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 dont seriously affect the separation position of the missile.
出处
《流体力学实验与测量》
CSCD
1999年第2期38-43,共6页
Experiments and Measurements in Fluid Mechanics
关键词
飞机外挂物
外挂物分离
气动干扰
风洞试验
aricraft store
store separation
aerodynamic interference
wind tunnel test
