Skip to main content

Gain-scheduled EKF for Nano-satellite Attitude Determination System

You are here

Extended Kalman filter (EKF) has been widely used for attitude determination in various satellite missions. However, it requires an extensive computational power which is not suitable for nano-satellite application. This paper proposes a gain-scheduled EKF (GSEKF) to reduce the computational requirement in nano-satellite attitude determination process. The proposed GSEKF eliminates the online recursive Kalman gain computation by analytically determines the Kalman gain based on the sensor parameters, such as the gyroscope noise variance, the quaternion variance, the observation matrix and the satellite rotational speed. Two GSEKF Kalman gains for two satellite operating modes are presented: the sun pointing and nadir pointing modes. The simulation and experimental results show that the proposed method has comparable attitude estimation accuracy to the conventional EKF. In addition, the proposed GSEKF reduces 86.29% and 89.45% of the computation load compared to the multiplicative EKF and Murrell’s version.
 

 

Contact: 
Shoushun Chen

Field of Interest

“The field of interest shall be the organization, systems engineering, design, development, integration, and operation of complex systems for space, air, ocean, or ground environments. These systems include but are not limited to navigation, avionics, mobile electric power and electronics, radar, sonar, telemetry, military, law-enforcement, automatic test, simulators, and command and control."

Resources

Technology Navigator
Spectrum

Send Us A Message