论文部分内容阅读
采用测力、测压以及粒子图像测速(PIV)流场测试试验技术,针对细长弹体大攻角时前体非对称涡控制的问题,应用连续有源微吹气与双出口合成射流微吹气手段,对前体非对称涡控制开展了试验研究。试验结果表明:连续有源微吹气控制时,在不同攻角选择适当的吹气流量可以将侧向力控制为零;双出口合成射流微吹气控制时,改变控制电压可以起到侧向力比例控制的效果。流场测试结果显示,弹体产生侧向力时背风涡为非对称结构,合成射流控制具有一定的控制频选特性。低频控制时,涡左右摆动,时均结果为对称分布;高频控制时,左右涡位置稳定,为对称分布。
Aiming at the problem of precursor asymmetric vortex control in the large angle of attack of slender projectile with force measurement, manometry and particle image velocimetry (PIV) flow field test, Inflatable means, the precursor asymmetric vortex control conducted a pilot study. The experimental results show that the lateral force can be controlled to zero when the continuous active micro-blowing control is selected by choosing proper blowing air flow rate at different angles of attack. When controlling the micro-blowing control of double-outlet synthetic jet, the control voltage can be changed sideways Force proportional control effect. The flow field test results show that the levitation vortex is asymmetric structure when the projectile lateral force is generated, and the synthetic jet control has certain control frequency selection characteristics. In the low-frequency control, the vortex swings from left to right, and the average result is symmetrical. In the high-frequency control, the left and right vortices are located at a stable position and symmetrically distributed.