摘要
两级入轨空天飞行器(TSTO)并联级间分离存在复杂的气动干扰现象,理解气动干扰特性对分离安全性设计和评估具有重要意义。本文在Φ0.5 m高超声速风洞中开展了基于压敏漆(PSP)与温敏漆(TSP)试验技术的级间气动干扰特性研究,解决了有遮挡条件下的压敏漆与温敏漆测量难题,获得了马赫数6条件下不同级间距的高分辨率大面积连续压力和温度分布特性。研究表明:轨道级头部激波直接入射至助推级壁面,与边界层相互干扰,诱导流动分离;入射激波与分离激波在级间区域会产生多次反射,形成三维复杂波系结构;随着分离距离增大,级间流场呈现从缝隙流到小通道流再到大通道流的流动特征,级间高压高温干扰区则呈现从前往后移动且峰值减弱的特点,这也是改变两级气动力/力矩特性、影响分离过程中两级位姿变化的主要因素。
There are complex aerodynamic interference phenomena in parallel stage separation of TSTO(two-stage-to-orbit)vehicles.Understanding the aerodynamic interference characteristics is of great significance for the separation safety design and evaluation of TSTO.In this study,the aerodynamic interference characteristics of the inter-stage flow has been studied in theΦ0.5 m hypersonic wind tunnel based on the test techniques of pressure sensitive paint(PSP)and temperature sensitive paint(TSP).By solving the difficulty of PSP and TSP measurement under shielding,we obtained a large area of continuous pressure and temperature distribution in high resolution at Mach number 6 for different separation distances.The results show that the head shock wave of the orbit stage directly hits on the surface of the booster stage model,then generates flow separation and multiple reflections between the stages,forming three-dimensional complex shock wave structures.With the increase of the separation distance,the flow field between the two stages presents flow features from small channel flow to large channel flow.The movement of the high pressure and high temperature interference zone between the two stages moves from front to back,with its peak value weakened,which is the main reason for the change of the aerodynamic/torque characteristics of the two stages as well as their pose variation during the separation process.
作者
解福田
张庆虎
林敬周
彭迪
陈磊
XIE Futian;ZHANG Qinghu;LIN Jingzhou;PENG Di;CHEN Lei(Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China;School of Mechanical and Power Engineering,Shanghai Jiaotong University,Shanghai 200240,China)
出处
《空气动力学学报》
CSCD
北大核心
2023年第5期98-108,I0002,共12页
Acta Aerodynamica Sinica
