A Study of Closed Loop Control of Active Technique for Helicopter BVI Noise Reduction
A feedback controller utilizing the global model with on-line identification for the BVI noise reduction is developed and evaluated in the wind tunnel test,where the active flap is used as a test bed of the active technique.This paper presents the research activities of this control law study applicable to the active technique for the rotor noise reduction.Taking into consideration to the application for real helicopters,the pressure fluctuation on the blade is used for control object,because this enables the control system to be made only by on-board sensors with BVI detection method.A control object reduced from multiple pressure sensors,which can more sufficiently represent the BVI phenomenon on the blade than by a single sensor,is proposed and its capability is studied experimentally using a 1-bladed rotor system.Strong correlation between the sound pressure level measured near the blade and the surface pressure fluctuation by multiple pressure sensors is observed.Also,from the closed loop test results,the good convergence for the active flap phase of minimum pressure fluctuation and minimum SPL is obtained.It is concluded that the validation of the proposed control law is demonstrated and the control object utilizing multiple pressure sensors is promising.
BVI Active Flap Closed loop control
KOBIKI Noboru Shigeru SAITO
JAXA,1-13-6 Osawa,Mitaka,Tokyo 181-0015,Japan
国际会议
2014 Asia-Pacific International Symposium on Aerospace Technology(2014亚太航空航天技术学术会议)
上海
英文
1-12
2014-09-24（万方平台首次上网日期，不代表论文的发表时间）