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首页> 外文会议>International Conference on Adaptive Structures and Technologies; 20051009-12; Paris(FR) >ON THE USE OF SHAPE MEMORY ALLOY WIRES FOR ANHEDRAL ANGLE CONTROL IN HELICOPTER ROTOR BLADES
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ON THE USE OF SHAPE MEMORY ALLOY WIRES FOR ANHEDRAL ANGLE CONTROL IN HELICOPTER ROTOR BLADES

机译：形状记忆合金丝在直升机转子叶片中的角度控制中的应用

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摘要

Noise and vibration is a major issue in helicopters. Active and passive control systems have been used in attempts to reduce these effects. This paper presents a system for the active control of a rotor blade anhedral tip flap with the intention of reducing noise due to Blade Vortex Interaction (BVI). In the experiments, the flap hinge is represented by a shaft and actuated by Shape Memory Alloy (SMA) wires. Closed-loop control of the angular position of the shaft is accomplished first with a single SMA wire, and next with two antagonistic SMA wires. The results of these experiments are presented and discussed. To get a rough approximation of the number of SMA wires that are required, the aerodynamic loads imposed at the anhedral tip flap are estimated by a one dimensional analysis. The setup is then modeled using the SMA constitutive and transformation equations as well as the equations of equilibrium of the whole system. The resulting system of nonlinear equations is solved using a fixed point solution method. The close agreement between the output of the simulations and the corresponding experimental results demonstrates the validity of the model.
机译：噪声和振动是直升机的主要问题。主动和被动控制系统已被用来减少这些影响。本文提出了一种主动控制转子叶片无角尖端襟翼的系统，目的是减少由于叶片涡旋相互作用（BVI）引起的噪声。在实验中，襟翼铰链由轴表示，并由形状记忆合金（SMA）线驱动。轴角位置的闭环控制首先通过一条SMA线完成，然后再通过两条SMA对抗线完成。这些实验的结果将被介绍和讨论。为了粗略估算所需的SMA线数，可通过一维分析估算施加在无角形尖端襟翼上的空气动力学载荷。然后使用SMA本构方程和变换方程以及整个系统的平衡方程对设置进行建模。最终的非线性方程组使用定点解法求解。仿真输出与相应的实验结果之间的密切一致性证明了该模型的有效性。

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