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Satellite solar cell on-orbit performance degradation prediction method

A technology of solar cells and prediction methods, applied in the field of spacecraft, can solve problems such as restricting life and reliability, satellite failure, etc., and achieve the effects of improving application capabilities, improving long-term, improving maturity and inheritance

Inactive Publication Date: 2015-11-11
SHANGHAI SATELLITE ENG INST
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  • Description
  • Claims
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Problems solved by technology

[0006] In view of the deficiencies in the prior art, the purpose of the present invention is to provide a method for predicting the on-orbit performance degradation of satellite solar cells to solve the problems of life and reliability of solar cells in space environments that restrict the life and reliability of satellite platforms. Avoiding satellite failure due to solar cell efficiency degradation

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  • Satellite solar cell on-orbit performance degradation prediction method
  • Satellite solar cell on-orbit performance degradation prediction method
  • Satellite solar cell on-orbit performance degradation prediction method

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Embodiment

[0037] This embodiment provides a method for predicting on-orbit performance degradation of satellite solar cells, including the following steps:

[0038] Step 1: According to the structure and layout of the solar cell, select the characteristic parameters representing the performance attenuation of the solar cell, that is, the original code of the current value telemetry data, and extract the data for one year;

[0039] Step 2: Data processing: convert the original code of the telemetry data into physical quantities, analyze and organize the data, and supplement the missing data with the method of mean value interpolation to form the current value telemetry data;

[0040] Step 3: Data analysis: Introduce the incident angle of the sun. When the sunlight is not perpendicular to the plane where the solar cell is located, its circuit will also change. The relationship is as follows:

[0041] I max =I / cosθ

[0042] In the formula, I max is the current under vertical illuminatio...

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Abstract

The invention discloses a satellite solar cell on-orbit performance degradation prediction method. The method comprises the steps of: analyzing life-related characteristic parameters of a solar cell; collecting, processing and refining on-orbit data of the characteristic parameters of the solar cell; establishing a theory model of on-orbit attenuation trend; and predicting an on-orbit life limit value of the solar cell. According to the prediction method, the life and reliability problems of the solar cell, restricting the life and reliability of a satellite platform, in a space environment are solved, thereby avoiding satellite failure due to efficiency reduction of the solar cell, favorably improving long-term and reliable operation capability of the satellite platform, favorably improving the maturity and inheritance of the satellite platform, favorably improving the application capability of the satellite platform and favorably expanding the application range of the satellite platform.

Description

technical field [0001] The invention relates to the technical field of spacecraft, in particular to a method for predicting on-orbit performance degradation of solar cells used in satellites. Background technique [0002] With the rapid development of aerospace technology, human exploration of space is becoming more and more frequent and deepening, which makes spacecraft develop in the direction of multi-function, multi-task and multi-equipment, requiring more and more complexity and diversification. Realization of long life, high reliability, and high precision is required. This needs to continuously increase the power and quantity of signal transponders to meet the demand, so the power demand for the power supply system also increases accordingly. The solar array power supply system is currently the main power supply system used by domestic spacecraft. Its performance determines the working status of the entire spacecraft. Therefore, the solar array needs to have higher p...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCY02E60/00
Inventor 张雷廖明曹敏韦锡峰吴东岳赟
Owner SHANGHAI SATELLITE ENG INST
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