激光微推进器用于微小卫星的姿轨控仿真

推进技术 ›› 2007, Vol. 28 ›› Issue (5): 467-470.

激光微推进器用于微小卫星的姿轨控仿真

郑航,胡晓军,郭海,唐志平

中国科技大学力学和机械工程系安徽合肥230026;中国科技大学力学和机械工程系安徽合肥230027;中国科技大学力学和机械工程系安徽合肥230028;中国科技大学力学和机械工程系安徽合肥230029

发布日期:2021-08-15
基金资助:
国家“九七三”项目(61328)

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

Dept.of Modern Mechanics,China Univ.of Science and Technology,Hefei 230026,China;Dept.of Modern Mechanics,China Univ.of Science and Technology,Hefei 230027,China;Dept.of Modern Mechanics,China Univ.of Science and Technology,Hefei 230028,China;Dept.of Modern Mechanics,China Univ.of Science and Technology,Hefei 230029,China

Published:2021-08-15

摘要/Abstract

摘要： 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。

关键词: 激光推进;微小卫星;卫星姿态控制;控制仿真

Abstract: 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.

Key words: Laser propulsion;Micro-satelite;Simulation platform;Satellite attitude control;Control simulation

郑航,胡晓军,郭海,唐志平. 激光微推进器用于微小卫星的姿轨控仿真[J]. 推进技术, 2007, 28(5): 467-470.