• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Smart Materials & Structures >Design, development, and hover testing of a helicopter rotor blade chord extension morphing system
【24h】

Design, development, and hover testing of a helicopter rotor blade chord extension morphing system

机译：直升机旋翼桨叶弦延伸变形系统的设计，开发和悬停测试

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

A rotor blade chord extension system was designed, fabricated and hover tested, using electromechanical and pneumatic actuation. A 1.5 in actuator stroke output in the spanwise direction was converted into chordwise motion of a trailing-edge plate (TEP), via a rigid link. On the hover stand, with a 20 V dc input, the electromechanical actuator was shown to fully extend and retract the plate at rotational speeds up to 385 RPM (which put the system at a centrifugal loading of 209.5 g, or 47.2% of that on a Black Hawk helicopter at 73% span). The configuration was changed to reduce the actuator force requirement for the pneumatic actuator. The rotor test facility allowed a maximum of 105 psi pressure input through the rotary union (significantly lower than the rating of the actuator). At these moderate pressure inputs, full TEP deployment was observed at 315 RPM (140.2 g, or 31.6% of that on a Black Hawk helicopter at 73% span). The model prediction of TEP displacement versus pressure showed good correlation with test results.
机译：使用机电和气动执行机构设计，制造和测试了转子叶片弦延伸系统。通过刚性连杆将在翼展方向上输出的1.5的执行器冲程转换为后缘板（TEP）的弦向运动。在具有20 V dc输入的悬停支架上，机电执行器显示为以高达385 RPM的旋转速度完全伸展和收回板（这使系统承受209.5 g的离心载荷，即系统的47.2％一架黑鹰直升机，跨度为73％）。更改了配置，以减少气动执行器的执行器力要求。转子测试设备允许通过旋转接头输入最大105 psi的压力（明显低于执行器的额定值）。在这些中等压力输入下，观察到TEP的完全部署为315 RPM（140.2 g，或73％跨度的黑鹰直升机的31.6％）。 TEP位移与压力的模型预测与测试结果显示出良好的相关性。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号