Vector perpendicular to the plane of an elliptical orbit created from the motion of the specified point with respect to the center of the specified central body.

CentralBody	Specify a central body.
MeanElementType	Specify the mean element theory type for approximating motion.
ReferencePoint	Eliptical orbit is fit to the current motion of the reference point according to the selected mean theory.

At any time, the orbit is fit to the current motion of the specified point according to the specified type orbital elements. Available types are: osculating, Brouwer-Lyddane long and short, and Kozai. The vector's magnitude is equal to the current orbit angular momentum of the specified point with respect to the specified central body.

Name
AgCrdnVectorOrbitAngularMomentum