考虑隐身约束的舰载飞翼无人机翼尖装置气动设计和分析

Aerodynamic design and analysis of tip devices on carrier-based fly-wing UAV with stealth constraints

在隐身要求约束下,设计了舰载飞翼无人机翼下增升装置。并针对未来尾流雷达探测的反隐身技术,分析了增升装置对尾流消弱的作用,从而提高了该探测方式的隐身效果。计算结果表明,该增升装置可以较好地增加升力、减弱诱导阻力、提高升阻比,并能起到减弱尾流的作用。最后分析了增升、减阻、消弱尾流的机理,解释了在大迎角条件下气动优化效果更好的原因,并与常规布局飞机翼尖小翼的作用作了对比。

In consideration of the constraints of shape stealth, a under-wing lift augmenter was designed for carrier-based fly-wing UAV wings. Regarding future anti-stealth technology, i . e. ,wake flow detection,the flow mechanism around the lift augmenter was analyzed,and the wake flow can be weakened by the lift augmenter,so as to avoid the deradar. The results show that this lift augmenter can effectively increase aerodynamic lift weakeninduced drag,and improve lift-drag ratio . Moreover,the augmenter has the effect on weakeningthe wake flow. Based on mechanism analysis, the current configuration, compared with conventional aircraft with winglet, has the advantages of drag reduction, lift increment, and weakened wake flow at farge angle of attack.