固体火箭发动机推力振荡特性数值研究  

Numerical Analysis on Thrust Oscillation Characteristics in Solid Rocket Motor

作　　者：张峤[1] 苏万兴[1] 李军伟[1] 王伟臣[1] 王宁飞[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《宇航学报》2011年第4期835-841,共7页Journal of Astronautics

基　　金：国家自然科学基金(51076015)

摘　　要：为了揭示固体火箭发动机推力振荡特性,以大型助推器P230的缩比发动机为基础,使用大涡模拟方法,对障碍物旋涡脱落诱发的振荡流场开展数值模拟,通过对比燃烧室压力、推力的振频和振幅,总结了推力振幅的估算方法。研究结果表明,推力振幅对压力振幅放大机理的关键参数是喉通比,放大比例与喉通比成反比;奇数阶声振型对推力振幅的贡献最大,偶数阶声振型对推力振幅的影响可以忽略,旋涡脱落对推力振幅的作用小于奇数阶声振型,且随涡/声耦合程度的增大而增强。In order to discover the mechanism of thrust oscillation characteristics in solid rocket motors,large-eddy simulation with Wall-Adapting Local Eddy-Viscosity subgrid-scale turbulence model is carried out to study the oscillating flow field induced by obstacle vortex shedding based on the subscale motor of P230.An integrated method is presented to describe the relationship between thrust amplitude and pressure amplitude.The results indicate that the ratio of thrust amplitude to pressure amplitude is mainly determined by the throat to port area ratio J,and it varies inversely as J.It is concluded that odd-order acoustic modes have the greatest contribution to the thrust amplitude,while the effect of even order acoustic modes on thrust amplitude can be ignored.The contribution of vortex-shedding to the thrust amplitude is less than that of the odd order acoustic modes,and it increases with the level of vortex sound coupling.

关 键 词：固体火箭发动机 涡/声耦合 推力振荡 喉通比 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]