论文部分内容阅读
快响应控制技术已成为高超声速飞行器发展的关键技术之一,具有极快响应、零质量特性的等离子体合成射流(PSJ)已在超声速流动控制方面初步显示出优异的控制能力,极有潜力应用于高超声速飞行器的快响应控制。基于等离子体合成射流的快响应特性,提出了高超声速飞行器等离子体合成射流快响应控制技术,并通过建立简化的高超声速导弹流场控制模型,对等离子体合成射流控制高超声速导弹进行数值研究。首先,理论分析了高超声速导弹流场的典型结构特征,导弹流场中存在3个特征流场结构。在此基础上,在导弹3个特征位置前面安装等离子体合成射流激励器,研究等离子体合成射流对高超声速流场结构的控制作用,分析由此导致的导弹表面压力分布、升阻特性以及俯仰力矩特性变化。数值仿真结果表明:等离子体合成射流对高超声速导弹外流场中膨胀波和斜激波都具有控制作用,使得波的强度均变弱,且对斜激波的控制效果更为显著;导弹流场结构及气动特性变化具有很强的射流跟随性,射流作用下的导弹流场变化响应时间非常短,仅为0.2ms;通过合理布置等离子合成射流激励器的位置,可以使得导弹表面压力分布快速改变,从而实现高超声速导弹姿态的快速控制。
Fast response control technology has become one of the key technologies for the development of hypersonic vehicles. The highly responsive, zero-mass plasma jet (PSJ) has shown initial superiority in supersonic flow control and has great potential for applications Fast response control of hypersonic vehicles. Based on the fast response characteristics of plasma jet, a fast response control technology of plasma synthesized jet for hypersonic vehicle was proposed. The numerical simulation of plasma jet control hypersonic missile was performed by establishing a simplified flow control model of the hypersonic missile. Firstly, the typical structural characteristics of the flow field of hypersonic missile are analyzed theoretically. There are three characteristic flow field structures in the missile flow field. On this basis, a plasma jet actuator is installed in front of the three characteristic locations of the missile to study the control effect of the plasma jet on the structure of the hypersonic flow field. The analysis of the surface pressure distribution, lift-drag characteristics and pitch Torque characteristics change. The numerical simulation results show that the plasma jet has a control effect on the expansion and slant shocks in the outer flow field of the hypersonic missile so that the intensity of the wave is weakened and the control effect of the oblique shock wave is more pronounced. The flow of the missile The field structure and the aerodynamic characteristics change have a strong jet followability. The response time of the jet flow field under the jet action is very short, only 0.2 ms. By reasonably arranging the position of the plasma jet exciter, the surface pressure distribution of the missile can be rapidly Change, in order to achieve fast hypersonic missile attitude control.