Other
Scientific paper
Aug 2004
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.558..137d&link_type=abstract
Proceedings of the 5th International Symposium on Environmental Testing for Space Programmes Noordwijk, The Netherlands (ESA SP-
Other
Scientific paper
On board resources necessary to perform the mission tasks are very limited in nano-satellites. This paper proposes a real-time sub-system, which is able to manage Irecin Power Supply. Irecin power supply includes the solar panels, built with silicon solar cells, the batteries and the necessary electronic for Energy generation and distribution to its subsystems. The Power Control Unit (PCU), provided with electrical power by means of solar panels, optimises the batteries recharging using a Peek Power Tracking; generates and stabilizes the voltage of 5 V for all subsystems; checks subsystems power absorption notifying it to the main micro-processor board. The proposed subsystem controls whole satellite subsystems energy adsorption by monitoring battery recharge status and handling subsystems activation /deactivation. It allows isolating damaged subsystems which could put in short cut the nanosatellite power supply and, generally, it increases nanosatellite time-life. Moreover this configuration allows to let free the on board main microprocessor from the power control functions, increasing its communication capabilities with the others subsystems. IRECIN uses rechargeable lithium ion batteries, which ensure very high energy density reducing power system volume and weight. These batteries are characterised also by a wide temperature range, enabling a simpler thermal design and by a very low cost. All electronic components are SMD technology in order to reduce weight and size. The realized Electronic boards are completely developed, realized and tested at the Vitrociset S.P.A. under control of Research and Develop Group. The proposed sub-system is implemented on the Irecin, a modular nano-satellite weighting less than 1.5 kg, constituted by sixteen external sides with surface-mounted solar cells and three internal Al plates, kept together by four steel bars. Attitude is determined by three-axis magnetometer and the solar panels data. Control is provided by an active magnetic control system. The spacecraft will be spin-stabilized with the spin-axis normal to the orbit.
Del Re V.
Ferrrante M.
Ortenzi A.
Petrozzi M.
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