鸭式旋翼/机翼无人机飞行动力学建模与分析  

Flight dynamic modeling and analysis for the Canard Rotor/Wing UAV

作　　者：盖文东[1,2] 王宏伦[1,2] 李大伟[2] 

机构地区：[1]北京航空航天大学飞行器控制一体化技术重点实验室,北京100191 [2]北京航空航天大学无人驾驶飞行器设计研究所,北京100191

出　　处：《空气动力学学报》2012年第2期244-249,共6页Acta Aerodynamica Sinica

基　　金：教育部新世纪优秀人才支持计划(NCET-10-0032)

摘　　要：针对鸭式旋翼/机翼无人机兼有直升机和固定翼机飞行特性的特点,对其飞行动力学模型进行了理论建模与分析研究。应用动量理论建立了旋翼/机翼尾迹模型,分析了旋翼/机翼尾迹对鸭翼、平尾等气动部件的干扰特性,建立了直升机和转换飞行模式受旋翼/机翼尾迹干扰影响的动力学模型以及固定翼飞行模式的动力学模型。提出了各飞行模式的配平策略,使用Matlab工具箱函数简化了平衡特性计算和模型线性化过程,并进行了不同飞行模式、典型飞行状态的纵向运动稳定性分析。结果表明所建立的模型能够反映该类鸭式旋翼/机翼无人机各飞行模式的典型特性,并可用于飞行控制系统设计。Canard Rotor/Wing UAV combines the hover flight characteristic of a helicopter with high subsonic cruise of a fixed-wing aircraft. The flight dynamic model for the CRW was developed and analyzed. The momentum theory was used to build the rotor/wing slipstream model in the rotary-wing and conversion flight. The influence produced by rotor/wing slipstream on canard and horizontal tail was analyzed. In the rotary-wing and conversion flight, the flight dynamic model affected by the rotor/wing slipstream was developed. At the same time, the flight dynamic model in the fix-wing flight was developed too. The balance strategy was suggested in different flight modes. The Matlab toolbox functions were used to simplify trim calculation and model linearization in different flight modes. And the longitude dynamical stability for typical flight states was analyzed in different flight modes. The results show that the model contains the typical characteristic of the CRW, and can be used in flight control system design.

关 键 词：鸭式旋翼机翼无人机 模态转换 平衡特性计算 稳定性分析 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]