单喷管液体火箭发射喷流噪声模拟试验研究  

Test on launch jet noise of liquid rocket with single nozzle

作　　者：陈劲松[1] 曾玲芳[1] 胡小伟[1] 范虹[1] 

机构地区：[1]北京航天发射技术研究所,北京100076

出　　处：《空气动力学学报》2015年第6期818-822,共5页Acta Aerodynamica Sinica

摘　　要：针对捆绑式运载火箭发射噪声问题,研制了一种相对简化的单喷管液体火箭发射喷流噪声模拟试验系统,开展了发射喷流噪声模拟试验研究。研究表明:受发射平台结构扰动效应影响,空间高度方向发射喷流噪声变化规律不同于自由喷流噪声变化规律,但不同测点之间噪声声压级随时间变化规律存在相似性;发射喷流噪声频谱存在宽频特性,同时还存在突出倍谐频啸叫特征或突出单基频啸叫特征。发射喷流噪声模拟试验过程中综合了喷流流场研究,研究发现:喷流噪声声压时域变化规律与发动机工作压力、喷流流场压力时域变化规律也存在相似性。Based on the distinguishing launch technology of trapped launch vehicle,a simplified launch jet noise test system is designed and developed.The test system can be used to simulate jet noise and jet flow field about liquid rocket launching with single nozzle.Then the series of launch jet noise tests are accomplished.The test results show that the height domain SPL curves of launch jet noise are different from that of free jet noise,while changes of SPL along with time among different test points show the similar tendency,which is caused by the launch pad disturbing.The frequency domain SPL curves indicate that there are wide frequency characteristics and distinct screams about the launch jet noise,and the screams of launch jet noise usually have harmonic multiple frequencies or monophonic frequency.The launch jet flow field tests accomplished with the launch jet noise tests show that the developing tendencies of time domain SPL curves of launch jet noise are also similar with that of the engine working pressure and the launch jet flow pressure.

关 键 词：发射喷流噪声 模拟试验研究 噪声声压 噪声声压级 噪声频谱 

分 类 号：V411.6[航空宇航科学与技术—航空宇航推进理论与工程]