【作者】 王磊； 乐挺； 王立新；

【Author】 Wang Lei;Yue Ting;Wang LiXin;School of Aeronautic Science and Engineering,Beijing University of Aeronautics and Astronautics;

【机构】 北京航空航天大学航空科学与工程学院；

【摘要】 舵面时延大小是飞机飞行控制系统设计的重要约束之一。当舵面时延过大时,操纵输入不能及时作用飞机,在外界干扰或操纵下,飞机可能进入自激振荡状态,导致飞行品质下降,严重时危及飞行安全。本文建立了XX飞翼布局飞机舵面时延限制值的设计方法,从而计算出舵面时延限制值,在设计阶段作为舵机选择的依据,给出了XX飞翼布局飞机的三轴舵面时延设计的算例,分析了时延限制对飞机动态响应特性的影响。结果表明,对于XX飞翼布局飞机而言,其纵横向舵面时延限制值要求较高,航向较低。研究方法和结果可用于XX飞翼布局飞机的舵机选择与飞行控制系统设计时参考。更多还原

【Abstract】 The actuator delay is one of the important constraints in designing flight control system. When the actuator delay is long. The input cannot affect the aircraft in time. The disturbed aircraft may go into pilot induced oscillation(PIO) resulting in lowering the flying quality and even be dangerous. The design method of actuator delay for flying wing is built and we can choose the actuator by calculating the actuator delay in design phase. The design results of a XX flying wing are introduced and the effects of actuator delay on flying quality is analyzed in the article. The result indicates that the requested actuator delay of roll control and pitch control surface is the higher, the directional control surface is the lower. The research method and result can be used to guide the preliminary design of actuator and flight control system for flying wing.更多还原