摘要
在飞机着陆过程中,起落架已成为飞机的主要噪声源。因此,对起落架气动噪声进行研究,并建立其数值计算方法是从总体上降低飞机噪声的主要途径之一。在已提出的基于试验数据的飞机起落架气动噪声数值计算方法基础上,提出一类改进方法。该方法除保持原有方法计算效率高、指向性计算正确的优点外,还进行了如下改进:首先,通过对小部件进行建模,实现了高频噪声的计算。其次,建立了起落架气动噪声散射模型,并对机轮与声源距离,机轮与接收点距离以及机轮直径对散射系数的影响进行了详细分析。最终通过对波音737主起落架全尺寸简化模型气动噪声进行计算,并与试验结果进行对比验证了该方法的正确性。
On landing, the noise from the landing gear becomes comparable to and even exceeds the engine noise. Based on the proposed numerical computational method for predicting aircraft landing gear noise in reference 11, an improved method has been proposed. Besides high efficiency computation and the right result of cylinder directivity of the method in reference 11, the method includes two advantages ： （ 1 ）High frequency computation is performed by developing high frequency model; （2）A noise scattering model is developed. A detailed analysis is provided between scattering coefficient and its influence factors, e.g., the distance between the sound source and the wheel, the distance between the wheel and the observe point, the diameter of wheel. Finally, the method is validated by predicting the noise of a simplified Boeing 737 full scale landing gear and comparing results with tunnel test datca
出处
《机械设计与制造》
北大核心
2015年第12期23-26,30,共5页
Machinery Design & Manufacture
基金
国家自然科学基金(51375385)
航空科学基金(20131553019)
关键词
起落架
气动噪声
高频噪声模型
声散射模型
Landing Gear
Aeroacoustic Noise
High Frequency Noise Model
The Model of Noise Scattering
