LARES is a laser ranged satellite designed for testing a particular effect derived from general relativity: the Lense-Thirring effect. The Italian Space Agency has financed the mission in February 2008. The European Space Agency will provide the qualification launch of VEGA foreseen in year 2010. The high density of LARES will make the satellite, once in orbit, the most dense orbiting object known in the solar system. This peculiarity has some implications on the development of the separation system and the whole supporting subsystem. In fact the satellite cannot be positioned right at the launcher interface but must be located about one meter above it so that the position of its centre of mass can be representative of that one of a more typical satellite. But the main problem is represented by the high level of acceleration combined with the scientific requirements that allow only minimal impact on the satellite surface. In the qualification process the approach from parts to system has been followed. Two breadboards have been developed. The first one has been manufactured and the final test results will be presented. The reasoning behind the second breadboard will be described along with a drawing showing the hardware required to perform the test.

TESTING THE LARES SEPARATION SYSTEM BREADBOARDS / PAOLOZZI, Antonio; I., CIUFOLINI; PERONI, Isidoro; PARIS, Claudio; M., RAMICONI; F. M., ONORATI; L., ACQUAROLI. - STAMPA. - 10:(2009), pp. 8126-8131. ((Intervento presentato al convegno 60th International Astronautical Congress tenutosi a Daejeon; Korea, Republic of nel 12-16 October 2009.

TESTING THE LARES SEPARATION SYSTEM BREADBOARDS

PAOLOZZI, Antonio;PERONI, Isidoro;PARIS, Claudio;
2009

Abstract

LARES is a laser ranged satellite designed for testing a particular effect derived from general relativity: the Lense-Thirring effect. The Italian Space Agency has financed the mission in February 2008. The European Space Agency will provide the qualification launch of VEGA foreseen in year 2010. The high density of LARES will make the satellite, once in orbit, the most dense orbiting object known in the solar system. This peculiarity has some implications on the development of the separation system and the whole supporting subsystem. In fact the satellite cannot be positioned right at the launcher interface but must be located about one meter above it so that the position of its centre of mass can be representative of that one of a more typical satellite. But the main problem is represented by the high level of acceleration combined with the scientific requirements that allow only minimal impact on the satellite surface. In the qualification process the approach from parts to system has been followed. Two breadboards have been developed. The first one has been manufactured and the final test results will be presented. The reasoning behind the second breadboard will be described along with a drawing showing the hardware required to perform the test.
978-161567908-9
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Utilizza questo identificativo per citare o creare un link a questo documento: http://hdl.handle.net/11573/191431
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