大展弦比飞翼构型飞机阵风载荷减缓控制

Gust load alleviation control of aircraft with large ratio flying wing configuration

大展弦比飞翼构型具有优越的气动和隐身特性,但由于构型原因无法配置常规操纵面,因此常规构型飞机的阵风减缓控制方法不再适用.研究了大展弦比飞翼构型飞机新型多操纵面的典型配置方案,同时对其应用直接升力方法进行阵风减缓控制时的新的操纵及控制原理进行了分析.采用极点配置方法设计了相应的阵风减缓控制律,并且通过有关的准则检验了该控制律的效果.最后通过计算并比较开环和闭环飞机的频谱响应,验证了该控制律减缓飞机阵风响应的有效性.

The configuration of flying wing aircraft with large aspect ratio is advantageous on the characteristic of aerodynamics and stealth, but due to lack of conventional elevator and rudder, gust load alleviation control method for the aircraft with conventional configuration is not suitable anymore. The characteristics of representative arrangement of control surfaces on an aircraft with flying wing configuration were discussed ; also the specialty with configuration of flying wing in gust alleviation system was analyzed, when applying the method of direct lift force control. To improve a flying wing aircraft＇s response to atmospheric turbulence, a control law of the control system was designed, using the method of poles configuration of invariable characteristic structure. At last, both the aircraft＇s open-loop and closed-loop responses to atmospheric turbulence were calculated, analyzed and compared; meanwhile, the aircraft＇s ride quality was given and compared to some criterion. Results show that the control law given by the method can improve the aircraft response to atmospheric turbulence effectively.