Quadrotor aircraft attitude estimation and control based on Kalman filter

被引：7

作者：

Wang, Shao-Hua ^{[1
]}

Yang, Ying ^{[1
]}

机构：

[1] College of Engineering, Peking University

来源：

Kongzhi Lilun Yu Yingyong/Control Theory and Applications | 2013年 / 30卷 / 09期

关键词：

Attitude estimation; Auto regressive model; Double-gain PD controller; Hover control; Kalman filter; Quadrotor aircraft;

D O I：

10.7641/CTA.2013.12261

中图分类号：

学科分类号：

摘要：

The quadrotor, as one type of unmanned aircraft vehicles, has gained increasing interests in the control community, partially due to its simple aerodynamics and complex dynamics. In this work, a quadrotor system has been constructed with commercial off-the-shelf products. The sensors of inertial measurement unit are micro-electro-mechanical system, whose errors can be analyzed in an auto regressive model. A new attitude estimation scheme based on Kalman filter is proposed, which conducts separate data fusion tasks in both short and long cycle. The proposed attitude sensing method has been validated using the experimental system. In addition, a double-gain proportional differential controller has been designed to regulate the attitude dynamics. A satisfactory control performance has been achieved in some test cases.

引用

页码：1109 / 1115

页数：6

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