卫星偏置动量轮3D模型的优化设计与有限元分析

为提高卫星姿态控制系统的精度、寿命以及确定卫星合理的有效载荷和性能指标,提出了偏置动量轮整体优化设计方案.通过三维实体建模软件Pro/E建立轮体、壳体的密封罩和底座的简化几何模型,依据动量轮轮体和壳体的特性与设计要求,建立动量轮整体优化设计的数学模型;利用Matlab软件中fmincon和fminimax函数分别进行偏置动量轮整体优化设计计算.结合优化结果对结构尺寸进行适当调整,取动量轮半径为81 mm,轮缘高度和宽度分别为24、6 mm,轮辐高度和宽度分别为21、6 mm,轮体内环倒圆和外环倒圆为20、5 mm,壳体厚度为1 mm.经有限元分析验证后轮体的静态和动态性能均达到了指标要求,体积减小了15％.

Optimization design and finite element analysis on 3D model of satellite bias momentum wheel

This paper is motivated by the need for improving the precision and life of satellite attitude control system and determining the reasonable satellite payload and its performance indicators and proposes the design scheme for overall optimization of bias momentum flywheel system.The scheme consists of obtaining the wheel body,the seal cover of shell,and simplified geometric model of base design using 3D entities modeling software Pro/E,and developing a mathematical model for integral optimization design,based on the characters and design specifications of momentum wheel body and shell,and performing overall optimization design calculations to bias momentum wheels using the fmincon and fminimax functions in Matlab software.The reasonable adjustment of structure size,combined with the optimization results,justifies momentum wheel radius of 81 mm,height and width of the rim of 24 mm and 6 mm,height and width of the spokes of 21 mm and 6 mm,inner and outer radius of wheel body of 20 mm and 5 mm,shell thickness of 1 mm.The finite element analysis verifies that the wheel body,with the static and dynamic performance up to the indicator,has a reduction in volume of 15％.