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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%。
In order to improve the accuracy and life expectancy of the satellite attitude control system and to determine the reasonable payload and performance index of the satellite, the overall optimization design scheme of the bias momentum wheel is proposed. A simplified geometrical model of wheel and shell seal cover and base is established by 3D solid modeling software Pro / E. Based on the characteristics and design requirements of momentum wheel and shell, a mathematical model of the overall optimization design of momentum wheel is established. The fmincon and fminimax functions in Matlab software respectively optimize and design the offset momentum wheel. According to the result of optimization, the size of the structure is properly adjusted. The radius of the take-off wheel is 81 mm. The height and width of the rims are 24.6 mm and 21.6 mm respectively. The circle is 20,5 mm and the shell thickness is 1 mm. After the finite element analysis verified the static and dynamic performance of the wheel body meet the index requirements, the volume reduced by 15%.