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首页> 外文会议>AHS International Annual Forum vol.1; 20050601-03; Grapevine,TX(US) >DESIGN OPTIMIZATION OF A CONTROLLABLE CAMBER ROTOR AIRFOIL
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DESIGN OPTIMIZATION OF A CONTROLLABLE CAMBER ROTOR AIRFOIL

机译：可控外倾旋翼机翼的设计优化

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摘要

The present study focuses on the design of an actively conformable rotor airfoil. The design consists of several compliant mechanisms of predetermined topology that are placed serially within the airfoil along the chord, aft of the Leading Edge spar, to effectively change the camber. This design requires only a small number of actuators. The study carries out shape optimization of the passive members of the compliant mechanisms along the chord. The designs aim to maximize the vertical airfoil tip deflection under actuation loads, and simultaneously limit the airfoil deflection under aerodynamic loads. This is achieved by two approaches, the first optimizing a single-objective function of actuation tip deflection, and the second optimizing a multi-criteria objective function that contains a ratio of actuation tip deflection and strain energy, representing stiffness under aerodynamic loads. The results of the study indicate that the optimal compliant mechanism shape varies depending on the objective function used as well as other geometric factors. Using the tip deflection objective function the compliant members are relatively uniform in thickness, with flexures developing at the ends of the individual compliant links. Using the multi-criteria objective function the optimized geometry is more complex. The optimal geometry and performance of the compliant mechanism are examined for variations in compliant mechanism unit aspect ratio, maximum allowable passive material, and actuator thickness. The best optimized structures can achieve a trailing edge tip deflection of ±6-8 mm providing an increase in lift of 17-22%.
机译：本研究的重点是主动适形转子翼型的设计。该设计由几个预定拓扑结构的顺应性机构组成，这些机构顺着前缘翼梁的弦向后顺次放置在机翼内，以有效地改变外倾角。该设计仅需要少量的致动器。该研究对沿弦顺应机构的被动构件进行了形状优化。这些设计旨在最大程度地提高致动载荷下的垂直翼型偏转，并同时限制气动载荷下的翼型偏转。这可以通过两种方法来实现，第一种方法是优化致动尖端挠度的单目标函数，第二种是优化多准则目标函数，该目标函数包含致动尖端挠度与应变能之比，代表气动负载下的刚度。研究结果表明，最佳的柔顺机构形状根据所使用的目标函数以及其他几何因素而变化。使用尖端偏转目标功能，顺应构件的厚度相对均匀，在各个顺应链节的端部产生挠曲。使用多准则目标函数，优化后的几何更加复杂。检查柔性机构的最佳几何形状和性能，以检查柔性机构单元纵横比，最大允许被动材料和致动器厚度的变化。最佳的最佳结构可以实现±6-8 mm的后缘尖端挠度，从而使升力提高17-22％。

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