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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.
Maglev flywheel locking mechanism locks the flywheel when the satellite launches to reduce the vibration and impact load; unlock after launch to ensure the normal operation of the flywheel. Presently, the locking mechanism driven by the explosive or the stepper motor has the impact Large, bulky and non-reusable, etc. A design scheme of the space magnetic flywheel locking mechanism driven by Shape Memory Alloy (SMA) is proposed. Based on the Liang constitutive model, After that, the prototype of the locking mechanism was developed and debugged, and the ground performance test, vibration test and high temperature environment test were carried out.The results show that the SMA locking mechanism has a small installation volume, Fully locked within 6 s at 28 V, fully unlocked within 1 s, and able to pass vibration and environmental tests.SMA-driven magnetic levitation flywheel locking mechanism with large locking force, synchronization, reusable, Low impact, no pollution and other advantages, there is great potential for engineering applications.