战术导弹非对称涡控制技术研究

Numerical Aerodynamic Research of Asymmetric Vortice Control Based on Tactical Missile

为开展非对称涡主动流动控制技术在战术导弹气动设计领域应用研究,采用有限体积法求解N-S方程,数值模拟了导弹和微型扰流块的超音速耦合流场。结果表明:体积微小的扰流块能使导弹产生非常可观的侧向力,同时,对导弹其它气动特性影响很小。这为利用"开-关控制"的微型扰流装置对导弹进行飞行姿态控制,提高侧向机动能力提供了理论依据。

In order to research the application of asymmetric vortice control to tactical missile,the N-S equations were solved using finite volume method and the numerical studies were performed for supersonic flow past a tactical missile equipped with miniature spoiler blocks.The results show that the side forces induced by the miniature spoiler blocks are powerful and the effects on other aerodynamic characters are small.This supports the idea of using small devices with ＂on-off＂ ability on tactical missile to control the flying attitude and improve the side maneuverability.