小卫星用反作用飞轮系统设计

Design of reaction flywheel systems for small satellites

考虑小卫星用反作用飞轮系统小型化的要求,提出了飞轮电机体积最小时的电枢尺寸确定方法,并设计了一种定子无铁芯式反作用飞轮系统。为防止磁路饱和,将多学科优化设计方法应用于飞轮转子结构和电机磁场联合设计中,并采用外罚函数法及序列二次规划算法(SQP)组合优化策略对飞轮系统进行多目标优化设计。选取飞轮转子质量最小和电机气隙磁通密度最大为优化目标,以最大等效应力、一阶共振频率、极转动惯量、磁饱和等作为约束条件,将iSIGHT软件作为优化平台,集成有限元软件ANSYS实现了优化过程,最后依据优化结果制造出飞轮样机。优化结果表明,优化后飞轮转子质量由0.73kg减小到0.67kg,减小了8.22%,气隙磁通密度由0.376T增大到0.401T,增大了6.65%。设计的优化方法提高了飞轮设计的合理性,推动了飞轮系统的小型化研究。

According to the requirement of reaction flywheels in small satellites for small sizes,the de sign method for an armature size was proposed when the electrical motor was at a minimal volume,and a stator coreless reaction flywheel system was designed based on the method.To avoid the magnetic saturation,the multidisciplinary design optimization method was applied to the design of flywheel rotor and magnetic field of the motor.A optimization strategy combined with Exterior Penalty （EP） function and Sequential Quadratic Programming（SQP） was proposed to optimize the system as well.With optimization,the minimum mass and maximum air gap magnetic flux density of the rotor were chosen as the objects,respectively,and the maximum equivalent stress,resonance frequency,the polar moment of inertia and the magnetic saturation were taken as constrains.Then,the software iSIGHT with finite element analysis （ANSYS） were integrated to achieve the optimization.Finally,a flywheel prototype was designed based on the optimal results.The results indicate that the total mass of the flywheel rotor has been decreased from 0.73 kg to 0.67 kg （reduced by 8.22%） and the flux density has been increased from 0.376 T to 0.401 T （increased by 6.65%）.The optimal design method can improve the rationality of flywheel design,and will promote the progress of the miniaturization investigation of flywheel systems.