| 舰载机弹射起飞建模与控制 |
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| 引用本文： | 王俊彦,吴文海,高丽,张晓杰.舰载机弹射起飞建模与控制[J].飞机设计,2010,30(2):10-13. |
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| 作者姓名： | 王俊彦 吴文海 高丽 张晓杰 |
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| 作者单位： | 海军航空工程学院,青岛分院,山东,青岛,266041 |
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| 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。
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| 关 键 词： | 舰载机 弹射起飞 动力学模型 自动控制飞行 |
Modeling and Control of Carrier-based Airplane During Catapult Launch |
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| WANG Jun-yan,WU Wen-hai,GAO Li,ZHANG Xiao-jie.Modeling and Control of Carrier-based Airplane During Catapult Launch[J].Aircraft Design,2010,30(2):10-13. |
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| Authors: | WANG Jun-yan WU Wen-hai GAO Li ZHANG Xiao-jie |
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| Institution: | (Qingdao Branch,Naval Institute of Aeronautics Engineering,Qingdao 266041,China) |
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| Abstract: | 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. |
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| Keywords: | carrier-based airplane catapult launch dynamic model automatic control flight |
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