Orbit Estimation Using a Horizon Detector in the Presence of Uncertain Celestial Body Rotation and Geometry
For spacecraft navigation around poorly characterized celestial bodies, this method improves orbit estimation robustness without requiring simultaneous measurements.
This paper develops an orbit estimation method using non-simultaneous horizon detector measurements that accounts for uncertainties in celestial body rotation and geometry, achieving convergence of spacecraft state errors to zero in Monte Carlo simulations.
This paper presents an orbit estimation using non-simultaneous horizon detector measurements in the presence of uncertainties in the celestial body rotational velocity and its geometrical characteristics. The celestial body is modelled as a tri-axial ellipsoid with a three-dimensional force field. The non-simultaneous modelling provides the possibility to consider the time gap between horizon measurements. An unscented Kalman filter is used to estimate the spacecraft motion states and estimate the geometric characteristics as well as the rotational velocity of the celestial body. A Monte-Carlo simulation is implemented to verify the results. Simulations showed that using non-simultaneous horizon vector measurements, the spacecraft state errors converge to zero even in the presence of an uncertain geometry and rotational velocity of the celestial body.