高超声速风洞子母弹分离干扰测力试验技术  

Hypersonic wind tunnel interference force test of sub-munition reentry separation

作　　者：赵忠良[1] 龙尧松[2] 余立[3] 王玉花[3] 白本奇[3] 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系,北京100083 [2]中国三江航天集团设计所,湖北武汉430035 [3]中国空气动力研究与发展中心高速所,四川绵阳621000

出　　处：《流体力学实验与测量》2004年第3期32-35,共4页Experiments and Measurements in Fluid Mechanics

摘　　要：本文给出了子母弹模型在高超声速风洞中的分离干扰测力的试验方案、试验系统设计、网格位置、天平研制和干扰试验结果。试验马赫数为6.97;模型迎角范围为-20°～20°;试验充分反映了母弹模型的头部激波对子弹模型的干扰特性。试验结果表明:法向力、轴向力、俯仰力矩及压心测值规律正确、量值可靠,为开展高超声速风洞CTS试验技术奠定了良好的技术基础。The implement scheme, test system design, sub- missile position to reentry, balance of sub-munition and test results for interference force test of sub- missile in FL-31 hypersonic wind tunnel are presented. The test Mach number is 6.97, and the angles of attack of the model from - 20° to 20°. The interference characteristic of the bow shock on the sub-munition model is described. It is shown that the testing data of normal force, axial force, pitching moment and center-of-pressure are reasonable and reliable. This research has paved the way for hypersonic CTS technique.

关 键 词：高超声速风洞 子母弹分离 干扰测力 风洞试验 

分 类 号：TJ414.5[兵器科学与技术—火炮、自动武器与弹药工程]