Incorporation of Blade Twist and Non-Uniform Inflow Effects In Undergraduate Helicopter Aeronautics Whirl Stand Laboratory

Jeremy D. Paquin, Evan Harris, Emma San Martin, Dennis P. Kirby, R. Melnyk, Nathan Humbert
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Abstract

Flight and aerodynamics laboratory experiences have supported the aeronautical engineering courses in the United States Military Academy’s mechanical engineering program for over 50 years. Whirl stands are the rotary-wing equivalent of wind tunnels; they are used to generate experimental data on small- or full-scale rotor systems. The helicopter whirl stand laboratory is a cornerstone event in the program’s Helicopter Aeronautics course, used to reinforce students’ understanding for predicting and calculating hover performance data. The experimental apparatus includes a remote control (RC) helicopter mounted to a static test stand, instrumented with load cells to measure lift and torque. The helicopter is capable of varied revolutions per minute (RPM) and collective blade pitch. Control of the apparatus and measurement readings occur from behind a protective wall with an observation window. The objective of the laboratory is to compare the results of predictive analyses, conducted using Blade Element Theory (BET) and Blade Element Momentum Theory (BEMT), to experimental data. Students calculate the coefficient of thrust based on collective pitch angles and atmospheric conditions using an iterative approach in numerical analysis software. A recent effort appreciably improved the lab by adding two experimental twisted-blade cases in addition to the original untwisted blades. The ability to change between the original and updated (twisted) blades offers insight into the advantages and disadvantages of each in hover. The upgraded blades were designed internally by students to match the original rotor diameter, outsourced for precision manufacturing, and tested for incorporation into the laboratory. Overall, the upgraded laboratory offers a relevant, comprehensive application to deepen students’ conceptual understanding of rotorcraft aerodynamics, laboratory procedures, and modeling principles taught in the course.
本科直升机航空旋翼架实验室叶片扭扭与非均匀入流效应的结合
飞行和空气动力学实验室的经验已经为美国军事学院机械工程项目的航空工程课程提供了50多年的支持。旋涡架是相当于风洞的旋翼;它们用于生成小型或全尺寸转子系统的实验数据。直升机旋翼架实验室是该项目直升机航空学课程的基石,用于加强学生对预测和计算悬停性能数据的理解。实验装置包括一个远程控制(RC)直升机安装在一个静态试验台,仪器与称重传感器测量升力和扭矩。直升飞机能够改变每分钟的转数(RPM)和集体桨距。仪器的控制和测量读数发生在带有观察窗的保护墙后面。该实验室的目的是将使用叶片单元理论(BET)和叶片单元动量理论(BEMT)进行的预测分析结果与实验数据进行比较。学生利用数值分析软件中的迭代方法计算基于集体俯仰角和大气条件的推力系数。最近的一项努力明显改善了实验室,除了原来的未扭曲叶片外,还增加了两个实验扭曲叶片的情况。在原始和更新(扭曲)叶片之间切换的能力提供了对悬停中每个叶片的优点和缺点的洞察。升级后的叶片由学生在内部设计,以匹配原始转子直径,外包精密制造,并在实验室进行测试。总的来说,升级后的实验室提供了一个相关的,全面的应用,以加深学生对旋翼飞机空气动力学,实验室程序和建模原理的概念理解。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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