Planetary flybys resulting in heliocentric orbits normal to the ecliptic with fixed perihelia.

An iterative procedure is applied to a patched conic trajectory sequence in which a spacecraft is launched from the earth, flys by the planet Jupiter, and leaves Jupiter along a heliocentric trajectory whose plane is normal to the ecliptic, and whose perihelion is fixed at 0.1 AU. Six launch opportunities, spaced apart in time at approximately the mean synodic period of earth and Jupiter (roughly 400 days), are examined.