ROEKF-MPC Estimator for Satellite Attitude and Gyroscope Bias Estimation

Micro-electro-mechanical system (MEMS) based gyroscopes are commonly used for satellite's attitude determination and control system in recent years. They are packaged in a small form factor and have lower power consumption. They provide a low-cost solution to the emerging NewSpace industry. MEM...

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Bibliographic Details
Published in:IEEE transactions on aerospace and electronic systems 2023-10, Vol.59 (5), p.1-14
Main Authors: Tissera, Mihindukulasooriya Sheral Crescent, Foo, Kai Jie Ethan, Low, Kay-Soon, Goh, Shu Ting, Tan, Rongde Darius
Format: Article
Language:English
Subjects:
Bias
Calibration
Estimation
Extended Kalman filter
Form factors
Gyroscopes
Microelectromechanical systems
Micromechanical devices
Power consumption
Predictive control
Quaternions
Reduced order filters
Satellite attitude control
Satellite tracking
Satellites
Self calibration
Temperature measurement
Torque
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Summary:Micro-electro-mechanical system (MEMS) based gyroscopes are commonly used for satellite's attitude determination and control system in recent years. They are packaged in a small form factor and have lower power consumption. They provide a low-cost solution to the emerging NewSpace industry. MEMS gyroscopes exhibit time-zero null bias with variation over temperature. To overcome this problem, this paper proposes a technique for self-calibration of gyroscope bias based on reduced order Extended Kalman Filter (EKF) working alongside an estimator based on the model predictive control (MPC) approach. The proposed technique is referred as the ROEKF-MPC Estimator. Both simulation results and experimental verification using an in-house developed spacecraft simulator are presented. Unlike the EKF method, the proposed method can estimate the gyroscope bias instantly and it is robust against changes in temperature. In addition, the proposed method employing a reduced order EKF is 28.4% computationally more efficient than the typical higher order EKF method. Results show that the pointing performance is better than 0.35deg making the proposed method very attractive for most NewSpace applications. While the proposed method allows for self-calibration of gyroscope bias, its performance is affected by the gyroscope noise and requires the satellite's attitude to be nearly in steady state. This limitation will be addressed in detail.
ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2023.3244896