摘要
文章介绍了国内外微小空间碎片超高速撞击地面模拟实验研究的现状,描述了国内等离子体微小空间碎片加速器的研制进展和初步实验结果,分析了该加速器在空间碎片防护研究工作中的应用。在初步调试阶段,在系统设计满负荷储能6%和35%的条件下,分别将100μm和200μm的玻璃微粒加速至5.5km/s和9.3km/s。利用该加速器可以模拟研究10～1000μm的微小空间碎片对卫星功能材料的撞击损伤特性,可以加速模拟研究卫星关键部件或分系统在大量微小空间碎片撞击下的失效机理和失效模式,为卫星防护微小空间碎片的设计提供技术支持。该加速器还能为国内发展星载空间微小碎片探测仪器的设计和标定提供模拟实验条件。
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.
出处
《航天器环境工程》
2006年第4期205-209,共5页
Spacecraft Environment Engineering
