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首页> 外文期刊>Journal of the American Helicopter Society >Methodology for In-Flight Tracking of Helicopter Rotor Blades Using Shape Memory Alloy Actuators
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Methodology for In-Flight Tracking of Helicopter Rotor Blades Using Shape Memory Alloy Actuators

机译：使用形状记忆合金作动器在空中跟踪直升机旋翼叶片的方法

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摘要

This paper describes the concept, design, fabrication and testing of a shape memory alloy (SMA) wire actuated tab for in-flight tracking of helicopter rotors. To achieve fine adjustment of tab angle, it is equipped with a locking mechanism and a position feedback controller. The primary components of the actuator are the SMA wires, a fiberglass clamp and a fiberglass hinge tube. The clamp and the hinge tube allow for two separate sets of SMA wires to be utilized. One set of the wires is heat activated while the other remains at ambient conditions. The actuator was mounted in an NACA 0012 blade section chord. Bench-top and open-jet wind tunnel tests conducted on a wing section with 2-wire and 4-wire actuators mounted inside the profile and at a maximum angle of attack of 15 deg and velocity of 120 ft/sec (Mach .11) are described. It is shown that a 2-wire actuator, with an initial plastic deformation of 4.2% is sufficient to deflect the tab down by 31 deg at a wind speed of 120 ft/sec. In bench-top tests, a position feedback controller demonstrated the ability to track a desired tab position in about 10 seconds. The locking mechanism showed the ability to lock the tab in a desired position during power-off condition.
机译：本文介绍了用于空中跟踪直升机旋翼的形状记忆合金（SMA）线致动翼片的概念，设计，制造和测试。为了实现对接片角度的微调，它配备了锁定机构和位置反馈控制器。执行器的主要组件是SMA线，玻璃纤维夹和玻璃纤维铰链管。夹具和铰链管允许使用两组独立的SMA线。一组电线被热激活，而另一组电线保持在环境条件下。促动器安装在NACA 0012叶片截面弦中。在机翼部分进行了台式和开放式风洞测试，机翼部分装有2线制和4线制执行器，最大迎角为15度，速度为120英尺/秒（0.11马赫）描述。结果表明，初始塑性变形为4.2％的2线致动器足以使翼片在120 ft / sec的风速下向下偏转31度。在台式测试中，位置反馈控制器展示了能够在大约10秒内跟踪所需标签位置的能力。锁定机制显示了在断电条件下将凸片锁定在所需位置的能力。

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