火箭喷气强噪声模拟装置动态特性分析

Dynamic Characteristic Analysis on a Simulation Device of the Strong Noise Caused by Rocket Exhaust

首次建立了考虑电磁力与气动力耦合特性的火箭喷气强噪声模拟装置动态特性仿真分析模型。仿真结果表明,音环质量减轻、弹性元件力顺减小、磁场强度增大、音环振动频率快则系统响应特性好。环形喷口缝隙高度和激励信号电流增大,则音环振动位移增大,声辐射器喉部处声压提高。仿真结果为大推力火箭发动机噪声模拟装置的改进设计提供了理论研究数据。

A dynamic characteristic mathematical model of a simulation device of the strong noise caused is established by rocket engines. Electromagnetic force-aerodynamic force coupling has been considered with innovation. Simulation result indicates that when lightening the sound loop mass , decreasing elastic materials softy, in-creasing magnetic field intensity, heightening vibration frequency of the sound loop will make system response characteristic perform better respectively. Increasing the height of the gap of air-jet mouth and the current of input signal will make the vibration displacement amplitude of sound loop and the sound pressure in throat of the megaphone both increase accordingly. Those results will provide theoretic data in improving the design of simulation device of high-thrust rocket engine noise.