舰载机弹射起飞上升段控制律研究

Control Law for Climbing Stage of Carrier-Based Aircraft in Catapult-Assisted Take-Off

针对舰载机的安全弹射起飞要求,研究了弹射起飞上升段控制律设计问题。分析了常用弹射装置原理以及弹射起飞的工作流程。构建了弹射起飞过程中的上升段相关数学模型,包括某型舰载机的纵向模型、前起落架突伸结构和阵风模型。设计了舰载机起飞离舰后上升段的飞行姿态控制律,在仿真中将加速滑跑阶段的各种因素转化成初始条件,同时分析了阵风干扰对上升段飞机飞行特性的影响。仿真结果表明:设计的姿态控制律可以改善舰载机在离舰上升段的姿态,抵抗气流干扰等因素的影响,提高弹射起飞的安全性。

According to the safety requirements of catapult-assisted take-off,the control law design for the aircraft in the climbing stage was studied.The principle of a common catapult device was studied and the process of catapult-assisted take-off was introduced.The mathematic models in the climbing stage were established,including the model of longitudinal small perturbation equations of the aircraft,the sudden stretch structure of the nose gear and the gust disturbance.The attitude control law of the climbing stage was designed.In simulation,the initial value was based on the influence of different factors in speeding stage.The influence of the gust disturbance on flight performance of the aircraft in its climbing stage was also analyzed.The results of simulation showed that the designed control law can improve the aircraft attitude in the climbing stage,decrease the adverse effect of gust disturbance,and thus can enhance the security of the catapult-assisted take-off.