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Smart actuation mechanisms for helicopter blades: design case for a mach-scaled model blade

机译:直升机叶片的智能致动机制:马赫比例模型叶片的设计案例

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摘要

This work is part of the European project “Clean Sky”, which aims at improving the efficiency and the global transport quality of aircraft. The research, in this project, is currently focussing on active flap systems for helicopters to adapt the blade aerodynamic properties to local aerodynamic conditions. Fuel-efficiency, reduction of vibration and noise and increase of the helicopter maximum speed are the expected benefits. To validate this technology, numerical studies and wind-tunnel testing on reduced-scale rotor blades are necessary. This thesis investigates the selection process for actuators, the methods to design and optimise actuation systems and the procedures to validate them through simulations and testing. These methods are applied to the design of an actuation system to fold and deploy a Gurney flap for a Mach-scaled rotor blade. Integrating an actuation system in helicopters is especially difficult because of a combination of challenges: tremendous loads are caused due to rotation of the blade, the space inside a rotorblade is limited and durability constraints need to be addressed. Piezoelectric actuators mechanisms provide potential so- lutions to meet these challenges. The selection process and experimental testing of piezoelectric actuators showed the superior characteristics of Physik Instrumente patch actuators for the purpose of integration inside a rotor blade. The design procedure starts with the investigation of the aerodynamics loads on the Gurney flap using numerical solutions. Then, an algorithm is developed to generate and optimise geometries for actuation mechanisms that comprise of piezoelectric actuators and a deformable structure. The resulting structure presents the characteristic shape of a “Z”. It amplifies the strains generated by the piezoelectric actuator to operate the Gurney flap. A multi-domain numerical validation ensures the behaviour of the mechanism under loads from the airflow and the blade rotation. Finally, a z-shaped structure prototype is manufactured and its deformation is experimentally verified. This work provides methods for implementing actuation in the very demanding environments encountered in the aeronautic field and will help the next generation of smart rotorcraft to take off.
机译:这项工作是欧洲“清洁天空”项目的一部分,该项目旨在提高飞机的效率和全球运输质量。该项目的研究目前集中在直升机的主动襟翼系统上,以使叶片的空气动力特性适应当地的空气动力条件。燃油效率,减少振动和噪音以及增加直升机最大速度是预期的好处。为了验证该技术,需要对缩小规模的转子叶片进行数值研究和风洞测试。本文研究了执行器的选择过程,设计和优化执行器系统的方法以及通过仿真和测试对其进行验证的过程。这些方法应用于致动系统的设计中,以折叠和展开用于马赫缩放比例的转子叶片的格尼襟翼。由于一系列挑战,将致动系统集成到直升机中尤其困难:由于叶片的旋转会导致巨大的负载,旋翼桨叶内部的空间有限,并且需要解决耐久性方面的限制。压电执行器机构提供了解决这些挑战的潜在解决方案。压电促动器的选择过程和实验测试表明,出于集成在转子叶片内部的目的,Physik Instrumente贴片促动器具有卓越的特性。设计过程开始于使用数值解研究格尼襟翼上的空气动力载荷。然后,开发了一种算法来生成和优化用于包括压电致动器和可变形结构的致动机构的几何形状。所得的结构呈现出“ Z”的特征形状。它放大了压电致动器产生的应变,以操作格尼襟翼。多域数值验证可确保机制在气流和叶片旋转负载下的行为。最后,制造出Z形结构原型,并通过实验验证了其变形。这项工作提供了在航空领域遇到的非常苛刻的环境中执行致动的方法,并将帮助下一代智能旋翼飞机起飞。

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    Paternoster, Alexandre;

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  • 年度 2013
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