仲健林, 任杰, 马大为, 王玺. 基于精确数值建模方法的自适应底座优化设计研究[J]. 工程力学, 2015, 32(9): 229-235,249. DOI: 10.6052/j.issn.1000-4750.2014.05.0371
引用本文: 仲健林, 任杰, 马大为, 王玺. 基于精确数值建模方法的自适应底座优化设计研究[J]. 工程力学, 2015, 32(9): 229-235,249. DOI: 10.6052/j.issn.1000-4750.2014.05.0371
ZHONG Jian-lin, REN Jie, MA Da-wei, WANG Xi. THE OPTIMIZATION DESIGN FOR THE ADAPTIVE BASE BASED ON ACCURATE NUMERICAL MODELLING METHOD[J]. Engineering Mechanics, 2015, 32(9): 229-235,249. DOI: 10.6052/j.issn.1000-4750.2014.05.0371
Citation: ZHONG Jian-lin, REN Jie, MA Da-wei, WANG Xi. THE OPTIMIZATION DESIGN FOR THE ADAPTIVE BASE BASED ON ACCURATE NUMERICAL MODELLING METHOD[J]. Engineering Mechanics, 2015, 32(9): 229-235,249. DOI: 10.6052/j.issn.1000-4750.2014.05.0371

基于精确数值建模方法的自适应底座优化设计研究

THE OPTIMIZATION DESIGN FOR THE ADAPTIVE BASE BASED ON ACCURATE NUMERICAL MODELLING METHOD

  • 摘要: 建立自适应底座的精确数值模型,对底座进行优化设计研究。推导了帘线拉伸模量修正公式,给出了橡胶材料Mooney-Rivilin模型相关参数计算方法;建立了底座精确数值模型,得到附加载荷数值解并与试验对比验证;推导了附加载荷的积分表达式,获得了影响附加载荷的4个主要参数;以4个主要参数为设计变量,定义附加载荷匹配弹重为优化目标,基于试验设计方法(DOE)和神经网络算法(RBF),建立了底座数学近似模型,结合多岛遗传算法(MIGA)获得了底座的优化设计方案。结果表明:优化后底座的附加载荷峰值与弹重差值减小至原差值的9.1%,导弹俯仰、偏航方向角位移分别下降了8.2%、15.8%。

     

    Abstract: The accurate numerical model of the adaptive base is established in this paper, and the optimization design for the adaptive base is conducted. The tension modulus amendment formula for cord is firstly derived, and then the calculation method for the parameters of Mooney-Rivilin model used for rubber material is provided. The accurate numerical model of the adaptive base is built, and the numerical results of the additional load are compared with the testing results. Finally, the integral formula of the additional load is deduced, and the four main parameters affecting the additional load are obtained. Treating the four main parameters as design variables, and defining the additional load matching the mass of the missile as the optimizing objective, the approximate mathematical model of the adaptive base is developed on the basis of the DOE method and the RBF method. Using the MIGA method, the optimization design scheme is obtained. The results show that the optimal difference value between the gravity of the missile and the peak value of the additional load decreases to 9.1% of the original difference value, and the angular displacement of the missile in the pitch and yaw decreases by 8.2% and 15.8% respectively.

     

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