三维内收缩前体/进气道设计参数影响规律研究  

Effects of design parameters on hypersonic inward turning inlet and forebody

作　　者：徐锦[1] 罗金玲 戴梧叶 李超 

机构地区：[1]北京机电工程研究所,北京100074 [2]北京空天技术研究所,北京100074

出　　处：《空气动力学学报》2014年第5期646-653,共8页Acta Aerodynamica Sinica

摘　　要：采用有旋特征线理论求解壁面压力分布可控的内收缩基准流场,再结合流线追踪,设计了五种不同位置的矩形捕获型线的三维内收缩前体/进气道。通过数值模拟,研究了进气道捕获型线的不同径向与周向位置对进气道性能与飞行器前体纵、航向气动性能的影响规律。结果表明:三维内收缩前体/进气道产生了较大的力与力矩,对飞行器纵、航向操稳特性均有影响;捕获型线径向位置远离中心体时,有利于改善前体/进气道的纵、航向静稳定性;捕获型线沿周向位置变化时,对纵向静稳定性影响较小,捕获型线纵向面对称时,溢流口朝下,能显著提高有攻角时进气道的流量系数,但会产生较大抬头力矩,航向静稳定性也变差。The hypersonic inward turning inlet has characteristics of high mass capture capability and compression capability,meanwhile it has direct influences on the design of the flight vehicle control ability and stability,therefore the design of forebody/inlet integration is of critical importance.In the paper,axi-symmetrical basic flow fields with controlled pressure distribution used for the designing of hypersonic inward turning inlet was established using the rotational method of characteristics.In combination of the streamline tracing technique,five forebodies/inward turning inlets were designed.The influences of different radial and circumferential positions on the inlet and forebody performances in longitudinal and course were＆amp;nbsp;studied numerically.The results show that the forebodies/inlets generate large aerodynamic forces and mo-ments which influence both the flight vehicle control ability and stability.With the capture line being off from the center body,the performances of the flight vehicle static instability both longitudinal and lateral are improved;when the capture line changes in the circumferential direction,the degree of longitudinal static stability remains nearly unchanged;when the capture line is symmetrical about the longitudinal plane,mass flow ratio increases significantly compared to those with asymmetrical capture lines,but the penalty is the deterioration of the performance of course static stability.These conclusions presented in this paper have val-uable contributions to the design of flight vehicles with high performance of handling and stability.

关 键 词：高超声速内收缩进气道 流线追踪 前体/进气道一体化 气动性能 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]