可变形翼导弹动态气动特性的仿真研究

导弹发射后,飞行高度从近地面到高空域,气压、温度变化巨大,同时飞行马赫数也从低速到超声速、高超声速。在不同飞行阶段稳定性能和升阻比需求不同,对导弹气动性能要求不同。固定外形导弹的气动性能难以适用于不同的飞行任务,而可变形翼导弹通过改变翼面的形状,实现外形上的变化,从而适应不同的作战环境。通过分析可变形收缩弹翼不同收缩速度(快速、中速、慢速3种状态)的气动性能,研究了导弹气动性能随弹翼收缩速度变化的规律,揭示了升力系数和阻力系数随弹翼的收缩速率的线性变化特征。同时还分析了变形前后导弹附近流场的压强、速度和温度的变化,以及这些物理量对导弹的影响。结果表明,伸缩翼改变了翼面面积和展弦比,弹翼伸长时具有高升阻力,适合亚声速巡航,弹翼收缩可以减小高马赫数飞行时阻力,提高导弹射程。

Simulation Study on Dynamic Aerodynamic Characteristics of Deformable Wing Missile

After the missile is launched, the flight altitude changes from near ground to high airspace, and the air pressure and temperature change greatly. At the same time, the flight Mach number also changes from low speed to supersonic and hypersonic. The aerodynamic performance of fixed shape missile is difficult to adapt to such changing flight environment. The shape of the deformable wing missile can be transformed by the wing surface deformation, so as to adapt to different combat environments. In this paper, by analyzing the influence of different wing contraction velocity (fast, medium and slow), the aerodynamic performance of missile varying with wing contraction velocity is studied. It is found that the lift coefficient and drag coefficient change linearly with wing contraction velocity.At the same time, the changes of pressure, velocity and temperature in the flow field around the missile before and after deformation are analyzed, as well as the influence of these physical variables on the missile. The results show that the telescopic wing that changes the area and aspect ratio of the wing has high ratio of lift to drag when the wing is extended, which is favorablefor subsonic cruise.Meanwhile, the wing contraction can reduce the drag at high Mach number and improve the whole flight range of missile.