亚跨声速风洞机弹干扰试验技术  

An experimental technique for missile-wing interference in sub-transonic wind tunnel

作　　者：刘明霞[1] 杨辉[1] 白葵[1] 

机构地区：[1]航天空气动力技术研究院,北京100083

出　　处：《空气动力学学报》2007年第1期80-84,共5页Acta Aerodynamica Sinica

摘　　要：介绍了一种利用小尺寸风洞进行亚跨声速挂弹/载机干扰试验的试验技术,该试验技术是在小尺寸风洞内进行挂弹/载机局部干扰试验,可以测量挂弹投放过程中作用于挂弹及其折叠尾翼上的气动力和舵效率。为验证该试验技术,选取了某空射型导弹进行了挂机干扰试验验证,试验前对局部干扰流场和完整干扰流场进行了数值计算,计算结果表明局部干扰流场与完整干扰流场流态基本一致。试验结果表明,小风洞对局部流场的模拟可以取得合理的试验结果,该试验技术具有可行性。An experimental technique for missile-wing interference in small-sized wind tunnel is presented. Using this technique, the aerodynamic force acting on the missile and rudder efficiency of the missile can be measured during the missile separation,To validate this experimental technique ,a standard configuration of missile is selected to measure the interference force between the missile and the wing. Before the test, a local interference flow field and the whole interference flow field are caculated, the result shows that the local flow field is accurate to describe the flow field near the missile. The wind tunnel test shows that using the small-sized wind tunnel and the local flow field simulation, the aerodynamic characteristics of the missl-wing interference can be measured. The experimental technique for missile-wing interference in small-sized wind tunnel is feasible.

关 键 词：机弹干扰 外挂分离 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]