实验流体力学Issue(3)：18-24,7.DOI:10.11729/syltlx20140124
直升机气动噪声研究进展
Progress in aero-acoustic technology of helicopter
陈平剑 1仲唯贵 1段广战1
作者信息
- 1. 中国直升机设计研究所，江西 景德镇 333000
- 折叠
摘要
Abstract
The status and progress in helicopter aero-acoustic technology is presented,inclu-ding test technology,analysis method and rotor noise control technology.The advanced test technologies such as unsteady pressure measurement,flow field visualization and noise source lo-calization,have been implemented in the acoustic wind tunnel test of rotor noise,which is the es-sential instrument for helicopter aero-acoustic research.Flight test of helicopter aero-acoustic measurements has become a necessary technique in the programs of helicopter noise certification and helicopter noise reduction investigation.With the development of helicopter aero-acoustic noise analysis method,many software tools for rotor noise prediction have been developed and applied in the helicopter design and noise reduction research,based on the solutions of the FW-H equation and Kirchhoff equation.Low noise blade tip is the primary and effective method for heli-copter noise control,and is used widely in helicopter design.Moreover,new technologies such as noise abatement operation and active rotor noise control have been validated by flight test,but have not been used in helicopter design get.Initiated by the demands to design environmentally compatible helicopter,both societies of industry and academia will devote more effort in helicop-ter aero-acoustic technology research.关键词
直升机/旋翼噪声/气动噪声/声学试验/噪声控制Key words
helicopter/rotor noise/aero-acoustic/acoustic test/noise control分类
航空航天引用本文复制引用
陈平剑,仲唯贵,段广战..直升机气动噪声研究进展[J].实验流体力学,2015,(3):18-24,7.
