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Survey of Recent Developments in Rotorcraft Design Optimization

机译:旋翼飞机设计优化的最新发展概况

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摘要

From the literature reviewed in this paper, the following conclusions can be drawn about the nature of the helicopter optimization problem. These problems involve 1) computationally expensive and unwieldy aeroelastic or finite element analysis, 2) presence of local minima, and 3) presence of numerical noise and/or convergence difficulties. The increasing power of computers decreases the problem of expensive aeroelastic and finite element analysis. However, the search for better modeling is resulting in the use of CFD for aerodynamic predictions and full finite element method formulations for the composite rotor blade structural analysis. The use of computer power to advance modeling and analysis of systems always appears to precede the use in optimization. Therefore, it is unlikely that the rotor aeroelastic problem will be computationally cheap for quite some time. Whenever gradient-based methods are used for optimization, a large portion of the computer time is taken up by gradient calculation. Finite difference-based derivatives are prohibitively expensive. In addition, finite difference derivatives need a good estimation of step size. In some case, forward difference derivatives may not be sufficiently accurate leading to the requirement of central difference derivatives and the resultant increase in computer time.83 Whereas the use of analytical or semi-analytical sensitivity derivatives can alleviate the computer time requirements to a great extent, they need major and time-consuming changes to be made to computer programs. Whereas this may be possible in an academic setting, it is almost impossible in an industrial setting, where proprietary computer codes are guarded carefully. Furthermore, any changes to the computer code or inclusion of new design variables or objective functions and constraints require a rederivation of the analytical derivatives and subsequent recoding into the computer program. The analysis and sensitivity calculations will deviate with the passage of time unless proper code management is done. Finally, the time saved in terms of computer expense by analytical derivatives should be weighed with the cost of labor involved on the part of skilled domain experts.
机译:从本文回顾的文献中,可以得出有关直升机优化问题性质的以下结论。这些问题涉及1)计算上昂贵且笨拙的气动弹性或有限元分析,2)存在局部最小值,以及3)存在数字噪声和/或收敛困难。计算机功能的增强减少了昂贵的气动弹性和有限元分析的问题。然而,寻求更好的建模的结果是将CFD用于空气动力学预测,并将全有限元方法公式化用于复合材料转子叶片结构分析。在优化之前,总是使用计算机功能来推进系统的建模和分析。因此,转子空气弹性问题在相当长的一段时间内在计算上不太可能便宜。每当使用基于梯度的方法进行优化时,计算机的大部分时间都会被梯度计算所占用。基于差异的有限衍生工具非常昂贵。另外,有限差分导数需要步长的良好估计。在某些情况下,前向差分导数可能不够精确,从而导致需要中心差分导数并导致计算机时间增加。83而使用分析或半分析灵敏度导数可以在很大程度上减轻计算机时间需求,他们需要对计算机程序进行重大而费时的更改。尽管这在学术环境中是可行的,但在工业环境中几乎是不可能的,因为在工业环境中必须谨慎保护专有的计算机代码。此外,对计算机代码的任何更改或包含新的设计变量或目标函数和约束的操作都需要重新分配分析导数,然后将其重新编码到计算机程序中。除非进行适当的代码管理,否则分析和灵敏度计算将随着时间的流逝而发生偏离。最后,应将分析派生在计算机支出方面节省的时间与熟练的领域专家所涉及的劳动成本进行权衡。

著录项

  • 来源
    《Journal of Aircraft》 |2004年第3期|p.493-510|共18页
  • 作者

    Ranjan Ganguli;

  • 作者单位

    Indian Institute of Science, Bangalore 560 012, India;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 航空;
  • 关键词

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