Analysis method for calculating energy balance by shielding solar cell array through satellite body and antenna

Abstract

The invention discloses an analysis method for energy balance calculation by shielding a solar cell array through a satellite body and an antenna. The analysis method comprises the steps that 1) shielding working conditions are simulated, and shielding conditions of the satellite body, an antenna truss, antenna truss nodes and an antenna net on the solar cell array under different shielding working conditions are analyzed; 2) according to a ground test, testing electrical performance attenuation change caused by partial shielding of the antenna to the solar cell array under different shielding working conditions; and 3) analyzing electrical performance attenuation caused by the shielding of the solar cell array by the satellite body, the antenna truss, the antenna truss node and the antenna network, and further calculating whether the energy of the whole satellite is balanced or not. According to the method, the simulation shielding working condition is combined with the ground test, solar cell array energy balance calculation under different satellite body and antenna shielding working conditions is analyzed, and technical support can be provided for whole satellite energy balance, solar cell array power design and layout optimization; and theoretical prediction is provided for electric performance attenuation of the solar cell array under a subsequent satellite in-orbit complex shielding working condition.

Description

Technical Field

[0001] The invention belongs to the technical field of solar cell arrays of satellite power supply systems, and in particular relates to an analysis method for energy balance calculation when a satellite body and an antenna shield a solar cell array. Background Art

[0002] As a crucial component of satellites, the power system provides energy for the entire satellite platform and payload, ensuring their survival and reliable operation. Currently, most satellite power systems use solar arrays as their primary power generation device. The power generation capacity of a satellite's solar array depends on various conditions, including light intensity, operating temperature, charged particle irradiation, and partial shading. As the relative positions of the satellite, antenna, and solar array change, there may be periods of time when the satellite and antenna obstruct the solar array. Antenna shading is complex, potentially causing energy imbalances across the satellite and impacting the application of the entire payload.

[0003] Given the above issues, previous technologies often analyzed the impact of complex antenna shielding conditions on solar arrays using image detection or model projection methods, using a general maximum envelope. This lacked accuracy in analyzing the electrical performance degradation caused by shielding. Actual antenna shielding includes both physical shielding caused by the antenna truss and its nodes, as well as partial shielding caused by the antenna mesh. The number of solar cells shielded by the antenna truss and truss nodes also varies. While the antenna mesh provides partial shielding, the electrical performance degradation caused by different shielding angles and distances can also vary. Therefore, a simple and accurate analysis method is needed to provide a basis for overall satellite energy balance and satellite solar array design through simulation analysis combined with ground testing. Summary of the Invention

[0004] The purpose of the present invention is to provide an analysis method for calculating the energy balance of a satellite body and antenna blocking a solar cell array, so as to solve the problem of difficulty in calculating the energy balance under various blocking conditions of the satellite body and antenna blocking the solar cell array.

[0005] In order to achieve the above-mentioned objectives, the present invention provides an analysis method for calculating the energy balance of a solar array blocked by a satellite body and antenna, comprising: 1) simulating blocking conditions and analyzing the blocking of the solar array by the satellite body, antenna truss, antenna truss nodes and antenna network under different blocking conditions; 2) testing, based on ground tests, the changes in electrical performance attenuation caused by partial blocking of the solar array by the antenna under different blocking conditions; 3) analyzing the electrical performance attenuation caused by the blocking of the solar array by the satellite body, antenna truss, antenna truss nodes and antenna network, and then calculating whether the energy of the entire satellite is balanced.

[0006] The method for analyzing the satellite body and the antenna shielding the solar cell array for energy balance calculation, wherein in step 1), the shielding analysis diagram is formed by combining the shielding pattern diagram of the satellite body and the antenna under the worst working condition and the solar cell array sheet diagram, and the shielding of the satellite body, the antenna truss, the antenna truss node and the antenna net to the solar cell array is analyzed.

[0007] The method for analyzing the satellite body and the antenna shielding the solar cell array for energy balance calculation, wherein step 2) comprises: 2-1) testing the different solar cell components under the condition without antenna shielding by using the antenna shielding solar cell array electric performance testing system to obtain the testing result I0; 2-2) testing the different solar cell components, the distance between the antenna and the solar cell array and the antenna illumination angle by using the antenna shielding solar cell array electric performance testing system to obtain the testing result I1; 2-3) obtaining the electric performance decay rate Q=1-(I1 / I0) of the different antenna illumination angles and the different distances between the antenna and the solar cell array according to the testing results.

[0008] The method for analyzing the satellite body and the antenna shielding the solar cell array for energy balance calculation, wherein the antenna shielding solar cell array electric performance testing system is placed in a darkroom and comprises a solar cell array, a solar cell array support vehicle, a sun simulator, an antenna and an antenna support vehicle; the antenna is placed on the antenna support vehicle; the solar cell array is fixedly installed on the solar cell array support vehicle; the antenna support vehicle has the moving ability, the rotating angle ability and the lifting ability, and the distance between the antenna and the solar cell array, the included angle between the antenna normal line and the sunlight and the height of the antenna relative to the solar cell array can be adjusted by the antenna support vehicle; the solar cell array comprises a substrate, different solar cell components are arranged on the front surface of the substrate, the output end of the solar cell component is led to the back surface of the substrate through a threading hole and is connected with the sun simulator.

[0009] The above-mentioned analysis method for calculating the energy balance of the satellite body and antenna blocking the solar cell array, wherein the ground test specifically includes the following steps: S1, turning on the solar simulator and calibrating the solar simulator, and the light intensity of the solar simulator conforms to the AM0 spectrum; S2, pasting different solar cell modules on both sides of the central axis of the solar cell array substrate, and leading the output ends of the solar cell modules to the back of the substrate through the threading holes with positive and negative wires to form a solar cell array; S3, installing the solar cell array on the solar cell array support vehicle, and pushing the solar cell array support vehicle to a position on the same plane as the standard film, and the solar cell array patch surface is perpendicular to the solar simulator light; S4, stretching the woven metal mesh on the metal frame to form an antenna, and placing the antenna on the antenna support vehicle; S5, first connecting different solar cell modules to the solar simulator without antenna blocking, filling in different solar simulator parameters, and testing the electrical performance of the solar cell modules; S6, adjusting the antenna height by adjusting the antenna support vehicle to ensure that the antenna can block the solar cell modules of the solar cell array;

[0010] S7. Change the distance between the antenna and the solar cell array by moving the antenna support vehicle. The moving distances are 0.5m, 1.0m, and 1.5m respectively. Use a solar simulator to irradiate and test the electrical performance of the solar cell module at different distances. S8. Change the angle between the antenna normal and the solar simulator light. Use a solar simulator to irradiate and test the electrical performance of the solar cell module at illumination angles of 0 to 70°, respectively. Test every 10°.

[0011] The above-mentioned analysis method for calculating the energy balance of the satellite body and antenna blocking the solar cell array, wherein the electrical performance of the solar cell module includes short-circuit current, open-circuit voltage, optimal operating point current, optimal operating point voltage, volt-ampere characteristic curve and electrical performance degradation rate Q.

[0012] The method comprises the following steps: 1) obtaining the satellite body, the antenna truss, the antenna truss node and the antenna net; 2) obtaining the solar cell array; 3) obtaining the energy balance calculation method; 4) obtaining the energy balance calculation method; and 5) obtaining the energy balance calculation method.

[0013] The method comprises the following steps: 1) obtaining the satellite body, the antenna truss, the antenna truss node and the antenna net; 2) obtaining the solar cell array; 3) obtaining the energy balance calculation method; 4) obtaining the energy balance calculation method; and 5) obtaining the energy balance calculation method. 帆 <I 负 The method comprises the following steps: 1) obtaining the satellite body, the antenna truss, the antenna truss node and the antenna net; 2) obtaining the solar cell array; 3) obtaining the energy balance calculation method; 4) obtaining the energy balance calculation method; and 5) obtaining the energy balance calculation method.

[0014] Compared with the prior art, the method has the beneficial technical effects that:

[0015] The method comprises the following steps: 1) obtaining the satellite body, the antenna truss, the antenna truss node and the antenna net; 2) obtaining the solar cell array; 3) obtaining the energy balance calculation method; 4) obtaining the energy balance calculation method; and 5) obtaining the energy balance calculation method. BRIEF DESCRIPTION OF DRAWINGS

[0016] The analysis method of the energy balance calculation of the satellite body and antenna blocking the solar array of the present invention is given in the following embodiments and drawings.

[0017] Figure 1 Schematic diagram of a system for testing the electrical performance of a solar cell array shielded by a ground antenna in a preferred embodiment of the present invention.

[0018] Figure 2 Schematic diagram of the distance change between the antenna and the solar cell array in a preferred embodiment of the present invention.

[0019] Figure 3 Schematic diagram of the change of the angle (illumination angle) between the antenna normal and sunlight in a preferred embodiment of the present invention.

[0020] Figure 4 This is a curve diagram of the output current of the entire solar array under different shading conditions in a preferred embodiment of the present invention. DETAILED DESCRIPTION

[0021] The following will be combined Figures 1-4 The analysis method of the energy balance calculation caused by the satellite body and antenna blocking the solar array is further described in detail.

[0022] The analysis method of the present invention for calculating the energy balance due to the satellite body and antenna blocking the solar array includes:

[0023] 1) Simulate shielding conditions and analyze the shielding of the solar array by the satellite body, antenna truss, antenna truss nodes, and antenna network under different shielding conditions;

[0024] Through simulation analysis of the shielding conditions of the satellite body, antenna truss, antenna truss nodes and antenna network on the solar array under different shielding conditions, the worst shielding condition is determined. The shielding morphology of the satellite body and antenna on the solar array under the worst shielding condition is combined with the solar array layout to form a shielding analysis diagram to analyze the shielding conditions of the satellite body, antenna truss, antenna truss nodes and antenna network on the solar array.

[0025] 2) Based on ground tests, test the changes in electrical performance attenuation caused by partial shading of the solar array by the antenna under different shading conditions;

[0026] 2-1) Under no-antenna-blocking working conditions, different solar cell modules are tested using the antenna-blocking solar cell array electrical performance test system to obtain test results I0;

[0027] 2-2) Using the antenna shielding solar cell array electrical performance test system, different solar cell modules, antenna-to-solar cell array distances, and antenna illumination angles are tested to obtain test results I1;

[0028] 2-3) According to the test results, the different antenna illumination angles and the electrical performance attenuation rate Q = 1-(I1 / I0) of the antenna and the solar cell array at different distances are obtained;

[0029] The antenna shielding solar cell array electrical performance test system used in the ground test comprises a solar cell array, a solar cell array support vehicle, a solar simulator, an antenna and an antenna support vehicle;

[0030] The solar simulator is placed in a darkroom, and the solar simulator needs to be started and calibrated before the test to simulate AM0 light conditions;

[0031] The antenna support vehicle has a moving ability, can change the distance between the antenna and the solar cell array, has a rotating angle ability, can change the angle between the normal line of the antenna and the sunlight, and can also fix the angle between the normal line of the antenna and the sunlight at a certain value, has a lifting ability, can control the height of the antenna relative to the solar cell array, and ensures that the antenna shields or partially shields the solar cell array; the metal frame of the antenna support vehicle is painted black, avoiding light scattering through the antenna;

[0032] The antenna is tensioned on a metal tensioning frame according to a related process to simulate the working state of the antenna in orbit; the metal tensioning frame has two cylindrical handles (rotation shafts), and the antenna is installed on the antenna support vehicle by using the cylindrical handles to realize the adjustment of the distance, angle and height between the antenna and the solar cell array; the metal tensioning frame of the antenna is painted black, avoiding light scattering through the antenna;

[0033] The solar cell array comprises a substrate, a solar cell component and a metal frame, the substrate is arranged in the metal frame, the solar cell component is arranged on the front surface of the substrate, and a wire is led to the back surface of the substrate through a threading hole at the output end of the solar cell component and connected with a test wire of the solar simulator;

[0034] The solar cell array is fixed on the solar cell array support vehicle through the metal frame;

[0035] In the antenna shielding solar cell array electrical performance test system, the satellite, the antenna and the solar cell array are scaled at the same proportion;

[0036] The ground test specifically comprises the following steps:

[0037] S1, start the solar simulator, calibrate the solar simulator, the light intensity of the solar simulator meets the AM0 spectrum, and the light intensity is 1353W / m 2 ;

[0038] S2, different solar cell components are respectively pasted on both sides of the central axis of the substrate of the solar cell array, the output ends of the solar cell components are respectively led to the back surface of the substrate through a threading hole by using positive and negative wires, and the solar cell array is formed.

[0039] S3. Install the solar cell array on the solar cell array support vehicle, and push the solar cell array support vehicle to a position on the same plane as the standard film, with the solar cell array patch surface perpendicular to the solar simulator light;

[0040] S4. Stretch the woven metal mesh on the metal frame to form an antenna; place the antenna on an antenna support vehicle. The antenna can be rotated and raised and lowered on the antenna support vehicle, and can also be moved with the antenna support vehicle;

[0041] S5. First, connect different solar cell modules to the solar simulator without antenna obstruction, fill in different solar simulator parameters, and test the electrical performance of the solar cell modules;

[0042] S6. Adjust the height of the antenna by adjusting the antenna support vehicle to ensure that the antenna can shield the solar cell components of the solar cell array;

[0043] S7. Move the antenna support vehicle to change the distance between the antenna and the solar cell array. The moving distances are 0.5m, 1.0m, and 1.5m respectively. Use a solar simulator to test the electrical performance of the solar cell module at different distances.

[0044] S8. Changing the angle between the antenna normal and the solar simulator light, using the solar simulator to illuminate, and testing the electrical performance of the solar cell assembly at illumination angles of 0° to 70° (testing every 10°);

[0045] Ground tests use solar simulators to measure the electrical performance of solar cell modules, including short-circuit current (Isc), open-circuit voltage (Voc), optimal operating point current (Im), optimal operating point voltage (Vm), volt-ampere characteristic curve (IV curve), and electrical performance degradation rate Q.

[0046] 3) Analyze the electrical performance degradation caused by the shielding of the solar array by the satellite body, antenna truss, antenna truss nodes, and antenna network, and then calculate whether the energy balance of the entire satellite is balanced;

[0047] The various composite working conditions of the satellite body, antenna truss, antenna truss node and antenna network blocking the solar cell array are classified into two cases: physical blocking and partial blocking. Among them, the satellite body, antenna truss and antenna truss node blocking the solar cell array is physical blocking, and the antenna network blocking the solar cell array is partial blocking. If a string of xx or more cells is physically blocked, the string of cells is considered to have no output. Partial blocking will only cause the current to attenuate, and will not cause the entire string of cells to have no output. The current attenuation ratio is proportional to the area of ​​the blocked cell string. The total solar array output is proportional to the solar power of the entire satellite. Therefore, the output of the solar array is I = A*I0 + B*I1 + D*0, where A represents the number of unobstructed parallel cells, B represents the number of parallel cells with less than xx physical obstructions and blocked by the antenna network, and D represents the number of parallel cells with xx or more physical obstructions. A+B+D = the total number of parallel solar cells in the array. I0 is the output current of all unobstructed cells; I1 is the output current of all partially obstructed cells, I1 = I0*Q. The power C = I*t, where t is the illumination time or shadow time.

[0048] Energy balance calculation method:

[0049] When the solar array power capacity is greater than the load power consumption (I 帆 >I 负 ), Ccharge1+Ccharge2=Cdischarge, where Ccharge1: charging capacity when the solar array is shaded and the power generation capacity is reduced; Ccharge2: charging capacity when the solar array is not shaded; Cdischarge: discharge capacity in the shadow area;

[0050] When the solar array's power generation capacity is less than the load's power consumption (I 帆 <I 负 ), Ccharge = Cdischarge1 + Cdischarge2, Ccharge: charging capacity when the solar array is not blocked; Cdischarge1: discharge capacity when the solar array is blocked and the power generated is less than the load power consumption; Cdischarge2: discharge capacity in the shadow area.

[0051] The present invention uses simulated shielding conditions combined with ground tests to analyze the energy balance calculation of solar arrays under different satellite body and antenna shielding conditions, which can provide technical support for the energy balance of the entire satellite, the power design and layout optimization of the solar array, and provide theoretical predictions for the degradation of the electrical performance of the solar array under complex shielding conditions of subsequent satellites in orbit.

[0052] Example:

[0053] like Figure 1As shown, the ground antenna shielding solar array electrical performance test system includes: a solar simulator 1, an antenna, an antenna support vehicle 3, a solar array, and a solar array support vehicle 5. The solar array 4 includes a 1000mm×600mm carbon fiber substrate 41 and four solar cell modules. The substrate 41 is set in a metal frame 42, and the solar array 4 is installed on the solar array support vehicle 5 to simulate an in-orbit satellite solar array and test the impact of different antenna network shielding conditions on the solar array's power generation capacity. The metal mesh 21 is tensioned with a metal tensioning frame 22 to form an antenna, simulating an actual satellite antenna. The antenna is then installed on the movable, rotating, and elevating antenna support vehicle 3 to verify the impact of the antenna and solar array at distances of 0.5m, 1.0m, and 1.5m, respectively. The antenna is adjusted to a 0-70° illumination angle between the antenna and sunlight to ensure that the antenna network can block the solar cell modules. The ground antenna blocking the solar cell array electrical performance test system is placed in a darkroom, and the antenna support vehicle 3 and the metal tensioning frame 22 are all painted black to reduce the error caused by light source scattering on the test results. The solar simulator 1 is connected to different solar cell modules of the solar cell array to first test the electrical performance of the solar cell modules without antenna blocking. Then, the angle between the normal line of the antenna network and sunlight, the distance between the antenna network and the solar cell array, and the height between the antenna network and the solar cell array are changed to test the electrical performance of the solar cell modules under different working conditions.

[0054] like Figure 2 The following figure shows the effect of the distance between the antenna grid and sunlight on the electrical performance of the solar array. First, the electrical performance of the solar cell modules was tested without antenna obstruction. Then, by adjusting the distance between the antenna support vehicle and the solar array, the changes in solar cell efficiency and electrical performance at different distances (0.5m, 1.0m, and 1.5m) were tested. This simulates the effect of different distances between the actual satellite antenna and the solar array on the solar array's power generation capacity.

[0055] like Figure 3 As shown in the figure, the effect of the antenna grid normal and sunlight angle on the electrical performance of the solar cell array was tested. First, the electrical performance of the solar cell array was tested without antenna obstruction. Then, by adjusting the antenna normal and sunlight angle, the electrical performance of different solar cell modules was tested at different illumination angles (0°, 10°, 20°, 30°, 40°, 50°, 60°, and 70°). This simulated the effect of different satellite antenna and sunlight angles on the solar cell array's power generation capacity.

[0056] like Figure 4As shown in the figure, when the solar incident angle is 19.46° and the solar array rotation angle is different, the satellite body and antenna block the output I of the entire satellite solar array. According to the formula I = A*I0 + B*I1 + C*0, combined with the specific blocking conditions, the change of solar array output I under different blocking conditions is obtained, which further provides support for the energy balance calculation of the entire satellite.

[0057] In summary, the present invention overcomes the shortcomings of the existing technology and provides an analysis method for energy balance calculation when the satellite body and antenna block the solar array, which solves the problem of energy balance calculation caused by the satellite being blocked by the antenna, and provides technical support for the ground power design of the satellite solar array, battery cell layout and smooth operation in orbit.

[0058] The present invention provides an analysis method for calculating the energy balance of a solar cell array when a satellite body and antenna block it. The method solves the problem of difficulty in calculating the energy balance under various blocking conditions of the solar cell array by the satellite body and antenna, solves the problem of inaccurate changes in the electrical performance attenuation of the solar cell array when the antenna network blocks it at different angles and distances, and solves the problem of difficulty in analyzing complex blocking conditions. The method provides technical support for ground power design, cell layout, and smooth on-orbit operation of satellite solar cell arrays.

[0059] Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modification to the above embodiments made according to the technical essence of the present invention without departing from the content of the technical solution of the present invention is not limited to the present invention.

[0060] Equivalent changes and modifications all fall within the protection scope of the technical solution of the present invention.

[0061] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. An analytical method for calculating the energy balance due to the obstruction of the solar array by the satellite body and antenna, characterized in that: include: 1) Simulate shielding conditions and analyze the shielding of the solar array by the satellite body, antenna truss, antenna truss nodes, and antenna network under different shielding conditions; 2) Based on ground tests, test the changes in electrical performance attenuation caused by partial shading of the solar array by the antenna under different shading conditions; 3) Analyze the electrical performance degradation caused by the shielding of the solar array by the satellite body, antenna truss, antenna truss nodes and antenna network, and then calculate whether the energy of the entire satellite is balanced.

2. The method for analyzing the effect of satellite body and antenna blocking solar array on energy balance calculation as claimed in claim 1, characterized in that: In the step 1), the shading topography of the satellite body and antenna to the solar cell array under the worst working conditions is combined with the solar cell array layout diagram to form a shading analysis diagram to analyze the shading of the satellite body, antenna truss, antenna truss nodes and antenna network to the solar cell array.

3. The method for analyzing the effect of satellite body and antenna blocking solar array on energy balance calculation as claimed in claim 1, characterized in that: The step 2) comprises: 2-1) Under no-antenna-blocking working conditions, different solar cell modules are tested using the antenna-blocking solar cell array electrical performance test system to obtain test results I0; 2-2) Using the antenna shielding solar cell array electrical performance test system, different solar cell modules, antenna-to-solar cell array distances, and antenna illumination angles are tested to obtain test results I1; 2-3) Based on the test results, the electrical performance attenuation rate Q = 1-(I1 / I0) at different antenna illumination angles and different distances between the antenna and the solar cell array is obtained.

4. The method for analyzing the effect of satellite bodies and antennas blocking solar arrays on energy balance calculation according to claim 3, wherein: The antenna-shielded solar array electrical performance test system is placed in a darkroom and includes: a solar array, a solar array support vehicle, a solar simulator, an antenna, and an antenna support vehicle; the antenna is placed on the antenna support vehicle; the solar array is fixedly installed on the solar array support vehicle; the antenna support vehicle has the ability to move, rotate, and lift, and the antenna support vehicle can be used to adjust the distance between the antenna and the solar array, the angle between the antenna normal and sunlight, and the height of the antenna relative to the solar array.

5. The method for analyzing the effect of satellite bodies and antennas blocking solar arrays on energy balance calculation according to claim 4, wherein: The solar cell array comprises a substrate, different solar cell modules are arranged on the front side of the substrate, and the output ends of the solar cell modules are led to the back side of the substrate through wire holes and connected to the solar simulator.

6. The method for analyzing the effect of satellite body and antenna blocking solar array on energy balance calculation as claimed in claim 5, characterized in that: The ground test specifically includes the following steps: S1. Turn on the solar simulator and calibrate it. The light intensity of the solar simulator complies with the AM0 spectrum. S2. Attach different solar cell modules to both sides of the central axis of the solar cell array substrate. Lead the positive and negative wires at the output ends of the solar cell modules to the back of the substrate through the wire holes to form a solar cell array. S3. Install the solar cell array on the solar cell array support vehicle, and push the solar cell array support vehicle to a position on the same plane as the standard film, with the solar cell array patch surface perpendicular to the solar simulator light; S4. Stretch the woven metal mesh on the metal frame to form an antenna, and place the antenna on the antenna support vehicle; S5. First, connect different solar cell modules to the solar simulator without antenna obstruction, fill in different solar simulator parameters, and test the electrical performance of the solar cell modules; S6. Adjust the height of the antenna by adjusting the antenna support vehicle to ensure that the antenna can block the solar cell components of the solar cell array; S7. Move the antenna support vehicle to change the distance between the antenna and the solar cell array. The moving distances are 0.5m, 1.0m, and 1.5m respectively. Use a solar simulator to irradiate the solar cell array and test the electrical performance of the solar cell module at different distances. S8. Change the angle between the antenna normal and the solar simulator light, use the solar simulator to test the electrical performance of the solar cell module at illumination angles of 0 to 70 degrees, and test once every 10 degrees.

7. The method for analyzing the effect of satellite bodies and antennas blocking solar arrays on energy balance calculation according to claim 6, wherein: The electrical performance of solar cell modules, including short-circuit current, open-circuit voltage, optimal operating point current, optimal operating point voltage, volt-ampere characteristic curve and electrical performance degradation rate Q.

8. The method for analyzing the effect of satellite bodies and antennas blocking solar arrays on energy balance calculation as claimed in claim 1, wherein: In the step 3), the various composite working conditions of the satellite body, antenna truss, antenna truss node and antenna network shielding the solar cell array are classified into two cases: physical shielding and partial shielding. Among them, the shielding of the solar cell array by the satellite body, antenna truss and antenna truss node is physical shielding, and the shielding of the solar cell array by the antenna network is partial shielding. If a string of xx or more batteries is physically shielded, the string of batteries is considered to have no output. Partial shielding will only cause the attenuation of the current, and will not cause the entire string of batteries to have no output. The current attenuation ratio is the same as the shielding battery string. The area of ​​the solar array is proportional to the solar cell area, so the output of the entire satellite solar cell array is I = A*I0 + B*I1 + D*0, where A is the number of unobstructed parallel cells, B is the number of parallel cells with less than xx cells obscured by physical objects and blocked by the antenna network, and D is the number of parallel cells with xx cells obscured by physical objects, and A+B+D = the total number of parallel solar cells in the array; I0 is the output current of all unobstructed cells; I1 is the output current of all partially obscured cells, I1 = I0*Q; and the power C = I*t, where t is the illumination time or shadow time.

9. The method for analyzing the effect of satellite bodies and antennas blocking solar arrays on energy balance calculation according to claim 8, wherein: In step 3), the energy balance calculation method is: When the solar array's power generation capacity is greater than the load's power consumption (I 帆 >I 负 ), Ccharge1+Ccharge2=Cdischarge, where Ccharge1: charging capacity when the solar array is shaded and the power generation capacity is reduced; Ccharge2: charging capacity when the solar array is not shaded; Cdischarge: discharge capacity in the shadow area; When the solar array's power generation capacity is less than the load's power consumption (I 帆 <I 负 ), Ccharge = Cdischarge1 + Cdischarge2, Ccharge: charging capacity when the solar array is not blocked; Cdischarge1: discharge capacity when the solar array is blocked and the power generated is less than the load power consumption; Cdischarge2: discharge capacity in the shadow area.

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