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A high cycle fatigue reliability analysis approach to helicopter rotor hub is proposed under working load spectrum. Automatic calculation for the approach is implemented through writing the calculating programs. In the system, the modification of geometric model of rotor hub is controlled by several parameters, and finite element method and S-N curve method are then employed to solve the fatigue life by automatically assigned parameters. A database between assigned parameters and fatigue life is obtained via Latin Hypercube Sampling (LHS) on toler- ance zone of rotor hub. Different data-fitting technologies are used and compared to determine a highest-precision approximation for this database. The parameters are assumed to he independent of each other and follow normal distributions. Fatigue reliability is then computed by the Monte Carlo (MC) method and the mean-value first order second moment (MFOSM) method. Results show that the approach has high efficiency and precision, and is suit- able for engineering application. 相似文献
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直升机振动主动控制中作动器的最佳布置研究 总被引:2,自引:0,他引:2
在振动主动控制技术中,作动器的位置对控制效果有着重要的影响,其先取是一个在可行集内确定一定数量的子集使其在给定的约束条件下性能指标达到最小的优化问题。它是一个离散的位置诉优化难以解决。遗传算法是求解这类优化问题的有效方法。文中没有 二进制码方法,而是采用了按作动器序号进行编码的方法,并提出了一种新的交叉变异方法,有效地解决了遗传算法中非二进制编码所产生的交叉操作和变异的困难。将该遗传算法求得的最优 相似文献