涵道风扇无人机增稳控制律设计与仿真  

Design and Simulation of CAS for a Ducted-Fan UAV

作　　者：沈广琛[1] 张怡哲[1] 王云[1] 李国俊[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《航空计算技术》2013年第5期70-73,77,共5页Aeronautical Computing Technique

基　　金：2012年度第一批国家级大学生创新创业训练计划项目资助(201210699002)

摘　　要：针对小型涵道风扇无人机本体不稳定特性,设计增稳控制律并通过仿真进行了验证。利用软件CATIA建立三维模型,并制作出实体模型。对模型进行受力分析,建立涵道风扇无人机六自由度动力学模型。在所建模型基础上,设计增稳控制律,包括姿态控制律及轨迹控制律。建立非线性仿真模型,通过Matlab/Simulink仿真对所设计的控制律有效性进行了验证。仿真结果表明,所设计的控制律达到了增加涵道风扇无人机稳定性的目的。Aiming at the instability of a small scale ducted- fan UAV, CAS is designed and tested through simulation. First and foremost, a three- dimensional model is established with the three- dimensional mod- eling software CATIA. The physical model has also been built. The forces and moments of the UAV are analyzed and the 6- D dynamic model of ducted fan UAV is established. Based on the model developed, CAS is designed, including attitude control law and path tracking control law. Nonlinear simulating- sys- tem of the control law is established. The effectiveness of the CAS is also tested by Matlab/Simulink simu- lation. The simulation result shows that the CAS can meet the need to augment stability.

关 键 词：涵道风扇无人机 动力学建模 增稳控制律 MATLAB SIMULINK 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]