基于COTS器件的纳级卫星反作用飞轮的设计 -- 西北工业大学学报,2017,35(6):935-940
论文:2017,Vol:35,Issue(6):935-940
引用本文:
刘光辉, 周军, 马学龙. 基于COTS器件的纳级卫星反作用飞轮的设计[J]. 西北工业大学学报
Liu Guanghui, Zhou Jun, Ma Xuelong. Design of Reaction Wheels Based on COTS Device for Nano-Satellite[J]. Northwestern polytechnical university

基于COTS器件的纳级卫星反作用飞轮的设计
刘光辉, 周军, 马学龙
西北工业大学 航天学院, 陕西 西安 710072
摘要:
针对纳级卫星的任务需求,设计了一种基于商用货架器件(commercial off the shelf components、COTS)、模块化的低成本反作用飞轮方案。采用非密闭式结构,无刷电机驱动轮缘式轮盘,两者之间振动模态分析结果表明不存在共振问题;控制器采用积分分离控制算法,基于超低功耗处理器捕获霍尔信号测速,驱动MOSFET桥换相。所研制飞轮成功通过了地面性能与环境试验测试,实测结果:重量63 g,尺寸/mm为36×36×28,最大转速9 000 r/min,最大角动量≥ 5.5 mNms,输出力矩为≥ 0.2 mNm,功耗≤ 500 mW。2016年6月25日,该飞轮随世界首颗12U立方星"翱翔之星"即西北工业大学首颗卫星,搭载"长征7号"发射入轨,在轨服役99天直到卫星坠入大气层,工作状态良好。地面测试与飞行验证结果均表明:基于COTS的飞轮设计方案有效可行,满足卫星任务需求。
关键词:    微型飞轮    反作用飞轮    COTS    纳级卫星    立方星    角速度    角动量    无刷电机    控制器    实验测试    振动分析   
Design of Reaction Wheels Based on COTS Device for Nano-Satellite
Liu Guanghui, Zhou Jun, Ma Xuelong
School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:
In this paper, a modular micro-reaction wheel based on Commercial off the Shelf Components (COTS) is designed to meet the mission requirements of nano-satellites. The system is guided by open box-shaped structure and the flywheel is drived by brushless DC motor(BLDCM), which can avoid the resonance problem according to vibration mode analysis. The controller uses the integral separation control algorithm and based on Ultra-low-power processor to capture the Hall Signal speed and drive the MOSFET bridge to change phase. The proposed flywheel has successfully passed the ground test and environmental test, the measured flywheel parameters are as follows:mass 63 g, size 36 mm×36 mm×28 mm, maximum speed 9 000 r/min, maximum angular momentum ≥ 5.5 mNms, torque ≥ 0.2 mNm, power consumption ≤ 500 mW. On June 25, 2016, the flywheel as part of the world's first 12U CubeSat "Star of AoXiang", which is the first satellite of Northwestern Polytechnic University, launched into the orbit along with "CZ-7" and served as the actuator for 99 days with excellent working conditions, until it fell into the atmosphere. Both the ground test experiment and the flight verification results show that the proposed COTS flywheel can meet the mission requirements for nano-satellite and CubeSat.
Key words:    micro-flywheel    reaction wheels    COTS    nano-satellite    CubeSat    angular velocity    angular momentum    BLDCM    controllers    experiment test    vibration analysis   
收稿日期: 2017-02-12     修回日期:
DOI:
基金项目: 国家自然科学基金(61231016)资助
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作者简介: 刘光辉(1983-),西北工业大学助理研究员、博士,主要从事星载/弹载电气系统、执行机构研究。
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