The paper deals with the design, the realization and test campaign of an autonomous system for deorbiting microsatellites in low earth orbit (SIRDARIA, Spacecraft Integrated Re-entry Device, Aero-Resistant, Increasing Area). The system based on the increasing of ballistic coefficient reduces satellite life time overcoming complexity related to using propulsion system or electrodynamic tether. Main components of the proposed system are the sail, the booms, thermal cut for deployment command and power generation and management unit. The whole system is contained, in bowed configuration, inside a box with dimensions of 3x10x10 cm. The sail, deployed exploiting booms, is large about 0.5 m2. A prototype has been realized and boarded on UNISAT-4. This is the fourth satellite manufactured in the framework of UNISAT program which was established in early nineties by professors, researchers and students at Scuola di Ingegneria Aerospaziale of University of Rome with the aim to design, realize and operate in orbit small educational satellites. The deorbiting system realization fits well with UNISAT program educational goals since a complete space culture and didactical aims cannot ignore the education to comply with a sustainable space environment .
A deorbiting system for microsatellites / F. Piergentili; F. Graziani. - ELETTRONICO. - (2007). (Intervento presentato al convegno XIX Congresso Nazionale A.I.D.A.A. tenutosi a Forlì. Italy nel 17-21 Settembre 2007.).
A deorbiting system for microsatellites
PIERGENTILI, FABRIZIO;
2007
Abstract
The paper deals with the design, the realization and test campaign of an autonomous system for deorbiting microsatellites in low earth orbit (SIRDARIA, Spacecraft Integrated Re-entry Device, Aero-Resistant, Increasing Area). The system based on the increasing of ballistic coefficient reduces satellite life time overcoming complexity related to using propulsion system or electrodynamic tether. Main components of the proposed system are the sail, the booms, thermal cut for deployment command and power generation and management unit. The whole system is contained, in bowed configuration, inside a box with dimensions of 3x10x10 cm. The sail, deployed exploiting booms, is large about 0.5 m2. A prototype has been realized and boarded on UNISAT-4. This is the fourth satellite manufactured in the framework of UNISAT program which was established in early nineties by professors, researchers and students at Scuola di Ingegneria Aerospaziale of University of Rome with the aim to design, realize and operate in orbit small educational satellites. The deorbiting system realization fits well with UNISAT program educational goals since a complete space culture and didactical aims cannot ignore the education to comply with a sustainable space environment .I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
