鸭式布局旋转导弹舵翼干扰问题气动特性研究

Aerodynamic Research on the Problem of Canard-Wing Interference of Rolling Airframe Missile

本文通过风洞旋转测力试验针对鸭式布局旋转导弹的舵翼干扰问题进行了研究。采用风洞试验方法对于不同舵翼周向角气动数据进行分析,得到转速随舵翼周向角变化规律;运用四点、八点平均获得的法向力系数与旋转情况下测得的平均法向力系数基本一致,可采用准定常方法解决旋转弹纵向气动问题;小攻角下洗流干扰强烈,使得纵向气动性能波动较大;通过研究得到了舵翼干扰造成的马格努斯效应随转速及攻角变化的波动规律,马格努斯力与力矩在中等攻角下随攻角非线性变化较大且产生的绝对值也较大。

This article demonstrated the research work on the problem of canard-wing interference of rolling airframe missile via wind tunnel rotating force measuring experiment.According to the result of the wind tunnel experiment,the variation law of rolling rate with different canard-wing setting angle is obtained.The results obtained by four point average method or eight point average method show that the longitudinal aerodynamic problem of rolling airframe missile can be solved with quasi-steady method.The strong interference from down wash under small attack angle condition is one of the main causes which lead to large fluctuation of the longitudinal aerodynamics.The research concluded a rule of the Magnus effect caused by canard-wing interference refer to the rolling rate and change of attack angle.Magnus force and Magnus moment at medium angle of attack have a strong nonlinearity and large absolute value.