【作者】 郭经经；

【导师】 齐乃明；

【作者基本信息】 哈尔滨工业大学 ， 飞行器设计， 2009， 硕士

【摘要】 本文针对目前流动控制的两种主要方式,即局部加热控制和磁流体控制,分别对高超声速飞行器前体/进气道虚拟前罩流动控制,前体/进气道MHD控制和后体/尾喷管的虚拟舵流动控制进行了数值试验原理验证和局部控制变量的控制特性研究。具体工作如下:对于飞行器前体/进气道虚拟前罩流动控制,本文在虚拟前罩局部加热控制流场的原理下,确定了虚拟前罩的流动控制计算验证模型,数值计算方法和计算网格结构。通过数值仿真二维的高超声速进气道溢流条件下流场结构和不同控制变量下的性能参数,得到二维的飞行器/前体流动控制性能,说明了主要的控制变量变化对进气道性能的影响。对于飞行器前体/进气道磁流体流动控制,本文研究了电子束注入形成局部可控等离子体的机制和数学模型,建立了外加磁场对其进行加速减速的计算模型;建立MATLAB与FLUENT的局部计算域数据交换进行耦合求解MHD进气道流场控制的计算平台;通过算例验证了模型的有效性,并计算了在控制位置一定时,能量注入大小的流动控制特性。对于飞行器后体/尾喷管虚拟舵控制:研究了通过虚拟舵(局部加热)来进行尾喷管推力、升力控制及俯仰力矩控制的有效性。建立了虚拟舵控制的数学模型,二维的计算模型和计算网格结构;通过FLUENT计算在不同的能量注入形状和能量注入大小的情况下,验证虚拟舵提高飞行器/后体尾喷管特性和配平俯仰力矩的有效性,并获得了控制参数的特性。更多还原

【Abstract】 To improve scramjet propulsion characteristics, this study utilizes two major flow control methods, namely, energy input control and magnetohydrodynamics (MHD) flow control, to control flow flied patterns in such three fields as hypersonic vehicle forebody/inlet virtual cowl flow control, hypersonic vehicle forebody/inlet MHD flow control, and hypersonic vehicle afterbody/nozzle flow control. Numerical computation principles are established and characteristics of control parameters for each application are studied.First, a virtual cowl control governing equations are explored, for working Mach numbers lower than designed Mach numbers. Computing models, both physical and geometric, are constructed. Validation cases are decided and 2-D computations are executed. Results validate computation methods and accuracy, inlet flow spillage of studied conditions are mitigated, and more importantly inlet performance characteristics are improved. Characteristics for controlling parameters in terms of energy addition amount and heating region locations are presented and analyzed.Second, for working Mach number higher than designed Mach number, MHD flow control principles are studied. Via analysis on air ionization process and FLUENT governing equations, computing platform of a partial coupling methods are constructed. The platform is based on interaction of data between MATLAB and FLUENT. Computing cases validate the computing platform and indicate that MHD flow control has effective controlling character at non-designed flying condition. Controlling parameter characteristics are also studied.Finally, a heating region is introduced to scramjet nozzle in order to provide a lift and thrust controlling method. Through establishment of mathematic models and 2-D computing models, validating cases are computed in FLUENT with energy addition via a UDF attachment. Results show that this heating region has effective controlling characteristics.更多还原