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Attitude determination using a MEMS-based flight information measurement unit.

Der-Ming Ma1, Jaw-Kuen Shiau, I-Chiang Wang

  • 1Department of Aerospace Engineering, Tamkang University, Tamsui, New Taipei City 25137, Taiwan. derming@mail.tku.edu.tw

Sensors (Basel, Switzerland)
|February 28, 2012
PubMed
Summary
This summary is machine-generated.

This study introduces a new algorithm for aircraft attitude determination using a low-cost MEMS unit. The quaternion-based extended Kalman filter provides precise navigation and control data, even during high-dynamic maneuvers.

Keywords:
attitude determinationextended Kalman filterflight information measurement unitquaternion

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Area of Science:

  • Aerospace Engineering
  • Navigation Systems
  • Sensor Fusion

Background:

  • Precise aircraft attitude information is critical for safe navigation and control.
  • Existing attitude determination methods can be costly or lack robustness in dynamic conditions.

Purpose of the Study:

  • To develop and validate a novel, low-cost attitude determination algorithm for aircraft.
  • To enhance the accuracy and reliability of attitude estimation using MEMS-based sensors.

Main Methods:

  • A quaternion-based extended Kalman filter (EKF) was designed, integrating quaternion dynamics and gravitational force decomposition.
  • The EKF utilizes quaternion elements as states and attitude angles from gravity/magnetic sensors as measurements.
  • Immeasurable gravity accelerations were estimated using accelerometer data, accounting for relative and body rotation accelerations.

Main Results:

  • The proposed algorithm successfully determined aircraft attitude using a low-cost MEMS-based flight information measurement unit.
  • Flight test data validated the algorithm's practicality and reliability, particularly during high dynamic maneuvers.
  • The integration of quaternion constraints as perfect measurements improved filter performance.

Conclusions:

  • The developed quaternion-based EKF offers an intuitive, implementable, and reliable solution for aircraft attitude determination.
  • This approach is suitable for long-term applications requiring high dynamic maneuver capability.
  • The study demonstrates the efficacy of sensor fusion and advanced filtering techniques for low-cost navigation systems.