Study on extended Kalman filtering for attitude estimation of micro flight vehicle

Min Xu, Ningjun Fan, Zhengjie Wang*

*Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

10 Citations (Scopus)

Abstract

In this paper an extended Kalman filter for real-time estimation of micro flight vehicle body attitude by using MEMS gyros, accelerometers, and magnetometers is presented. The algorithm uses quaternions to represent rotation, which can avoid the singularity problem caused by using Euler angles. Attitude quaternion errors and drift bias of gyros were selected to construct a state vector. The state equation is established on the base of attitude quaternion error differential equation. The measurements of Kalman filter were obtained through iteration using acceleration and magnetic field vector. The algorithm can significantly reduce calculated amount and can converge quickly to rotation attitude.

Original languageEnglish
Title of host publicationProceedings - 3rd International Conference on Measuring Technology and Mechatronics Automation, ICMTMA 2011
Pages457-460
Number of pages4
DOIs
Publication statusPublished - 2011
Event3rd International Conference on Measuring Technology and Mechatronics Automation, ICMTMA 2011 - Shanghai, China
Duration: 6 Jan 20117 Jan 2011

Publication series

NameProceedings - 3rd International Conference on Measuring Technology and Mechatronics Automation, ICMTMA 2011
Volume3

Conference

Conference3rd International Conference on Measuring Technology and Mechatronics Automation, ICMTMA 2011
Country/TerritoryChina
CityShanghai
Period6/01/117/01/11

Keywords

  • Attitude estimation
  • Kalman filter
  • Micro flight vehicle

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