摘要
根据舰载飞机弹射起飞上升段的纵向动力学方程和迎角自动控制的升降舵偏角调节规律，计算了Ａ－６飞机的迎角、俯仰角、飞机重心垂向位置等随时间的变化。确定了传递系数ｋα，ｋθ的合适范围。讨论了以最大容许的下沉量作为约束的指令迎角的量值。提出了舵面偏角调节规律的一种设计方法。
in this paper, variations of the angle of attack, the attitude and the vertical C. G. location with the time for the airplane A-6 are calculated accordiug to the longi tudinal dynamic equations and accommodation rule of elevator deflection of angle of attack autopilot for a carrier -based airplane in climb phase during catapult launch. The proper amount of the transfer coefficient k_α and k_θ are determined. The magnitude of the command angle of attack is discussed as constraint by maximum amount of sink allowable. A design method about elevator deflection accommodation rule is presented.
出处
《飞行力学》
CSCD
北大核心
1996年第1期41-47,共7页
Flight Dynamics
关键词
舰载机
迎角
自动控制
指令迎角
弹射起飞
Carrier-based airplane Atomatic control of angle of attack Sink Command angle of attack
