项目名称: 变推力固液火箭发动机燃烧过程研究
项目编号: No.51206007
项目类型: 青年科学基金项目
立项/批准年度: 2013
项目学科: 工程热物理与能源利用学科
项目作者: 田辉
作者单位: 北京航空航天大学
项目金额: 25万元
中文摘要: 本项目针对H2O2/HTPB固液火箭发动机,开展变推力固液火箭发动机瞬时燃速规律、静动态特性和非稳态流场结构的研究。考虑药柱通道尺寸、燃烧室压强、氧燃比等因素,建立瞬时燃速模型,研究燃速的控制机理;在瞬时燃速模型的基础上,建立变推力固液火箭发动机的静态模型,研究燃速、比冲、特征速度等静态参数在推力调节过程中的变化规律及其影响因素;考虑氧化剂蒸发时滞、燃料热解时滞和燃烧时滞等因素,建立变推力固液火箭发动机的动态模型,研究响应时间、超调量等动态响应参数及其影响因素;考虑液体氧化剂及蒸发、燃料的热解、燃面的退移和化学反应,开展变推力固液火箭发动机非稳态流场的数值仿真,研究非稳态流场结构及其变化规律。通过本项目研究,可以深入了解和掌握变推力固液火箭发动机的燃速规律和静动态特性,揭示变推力固液火箭发动机的流场结构,为变推力固液火箭发动机的发展和应用奠定基础。
中文关键词: 变推力固液火箭发动机;燃速;响应特性分析;数值仿真;推力调节技术
英文摘要: The transient regression rate, static and dynamic characteristics, and transient flow fields of variable thrust hybrid rocket motor are studied in this program. The motor employs hydrogen peroxide as oxidizer and HTPB as the fuel. The model of transient regression rate is established and the control process of regression is studied considering the effect of fuel port size, combustion pressure and oxidizer/fuel ratio. The static modeling is conducted to investigate the variation and influence factors of regression rate, specific impulse and characteristic velocity. Dynamic modeling is performed to investigate the response and overshoot of the hybrid rocket motor considering the effect of vaporization delay, thermal lags in solid fuel and diffusion combustion delay. A 2D axisymmetric transient numerical simulation is conducted to calculate the transient combustion flow field in the variable thrust hybrid rocket motor. The results of this program would provide a strong basis for the development and application of the variable thrust hybrid rocket motor.
英文关键词: throttleable hybrid rocket motor;regression rate;response performance;numerical simulation;throttling technology