to limit the scope of protection of this application. The specific working process of the units and modules in the above system can be referred to the corresponding process in the foregoing method embodiments, and will not be repeated here.

[0140] Figure 6 A schematic diagram of the hardware structure of an electronic device provided in yet another embodiment of this application is shown.

[0141] The device may include a processor 601 and a memory 602 storing programs or instructions.

[0142] When the processor 601 executes the program, it implements the steps in any of the above method embodiments.

[0143] For example, the program can be divided into one or more modules / units, one or more of which are stored in memory 602 and executed by processor 601 to complete this application. The one or more modules / units can be a series of program instruction segments capable of performing a specific function, which describe the execution process of the program in the device.

[0144] Specifically, the processor 601 may include a central processing unit (CPU), an application-specific integrated circuit (ASIC), or one or more integrated circuits that can be configured to implement the embodiments of this application.

[0145] Memory 602 may include mass storage for data or instructions. For example, and not limitingly, memory 602 may include a hard disk drive (HDD), floppy disk drive, flash memory, optical disk, magneto-optical disk, magnetic tape, or Universal Serial Bus (USB) drive, or a combination of two or more of these. Where appropriate, memory 602 may include removable or non-removable (or fixed) media. Where appropriate, memory 602 may be internal or external to the integrated gateway disaster recovery device. In a particular embodiment, memory 602 is non-volatile solid-state memory.

[0146] Memory may include read-only memory (ROM), random access memory (RAM), disk storage media devices, optical storage media devices, flash memory devices, and electrical, optical, or other physical / tangible memory storage devices. Therefore, typically, memory includes one or more tangible (non-transitory) readable storage media (e.g., memory devices) encoded with software including computer-executable instructions, and when the software is executed (e.g., by one or more processors), it is operable to perform the operations described with reference to the methods according to one aspect of this disclosure.

[0147] The processor 601 implements any of the methods described above by reading and executing programs or instructions stored in the memory 602.

[0148] In one example, the electronic device may also include a communication interface 603 and a bus 610. The processor 601, memory 602, and communication interface 603 are connected via the bus 610 and communicate with each other.

[0149] The communication interface 603 is mainly used to realize communication between various modules, devices, units and / or equipment in the embodiments of this application.

[0150] Bus 610 includes hardware, software, or both, that couples components of an online data traffic metering device together. For example, and not limitingly, the bus may include an Accelerated Graphics Port (AGP) or other graphics bus, an Enhanced Industry Standard Architecture (EISA) bus, a Front Side Bus (FSB), HyperTransport (HT) interconnect, an Industry Standard Architecture (ISA) bus, an Infinite Bandwidth Interconnect, a Low Pin Count (LPC) bus, a memory bus, a Microchannel Architecture (MCA) bus, a Peripheral Component Interconnect (PCI) bus, a PCI-Express (PCI-X) bus, a Serial Advanced Technology Attachment (SATA) bus, a Video Electronics Standards Association Local (VLB) bus, or other suitable buses, or combinations of two or more of these. Where appropriate, bus 610 may include one or more buses. Although specific buses are described and illustrated in embodiments of this application, any suitable bus or interconnect is contemplated herein.

[0151] Furthermore, in conjunction with the methods in the above embodiments, this application embodiment can provide a storage medium for implementation. This storage medium stores a program or instructions; when executed by a processor, the program or instructions implement any of the methods in the above embodiments.

[0152] This application embodiment also provides a chip, which includes a processor and a communication interface. The communication interface is coupled to the processor. The processor is used to run programs or instructions to implement the various processes of the above method embodiments and achieve the same technical effect. To avoid repetition, it will not be described again here.

[0153] It should be understood that the chip mentioned in the embodiments of this application may also be referred to as a system-on-a-chip, system chip, chip system, or system-on-a-chip, etc.

[0154] This application provides a computer program product, which is stored in a storage medium and executed by at least one processor to implement the various processes of the above method embodiments and achieve the same technical effects. To avoid repetition, it will not be described again here.

[0155] It should be clarified that this application is not limited to the specific configurations and processes described above and shown in the figures. For the sake of brevity, detailed descriptions of known methods are omitted here. In the above embodiments, several specific steps are described and shown as examples. However, the method process of this application is not limited to the specific steps described and shown. Those skilled in the art can make various changes, modifications, and additions, or change the order of steps, after understanding the spirit of this application.

[0156] The functional modules shown in the above-described block diagram can be implemented as hardware, software, firmware, or a combination thereof. When implemented in hardware, they can be, for example, electronic circuits, application-specific integrated circuits (ASICs), appropriate firmware, plug-ins, function cards, etc. When implemented in software, the elements of this application are programs or code segments used to perform the required tasks. Programs or code segments can be stored on a machine-readable medium or transmitted over a transmission medium or communication link via data signals carried on a carrier wave. "Machine-readable medium" can include any medium capable of storing or transmitting information. Examples of machine-readable media include electronic circuits, semiconductor memory devices, ROM, flash memory, erasable ROM (EROM), floppy disks, CD-ROMs, optical disks, hard disks, fiber optic media, radio frequency (RF) links, etc. Code segments can be downloaded via computer grids such as the Internet, intranets, etc.

[0157] It should also be noted that the exemplary embodiments mentioned in this application describe methods or systems based on a series of steps or apparatus. However, this application is not limited to the order of the above steps; that is, the steps can be performed in the order mentioned in the embodiments, or in a different order, or several steps can be performed simultaneously.

[0158] The aspects of this disclosure have been described above with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and program products according to embodiments of this disclosure. It should be understood that each block in the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by a computer program or instructions. These programs or instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, or other programmable data processing apparatus to produce a machine such that these instructions, executable via the processor of the computer or other programmable data processing apparatus, enable the implementation of the functions / actions specified in one or more blocks of the flowchart illustrations and / or block diagrams. Such a processor can be, but is not limited to, a general-purpose processor, a special-purpose processor, a special application processor, or a field-programmable logic circuit. It is also understood that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, can also be implemented by special-purpose hardware performing the specified functions or actions, or can be implemented by a combination of special-purpose hardware and computer instructions.

[0159] The above description is merely a specific implementation of this application. Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working processes of the systems, modules, and units described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here. It should be understood that the protection scope of this application is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this application, and these modifications or substitutions should all be covered within the protection scope of this application.

Claims

1. A method for energy balance analysis of a spherical satellite, characterized in that, The spherical satellite includes a power system, a spherical frame, M arc-shaped base plates, and a solar cell array. The M arc-shaped base plates are spliced ​​onto the spherical frame, where M is an integer greater than 1. The solar cell array is distributed on the outer surfaces of at least K first arc-shaped base plates among the M arc-shaped base plates, where K is an integer greater than 1 and K is less than or equal to M. Each first arc-shaped base plate has multiple first solar cells arranged in a series-parallel configuration on its outer surface, and the number of first solar cells connected in series on each first arc-shaped base plate is equal. The multiple first solar cells on the K first arc-shaped base plates form the solar cell array. The method includes: The effective illumination area, solar radiation flux, and photoelectric conversion efficiency of the solar cell array of the spherical satellite are obtained, and the illumination status information, first output power, and performance parameters of the power system of the spherical satellite are also obtained, wherein the first output power is the output power required corresponding to the illumination status information. The second output power is calculated based on the effective illuminated area, the solar radiation flux, and the photoelectric conversion efficiency. The second output power is the actual output power of the solar cell array. Based on the illumination status information, the first output power, and the performance parameters, calculate the third output power required for the solar array of the spherical satellite; Based on the second output power and the third output power, determine whether the energy of the spherical satellite is in a balanced state; Obtaining the effective illuminated area of ​​the solar array of the spherical satellite includes: Determine the incident direction of illumination parallel to the direction vector of each arc-shaped base plate of the spherical satellite, wherein the direction vector of the arc-shaped base plate is used to indicate the direction of the line connecting the center of the spherical satellite and the center of the arc-shaped base plate; Based on each of the light incident directions, determine the angle between each of the arc-shaped base plates and the light incident direction under each of the light incident directions; The target arc-shaped base plate is determined from the M arc-shaped base plates based on the angle between each arc-shaped base plate and the incident direction of the light. Based on the target arc-shaped base plate, determine the initial illumination area corresponding to each of the light incident directions; The effective illumination area of ​​the solar array of the spherical satellite is determined based on the M initial illumination areas.

2. The method according to claim 1, characterized in that, The step of calculating the third output power required by the solar array of the spherical satellite based on the illumination status information, the first output power, and the performance parameters includes: The required input power for the spherical satellite is determined based on the illumination status information, the first output power, and the performance parameters. Based on the input power and the performance parameters, determine the third output power required for the solar array of the spherical satellite.

3. The method according to claim 2, characterized in that, The illumination status information includes the shortest illumination time and the longest shadow time, and the first output power includes the first sub-output power required by the spherical satellite during the illumination time and the second sub-output power required by the spherical satellite during the shadow time; The step of determining the required input power for the spherical satellite based on the illumination status information, the first output power, and the performance parameters includes: Based on the shortest illumination time, the first sub-output power, and the performance parameters, calculate the first power consumption of the spherical satellite during the illumination time; The second power consumption of the spherical satellite during the shadow time is calculated based on the longest shadow time, the second sub-output power, and the performance parameters. The required input power for the spherical satellite is calculated based on the first power consumption, the second power consumption, and the shortest illumination time.

4. The method according to claim 1, characterized in that, Determining whether the energy of the spherical satellite is in a balanced state based on the second output power and the third output power includes: Calculate the power margin of the power supply system based on the second output power and the third output power; If the power margin meets the preset margin condition, it is determined that the energy of the spherical satellite is in a balanced state.

5. An energy balance analysis device, characterized in that, This invention is applied to a spherical satellite, which includes a power system, a spherical frame, M arc-shaped base plates, and a solar cell array. The M arc-shaped base plates are spliced ​​onto the spherical frame, where M is an integer greater than 1. The solar cell array is distributed on the outer surfaces of at least K first arc-shaped base plates among the M arc-shaped base plates, where K is an integer greater than 1 and K is less than or equal to M. Each first arc-shaped base plate has multiple first solar cells arranged in a series-parallel configuration on its outer surface, and the number of first solar cells connected in series on each first arc-shaped base plate is equal. The multiple first solar cells on the K first arc-shaped base plates form the solar cell array. The device includes: The acquisition module is used to acquire the effective illumination area, solar radiation flux and photoelectric conversion efficiency of the solar cell array of the spherical satellite, and to acquire the illumination status information, first output power and performance parameters of the power system of the spherical satellite, wherein the first output power is the output power required corresponding to the illumination status information; The first calculation module is used to calculate the second output power based on the effective illuminated area, the solar radiation flux and the photoelectric conversion efficiency, wherein the second output power is the actual output power of the solar cell array; The second calculation module is used to calculate the third output power required by the solar array of the spherical satellite based on the illumination status information, the first output power and the performance parameters. The determining module is used to determine whether the energy of the spherical satellite is in a balanced state based on the second output power and the third output power. The acquisition module is specifically used for: Determine the incident direction of illumination parallel to the direction vector of each arc-shaped base plate of the spherical satellite, wherein the direction vector of the arc-shaped base plate is used to indicate the direction of the line connecting the center of the spherical satellite and the center of the arc-shaped base plate; Based on each of the light incident directions, determine the angle between each of the arc-shaped base plates and the light incident direction under each of the light incident directions; The target arc-shaped base plate is determined from the M arc-shaped base plates based on the angle between each arc-shaped base plate and the incident direction of the light. Based on the target arc-shaped base plate, determine the initial illumination area corresponding to each of the light incident directions; The effective illumination area of ​​the solar array of the spherical satellite is determined based on the M initial illumination areas.

6. An electronic device, characterized in that, The device includes: a processor and a memory storing programs or instructions; When the processor executes the program or instructions, it implements the method as described in any one of claims 1-4.

7. A storage medium, characterized in that, The storage medium stores a program or instructions that, when executed by a processor, implement the method as described in any one of claims 1-4.

8. A computer program product, characterized in that, When the instructions in the computer program product are executed by the processor of the electronic device, the electronic device causes the electronic device to perform the method as described in any one of claims 1-4.

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