Orbit Module (partial)

Directory List

GravityModels	OrbitCoord	OrbitManeuver
OrbitMechanics	Visualization

GravityNormalized	Compute the gravitational acceleration in cartesian coordinates.
LoadSGM150	Load the SGM150 Lunar gravity model.

RARP2A	Computes the semi major axis from apogee and perigee radii
RPRA2AE	Converts perigee and apogee to semi-major axis and eccentricity
SLR	Computes the semi-latus rectum.

Compute maneuver duration given constant thrust.

LambertTOF	Solves the Lambert time of flight problem using Battin's method.
RVOrbGen	Generate an orbit by propagating Keplerian elements.
TimeOfFlightHyperbola	Time of flight in a hyperbola

Plot an orbit track in the Earth/Moon System.

SVN Revision: 42334

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