In this work, a Kalman filtering algorithm is proposed that estimates the spacecraft attitude and attitude parameters without gyroscope measurements for nanosatellites. The attitude parameters include sensor and actuator alignment, spacecraft body moment of inertia, reaction wheel moment of inertia, reaction wheel speed, and the dipole moment of the spacecraft. The new filtering formulation is based on the differential form of the rigid-body rotational dynamics, and so the body rate and the other attitude parameters can be updated directly by attitude measurements such that the gyroscope reading is not required. The new filter is derived in a closed form for implementation, and physical and mathematical approaches toward achieving convergence and stability with this filter are discussed. A detailed simulation is presented that demonstrates the utility of the proposed algorithm for three different types of unmodeled disturbance torques.
Kalman Filtering for Attitude and Parameter Estimation of Nanosatellites Without Gyroscopes
Journal of Guidance, Control, and Dynamics ; 40 , 9 ; 2272-2288
2017-03-30
17 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Kalman Filtering for Attitude and Parameter Estimation of Nanosatellites Without Gyroscopes
Online Contents | 2017
|Kalman Filtering for Attitude and Parameter Estimation of Nanosatellites Without Gyroscopes
Online Contents | 2017
|Miniaturized attitude control system for nanosatellites
Online Contents | 2012
|Miniaturized attitude control system for nanosatellites
Elsevier | 2012
|Kalman filtering for spacecraft attitude estimation
AIAA | 1982
|