高超声速大动压下整流罩分离测力风洞试验  

Wind tunnel force test of fairing separation in hypersonicand high dynamic pressure situation

作　　者：钟俊[1] 林敬周[1] 解福田[1] 赵健 ZHONG Jun;LIN Jingzhou;XIE Futian;ZHAO Jian(Hypervelocity Aerodynamics Institute of China Aerodynamics Research andDevelopment Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000

出　　处：《实验流体力学》2024年第2期98-106,共9页Journal of Experiments in Fluid Mechanics

摘　　要：针对高超声速试验模型整体式整流罩的反推火箭拔罩分离问题,开展了反推火箭喷流模拟方法和风洞测力试验装置设计研究,试验模拟了马赫数5、动压33 kPa时整流罩反推喷流干扰效应和分离距离影响,获得了反推喷流和分离距离影响下的整流罩气动特性。试验研究表明:反推火箭拔罩分离过程中,喷流干扰作用主导了整流罩的气动特性,使得法向力系数、轴向力系数和俯仰力矩系数分别出现了44.5%、32.4%和198.6%的最大变化量;在负迎角下,整流罩压心前移显著,使得静稳定设计的整流罩呈现出静不稳定性,不利于整流罩安全分离;分离距离越大,分离距离变化对整流罩气动特性的影响越弱;将分离初始迎角限定为小的正迎角,整流罩在分离过程中容易保持姿态稳定,有利于整流罩安全分离。For the problem of an integral fairing separating from a hypersonic testdemonstrator in a high dynamic situation,the reverse-thrust jets simulation method and windtunnel force test model design have been developed,to meet the requirements of simulating thejets interaction effect and separation distance influence in the hypersonic wind tunnel.Thefairing’s aerodynamic characteristics,including the jets interaction effect and the separationdistance influence,were obtained by the strain balance in circumstances where the Mach numberof the free-stream was 5 and the dynamic pressure was 33 kPa.The study indicates that the jetsinteraction effect dominates fairing’s aerodynamic characteristics in the separation process.Themaximum coefficients’variation of the normal force,axial force and pitching moment are 44.5%,32.4%and 198.6%respectively.The pressure center moves forward obviously,making the fairingwith designed static stability appears un-stability features in the minus attack angles.Theinfluence of the separation distance on fairing’s aerodynamic characteristics becomes weaker asthe separation distance increases.Using a small positive angle as the initial separation attackangle is conducive to keep a stable attitude for the fairing,which is beneficial to separationsecurity during the separation process.

关 键 词：整流罩分离 反推火箭喷流 天平测力试验 大动压 高超声速 

分 类 号：V211.71[航空宇航科学与技术—航空宇航推进理论与工程]