The paper deals with the mission analysis and conceptual design of an interplanetary 6U CubeSats system to be implemented in an Earth-Sun Lagrangian Points mission for solar observation and in-situ space weather measurements. Interplanetary CubeSats could be an interesting alternative to big missions, to fulfill both scientific and technological tasks in deep space, as proved by the growing interest in this kind of application in the scientific community and most of all at NASA. Such systems allow less costly missions, due to their reduced sizes and volumes, and consequently less demanding launches requirements. The CubeSats mission presented in this paper is aimed at supporting measurements of space weather. The mission envisages the deployment of a 6U CubeSats system in one of the Earth-Sun Lagrangian Points, where solar observations for in situ measurements of space weather to provide additional warning time to Earth can be carried out. The proposed mission is also intended as a technology validation mission, giving the chance to test advanced technologies, such as telecommunications and solar sails, envisaged as propulsion system. Furthermore, travelling outside the Van Allen belts, the 6U CubeSats system gives the opportunity to further investigate the space radiation environment: radiation dosimeters and advanced materials are envisaged to be implemented, in order to test their response to the harsh space environment, even in view of future implementation on other spacecrafts (e.g. manned spacecrafts). The main issue related to CubeSats is how to fit big science within a small package - namely power, mass, volume, and data limitations. One of the objectives of the work is therefore to identify and size the required subsystems and equipment, needed to accomplish specific mission objectives, and to investigate the most suitable configuration, in order to be compatible with the typical CubeSats (multi units) standards. The work has been developed as collaboration between Politecnico di Torino, University “La Sapienza” (Rome), “Osservatorio Astronomico di Torino – OATO” (Astronomical Observatory of Torino) and DLR (Deutsches Zentrum für Luft- und Raumfahrt) in Bremen.

CONCEPTUAL DESIGN OF AN INTERPLANETARY CUBESATS SYSTEM FOR SPACE EVALUATIONS AND TECHNOLOGY DEMONSTRATION / Viscio, MARIA ANTONIETTA; Viola, Nicole; Corpino, Sabrina; Circi, C.; Fineschi, S.; Fumenti, F.. - ELETTRONICO. - (2013). ((Intervento presentato al convegno 8th IAA symposium on the Future of Space Exploration: Towards the Stars tenutosi a Torino nel Luglio 2013.

CONCEPTUAL DESIGN OF AN INTERPLANETARY CUBESATS SYSTEM FOR SPACE EVALUATIONS AND TECHNOLOGY DEMONSTRATION.

VISCIO, MARIA ANTONIETTA;VIOLA, Nicole;CORPINO, Sabrina;
2013

Abstract

The paper deals with the mission analysis and conceptual design of an interplanetary 6U CubeSats system to be implemented in an Earth-Sun Lagrangian Points mission for solar observation and in-situ space weather measurements. Interplanetary CubeSats could be an interesting alternative to big missions, to fulfill both scientific and technological tasks in deep space, as proved by the growing interest in this kind of application in the scientific community and most of all at NASA. Such systems allow less costly missions, due to their reduced sizes and volumes, and consequently less demanding launches requirements. The CubeSats mission presented in this paper is aimed at supporting measurements of space weather. The mission envisages the deployment of a 6U CubeSats system in one of the Earth-Sun Lagrangian Points, where solar observations for in situ measurements of space weather to provide additional warning time to Earth can be carried out. The proposed mission is also intended as a technology validation mission, giving the chance to test advanced technologies, such as telecommunications and solar sails, envisaged as propulsion system. Furthermore, travelling outside the Van Allen belts, the 6U CubeSats system gives the opportunity to further investigate the space radiation environment: radiation dosimeters and advanced materials are envisaged to be implemented, in order to test their response to the harsh space environment, even in view of future implementation on other spacecrafts (e.g. manned spacecrafts). The main issue related to CubeSats is how to fit big science within a small package - namely power, mass, volume, and data limitations. One of the objectives of the work is therefore to identify and size the required subsystems and equipment, needed to accomplish specific mission objectives, and to investigate the most suitable configuration, in order to be compatible with the typical CubeSats (multi units) standards. The work has been developed as collaboration between Politecnico di Torino, University “La Sapienza” (Rome), “Osservatorio Astronomico di Torino – OATO” (Astronomical Observatory of Torino) and DLR (Deutsches Zentrum für Luft- und Raumfahrt) in Bremen.
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11583/2517739
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