Cassini/Huygens at Saturn and Titan

Mitchell, R. T.

doi:10.1016/j.actaastro.2006.02.040

Cited by 8 publications

(2 citation statements)

References 2 publications

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“…In Table III along with the results of our calculations are also presented data for the Cassini-Huygens mission taken from Refs. [44][45][46][47]. It is worth noticing that in the CT case, the DFD is capable of really fast travels, rapidly reaching extremely high velocity.…”

Section: The Natural Alternative Solution To the T-c-t Missionmentioning

confidence: 99%

Exploration of the solar system and beyond using a thermonuclear fusion drive

Kezerashvili

2021

Preprint

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Section: The Natural Alternative Solution To the T-c-t Missionmentioning

confidence: 99%

Exploration of the solar system and beyond using a thermonuclear fusion drive

Kezerashvili

2021

Preprint

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“…In Table 8 along with results of our calculations are also presented data for the Cassini-Huygens mission taken from Refs. [49][50][51][52]. It is worth noticing that Table 8: Comparison between the thrust-cost-thrust profile, the continuous thrust profile and Cassini-Huygens missions.…”

Section: Scenarios Comparisonmentioning

confidence: 99%

A Titan mission using the Direct Fusion Drive

Gajeri,

Aime,

Kezerashvili

2020

Preprint

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The main purpose of this work is to perform an analysis of realistic new trajectories for a robotic mission to Saturn's largest moon, Titan, in order to demonstrate the great advantages related to the Direct Fusion Drive (DFD). The DFD is a D -3 He fuelled, aneutronic, thermonuclear fusion propulsion system, related to the ongoing fusion research at Princeton Plasma Physics Laboratory (PPPL) [1]. This fusion propulsion concept is based on a magnetically confined field reversed configuration plasma, where the deuterium propellant is heated by fusion products, and then expanded into a magnetic nozzle, providing both thrust and electrical energy to the spacecraft. The trajectories calculations and analysis for the Titan mission are obtained based on the characteristics provided by the PPPL [1]. Two different profile missions are considered: the first one is a thrust-coast-thrust profile with constant thrust and specific impulse; the second scenario is a continuous and constant thrust profile mission, with a switch in thrust direction operated in the last phases. Each mission study is divided into four different phases, starting from the initial low Earth orbit departure, the interplanetary trajectory, Saturn orbit insertion and the Titan orbit insertion. For all mission phases, maneuver time and propellant consumption are calculated. The results of calculations and mission analysis offer a complete overview of the advantages in term of payload mass and travel time. It is important to emphasize that the deceleration capability is one of the DFD game changer: in fact, the DFD performance allows to rapidly reach high velocities and decelerate in even shorter time period. This capability results in a total trip duration of 2.6 years for the thrust-coast-thrust profile and less than 2 years considering the continuous thrust profile. The high payload enabling capability, combined with the huge electrical power available from the fusion reactor, leads to a tremendous advantage compared to present technology.

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