Kalman Filtering for Attitude and Parameter Estimation of Nanosatellites Without Gyroscopes
Name
JGCD_APKF_R1_Proof.pdf
Description
Submitted version
Size
2.63 MB
Format
Unknown
Checksum (MD5)
b1f169b71f0fda18062c25cad4b302c1
Author(s)
Yoon, Hyosang
Riesing, Kathleen Michelle
Cahoy, Kerri
Date Issued
2017
Journal
Journal of Guidance Control and Dynamics
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Version
Original manuscript
Abstract
Copyright © 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. 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.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
Creative Commons Attribution-Noncommercial-Share Alike
Persistent DSpace Link
DOI of Published Version
https://doi.org/10.2514/1.G002649
