摘要
针对微小卫星、钠卫星编队飞行时的姿态和轨道控制要求,提出星载微推力器的概念,而激光微推力器在众多的微推力器中以能产生10-7N.s^10-4N.s的最小冲量受到了国内外研究学者的关注。激光微推力器系统包括五个分系统,通过采用软件芯片DSP驱动步进电机的控制策略对控制分系统进行设计,实验结果表明可以取得较高的控制准确度。
According to the attitude control and orbit control of micro-satellite and nano-satellite, the concept the planet carrying micro-thruster is advanced. In numerous micro-thrusters, the laser microthruster is especially attentioned by researchers in because of its mini impulse of 10-6N · s· 10^ -4N·s. The whole thruster system is composed by five subsystems. The control subsystem is designed by utilizing DSP to drive stepping motor and has good performance by the experiment validation.
出处
《宇航计测技术》
CSCD
2008年第2期14-16,20,共4页
Journal of Astronautic Metrology and Measurement
基金
国家973项目(51328)
