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汪光文 《民用飞机设计与研究》2011,(1):13-19,28
风扇转子气动优化设计是结合CFD、遗传算法和风扇特性的跨学科自动设计方法,这种设计较少依赖经验,能实现多目标和多设计参数组合的优化设计。先研究了四个关键技术:具有耗时少、计算较准确的叶片通道流场数值计算方法;具有良好寻优能力的数值最优化方法;三维叶片造型的参数化方法;以气动性能为目标的多目标函数构建方法。再将上述四个关键技术模块整合,构建简易的气动优化设计软件。三维叶片优化算例证明了该软件的设计能力,其设计结果较满意、设计效率较高、设计周期短。 相似文献
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为保证月球探测器进入姿态调整段时具有充分的高度与速度余量,本文提出一种基于控制变量参数化的月球探测器动力下降段最优轨迹求解方法。在三维探测器软着陆动力学模型基础上,将月球探测器软着陆制导律设计等效为燃料最优约束下的探测器俯仰角控制问题,利用控制变量参数化(Control Variables Parameterization, CVP)方法将该控制问题中的控制变量与约束条件转化为非线性规划问题求解,并引入时间尺度变换,将着陆时间序列加入待规划参数,进而求得满足精度的最优数值解。蒙特卡罗仿真实验表明,与传统的显式制导律相比,本文提出的参数化制导方法在动力下降段燃料更省,动力下降段的起始高度在±20%范围内波动时,仍能以高精度速度和高度指标完成末制导。 相似文献
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《中国航空学报》2023,36(8):74-90
Shape parameterization has a crucial influence on the optimal solution of aerodynamic optimization. This paper proposes a novel parameterization method for compressor blade sections based on the three-level deformation of the ellipse, which simultaneously satisfies the requirements of flexibility, smoothness, intuitiveness, and compactness. In proposed method, the first-level deformation directly controls nine key geometric parameters to construct the blade section profile, and then the second- and third-level deformations are performed respectively to coarsely and finely modify the profile while keeping the key geometric parameters unchanged. These three levels of deformation effectively decompose the design space without destroying the ellipse’s infinite differentiability, allowing designers to work only with intuitive shape-related parameters to design blade sections with inherently high-order continuity. To verify the effectiveness, six existing blade sections are first fitted and then one of them is selected for a three-level optimization. The results show that the geometry and aerodynamic performance of the fitted and the original blade sections are in good agreement, and the loss coefficient of the optimized blade section is reduced by a total of 36.41%, with 27.34%, 8.45%, and 0.62% reductions for the first to the third level, respectively. Therefore, the proposed parameterization method facilitates the design of lower-loss and higher-load compressor blade sections. 相似文献
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周保民 《中国空间科学技术》1990,10(4):18
文章介绍了求解退化线性代数方程组的小参数法,推导出简便的求解公式,给出了小参数的选择方法,并且证明了方法的稳定性和高精度,最后给出了一些数值结果. 相似文献