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Specific angular momentum axis
w
Eccentricity vector
p
Semilatus rectum
q
Period of an orbit depends most directly on
mass of primary
Semi major axis length
For a parabolic orbit escape velocity depends most directly on
Radial distance from central body
Mass of primary
For a hyperbolic orbit the true anomaly of the asymptote depends most directly on
Eccentricity
Information needed to produce Lagrange coefficient
Initial position
Initial velocity