北京航空航天大学学报 ›› 2011, Vol. 37 ›› Issue (2): 127-131.

• 论文 •    下一篇

采用SMA驱动的小型空间磁悬浮飞轮锁紧机构

闫晓军1, 张小勇1, 聂景旭1, 张绍卫2   

  1. 1. 北京航空航天大学 能源与动力工程学院, 北京 100191;
    2. 北京控制工程研究所, 北京 100094
  • 收稿日期:2009-12-17 出版日期:2011-02-28 发布日期:2011-03-05
  • 作者简介:闫晓军(1973-),男,教授,yanxiaojun@buaa.edu.cn.
  • 基金资助:

    全国优秀博士学位论文作者专项资助项目(200351); 新世纪优秀人才支持计划(NCET-06-0178)

Prototype SMA actuated locking device for small space magnetic bearing flywheels

Yan Xiaojun1, Zhang Xiaoyong1, Nie Jingxu1, Zhang Shaowei2   

  1. 1. School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
    2. Beijing Institute of Control Engineering, Beijing 100190, China
  • Received:2009-12-17 Online:2011-02-28 Published:2011-03-05

摘要: 磁悬浮飞轮锁紧机构在卫星发射时锁紧飞轮,减小其振动和冲击载荷;在发射后解锁,保证飞轮正常工作.目前已有的以火工品或步进电机驱动的锁紧机构具有冲击大、体积较大、不可重复使用等缺点.提出了一种采用形状记忆合金(SMA, Shape Memory Alloy)驱动的空间磁悬浮飞轮锁紧机构的设计方案,并在Liang本构模型的基础上发展了机构驱动单元的设计方法.之后,完成了锁紧机构的样机研制和调试,并开展了地面的性能测试、振动试验和高温环境试验.研究结果表明:SMA锁紧机构安装体积小,在星载28 V电压下能在6 s内完全锁紧,在1 s内完全解锁,并能够通过振动和环境实验.SMA驱动的磁悬浮飞轮锁紧机构具有锁紧力大、同步性好、可重复使用、低冲击、无污染等优势,有很大的工程应用潜力.

Abstract: Based on magnetic levitation principle, the magnetic bearing flywheel is a new type of inertial actuator used in satellite attitude control. A locking device was used to eliminate the gap between the rotor and stator of magnetic bearing flywheel so as to protect it from shock and vibration damage during launch phase. The present pyrotechnical or motor actuated locking devices have the disadvantages of high shock, large size and un-resetable. A prototype shape memory alloys (SMA)actuated locking device for small space magnetic bearing flywheel was developed in this investigation. A method and procedures to design the actuator element based on Liang-s constitutive model was presented. Then the SMA locking device was assembled and the function, environment and vibration tests were carried out. Test results show that the device can complete lock function within 6 s and release function within 1 s under satellite power supply of 28 V. It can also undergo the environment and vibration tests which simulate the launch phase. It is concluded that the new SMA locking device owning advantages of great locking force, small size, low shock and easy to reset has a potential use in space engineering.

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