大力矩飞轮动不平衡及扰动力矩控制技术

Dynamic Unbalance and Disturbing Torque Control Technology of Large Torque Flywheel

在飞轮原有螺纹连接设计的基础上,利用飞轮轮体热胀冷缩原理,增加了胶接的连接方式。研制的飞轮经受了振动试验以及高低温试验的冷热循环交替的考核,实现了对飞轮动不平衡的有效控制,卫星整星姿态角速率偏差从1.04×10^(-4)°/s降低至4.8×10^(-6)°/s;经过微振动测试,飞轮最大扰动力、扰动力矩分别降低了44%、45.76%,有效缓解卫星姿态扰动响应,降低大力矩飞轮对整星姿态角速率偏差影响,已交付用户使用。

On the basis of the original tread connection,an adhesive connection mode is applied to the flywheel based on the principle of heat expansion and cold contraction.The vibration test and high-and-low temperature test were carried out to validate the unbalance controleffectiveness of the flywheel.The results show that the deviation of attitude angular rate for the whole satellite is reduced from 1.04×10^(-4)°/s to 4.8×10^(-6)°/s.The results of the micro-vibration tests reveal that the maximum disturbing force and torque of the flywheel are reduced by 44%and 45.76%respectively,as compared to the original product.The new flywheel has been put into service.