Automated design of the Europa Orbiter tour

Heaton, Andrew; Strange, Nathan; Longusaki, James M.; Bonfiglio, Eugene

doi:10.2514/6.2000-4034

Cited by 17 publications

(12 citation statements)

References 2 publications

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“…Its targeted flyby altitude was 1000 km, but its actual flyby altitude was 892 km (Wilson et al 1997). The Europa Orbiter Mission (Sweetser et al 1997;Johannesen and D'Amario 1999;Heaton et al 2002) and the Jupiter Icy Moons Orbiter (Whiffen and Lam 2006) had prepared single satellite-aided capture trajectories using Ganymede and Callisto, respectively.…”

Section: Introductionmentioning

confidence: 99%

Multiple-satellite-aided capture trajectories at Jupiter using the Laplace resonance

Lynam

Kloster

Longuski

2010

Celest Mech Dyn Astr

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Satellite-aided capture is a mission design concept used to reduce the delta-v required to capture into a planetary orbit. The technique employs close flybys of a massive moon to reduce the energy of the planet-centered orbit. A sequence of close flybys of two or more of the Galilean moons of Jupiter may further decrease the delta-v cost of Jupiter orbit insertion. A Ganymede-Io sequence can save 207 m/s of delta-v over a single Io flyby. A phase angle analysis based on the Laplace resonance is used to find triple-satellite-aided capture sequences involving Io, Europa, and Ganymede. Additionally, the near-resonance of Callisto and Ganymede is used to find triple-satellite-aided capture sequences involving Callisto, Ganymede, and another moon. A combination of these techniques is used to find quadruple-satellite-aided capture sequences that involve gravity-assists of all four Galilean moons. These sequences can save a significant amount of delta-v and have the potential to benefit both NASA's Jupiter Europa orbiter mission and ESA's Jupiter Ganymede orbiter mission.

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Section: Introductionmentioning

confidence: 99%

Multiple-satellite-aided capture trajectories at Jupiter using the Laplace resonance

Lynam

Kloster

Longuski

2010

Celest Mech Dyn Astr

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“…In the same line, Strange and Longuski (2002) developed a graphical method to study Swing-By trajectories with the goal of reducing the mass during the launch phases and/or the flight time; and Helton et al (2002) designed an Europa orbiter tour. In the next year, McConaghy et al (2003) combined Swing-By maneuvers with low thrust to obtain optimal trajectories.…”

Section: Introductionmentioning

confidence: 99%

A numerical study of powered Swing-Bys around the Moon

Ferreira

Prado

Winter

2015

Advances in Space Research

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“…Many authors have addressed ballistic patched conics tour design [9,13,18,19,32,33], but few have presented systematic algorithms for representing the results in nbody ephemeris models. Typically, the transition to the full ephemeris model is made in a single leap, and can stress even the best optimization algorithms tackling the simplest of problems.…”

Section: Introductionmentioning

confidence: 99%

A Continuation Method for Converting Trajectories from Patched Conics to Full Gravity Models

Bradley

Russell

2014

J of Astronaut Sci

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A method is introduced to transition space trajectories from low fidelity patched conics models to full-ephemeris n-body dynamics. The algorithm incorporates a continuation method that progressively re-converges solution trajectories in systems with incremental changes in the dynamics. Continuation is accomplished through the variation of a control parameter, which is tied to body ephemeris locations and masses, minimum flyby altitudes, and sphere of influence sizes. The intermediate models provide a continuous and differentiable path between solutions in the simplified and n-body dynamics, and the boundary values of the control parameter replicate the patched conics and full-ephemeris models exactly. Each successive step preserves the qualitative properties of the initial guess by successively altering flyby states and body masses. A similar approach to this methodology may be taken with any simplified starting guess, such as a restricted three-body model. Trajectories computed using the patched conics conversion method presented here may include gravity assists and rendezvous with any number of target bodies, so the method is ideal for constructing interplanetary or intermoon tour missions, and is amenable to patching shorter segments together to form longer tours.

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Automated design of the Europa Orbiter tour

Cited by 17 publications

References 2 publications

Multiple-satellite-aided capture trajectories at Jupiter using the Laplace resonance

Multiple-satellite-aided capture trajectories at Jupiter using the Laplace resonance

A numerical study of powered Swing-Bys around the Moon

A Continuation Method for Converting Trajectories from Patched Conics to Full Gravity Models

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