客机概念设计阶段起降噪声预测及起降航迹影响分析  

Takeoff and landing noise prediction and flight path impact analysis in the aircraft conceptual design

作　　者：柴啸 司江涛 朱正迪 Chai Xiao;Si Jiangtao;Zhu Zhengdi(Shanghai Aircraft Design and Research Institute,Commercial Aircraft Corporation of China Ltd.,Shanghai,201210,China)

机构地区：[1]中国商用飞机有限责任公司上海飞机设计研究院,上海201210

出　　处：《机械设计与制造工程》2023年第3期54-58,共5页Machine Design and Manufacturing Engineering

摘　　要：为了在客机概念设计阶段对起降噪声进行预测,在客机总体分析框架下开发了一套噪声预测程序,其中各噪声源预测采用半经验预测方法,起降航迹性能计算采用质点模型,发动机性能计算采用部件级分析模型。基于该程序,预测了某一宽体客机飞机噪声水平,并研究了减推力起飞和大角度进近对降低飞机噪声的效果,结果表明客机减推力起飞可以有效地降低客机飞越噪声;大角度进近可以有效地降低客机进近噪声。In order to predict the takeoff and landing noise in the aircraft conceptual design stage,a set of noise prediction program is developed under the overall analysis framework of the civil aircraft.The calculation of each noise source is based on semi empirical method.The particle model is used for the calculation of takeoff and landing flight path.The component level analysis model is used for the calculation of engine performance.Based on this program,the noise level of a wide body airliner is predicted,and the effects of thrust reduction takeoff and large angle approach on reducing aircraft noise are studied.The results show that the thrust reduction takeoff of airliner can effectively reduce the overflight noise of airliner;Large angle approach can effectively reduce aircraft approach noise.

关 键 词：噪声 概念设计 起降航迹 减推力 

分 类 号：V221[航空宇航科学与技术—飞行器设计]