基于风洞虚飞实验的双向飞翼纵向控制研究

Research on longitudinal control of bidirectional flying wing based on wind tunnel virtual flight test

双向飞翼飞行器作为针对空天飞行器宽速域飞行要求所提出的新概念飞行器,其独特的几何外形和模态转换方式为解决宽速域高升阻比设计矛盾提供了新的研究思路。首先,设计了一种双向飞翼飞行器,并开展风洞静态测力实验和虚飞实验,通过实验发现此类飞行器纵向静不稳定裕度过大,而纵向控制舵面不能提供足够的纵向控制能力,从而导致飞行器的纵向可控姿态角处于一个偏小的范围内。针对该问题,采用舵面吹气主动流动控制技术分别对低速及高速两个模态下纵向姿态的控制效能进行研究。研究结果表明,舵面吹气控制能有效提高两个模态下升降舵对纵向姿态的控制效能,同时提高纵向姿态角可控范围。

Bidirectional flying wing aerocraft is a new concept proposed for the wide-speed range flight requirements of aerospace vehicles.Its unique geometric shape and mode conversion method provide new research ideas for solving the design contradiction of wide-speed range and high lift-drag ratio.Firstly,a bidirectional flying wing aerocraft was designed,and wind tunnel static force measurement experiments and virtual flight experiments were carried out.Through the experiments,it was found that the longitudinal static instability margin of this type of aerocraft is too large,and the longitudinal control rudder can not provide sufficient longitudinal control capability,as a result,the controllable attitude angle in the longitudinal direction of the aerocraft is in a relatively small range.Aiming at this problem,the rudder blowing active flow control technology was adopted to study the control effectiveness of the longitudinal attitude in the two modes respectively.The results show that the rudder blowing control can effectively improve the control efficiency of the elevator in the longitudinal attitude in the two modes,which also heightens the controllable range of the attitude angle in the longitudinal direction.