摘要
对带有喉栓的可控推力固体火箭发动机进行了变几何构形的非稳态数值模拟。控制方程为非稳态轴对称N-S方程,采用标准k-ε湍流模型,应用FLUENT软件动态网格算法。结果显示喉栓能够有效改变发动机燃烧室压力和推力,满足发动机推力控制要求。得到了燃烧室压力、推力和喉栓受轴向力变化的基本规律,为带喉栓固体火箭发动机的设计和性能预报提供依据。
Unsteady numerical investigation was preformed for controllable thrust solid rocket motor whose configuration changed with pintle moving.Theκ-εturbulence model and dynamic meshes method of FLUENT software were used. Results show that pintle could change the nozzle throat area and thus the motor pressure and thrust,which provided the capability for thrust control.The basic rules of variation of motor pressure,thrust and axial force on pintle was got. which would be helpful for controllable thrust solid rocket motor design and performance prediction.
出处
《弹箭与制导学报》
CSCD
北大核心
2006年第S2期412-413,417,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
固体火箭发动机
推力控制
数值仿真
solid rocket motor
thrust control
numerical simulation
