This work introduces, examines and compares several quaternion normalization algorithms, which are shown to be an effective stage in the application of the additive extended Kalman filter to spacecraft attitude determination, which is based on vector measurements. Three new normalization schemes are introduced. They are compared with one another and with the known brute force normalization scheme, and their efficiency is examined. Simulated satellite data are used to demonstate the performance of all four schemes.
Quaternion normalization in additive EKF for spacecraft attitude determination
AIAA Guidance, Navigation and Control Conference ; 1991 ; New Orleans, LA, United States
1991-01-01
Conference paper
No indication
English
Spacecraft Attitude Determination Using Gyros and Quaternion Measurements
Online Contents | 1996
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