中文摘要：

在一种利用喷气反作用力的飞行器姿态控制方法的基础上,建立拉瓦尔喷管的热力学和动力学模型,取得了拉瓦尔喷管内部速度场、压力场及温度场的分布规律。分析结果表明：喉部及初始扩张段气流的速度变化快,气体对壁面的冲刷严重,该部位可采用抗冲刷防护材料和工艺处理措施;在收缩段的喷管壁面处的压力高,喉部及初始扩张段壁面的压力变化剧烈,可采用强度较高的防护材料;气流经过拉瓦尔喷管过程中,温度不断降低,但壁面温度变化幅度不大,在喷管喉部处的温度快速下降且出现不均匀变化现象,可见喷管收敛段及喉部着重注意耐烧蚀防护处理。本文的理论结果和实验结果相符,研究结果可作为拉瓦尔喷管结构和工艺设计的理论依据。

英文摘要：

Based on a new attitude control method,thermodynamics equations and dynamic basic equations of Laval nozzle are established.The velocity,pressure and temperature field distribution of Laval nozzle are obtained.The results show that the flow velocity in the throat and the initial expansion segment changes quickly to create serious wall erosion where should be made by anti-erosion protection materials.The wall pressure at convergent segment is high,and the pressure at throat and initial expansion segment changes quickly where should be made by high strength materials.The wall temperature variation range is not big.At the nozzle throat,the temperature dropped rapidly and there is partial uneven change phenomenon.Therefore,the nozzle convergent section and throat material should consider the protection of ablation resistance.The theoretical and experimental results are useful and can be used as the reference when laval nozzle used on other aerospace projects.