Table 5 - uploaded by Matteo Ceriotti
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This paper introduces the mission analysis and design of the Hevelius – Lunar Microsatellite Mission. The objective of the mission is to place at least three landers on the dark side of the Moon, to perform some scientific experiments. A microsatellite orbiter is required to support the net lander as data-relay to the Earth. Moreover, another space...
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Context 1
... 5 puts the spacecraft in a GTO parking orbit: this choice allows to reduce the fuel mass. The launcher imposes some constraints on the orbital elements, as shown in Table 5. The preferred parking orbit is GTO1 in Table 5 because, at this altitude, aerodynamic drag can be neglected and the periapsis longitude is close to the required one. ...
Context 2
... launcher imposes some constraints on the orbital elements, as shown in Table 5. The preferred parking orbit is GTO1 in Table 5 because, at this altitude, aerodynamic drag can be neglected and the periapsis longitude is close to the required one. The launch is scheduled in 2015, which has imposed some restrictions on the initial argument of the ascending node which has to be 180 °, the orbiter must wait 9.78 days (22 orbit periods) in GTO. ...
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Citations
... Some results are provided, based on a pre-phase A study of a similar mission to the Moon, called Hevelius [29]. Three landers, with miniaturized payloads, are supervised by a data relay microsatellite [6] (100 kg class) and are transported by a carrier from a LEO to the surface of the Moon, on which they perform a semi-hard landing. Moreover, the carrier has to map the lunar gravitational field and the landing site. ...
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