Abstract
Estimation of the satellite’s kinematic parameters based on sun sensor is of great significance to tumbling satellite and can also be used as a backup method for the satellite’s raw attitude measurement. A method for estimating the kinematic parameters of the nutational satellite based on sun sensor is proposed in this article. The kinematic model of the sun vector is established by separating the nutational motion into two rotations. The kinematic parameters are calculated by vector decomposing and motion decoupling. The parameter estimation accuracy is ensured by trajectory constraints. Simulated and experimental results indicate that the algorithm is effective. For sun sensor with accuracy of 0.1°, the estimation accuracy of angular velocity is less than 0.2°/s. The estimation accuracy of nutational angle is about 0.7°–1°. Therefore, this method can be an effective way to estimate essential kinematic parameters of satellite when needed.
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