Acoustic Analysis of a Hybrid Propulsion System for Drone Applications

Acoustics Pub Date : 2024-07-25 DOI:10.3390/acoustics6030038
Mădălin Dombrovschi, Marius Deaconu, L. Cristea, T. Frigioescu, G. Cican, G. Badea, Andrei Totu
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Abstract

This paper aims to conduct an acoustic analysis through noise measurements of a hybrid propulsion system intended for implementation on a drone, from which the main noise sources can be identified for further research on noise reduction techniques. Additionally, the noise was characterized by performing spectral analysis and identifying the tonal components that contribute to the overall noise. The propelling force system consists of a micro-turboshaft coupled with a gearbox connected to an electric generator. The propulsion system consists of a micro-turboshaft coupled with a gearbox connected to an electric generator. The electric current produced by the generator powers an electric ducted fan (EDF). The engineturbo-engine was tested in free-field conditions for noise generation at different speeds, and for this, an array of microphones was installed, positioned polarly around the system and near the intake and exhaust. Consequently, based on the test results, the acoustic directivity was plotted, revealing that the highest noise levels are at the front and rear of the engine. The noise level at a distance of 1.5 m from the turboengine exceeds 90 dBA at all tested speeds. Spectral analyses of both the far-field acoustic signals (measured with a polar microphone array) and the near-field signals (microphones positioned near the intake and exhaust) revealed that the primary contributors to the overall noise are the micromotor’s compressor, specifically the gas dynamic phenomena in the fan (BPF and 2× BPF). Thus, it was determined that at the intake level, the main noise contribution comes from the high-frequency components of the compressor, while at the exhaust level, the noise mainly originates from the combustion chamber, characterized by low-frequency components (up to 2 kHz). The findings from this study have practical applications in the design and development of quieter drone propulsion systems. By identifying and targeting the primary noise sources, engineers can implement effective noise reduction strategies, leading to drones that are less disruptive in urban environments and other noise-sensitive areas. This can enhance the acceptance and deployment of drone technology in various sectors, including logistics, surveillance, and environmental monitoring.
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无人机应用的混合推进系统声学分析
本文旨在通过对无人机混合推进系统的噪声测量进行声学分析,从中找出主要噪声源,以便进一步研究降噪技术。此外,还通过进行频谱分析,确定了造成整体噪声的音调成分,从而确定了噪声的特征。推进力系统由一个微型涡轮轴和一个与发电机相连的齿轮箱组成。推进力系统由一个微型涡轮轴和一个与发电机相连的齿轮箱组成。发电机产生的电流为电动管道风扇(EDF)提供动力。在自由场条件下,对发动机涡轮增压发动机在不同速度下产生的噪音进行了测试,为此安装了一个传声器阵列,极性地安装在系统周围以及进气口和排气口附近。因此,根据测试结果绘制了声学指向性图,显示发动机前部和后部的噪声水平最高。在所有测试速度下,距离涡轮发动机 1.5 米处的噪音水平都超过了 90 dBA。对远场声学信号(用极性传声器阵列测量)和近场信号(传声器安装在进气口和排气口附近)的频谱分析表明,总体噪声的主要贡献者是微电机的压缩机,特别是风扇中的气体动力现象(BPF 和 2× BPF)。因此可以确定,在进气口,主要噪声来自压缩机的高频成分,而在排气口,噪声主要来自燃烧室,其特征是低频成分(高达 2 kHz)。这项研究的结果可实际应用于设计和开发更安静的无人机推进系统。通过识别和锁定主要噪声源,工程师可以实施有效的降噪策略,从而减少无人机在城市环境和其他噪声敏感区域的干扰。这可以提高无人机技术在物流、监控和环境监测等各个领域的接受度和部署。
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