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Kalman Filtering for Spacecraft Attitude Estimation
HIS report reviews the methods of Kalman filtering in attitude estimation and their development over the last two decades. This review is not intended to be complete but is limited to algorithms
Unscented Filtering for Spacecraft Attitude Estimation
A new spacecraft attitude estimation approach based on the unscented filter is derived. For nonlinear systems the unscented filter uses a carefully selected set of sample points to map the
Attitude Error Representations for Kalman Filtering
The quaternion has the lowest dimensionality possible for a globally nonsingular attitude representation. The
Survey of nonlinear attitude estimation methods
A survey of modern nonlinear filtering methods for attitude estimation based on the Gaussian assumption that the probability density function is adequately specified by its mean and covariance is provided.
Fundamentals of Spacecraft Attitude Determination and Control
Attitude Determination and Estimation.- Matrices, Vectors, Frames, Transforms.- Rotational Kinematics and Dynamics.- Sensors and Actuators.- Static Attitude Determination Methods.- Filtering for
Sensors and actuators
The history of attitude sensor development has emphasized increased resolution and accuracy as well as decreased size, weight, and power (often abbreviated as SWaP).
Quaternion Attitude Estimation Using Vector Observations
This paper contains a critical comparison of estimators minimizing Wahba’s loss function. Some new results are presented for the QUaternion ESTimator (QUEST) and EStimators of the Optimal Quaternion
Attitude determination using vector observations: A fast optimal matrix algorithm
The attitude matrix minimizing Wahba's loss function is computed directly by a method that is competitive with the fastest known algorithm for finding this optimal estimate. The method also provides
Sliding Mode Control Using Modified Rodrigues Parameters
This work states that spacecraft pointing poses a complex problem involving nonlinear dynamics with either linear and/or nonlinear control laws, and closed-loop systems can provide robustness with respect to spacecraft modeling uncertainties and unexpected disturbances.