In this paper the authors assume that they have measurements of a first difference of a typical satellite navigation carrier phase differential, which is a homogeneous quadratic function of the components of the attitude quaternion. They illustrate the determination of large or sustained attitudes using a dedicated unscented Kalman filter. The unscented Kalman filter structure was chosen for the dedicated filter because of its derivative free nature and other advantages. When a Gaussian distributed vector random variable is transformed to an equivalent quaternion it does not continue to be Gaussian distributed. For this reason, a new predictor-corrector form of the unscented Kalman filter is proposed to maintain the normalization of the unscented mean quaternion estimate in the presence of additive disturbances. The results from their realistic simulations indicate that the large attitude of a spacecraft can be estimated to within 0-1 % accuracy over large time frames. The filter is particularly useful for autonomous operations of spacecraft as well as in other applications where the process model is bilinear or second order in the states.
Spacecraft large attitude estimation using a navigation sensor
Raumschiff-Orientierungsbestimmung mit Hilfe eines Navigationssensors
The Journal of Navigation ; 63 , 1 ; 89-104
2010
16 Seiten, 6 Bilder, 29 Quellen
Article (Journal)
English
Spacecraft Large Attitude Estimation Using a Navigation Sensor
Online Contents | 2010
|Spacecraft Attitude Estimation and Sensor Calibration Using Moving Horizon Estimation
Online Contents | 2013
|