舰载机弹射起飞建模与控制  

Modeling and Control of Carrier- based Airplane During Catapult Launch

作　　者：王俊彦[1] 吴文海[1] 高丽[1] 张晓杰[1] 

机构地区：[1]海军航空工程学院青岛分院,山东青岛266041

出　　处：《飞机设计》2010年第2期10-13,共4页Aircraft Design

摘　　要：舰载机弹射起飞过程由舰面滑跑和离舰上升两个阶段组成,各阶段舰载机的受力与约束不同。根据两阶段舰载机的气动特性和运动特性,建立了一种通用的舰载机纵向动力学模型确定其离舰速度、离舰迎角和预置舵偏角,从而选择合适的控制策略完成弹射起飞上升阶段的自动控制飞行。以某型机为例,建立了全量非线性模型,并在此基础上设计了离舰上升阶段的控制方案。仿真结果表明,该模型与控制方案具有较好的控制效果。The catapult launch of carrier-based airplane contains two phases,i.e.shipboard run and climb phase.The forces and restrictions to the carrier-based airplane differ during launch.According to the different movements and aerodynamic characteristics,a general whole nonlinear model is established by study a certain carrier-based airplane,the take-off speed,take-off angle of attack and presetting elevator deflection are calculated,and finally a control scheme for climb phase is designed.Simulation shows the better performance of the model and control scheme.

关 键 词：舰载机 弹射起飞 动力学模型 自动控制飞行 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]