飞翼布局飞行器航向射流控制方案优化

Scheme optimization of yaw control of flying-wing aircraft based on jet flow control

由于飞翼布局飞行器取消了垂尾,其航向控制困难。为辅助和优化航向控制,基于射流控制技术设计了多种激励方案。设计并制作了航向射流控制激励器,通过风洞测力实验和二维数值模拟,对各方案的控制效果和作用机理进行分析,并选取出最优控制方案。研究结果表明:相同射流动量系数下,产生阻力比施加推力更容易获得偏航力矩。当激励开启后,射流包含与来流相逆的分量越多,与来流作用越明显,形成的分离区越大,控制效果越好。其中前对称吹气为最优控制方案,可以产生约70°阻力舵偏转效果,且力矩耦合程度较小。

There are difficulties in yaw control of a flying-wing aircraft due to the cancella-tion of vertical tail. A variety of control schemes were designed based on the jet flow control tech-nology to assist in and optimize the yaw control. The jet control actuator was designed and manu-factured. Through the wind tunnel force measurement experiment and two-dimensional numerical simulation, the control effect and mechanism of each scheme were analyzed, and the optimal control scheme was selected. The results showed that under the same jet momentum coefficient,it was easier to obtain yaw moment by producing resistance than by applying thrust. After turning on the excitation,the more inverse components the jet contains in relation to the incoming flow,the more obvious the interaction with the incoming flow;the larger the separation zone formed,the better the control effect. The forward symmetric blowing was proved to be the optimal control scheme,which can produce about rudder effect equivalent to a split drag rudder deflection of 70°,and the coupling degree of moment was small.