On-Orbit Interval Estimation of Satellite Inertia Parameter Based on Zonotopic Kalman Filter

Accurately determining a satellite's moment of inertia is crucial for its flight mission, as it can change due to fuel depletion or other factors. This article proposes an interval estimation approach using a zonotopic Kalman filter to determine the satellite's moment of inertia. The proposed method is based on the attitude dynamics and conservation of angular momentum of satellites, using data from the satellite's gyroscopes and Hall sensors in the reaction wheels. Given the measurement noise interval from these sensors, interval estimation of the satellite's inertia parameter is performed using a zonotopic Kalman filter. This process necessitates a maneuver involving rotation around all three axes to achieve an accurate and consistent estimation of the inertia interval. Numerical simulations are provided to show the effectiveness of the proposed estimation method.