子弹束后向抛入底部流场的风洞试验  

Wind Tunnel Tests of Bound Submissiles Ejected Rearward Into Base Flow Field

作　　者：居贤铭[1] 吴甲生[1] 苗瑞生[1] 

机构地区：[1]北京理工大学飞行器工程系

出　　处：《北京理工大学学报》1994年第1期81-86,共6页Transactions of Beijing Institute of Technology

摘　　要：介绍了子弹束后向抛入底部流场的风洞试验：后抛观察试验、测力试验和测压试验．后抛观察试验时子弹束和天平之间用尼龙绳连接，观察子弹束后抛运动过程．测力试验时改用刚性连杆连接，测量子弹束所受的轴向力，通过测压管测量底部流场沿轴线的正、反向压力，试验马赫数为３．５和４．０；攻角为０°．试验表明，作用在后抛子弹束上的气动轴向力指向后方，子弹束在底部流场中加速向后运动．适宜的解捆区域是底面后（１．０～２．０）ＤＢ．Wind tunnel tests of bound submissiles ejected rearward into the base flow field are introduced. They include observations of the process of rearward ejection, as well as force and pressure measurements. Nylon ropes were to connect the bound submissiles with the balance during the observation of rearward ejection, in order to observe the process of motion of the ejected bound submissiles. A rigid connecting rod was used to replace the nylon ropes in the force test to measure the axial force borne by the bound submissiles. Both the positive and negative pressures along the axis in the base flow field were measured with Pilot tubes. Mach numbers ed ware 3.5 and 4.0 and the angle of attack 0°These tests demonstrate that the axial aerodynamic force acting on the ejected bound submissiles is in the rearward direction As a result, it can be concluded that the motion of the bound submissiles in the base flow field is ated rearward, and the suitable disbanding range for the bound submissiles is (1.0-2.0)DB behind the base section

关 键 词：风洞试验 后抛 子弹束 底部流场 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]