Method for estimating output power of spacecraft solar cell array in deep space at low temperature and low light intensity

Abstract

The invention discloses a method for estimating the output power of a spacecraft solar cell array in a deep space under low temperature and low light intensity, belongs to the technical field of spacecraft solar cell arrays, and relates to a ground electrical performance test, a ground irradiation test and an on-orbit power calibration mode under low temperature and low light intensity according to the on-orbit power calculation precision requirement. The method can guide the solar cell array on-orbit power estimation work in the deep space exploration field, the on-orbit power estimation precision is improved, and the solar cell array on-orbit power can be used to the maximum extent.

Description

Technical Field

[0001] The invention relates to the technical field of spacecraft solar cell arrays, and in particular to a method for estimating the output power of a spacecraft solar cell array under low temperature and low light intensity. Background Art

[0002] With the continuous development of my country's deep space exploration and the need to explore deeper interplanetary areas such as asteroids, Mars, Jupiter, and Pluto, efficient energy needs have become one of the main directions for the development of deep space probes. Solar arrays are a vital component of spacecraft and the main source of electrical energy for spacecraft. They convert solar energy in space orbit into electrical energy for spacecraft through solar cells, thereby ensuring the effective execution of various tasks throughout the life cycle of the spacecraft.

[0003] When working, the solar array is directly exposed to the harsh space environment. As the intensity of sunlight changes, the output power of the solar array also changes. How to accurately estimate the output power of the solar array under low temperature and low light intensity to provide accurate data support for the detector is a major problem in the design of solar arrays in this field. Therefore, it is very urgent to study and determine a method to accurately estimate the output power of the solar array under low temperature and low light intensity in deep space. Summary of the invention

[0004] The present invention can provide a method for estimating the output power of a spacecraft solar array under low temperature and low light intensity in deep space. The method can accurately obtain the on-orbit output power of the solar array, and the detector uses the estimated result to allocate power and maximize the utilization rate.

[0005] To achieve the above object, the present invention provides a method for estimating the output power of a spacecraft solar array under low temperature and low light intensity in deep space, comprising the following steps:

[0006] S1. Calculate the light intensity of the detector at different distances from the detector;

[0007] S2. Calculate the operating temperature of the solar array at different device-sun distances using finite element analysis;

[0008] S3. Use a 3A-class solar simulator to test the IV curve of the solar cell under standard test conditions to obtain the short-circuit current density, maximum power point current density, open circuit voltage, and maximum power point voltage of the solar cell under standard test conditions;

[0009] S4. Use a 3A-level solar simulator to test the IV curve of the solar cell under low temperature and low light intensity, and obtain the short-circuit current density, maximum power point current density, open circuit voltage, and maximum power point voltage of the solar cell under low temperature and low light intensity test conditions;

[0010] S5. Conduct ground low-temperature irradiation test to obtain the solar cell irradiation attenuation factor;

[0011] S6. Estimate the on-orbit output power of the entire solar array based on the test data and experimental results of the single solar cell.

[0012] In S1, the relationship between the solar intensity E and the distance between the device and the sun is: E = 1353 / r 2 , r is the ratio of the instrument-day distance to 1AU, 1AU = 150 million kilometers.

[0013] In S2, a model is established using finite element software Ansys Workbench to perform thermodynamic simulation of the solar array and obtain the on-orbit operating temperature of the solar array.

[0014] In S3, a 3A-class solar simulator is used to test the IV curve of the solar cell. The standard test conditions are 25°C, AM0 light intensity 1353W / m 2 , read the maximum power point current density Jm1 and maximum power point voltage Vm1 of the solar cell under standard test conditions from the IV curve.

[0015] In S4, a 3A-level solar simulator is used to test the IV curve of the solar cell. The temperature in the low-temperature and low-light-intensity test condition is taken as the analysis result of S102, and the light intensity is taken as the analysis result of S101. The maximum power point current density Jm2 and the maximum power point voltage Vm2 of the solar cell under the low-temperature and low-light-intensity test condition are read from the IV curve.

[0016] In S5, a ground low-temperature irradiation test is carried out using a linear electron accelerator device, a radiation shielding system and a test bench temperature control system. After the test, the IV curve of the solar cell under standard test conditions is tested according to the method of S103, and the maximum power point current density Jm3 and the maximum power point voltage Vm3 of the solar cell after the irradiation test are read from the IV curve; the voltage attenuation factor Kv=Vm3 / Vm1 and the current attenuation factor Ki=Jm3 / Jm1 are calculated.

[0017] In S6, the output power of the entire solar array under low temperature and low light intensity in orbit is calculated based on the series-parallel data of the solar array:

[0018] Solar array on-orbit output power P = Vm2×Jm2×S×Kv×Ki×N1×N2

[0019] Among them, S is the area of ​​a single battery, N1 is the number of series connections, and N2 is the number of parallel connections.

[0020] The advantages and positive effects of the present invention are as follows: the power estimation method of the present invention is scientific and highly accurate, and can provide accurate data to guide the on-orbit power allocation and use of the detector, thereby improving the utilization efficiency of the solar cell array. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a simulation model obtained by using an embodiment of the present invention;

[0022] Figure 2 is a temperature cloud map obtained by using an embodiment of the present invention;

[0023] Figure 3 It is a 3A-level solar simulator to test solar cells at 25°C, AM0 light intensity 1353W / m 2 Lower IV Curve

[0024] Figure 4 The solar cells were tested using a 3A solar simulator at -90°C, 216.5W / m 2 IV curve under light intensity;

[0025] Figure 5 The test was carried out at -90℃, 5×10 14 e / cm 2 Dose irradiation test, test the solar cell IV curve after the test. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solution and advantages of the present invention more clear, the present invention is further described in detail. It should be understood that the specific implementation methods described herein are only used to explain the present invention and are not used to limit the present invention.

[0027] The method for estimating the output power of a spacecraft solar cell array under low temperature and low light intensity in deep space of the present invention comprises the following steps:

[0028] S1. Calculate the light intensity of the detector at different distances from the detector;

[0029] S2. Calculate the operating temperature of the solar array at different device-sun distances using finite element analysis;

[0030] S3. Use a 3A-class solar simulator to test the IV curve of the solar cell under standard test conditions to obtain the short-circuit current density, maximum power point current density, open circuit voltage, and maximum power point voltage of the solar cell under standard test conditions;

[0031] S4. Use a 3A-level solar simulator to test the IV curve of the solar cell under low temperature and low light intensity, and obtain the short-circuit current density, maximum power point current density, open circuit voltage, and maximum power point voltage of the solar cell under low temperature and low light intensity test conditions;

[0032] S5. Conduct ground low-temperature irradiation test to obtain the solar cell irradiation attenuation factor;

[0033] S6. Estimate the on-orbit output power of the entire solar array based on the test data and experimental results of the single solar cell.

[0034] In S1, the relationship between the solar intensity E and the distance between the device and the sun is: E = 1353 / r 2 , r is the ratio of the instrument-day distance to 1AU, 1AU = 150 million kilometers.

[0035] In S2, a model is established using finite element software Ansys Workbench to perform thermodynamic simulation of the solar array and obtain the on-orbit operating temperature of the solar array.

[0036] In S3, a 3A-class solar simulator is used to test the IV curve of the solar cell. The standard test conditions are 25°C, AM0 light intensity 1353W / m 2 , read the maximum power point current density Jm1 and maximum power point voltage Vm1 of the solar cell under standard test conditions from the IV curve.

[0037] In S4, a 3A-level solar simulator is used to test the IV curve of the solar cell. The temperature in the low-temperature and low-light-intensity test condition is taken as the analysis result of S102, and the light intensity is taken as the analysis result of S101. The maximum power point current density Jm2 and the maximum power point voltage Vm2 of the solar cell under the low-temperature and low-light-intensity test condition are read from the IV curve.

[0038] In S5, a ground low-temperature irradiation test is carried out using a linear electron accelerator device, a radiation shielding system and a test bench temperature control system. After the test, the IV curve of the solar cell under standard test conditions is tested according to the method of S103, and the maximum power point current density Jm3 and the maximum power point voltage Vm3 of the solar cell after the irradiation test are read from the IV curve; the voltage attenuation factor Kv=Vm3 / Vm1 and the current attenuation factor Ki=Jm3 / Jm1 are calculated.

[0039] In S6, the output power of the entire solar array under low temperature and low light intensity in orbit is calculated based on the series-parallel data of the solar array:

[0040] Solar array on-orbit output power P = Vm2×Jm2×S×Kv×Ki×N1×N2

[0041] Among them, S is the area of ​​a single battery, N1 is the number of series connections, and N2 is the number of parallel connections.

[0042] The present invention is further described below in conjunction with examples. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0043] Example:

[0044] S1 takes the distance between the device and the sun as 2.5AU as an example, and calculates the solar intensity as 1353÷2.5÷2.5=216.5W / m 2 .

[0045] S2 uses the finite element software Ansys Workbench to build a model and perform thermodynamic simulation of the solar array. Figure 1 , 2 , the external heat flux at 2.5AU is 216.5W / m 2 , the temperature of the deep space cold back field is absolute zero. The simulation results show that the operating temperature of the solar array under this condition is -90℃.

[0046] S3 uses a 3A solar simulator to test solar cells at 25°C, AM0 light intensity 1353W / m 2 , IV curve see Figure 3 The test result is the maximum power point current density Jm1 = 18.2mA / cm 2 , the maximum power point voltage Vm1 = 2.36V.

[0047] S4 uses a 3A-class solar simulator to test solar cells at -90°C, 216.5W / m 2 Electrical performance data under light intensity. IV curve see Figure 4 The electrical performance test results are: Maximum power point current density Jm2 = 2.63mA / cm 2 , the maximum power point voltage Vm2 = 2.84V.

[0048] S5 was tested using a test device at -90°C, 5×10 14 e / cm 2 Dose irradiation test, after the test, the solar cell IV curve is shown in Figure 5 The calculated voltage attenuation factor Kv=0.94 and the current attenuation factor Ki=0.95.

[0049] The S6 solar array has 30 series connections, 100 parallel connections, and a single cell area of ​​24cm 2 . It is estimated that the solar array will be in low temperature and low light intensity (temperature -90℃, light intensity 216.5W / m 2 ) is:

[0050] P=Vm2×Jm2×S×Kv×Ki×number of series connections N1×number of parallel connections N2

[0051] =2.84×2.63×24×0.94×0.95×30×100=480W

[0052] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for estimating the output power of a spacecraft solar array under low temperature and low light intensity in deep space, characterized in that: The following steps are involved: S1. Calculate the light intensity of the detector at different distances from the detector; S2. Calculate the operating temperature of the solar array at different device-sun distances using finite element analysis; S3. Use a 3A-class solar simulator to test the IV curve of the solar cell under standard test conditions to obtain the short-circuit current density, maximum power point current density, open circuit voltage, and maximum power point voltage of the solar cell under standard test conditions; S4. Use a 3A-level solar simulator to test the IV curve of the solar cell under low temperature and low light intensity, and obtain the short-circuit current density, maximum power point current density, open circuit voltage, and maximum power point voltage of the solar cell under low temperature and low light intensity test conditions; S5. Conduct ground low-temperature irradiation test to obtain the solar cell irradiation attenuation factor; S6. Estimate the on-orbit output power of the entire solar array based on the test data and experimental results of the single solar cell.

2. The method for estimating the output power of a spacecraft solar array under low temperature and low light intensity in deep space according to claim 1, characterized in that: In S1, the relationship between the solar intensity E and the distance between the device and the sun is: E = 1353 / r 2 , r is the ratio of the instrument-day distance to 1AU, 1AU = 150 million kilometers.

3. The method for estimating the output power of a spacecraft solar array under low temperature and low light intensity in deep space according to claim 1, characterized in that: In S2, a model is established using finite element software Ansys Workbench to perform thermodynamic simulation of the solar array and obtain the on-orbit operating temperature of the solar array.

4. The method for estimating the output power of a spacecraft solar array under low temperature and low light intensity in deep space according to claim 1, characterized in that: In S3, a 3A-class solar simulator is used to test the IV curve of the solar cell. The standard test conditions are 25°C, AM0 light intensity 1353W / m 2 , read the maximum power point current density Jm1 and maximum power point voltage Vm1 of the solar cell under standard test conditions from the IV curve.

5. The method for estimating the output power of a spacecraft solar array under low temperature and low light intensity in deep space according to claim 1, characterized in that: In S4, a 3A-level solar simulator is used to test the IV curve of the solar cell. The temperature in the low-temperature and low-light-intensity test condition is taken as the analysis result of S102, and the light intensity is taken as the analysis result of S101. The maximum power point current density Jm2 and the maximum power point voltage Vm2 of the solar cell under the low-temperature and low-light-intensity test condition are read from the IV curve.

6. The method for estimating the output power of a spacecraft solar array under low temperature and low light intensity in deep space according to claim 4 or 5, characterized in that: In S5, a ground low-temperature irradiation test is carried out using a linear electron accelerator device, a radiation shielding system and a test bench temperature control system. After the test, the IV curve of the solar cell under standard test conditions is tested according to the method of S103, and the maximum power point current density Jm3 and the maximum power point voltage Vm3 of the solar cell after the irradiation test are read from the IV curve; the voltage attenuation factor Kv=Vm3 / Vm1 and the current attenuation factor Ki=Jm3 / Jm1 are calculated.

7. The method for estimating the output power of a spacecraft solar array in deep space at low temperature and low light intensity according to claim 6, characterized in that: In S6, the output power of the entire solar array under low temperature and low light intensity in orbit is calculated based on the series-parallel data of the solar array: Solar array on-orbit output power P = Vm2×Jm2×S×Kv×Ki×N1×N2 Among them, S is the area of ​​a single battery, N1 is the number of series connections, and N2 is the number of parallel connections.

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