Contini, Cristiano (Politecnico di Milano), Colombo, Camilla (Politecnico di Milano)

Attitude and Orbital Dynamics Fine Coupling for High Area-To-Mass Ratio Satellites

Scheduled for presentation during the Regular Session "Spacecraft dynamics and control 2" (ThA3), Thursday, April 4, 2019, 15:30−16:00, BL281.2

5th CEAS Conference on Guidance, Navigation and Control, April 3-5, 2019, Milano, Italy

This information is tentative and subject to change. Compiled on April 24, 2024

Abstract

Nowadays the interest in small satellites large constellations or MicroSats in formation flying is increasing and, as a consequence, the challenges related to the Attitude Determination and Control Subsystem are increasing, being related to the capability to enhance a fine pointing budget and to be able to take into account the coupling between attitude and orbital dynamics. In this paper, an Attitude Determination and Control Subsystem simulator will be presented, fundamental to evidence the fine dynamical coupling in the ZodiArt iSEE mission, by Politecnico di Milano. The simulator is characterised by a complete disturbances model, including: the Earth zonal harmonics, the Moon and Sun third body perturbations, solar radiation pressure, drag and lift. Moreover, compact plots, here called Orbital long-track envelope, will be presented, graphically showing the differential gain/loss in altitude and relative long-track shift obtained performing differential drag, depending on the manoeuvre epoch, angle of attack and true anomaly.