激光微推进器用于微小卫星的姿轨控仿真

为研究激光微推进器用于微小卫星在轨空间飞行任务的可行性,利用已建立的激光推进微小卫星仿真平台,对微小卫星在轨姿态调整、轨道维持和轨道转移等飞行任务进行了仿真和分析。仿真结果表明,星载激光微推进器可满足在轨微小卫星的高控制精度姿态调整、近地观测轨道维持以及较长时间要求的轨道转移等空间任务对推进系统的要求。

Attitude and orbit control simulations of laser micro-thruster to micro-satelite

To study laser micro-thruster feasibility for micro-satellite in space flying missions,based on simulation platform about laser propulsion of micro-satelite,the micro-satellite space flying missions of including attitude control,orbital maintenance and orbital maneuver are simulated and analyzed.The results show that laser micro-thruster can be applied as propulsion system in micro-satellite space flying missions,such as attitude control to high precision,low orbit maintain for observation and orbit transfer limited longer time.