应用微穿孔板吸声结构的飞机座舱内部噪声控制实验研究  

Experimental research of noise control in the fighter cockpit using microperforated panel absorber structure

作　　者：孙亚飞[1] 陈仁文[1] 徐志伟[1] 龚海燕[1] 王鑫伟[1] 

机构地区：[1]南京航空航天大学智能材料与结构航空科技重点实验室,南京210016

出　　处：《声学学报》2003年第4期294-298,共5页Acta Acustica

基　　金：国家自然基金(50135030);江苏省自然科学基金(BK2001044)

摘　　要：针对某些特殊情况下飞机座舱内部噪声过大的实际情况,对其进行了噪声无源控制实验研究。以某飞机座舱模型为研究对象,利用微穿孔板吸声结构成功实现了一套飞机座舱模型内部噪声无源控制系统。同时利用Cada-X结构动力学分析系统建立了一套振动噪声控制性能测试系统,可广泛应用于各种振动噪声有源、无源控制系统的控制性能测试。同时对所设计的微穿孔板吸声结构吸声系数进行了理论计算和实验测量,对比结果表明其一致性良好。最后利用该测试系统对飞机座舱模型噪声无源控制系统进行了控制性能测试,控制效果明显。从而说明了此方法对飞机座舱内部噪声抑制的有效性和可行性。Some experimental research work has been done on the passive noise control of the fighter cockpit, because of the larger noise generating under some circumstance. As to some fighter cockpit model in the research, using Mi-croperforated Panel Absorber (MPA) structure, a passive noise control system is realized. And using Cada-X structure dynamics analysis system, a testing system to test vibration and noise controlling performance is established. It is applied to testing the controlling performance of the active or passive vibration and noise control system. At the same time, the theoretical result of the absorber coefficient was compared with the testing result of the microperforated panel absorber structure. The experimental result of the control performance of the passive noise control system, shows that the control effect was notable. All these proved the validity and feasibility of the method to the reducing of noise in the fighter cockpit.

关 键 词：飞机 座舱 内部噪声 噪声控制 无源控制 实验研究 微穿孔板吸声结构 性能测试 

分 类 号：TB535[理学—物理]