差动平尾和方向舵辅助滚转的横航向数学模型研究

Study of the Lateral Model Adopt Differential Horizontal Tail and Rudder Effect

为了解决高速飞行时副翼效率不足的问题 ,现代战斗机在横航向操纵中广泛采用了差动平尾和方向舵辅助滚转 ,这样适用于常规操纵飞机的横航向运动方程已不能应用于此类飞机。本文重新推导了针对此类飞机的横航向运动方程和传递函数 ,并对模型进行了验证。可以为飞行品质分析、飞行模拟和空战仿真提供可用的数学模型。

Due to the differential horizontal tail and rudder are adopted to the roll control in many modern fighter planes, the motion equation and transfer functions suited the traditional fighters can't be used for them. In this paper, the new motion equation and transfer functions suitable for these fighters were deduced, then they were verified by using the actual data.