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首页> 外文期刊>The Aeronautical Journal >Minimising induced drag with weight distribution, lift distribution, wingspan, and wing-structure weight
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Minimising induced drag with weight distribution, lift distribution, wingspan, and wing-structure weight

机译：用重量分布，提升分布，翅膀和翼状结构重量最小化诱导拖曳

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Because the wing-structure weight required to support the critical wing section bending moments is a function of wingspan, net weight, weight distribution, and lift distribution, there exists an optimum wingspan and wing-structure weight for any fixed net weight, weight distribution, and lift distribution, which minimises the induced drag in steady level flight. Analytic solutions for the optimum wingspan and wing-structure weight are presented for rectangular wings with four different sets of design constraints. These design constraints are fixed lift distribution and net weight combined with 1) fixed maximum stress and wing loading, 2) fixed maximum deflection and wing loading, 3) fixed maximum stress and stall speed, and 4) fixed maximum deflection and stall speed. For each of these analytic solutions, the optimum wing-structure weight is found to depend only on the net weight, independent of the arbitrary fixed lift distribution. Analytic solutions for optimum weight and lift distributions are also presented for the same four sets of design constraints. Depending on the design constraints, the optimum lift distribution can differ significantly from the elliptic lift distribution. Solutions for two example wing designs are presented, which demonstrate how the induced drag varies with lift distribution, wingspan, and wing-structure weight in the design space near the optimum solution. Although the analytic solutions presented here are restricted to rectangular wings, these solutions provide excellent test cases for verifying numerical algorithms used for more general multidisciplinary analysis and optimisation.
机译：由于支撑关键翼段弯曲时刻所需的机翼结构重量是翼板，净重，重量分布和升力分布的函数，所以存在最佳的翼展和机翼结构重量，用于任何固定的净重，重量分布，和升力分布，最大限度地减少了稳态飞行中的诱导拖动。为具有四组不同设计约束的矩形翼而呈现最佳翼展和翼形结构重量的分析解决方案。这些设计约束是固定提升分布和净重的净重与1）固定的最大应力和机翼装载，2）固定最大偏转和机翼装载，3）固定最大应力和失速速度，4）固定最大偏转和失速速度。对于这些分析解决方案中的每一个，发现最佳的翼状结构重量仅取决于净重，与任意固定提升分布无关。对于相同的四组设计约束，还呈现了最佳重量和升力分布的分析解决方案。根据设计约束，最佳提升分布可能与椭圆升力分布有显着差异。提出了两个示例翼设计的解决方案，这证明了在最佳解决方案附近的设计空间中的升力分布，翼板和翼状结构重量如何随着升力分布，翅膀和机翼结构的重量而变化。虽然这里呈现的分析解决方案仅限于矩形翼，但这些解决方案提供了优异的测试用例，用于验证用于更一般的多学科分析和优化的数值算法。

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