Flight Controller Design for Small Quad Tilt Wing UAV
Flight Controller Design for Small Quad Tilt Wing UAV
复制标题
小型四倾翼无人机飞行控制器设计
DOI：
10.2322/jjsass.64.79
复制
发表时间：
2016
期刊：
影响因子：
--
通讯作者：
K. Muraoka
中科院分区：
文献类型：
--
作者：
Masayuki Sato;K. Muraoka
针对小型四翼无人机（QTW）的增稳/控制系统（S/CAS）设计问题，提出了一种用于小型四翼无人机（QTW）制导与控制系统验证的试验平台。我们设计的基本S/CAS的飞机使用我们以前提出的设计方法。通过比较新研制的和以前研制的QTWUAV的线性化运动的特征值，说明了我们的方法的有效性S/CAS设计。我们还显示了使用我们的S/CAS的飞行试验结果。
This paper is concerned with the design of Stability/Control Augmentation System (S/CAS) for small Quad Tilt Wing (QTW) Unmanned Aerial Vehicle (UAV) which has been developed as a test bed for guidance and control system demonstrations. We design the basic S/CAS for the aircraft using our previously proposed design method. By comparing the eigenvalues of linearized motions of the newly developed and the previously developed QTWUAVs, the effectiveness of our method for S/CAS design is illustrated. We also show the flight test results using our S/CAS.