摘要
基于涡扇发动机动态模型和飞机气动模型,以舰载机着舰过程为典型剖面,依据能量法建立飞/发一体化控制模型,作为舰载机着舰复飞研究的基础。模型充分考虑了着陆时的升阻特性、地面效应和飞机重量等因素,采用功率提取法改进涡扇发动机加速控制规律和供油规律,并与原控制规律进行比较,结果表明新加速控制规律可以有效减少复飞所需的甲板滑跑长度和增加着舰重量,为舰载机着舰复飞方案设计提供借鉴和参考。
Based on the dynamic model of turbofan engine and the dynamic model of aircraft,taking the landing process of shipboard aircraft as a typical section,the integrated control model of aircraft/engine is established according to the energy method,which is the basis of the research on the missed approach of shipboard aircraft landing.The model fully considers landing lift drag characteristics,ground effect,aircraft weight and other factors.The acceleration control law and oil supply law of turbofan engine are improved by power extraction method,and compared with the original control law.The results show that the new acceleration control law can effectively reduce the deck slide length and increase the landing weight required by the go around.It can be used for reference in the design of carrier aircraft landing and missed approach.
作者
冯玉博
姚明智
李冬
张伟
欧阳文恒
Feng Yubo;Yao Mingzhi;Li Dong;Zhang Wei;Ouyang Wenheng(The army of unit 92728,Shanghai 200436,China;The army of unit 91899,Liaoning Huludao 125001,China;The first military representative office of the naval equipment department in Shenyang,Shenyang 110000,China;Military representative office of naval equipment department in Jiujiang district,Jiangxi Jiujiang 332000,China)
出处
《燃气轮机技术》
2020年第3期51-56,共6页
Gas Turbine Technology
关键词
飞/发模型
着舰复飞
加速控制规律
一体化控制
升阻特性
aircraft/engine model
landing and reflying
acceleration control law
integrated control
lift and drag characteristic
