摘要
以某推力可调固体火箭发动机为研究对象,采用数值分析方法对包含发动机以及执行机构的流场区域进行网格划分,选择适合发动机管道流动的RNG k—ε湍流模型对其进行数值计算。计算结果揭示了发动机尾流场的流动状况,并得到了发动机主推力、执行机构桨片所受力矩随桨偏角以及发动机喷口阻塞率的变化关系。所得结论可以为相关工程运用提供参考。
Taking a thrust-adjustable solid rocket motor as the research object,the flow field region including the engine and the actuator is meshed by numerical analysis method,and the RNG k—εturbulence model suitable for engine pipeline flow is selected for numerical calculation.The results open out the flow state of the engine wake field and the relationship between the main thrust of the engine,the moment of the actuator blade and the deflection angle of the propeller,the blocking ratio of the engine nozzle is also obtained.The conclusions obtained can provide reference for the application of related projects.
作者
陈运剑
刘畅
帅超
CHEN Yun-jian;LIU Chang;SHUAI Chao(No.710 R&D Institute,CSIC,Yichang 443003,China)
出处
《机械工程与自动化》
2019年第5期102-103,106,共3页
Mechanical Engineering & Automation
关键词
推力可调
固体火箭发动机
仿真
adjustable thrust
solid-propellant rocket engine
simulation
