Study and design of CubeSats for deep space

Abstract

This study aims to create a preliminary design of a CubeSat mission to a near-Earth asteroid. Three main subsystems are analysed in order to develop the study. The first one is the propulsion subsystem, the feasibility of which is determined by the type of trajectory chosen to arrive to the asteroid. Secondly, the communications subsystem, that serves as a link between the spacecraft and the Earth to transmit data. Finally, the protection against deep space radiation to avoid the malfunction of electrical components or the origin and spread of cracks. At the end of the study, a summary is made to develop the proposal of a mission preliminary design, in terms of trajectory and communication link feasibility. The path will need a delta-v of the order of 5 km/s, with specific impulses ranging from 1000 s to 2000 s, using an electric propulsion system. The data will be transmitted at a high frequency to generate a more robust signal.