摘要
燃烧室的声场特性分析是固体火箭发动机声不稳定研究的一个重要组成部分,建立了复杂装药结构固体火箭发动机的燃烧室声场特性的计算模型,推导了小振幅三维波动方程,采用有限元法进行仿真,得到了有喷管潜入段和无喷管潜入段的翼柱型装药结构空腔的声振频率、振型和小扰动时的频率响应特性,分析表明,小扰动出现在声腔不同位置时,声压响应均出现在声腔固有频率段上,但是声压幅值有较大差异,喷管潜入段的空腔对基频有强阻尼作用。
Analyzing acoustic properties of combustion chamber is important part of acoustic instability of solid rocket motor. In this paper a numerical model about acoustic properties of combustion chamber in solid rocket motor with complicated grain shape has been established. Using small amplitude three-dimensional wave equation and finite-element method, acoustic wave frequency, shape and the response frequency property of perturbed field were obtained in the cavity of finocyl grain with and without submerged nozzle. It shows that acoustic pressure response present in inherent frequency sect when the position of microseism is different, but the amplitude of acoustic pressure response is different, cavity with submerged nozzle is as a damp to first frequency.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2008年第5期1593-1597,共5页
Journal of Astronautics
关键词
固体火箭发动机
燃烧室声腔
声场分析
有限元法
Solid rocket motor
Cavity of combustion chamber
Acoustic field analyse
Finite-element method
