Application of Kalman Filter in the Attitude Four-Axis Aircraft Control System

Xuan Cui; Zhong Yan Fan; Hua Sun

doi:10.4028/www.scientific.net/AMM.241-244.1261

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 241-244Application of Kalman Filter in the Attitude...

Application of Kalman Filter in the Attitude Four-Axis Aircraft Control System

Abstract:

Attitude control is the core of the four-axis aircraft flight control，By analyzing the principle of four-axis aircraft flight，this paper, on the basis of the traditional method ,acceleration sensors to obtain data, we use the Kalman filter method, fuse acceleration sensor data and gyroscope data, MCU as the core of the inertial measurement unit test，The results showed that，The aircraft can be better stabilized at the test platform, can achieve the requirements of attitude control of the four-axis aircraft.

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Periodical:

Applied Mechanics and Materials (Volumes 241-244)

Pages:

1261-1264

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.241-244.1261

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Online since:

December 2012

Authors:

Xuan Cui, Zhong Yan Fan, Hua Sun

Keywords:

Four-Axis Aircraft, Kalman Filter (KF), Micro Controller Unit (MCU)

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