CAJ | 학술논문

对直升机气动噪声的研究进展进行了综述，内容包括试验技术、理论分析方法和噪声抑制技术。声学风洞试验是直升机气动噪声研究的基本手段，其中非定常载荷测试、流场显示和声源定位等先进测试技术已实现应用；飞行试验在直升机噪声适航标准完善和噪声控制技术研究等方面已成为必不可少的研究和验证手段。直升机气动噪声的理论体系不断完善，包括声类比法、Kirchhoff／CFD 混合法等旋翼气动噪声分析方法都已形成分析程序，成为直升机研发的有效工具。直升机气动噪声的抑制仍然以旋翼桨尖设计为主，飞行轨迹优化、旋翼噪声主动控制等新技术已实现飞行验证，但尚未进行型号应用。在用户和市场需求的推动下，在新型直升机的研发中，引入气动噪声的抑制技术将是必然的发展趋势。
대직승궤기동조성적연구진전진행료종술，내용포괄시험기술、이론분석방법화조성억제기술。성학풍동시험시직승궤기동조성연구적기본수단，기중비정상재하측시、류장현시화성원정위등선진측시기술이실현응용；비행시험재직승궤조성괄항표준완선화조성공제기술연구등방면이성위필불가소적연구화험증수단。직승궤기동조성적이론체계불단완선，포괄성류비법、Kirchhoff／CFD 혼합법등선익기동조성분석방법도이형성분석정서，성위직승궤연발적유효공구。직승궤기동조성적억제잉연이선익장첨설계위주，비행궤적우화、선익조성주동공제등신기술이실현비행험증，단상미진행형호응용。재용호화시장수구적추동하，재신형직승궤적연발중，인입기동조성적억제기술장시필연적발전추세。
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.