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首页> 外文学位 >Primary control of a Mach scale swashplateless rotor using brushless DC motor actuated trailing edge flaps.
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Primary control of a Mach scale swashplateless rotor using brushless DC motor actuated trailing edge flaps.

机译：使用无刷直流电机驱动的后缘襟翼对马赫秤无旋转斜盘转子进行主控制。

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摘要

The focus of this research was to demonstrate a four blade rotor trim in forward flight using integrated trailing edge flaps instead of using a swashplate controls. A compact brushless DC motor was evaluated as an on-blade actuator, with the possibility of achieving large trailing edge flap amplitudes. A control strategy to actuate the trailing edge flap at desired frequency and amplitude was developed and large trailing edge flap amplitudes from the motor (instead of rotational motion) were obtained. Once the actuator was tested on the bench-top, a lightweight mechanism was designed to incorporate the motor in the blade and actuate the trailing edge flaps. A six feet diameter, four bladed composite rotor with motor-flap system integrated into the NACA 0012 airfoil section was fabricated. Systematic testing was carried out for a range of load conditions, first in the vacuum chamber followed by hover tests. Large trailing edge flap deflections were observed during the hover testing, and a peak to peak trailing edge flap amplitude of 18 degree was achieved at 2000 rotor RPM with hover tip Mach number of 0.628. A closed loop controller was designed to demonstrate trailing edge flap mean position and the peak to peak amplitude control. Further, a soft pitch link was designed and fabricated, to replace the stiff pitch link and thereby reduce the torsional stiffness of the blade to 2/rev. This soft pitch link allowed for blade root pitch motion in response to the trailing edge flap inputs. Blade pitch response due to both steady as well as sinusoidal flap deflections were demonstrated. Finally, tests were performed in Glenn L. Martin wind tunnel using a model rotor rig to assess the performance of motor-flap system in forward flight. A swashplateless trim using brushless DC motor actuated trailing edge flaps was achieved for a rotor operating at 1200 RPM and an advance ratio of 0.28. Also, preliminary exploration was carried out to test the scalability of the motor driven trailing edge flap concept. In conclusion, the concept of using brushless DC motors as on-blade actuators, actuating trailing edge flaps has the potential to replace the current mechanically complex swashplate with a hydraulic-free swashplateless system and thereby reduce overall weight and hub drag.
机译：这项研究的重点是演示使用集成式后缘襟翼而不是旋转斜盘控件在前向飞行中的四叶片转子微调。紧凑型无刷直流电动机被评估为叶片上的致动器，并有可能实现较大的后缘襟翼幅度。开发了一种以所需频率和幅度致动后缘襟翼的控制策略，并从电动机获得了较大的后缘襟翼幅度（而不是旋转运动）。一旦在台式机上对执行器进行了测试，就可以设计出一种轻巧的机构，将电动机整合到刀片中并启动后缘襟翼。制作了一个六英尺直径的四叶片复合转子，该转子具有集成在NACA 0012机翼部分中的电机襟翼系统。针对各种负载条件进行了系统测试，首先是在真空室内，然后进行悬停测试。在悬停测试过程中观察到较大的后缘襟翼挠度，并且在2000转子RPM且悬停尖端马赫数为0.628时，峰到峰的后缘襟翼幅度达到18度。设计了一个闭环控制器来演示后缘襟翼的平均位置和峰峰值幅度控制。此外，设计并制造了软节距连杆，以代替刚性节距连杆，从而将叶片的扭转刚度减小到2 / rev。该软俯仰连杆允许叶片根部俯仰运动响应后缘襟翼输入。证明了由于稳定的和正弦的襟翼偏转引起的桨距变化。最后，在Glenn L. Martin风洞中使用模型旋翼钻机进行了测试，以评估前向飞行中电动襟翼系统的性能。对于以1200 RPM和0.28的提前比运行的转子，使用了无刷直流电动机驱动的后缘襟翼实现了无旋转斜盘的修整。同样，进行了初步探索以测试电动机驱动的后缘襟翼概念的可扩展性。总之，将无刷直流电动机用作叶片式执行器，驱动后缘襟翼的概念有可能用无液压的无旋转斜盘系统代替当前机械复杂的旋转斜盘，从而降低整体重量和轮毂阻力。

著录项

  • 作者

    Saxena, Anand.;

  • 作者单位

    University of Maryland, College Park.;

  • 授予单位 University of Maryland, College Park.;
  • 学科 Aerospace engineering.
  • 学位 Ph.D.
  • 年度 2015
  • 页码 343 p.
  • 总页数 343
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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