Application of horizon sensor measurements in Kalman filtering techniques for on-board orbit navigation during aerobraking. (Q1851459)

The paper describes an application of the extended Kalman filtering algorithm for the estimation of the dynamic state vector of a spacecraft (orbit navigation problem). In particular the aerobraking phase of a mission is considered, namely the use of atmospheric drag passes to control the transition of the spacecraft from a highly elliptic orbit to the desired mission orbit. The filter uses optical on-board sensors such as star cameras and horizon scanners and two different models for disturbance effects are examined (one of which considering state augmentation). Results of Monte Carlo simulations are finally provided.