Radiosotope Electric Propulsion Centaur Orbiter Spacecraft Design Overview

Oleson, Steve; McGuire, Melissa L.; Sarver-Verhey, Tim; Juergens, Jeff; Parkey, Tom; Dankanich, John; Fiehler, Doug; Gyekenyesi, John P.; Hemminger, J. A.; Gilland, James H.; Colozza, Tony; Packard, Tom; Nguyen, Thahn; Schmitz, Paul; Ostdiek, P. H.; Gold, R. E.; Lisse, C. M.; Hibbits, K.

doi:10.2514/6.2008-5179

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2020

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“…For example, Ref. [49] proposes a mission to a Centaur body using long-lived 700 W Hall thrusters powered by six ASRGs (150 W each). This concept would deliver a 60 kg science payload with a mission duration of 10 years.…”

Section: Technological Aspects and Applicabilitymentioning

confidence: 99%

Reduction of Saturn Orbit Insertion Impulse Using Deep-Space Low Thrust

Fantino

Flores

Peláez

et al. 2020

Journal of Guidance, Control, and Dynamics

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Orbit insertion at Saturn requires a large impulsive manoeuver due to the velocity difference between the spacecraft and the planet. This paper presents a strategy to reduce dramatically the hyperbolic excess speed at Saturn by means of deep-space electric propulsion. The interplanetary trajectory includes a gravity assist at Jupiter, combined with low-thrust maneuvers. The thrust arc from Earth to Jupiter lowers the launch energy requirement, while an ad hoc steering law applied after the Jupiter flyby reduces the hyperbolic excess speed upon arrival at Saturn. This lowers the orbit insertion impulse to the point where capture is possible even with a gravity assist with Titan. The control-law algorithm, the benefits to the mass budget and the main technological aspects are presented and discussed. The simple steering law is compared with a trajectory optimizer to evaluate the quality of the results and possibilities for improvement.

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Section: Technological Aspects and Applicabilitymentioning

confidence: 99%