舰载飞机弹射起飞上升段的自动控制飞行

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平尾偏度调节规律，计算了Ａ－６飞机迎角，俯仰角，飞机重心垂向位置随时间的变化，结果表明，过舰首航迹下沉量随自动增稳系统的传统系数Ｋ增大而增加，Ｋａ的增大而减小。依据自动增稳系统对示例飞机的动态反应特性，下沉量和爬升率的影响，选择了合适的传递系数量值。文中以容许的最下沉量作为约束，讨论了该机的指令迎角大小，提出了平尾偏度调节规律的一种设计方法

Automatic Control Flight for a Carrier-Based Airplane in Climb Phase during Catapult Launch

Variations of the angle of attack,the attitude and the vertical C. G. location with the time for the airplane A-6 are calculated according to the longitudinal dynamic equations and the accommodation rule of the horizontal tail deflection of the automatically controlled angle of attack for a carrier--based airplane in the climb phase during the catapult launch.The results show that the sink over the bow will increase with the rise of the transfer coefficient K of the command augmentation stability system and decrease with.the rise of Ka.The proper amount of the transfer coefficient is chosen on the basis of the effect of the command augmentation stability system on dynamic response characteristics,and the sink and climb rate of the airplane. The magnitude of the command angle of attack is discussed by taking the maximum allowable amount of sink as a constraint. A design method for the tail defletion accommodation rule is presented.