基于轴向磁通电动机的反作用飞轮系统设计

Design of the Reaction Flywheel System Based on Axial-flux Motor

针对分布式小卫星系统对姿控单元小型化的要求,提出基于轴向磁通电动机的反作用飞轮系统设计方案。运用有限元法分析轴向磁通电动机的三维气隙磁场分布,建立基于印制电路板(Printed circuit board,PCB)绕组的反电动势参数计算模型。采用多学科优化设计方法,以反作用飞轮系统质量最小为目标,在同时满足飞轮系统结构强度、刚度和电动机气隙磁通密度要求的前提下,采用序列二次规划算法(Sequential quadratic programming,NLPQL)对飞轮转子主要结构尺寸进行优化,使反作用飞轮系统质量由0.899 kg减小到0.741 kg,减小了17.6%,结合优化结果制作出飞轮样机,并对样机进行空载试验。试验结果表明,样机反电动势实测值与理论计算值间的最大误差为9.7%,验证了设计方法的正确性和实用性,可有效地指导反作用飞轮小型化设计。

To satisfy the requirements of miniaturization for attitude control unit in distributed small satellite system（DSSS）,a reaction flywheel system based on axial-flux motor is presented.The three-dimensional distribution of air-gap magnetic field is analyzed by using the finite element method（FEM）.A computational model for back-EMF of the motor is established based on the printed circuit board（PCB） winding.The multidisciplinary design optimization method is applied to optimize the main structure size of the flywheel rotor to minimize the weight of the flywheel system while meeting the requirements of strength,stiffness and the air-gap flux density under the premise of using sequential quadratic programming（NLPQL）.The total mass of the flywheel rotor is decreased from 0.899 kg to 0.741 kg（namely reduced by 17.6%） after optimization.A flywheel prototype is designed based on the optimal results and the no-load performance is tested.The results show that the maximum error between the calculated and measured values of back-EMF is 9.7%,which verifies the correctness of the design method and provides an important reference in the miniaturization design of reaction flywheel system.