There are several different ways to represent spacecraft attitude and its time rate of change. For spinning or momentum-biased spacecraft, one particular representation has been put forward as a superior parameterization for numerical integration. Markley has demonstrated that these new variables have fewer rapidly varying elements for spinning spacecraft than other commonly used representations and provide advantages when integrating the equations of motion. The current work demonstrates how a Kalman filter can be devised to estimate the attitude using these new variables. The seven Markley variables are subject to one constraint condition, making the error covariance matrix singular. The filter design presented here explicitly accounts for this constraint by using a six-component error state in the filter update step. The reduced dimension error state is unconstrained and its covariance matrix is nonsingular.
Kalman Filter Estimation of Spinning Spacecraft Attitude using Markley Variables
18th International Symposium on Space Flight Dynamics ; 2004 ; Munich, Germany
2004-01-01
Preprint
No indication
English
Kalman Filter Estimation of Spinning Spacecraft Attitude using Markley Variables
British Library Conference Proceedings | 2004
|Kalman Filter for Spinning Spacecraft Attitude Estimation
Online Contents | 2008
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