Initial Galileo propulsion system in-flight characterization

Barber, Todd J.; Krug, F.; Froidevaux, B. M.

doi:10.2514/6.1993-2117

Cited by 10 publications

(2 citation statements)

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“…RAVITY-assist trajectories have been used in a number of deep space missions. The Galileo and Cassini missions both used several gravity-assist flybys of planets to obtain enough orbital energy to reach their destinations (Jupiter and Saturn, respectively) [1][2][3][4][5][6][7][8]. As Galileo arrived at Jupiter, it captured into orbit about Jupiter using a gravity assist of Io and a sizable impulsive ΔV from its main engine.…”

Section: Introductionmentioning

confidence: 99%

Impulsive Trajectories from Earth to Callisto-Io-Ganymede Triple Flyby Capture at Jupiter

Lynam

Didion

2014

AIAA/AAS Astrodynamics Specialist Conference

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Section: Introductionmentioning

confidence: 99%

Impulsive Trajectories from Earth to Callisto-Io-Ganymede Triple Flyby Capture at Jupiter

Lynam

Didion

2014

AIAA/AAS Astrodynamics Specialist Conference

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“…Introduction G RAVITY-ASSIST trajectories have been used in a number of deep-space missions. The Galileo and Cassini missions both used several gravity-assist flybys of planets to obtain enough orbital energy to reach their destinations (Jupiter and Saturn, respectively) [1][2][3][4][5][6][7][8]. As Galileo arrived at Jupiter, it captured into orbit about Jupiter using a gravity assist of Io and a sizable impulsive ΔV from its main engine.…”

mentioning

confidence: 99%

Impulsive Trajectories from Earth to Callisto–Io–Ganymede Triple Flyby Jovian Capture

Didion

Lynam

2015

Journal of Spacecraft and Rockets

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Triple-satellite-aided capture sequences use gravity-assist flybys of three of Jupiter's four massive Galilean moons to help capture a spacecraft into orbit about Jupiter. A novel triple-satellite-aided capture uses sequential flybys of Callisto, Io, and Ganymede to reduce the ΔV required to capture into orbit about Jupiter. An optimal broken-plane maneuver is added between Earth and Jupiter to form a complete chemical/impulsive interplanetary trajectory from Earth to Jupiter. Such a trajectory can yield significant fuel savings over single and double-flyby capture schemes while maintaining a brief and simple interplanetary transfer phase. The developed methods maintain flexibility for adaptation to similar launch, cruise, and capture conditions. Nomenclature a = semimajor axis B = B-plane miss radius e = eccentricity i = inclination R = radius V = velocity θ = B-plane angle ν = true anomaly Ω = right ascension of the ascending node ω = argument of periapsis

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