SMART-1 mission description and development status

Extension of Highly Elliptical Earth Orbits Using Continuous Low-Thrust Propulsion

“…Where, it is shown that the required sizes of the solar arrays are modest and feasible using current solar array technology. With the solar arrays of Rosetta totaling 61.5m 2 [26] and SMART-1Õs arrays having an area of 10m 2 [27] for spacecraft of 3000kg and 370kg respectively. Finally, the storage requirements for the requisite propellant mass for a given duration are examined.…”

Static, Highly Elliptical Orbits Using Hybrid Low-Thrust Propulsion

“…With the solar arrays of Rosetta totaling 61.5m 2 [20] and SMART-1Õs arrays having an area of 10m 2 [21] for spacecraft of 3000kg and 370kg respectively. Table 12 shows that, as with the fixed launch mass case, the required sizes of the solar arrays, for all cases, are feasible using current solar array technology.…”

Space Propulsion Technology for Small Spacecraft

“…Significant other development highlights include the development of the Shell 405 catalyst allowing the utilization of high performance hydrazine-based chemical propulsion systems [8] and the SMART-1 mission showing the capability of an electric Hall thruster in an Earth-moon transfer [9], as well as the interplanetary Deep Space-1 mission, which was propelled by an NSTAR ion engine [10]. With the ABS-3A and Eutelsat 115 West B, we have seen the first instances of commercial platforms to use EP for orbit raising from a low earth orbit to the final geostationary orbit.…”