Orbit Functions

Orbit Module (partial)

Directory List

GravityModels OrbitCoord OrbitManeuver
OrbitMechanics Visualization


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

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

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Compute maneuver duration given constant thrust.

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

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Plot an orbit track in the Earth/Moon System.

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SVN Revision: 42334

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