The international gravity waves scientific community has presented the SAGITTARIUS mission in parallel to NASA and ESA during this year 1993. This mission has as main goals the first direct detection of gravitational waves from galactic binary stars and the opening orthe Low Frequency (LF) gravitational wave window on the universe. The SAGITTARIUS mission will be formed by six spacecraft, located in a circular earth orbit at an altitude of 600 000 km and linked by laser beams. A laser tracking signal wiU be generated in each of the respective end spacecraft where will be actively transponded back to the central spacecraft. This system will operate as an interferometer detecting any gravity wave passing through the spacecraft configuration. Each of the spacecraft will contain an accelerometer and wiU be equipped with the FEEP thrusters, the only propulsion system capable to operate in the range 1 microN-25 microN. The thrusters will be driven by output from the accelerometers to provide a drag free system. This paper will describe the SAGITTARIUS mission concept and the FEEP reaction and attitude control system as it will be designed for each of the spacecraft involved in the mission.
Space-Borne Astronomical Gravity-Wave Interferometer Mission (SAGITTARIUS): The Field Emission Electric Propulsion Option
ANDRENUCCI, MARIANO;MARCUCCIO, SALVO;
1993-01-01
Abstract
The international gravity waves scientific community has presented the SAGITTARIUS mission in parallel to NASA and ESA during this year 1993. This mission has as main goals the first direct detection of gravitational waves from galactic binary stars and the opening orthe Low Frequency (LF) gravitational wave window on the universe. The SAGITTARIUS mission will be formed by six spacecraft, located in a circular earth orbit at an altitude of 600 000 km and linked by laser beams. A laser tracking signal wiU be generated in each of the respective end spacecraft where will be actively transponded back to the central spacecraft. This system will operate as an interferometer detecting any gravity wave passing through the spacecraft configuration. Each of the spacecraft will contain an accelerometer and wiU be equipped with the FEEP thrusters, the only propulsion system capable to operate in the range 1 microN-25 microN. The thrusters will be driven by output from the accelerometers to provide a drag free system. This paper will describe the SAGITTARIUS mission concept and the FEEP reaction and attitude control system as it will be designed for each of the spacecraft involved in the mission.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
