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《Spacecraft Environment Engineering》 2006-04
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Launching of Hypervelocity Micro Space Debris by Plasma Accelerator

HAN Jianwei, ZHANG Zhenlong, HUANG Jian’guo, LI Xiaoyin, CHEN Zhaofeng, QUAN Ronghui, LI Hongwei ( Center for Space Science and Applied Research, Beijing 100080, China )  
A brief introduction on ground-based simulation for micro space debris impact is presented. Using plasma accelerator to launch simulated micro space debris is described, together with some preliminary testing results, as well as the further application of the facility. Using 6% and 35% of the maximum energy, the facility has successfully launched 100 and 200 microns glass beads to the velocities of 5.5 km/s and 9.3 km/s, respectively. Single impact of micro space debris with diameter of 10~1000 microns on spacecraft materials is simulated using the facility, and the accumulated damage of spacecraft in flight by a mass of micro space debris can be tested. In addition, a simulation for design and calibration of space-based detector for micro space debris can be provided.
【CateGory Index】: V439
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