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| Research of Micron-sized Space Debris Impacting on Solar Cells |
| Received:January 20, 2015 Revised:June 15, 2015 |
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| DOI：10.7643/issn.1672-9242.2015.03.009 |
| KeyWord:micron space debris laser-driven flyer system solar cell volt-ampere characteristics ORDEM2000 |
| Author | Institution |
| MA Zi-liang |
Beijing Institute of Spacecraft Environment Engineering， Beijing 10094， China |
| YANG Ji-yun |
Beijing Institute of Spacecraft Environment Engineering， Beijing 10094， China |
| LI Yu |
Beijing Institute of Spacecraft Environment Engineering， Beijing 10094， China |
| CAO Yan |
Beijing Institute of Spacecraft Environment Engineering， Beijing 10094， China |
| XU Kun-bo |
Beijing Institute of Spacecraft Environment Engineering， Beijing 10094， China |
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| Abstract: |
| Objective To evaluate the performance degradation degree of solar cell arrays of spacecrafts after impacted by micron-sized space debris. Methods Single impact and cumulate impact tests were carried out for the silicon solar cells using the laser-driven flyer system. Their characteristics, including mechanical damage characteristicsand volt-ampere characteristics were measured and compared after tests. Cumulative flux and speed of Tiangong 1st orbital debris were calculated by ORDEM 2000. Taking the test results into account, the attenuation rate of maximum output power caused by micron-sized space debris were obtained for the solar cell arrays of spacecrafts. Results The results showed that the attenuation rate of maximum output power could be presented by quadratic function of the diameter of splash region, which approached the surface contaminated rate of solar cells. The attenuation rate of maximum power of the solar cell arrays for spacecrafts in Tiangong 1st orbit would be 0.45% in next 5 years. Conclusion The attenuation rate of maximum output power of the solar cell arrays for spacecrafts caused by micron-sized space debris could be estimated using this research result, which provides technical support for system design of spacecrafts. |
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