Author ORCID Identifier

https://orcid.org/0009-0002-6464-8992

Date Available

7-20-2025

Year of Publication

2025

Document Type

Master's Thesis

Degree Name

Master of Science in Mechanical Engineering (MSME)

College

Engineering

Department/School/Program

Mechanical Engineering

Faculty

David W. Herrin

Abstract

Unmanned Aerial Vehicles (UAVs) with multirotor propulsion and control, commonly called drones or multicopters, generate a complex acoustic field that is not entirely understood. Many components and their interactions contribute to the overall noise level and behavior of the acoustic field. However, performing acoustic measurements on a multicopter in a confined space, such as a small anechoic chamber, can be an extremely difficult and time-consuming process. A test stand was developed to allow for rapid and safe acoustic measurements in a controlled environment. The design, development, and initial measurements are discussed. The performance and acoustic response are assessed to examine the effectiveness of the test stand. The contribution noise from the test stand and a measurement grid are evaluated, as well as the influence of stationary propeller testing.

The test stand was configured to emulate a small quadcopter to determine the acoustic response of a multicopter. Sound intensity scans were performed using a coupled sound pressure and particle velocity sensor to obtain sound intensity measurements close to the source and along propagation planes for three-dimensional visualizations containing both amplitude and direction. Draw away measurements using a sound pressure and particle velocity sensor were also completed to analyze the sound field characteristics further from the source. The number of propellers in operation was varied to determine the impact of adding additional sources. Aeroacoustic sources, near and far field behavior, interaction noise, directivity, and sound field propagation are discussed.

Digital Object Identifier (DOI)

https://doi.org/10.13023/etd.2025.408

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