高超声速再入飞行器的多孔流动控制

针对高超声速再入飞行器流动控制问题,提出一种头部进气、尾部排气的多孔流动控制概念。采用Fluent软件针对高超声速再入飞行器无孔模型、排气孔模型在马赫数为6,高度为25km状态下开展了三维雷诺平均N-S方程(RANS)数值模拟研究。结果表明:排气孔模型阻力系数略有增加,下排气孔(SH-DB)模型产生正的升力系数增量和低头力矩增量,上排气孔(SH-UB)模型产生负的升力系数增量和抬头力矩增量,实现了无活动气动面产生控制力矩的目的,为高超声速再入飞行器复合控制提供了参考。 

Flow control of hypersonic reentry vehicle based on multi-jets interaction

A concept of multi-jets flow control was proposed for a hypersonic reentry vehicle. The high pressure air behind the bow shock flowed into the tunnel through the multihole head, and then sprayed out through the downstream multi-jets arrays. The 3-D Reynold-averaged Navier-Stokes (RANS) simulations based on Fluent software were conducted to study the effect of multi-jets configuration at Mach number of 6,height of 25km. The results showed that the multi-jets flow induced a drag coefficient increment for both the side-hole down-bottom (SH-DB) case and the side-hole upper-bottom (SH-UB) case. The increment of lift coefficient and head-down moment was observed for the SH-DB case, and the decrement of lift coefficient and head-up moment was observed for the SH-UB case. This study provides a method of using non-movement aerodynamic control surface to produce control moment, and also a reference for combination control of hypersonic reentry vehicle.