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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >OPTIMAL SIZING OF TRAILING EDGE FLAPS FOR HELICOPTER VIBRATION REDUCTION: A RESPONSE SURFACE APPROACH
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OPTIMAL SIZING OF TRAILING EDGE FLAPS FOR HELICOPTER VIBRATION REDUCTION: A RESPONSE SURFACE APPROACH

机译：用于直升机减振的拖尾襟翼的最佳尺寸：响应表面法

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摘要

On-blade active trailing edge flaps are considered for helicopter vibration reduction. A Pareto optimal multi-objective optimization approach is used to obtain the spanwise and chordwise dimensions of single and dual trailing- edge flaps. The objective of this study is to simultaneously achieve minimum hub vibration levels and minimize the flap actuation power requirement. Helicopter aeroelastic analysis is used in conjunction with an optimal controller to minimize hub vibration and flap power levels. It is found that nonlinear polynomial response surfaces based on L9 orthogonal array could adequately describe both the objectives. An intense sampling of the surrogate objective space is used to obtain optimal design points for the mutually conflicting objectives. A Pareto optimal design reduces vibration levels by about 70% and also reduces flap actuation power requirement by about 20%, in comparison to the initial design. The present study leads to an optimal design of trailing edge flaps which expend less power and can be further explored for self-powered control surfaces towards a self-powered smart blade design concept. The optimal designs are robust to uncertainty introduced by manufacturing.
机译：刀片式主动后缘襟翼被认为可以降低直升机的振动。使用帕累托最优多目标优化方法来获得单和双后缘襟翼的翼展方向和弦向尺寸。这项研究的目的是要同时达到最小的轮毂振动水平，并最大程度地降低襟翼驱动功率需求。直升机气动弹性分析与最佳控制器结合使用，可将轮毂振动和襟翼功率水平降至最低。发现基于L9正交阵列的非线性多项式响应面可以充分描述这两个目标。大量使用替代物目标空间来获取相互冲突的物镜的最佳设计点。与初始设计相比，帕累托最优设计可将振动水平降低约70％，并将襟翼驱动功率需求降低约20％。本研究导致后缘襟翼的优化设计，该设计消耗的功率更少，可以针对自供电的智能叶片设计概念进一步探索自供电的控制面。最佳设计对于制造带来的不确定性具有鲁棒性。

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