空气动力对飞机内藏式导弹分离轨迹影响的低速风洞试验研究  

A Test Research in Wind Tunnel for AerodynamicLoads Effect on Separation Trajectories of TheInternal Missile of Fighter

作　　者：王勋年[1] 李军[1] 刘晓晖[1] 

机构地区：[1]中国空气动力研究与发展中心

出　　处：《流体力学实验与测量》1999年第2期38-43,共6页Experiments and Measurements in Fluid Mechanics

摘　　要：在４ｍ×３ｍ低速风洞中研究了空气动力对战斗机内藏式导弹弹射分离轨迹的影响。采用简单网格法测量了导弹在干扰流场中的气动力，进行了分离轨迹估算，用捕获轨迹试验得到了分离轨迹，选定了最佳弹射力参数。试验结果表明，实验导弹安全分离必须采用弹射力，气动俯仰力矩是影响导弹姿态的重要因素，气动力对分离位置影响较小。This paper introduces a test research for separation trajectories of a fighter internal missile in 4m×3m low speed wind tunnel.The test model is a fighter with canard wing layout and an internal missile.Aerodynamic loads of the missile are measured at points of simple grid in disturbed flow field.Based on test result of the simple grid,separation trajectories of the missile are estimated.The separation trajectories have been obtained by CTS test in the tunnel.The optimum parameters of ejection have been found through calculation and test.Results of the investigation show that the internal missile must be ejected off the fighter to assure flight safety.Pitch moment is the main factor determining the attitude of the missile.Pitch damping reduces variation of pitch angle of the missile.Aerodynamic loads dont seriously affect the separation position of the missile.

关 键 词：飞机外挂物 外挂物分离 气动干扰 风洞试验 

分 类 号：V211.46[航空宇航科学与技术—航空宇航推进理论与工程] V211.7