一种低速情况下无尾飞翼飞机航向控制方法  

A Yaw Control Method for Tailless Flying Wing Aircraft under Low Speed Condition

作　　者：屈晓波[1] 章卫国[1] 史静平[1] 倪烨斌 

机构地区：[1]西北工业大学自动化学院,陕西西安710072

出　　处：《西北工业大学学报》2015年第1期70-75,共6页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(61374032);陕西省自然科学基金(2013JQ8026)资助

摘　　要：无尾飞翼飞机通常使用开裂式阻力方向舵或者嵌入式操纵面来解决其航向控制问题。开裂式阻力方向舵对飞机的航向控制机理与传统方向舵不同,其舵效随舵偏角的变化呈非线性特性,且在较大迎角时会产生操纵反效现象,诱发航向振荡,产生飞行事故。针对此问题,利用CFD方法分析了某小型无尾飞翼飞机开裂式阻力方向舵的操纵特性,提出一种基于迎角反馈的开裂式阻力方向舵预偏差动控制方法,并进行了非线性数值仿真和试飞验证。结果表明:该方法可以改善开裂式阻力方向舵的非线性特性,解决操纵反效问题,增强无尾飞翼飞机低速飞行时的航向控制性能。The yaw of a tailless flying wing aircraft （TFWA） is usually controlled with a split drag rudder or spoiler slot deflector. The yaw control mechanism of the split drag rudder is different from that of the traditional rudder in that the former＇s rudder effect is nonlinear as the deflection varies. The split drag rudder may produce control rever- sal when the TFWA has large angle of attack, causing directional oscillation and a flight accident. Therefore we use the CFD method to analyze the control characteristics of the split drag rudder of a certain miniature TFWA and pro- pose a method for dynamically controlling the biased deflection of the split drag rudder based on the angle of attack feedback, which is then verified through nonlinear numerical simulations and flight tests. The simulation and test re- sults and their analysis show preliminarily that our method can reduce the nonlinearity and control reversal of the split drag rudder and enhance the yaw control performance of the TFWA under the low speed condition.

关 键 词：无尾飞翼飞机 开裂式阻力方向舵 航向控制 非线性 操纵反效 

分 类 号：V249[航空宇航科学与技术—飞行器设计]