Analyzing Methods of Optimizing Low ΔV Gravity Assist Trajectories in the Jovian System
DOI:
https://doi.org/10.47611/jsrhs.v14i1.8580Keywords:
Gravity Assist, Trajectory Design, Trajectory Optimization, Jovian System, Orbital Mechanics, Planetary Flybys, Spacecraft NavigationAbstract
To accomplish scientific objectives, spacecraft exploring the Jovian system require close flybys of Jupiter’s inner moon of Europa. However, the ΔV cost of a direct transfer to Europa is prohibitively expensive, so ballistic flybys with the other moons in the system are required to lower the energy of the spacecraft relative to Jupiter. Sequences of ballistic flybys can simultaneously alter the spacecraft’s trajectory in a desirable way and provide additional opportunities for scientific observation. Using a patched conics simulation, the N-Revolution Lambert’s problem can be solved to find sequences of flybys that enable low transfers between the four major Jovian moons.
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