面对称重复使用运载器尾部喷流风洞试验  

Wind tunnel experiment on supersonic exhaust flow of symmetric reusable space vehicles

作　　者：刘杰平[1] 马元宏 蔡巧言[1] 任少洁 王苏宁 杨子盟 LIU Jieping;MA Yuanhong;CAI Qiaoyan;REN Shaojie;WANG Suning;YANG Zimeng(China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]中国航天空气动力技术研究院,北京100074

出　　处：《航空学报》2021年第2期50-59,共10页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(U20B2006)。

摘　　要：研究面对称重复使用运载器尾部发动机的喷流干扰特性对于飞行器设计具有重要意义。在中国航天空气动力技术研究院的FD-12风洞中开展了亚/跨声速飞行条件下的喷流试验。试验使用常温压缩空气作为喷流介质模拟发动机的高温燃气,采用的相似参数包括:飞行器的几何外形尺寸、飞行器的飞行马赫数、发动机喷管的出口马赫数、发动机喷流与自由来流静压比。试验结果表明了发动机喷流对全飞行器气动特性和体襟翼铰链力矩的影响随来流马赫数、喷管、体襟翼偏角等因素的变化规律。The characteristics of engine-jet interference are highly significant for the design of symmetric reusable vehicles.A jet experiment under the condition of subsonic/transonic flight was performed in the wind tunnel FD-12 at China Academy of Aerospace Aerodynamics.This experiment used the normal temperature compressed air as the high temperature fuel gas of the engine-jet.Similar parameters of the experiment include geometry dimensions of the vehicle,flight Mach number of the vehicle,Mach number of the exit on the engine nozzle,and the static pressure ratio of the engine nozzle exit to the faraway inflow.Experimental results show that the engine-jet effect on the aerodynamic characteristics of the vehicle and the hinge moment of the body flap varies with the Mach number of inflow,the deflection angle of the nozzle,and the body flap.

关 键 词：面对称重复使用运载器 发动机喷流 体襟翼 亚/跨声速 风洞试验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]