飞翼布局飞机舵面偏转速率设计

舵面偏转速率的大小是飞机飞行控制系统设计的重要约束之一.当偏转速率饱和时,在外界干扰或操纵下,飞机可能进入自激振荡(PIO)状态,导致飞行品质下降.建立了飞翼布局飞机舵面偏转速率限制值的设计方法,给出了某大展弦比飞翼布局飞机的三轴主操纵面偏转速率设计的算例,分析了偏转速率限制对飞机动态响应特性的影响及其与飞机本体气动导数、转动惯量、展弦比构成的组合参数间的关系.结果表明:对于大展弦比飞翼布局飞机而言,其横向主操纵面偏转速率限制值要求最高,纵向次之,航向最低.研究方法和结果可用于飞翼布局飞机的操纵舵面与飞行控制系统初步设计时参考. 

Design of actuator rate for flying wing aircraft

The actuator rate is one of the important constraints in designing flight control system. When the actuator rate is saturated, the disturbed aircraft or the aircraft under control may go into pilot induced oscillation (PIO) resulting in lowering the flying quality. The design method of limiting the actuator rate value for flying wing was built. The design examples of actuator rate for the triaxial main control surface of high-aspect-ratio flying wing aircraft were introduced. The effects of actuator rate limit on dynamic response characteristics of the aircraft and a combined parameter composed of aerodynamic derivative of aircraft, moment of inertia, and aspect-ratio were analyzed. The result indicates that for aircraft with high-aspect-ratio the requested actuator rate of roll control surface is the highest, later is in the pitch control and that of the directional control surface is the lowest. The research method and results can be used to guide the preliminary design of actuator and flight control system for flying wing aircraft.