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Orbital Mechanics Fortran Toolbox  
This web site contains Fortran 77 and Fortran 90 subroutines and functions that can be used to solve a variety of practical problems in orbital mechanics, including: Convert a calendar date to a Julian date, Convert a Julian date to a calendar date, Convert an ECI state vector to classical orbital elements Convert classical orbital elements to an ECI state vector, Convert geocentric coordinates to geodetic coordinates, Danby's solution of Kepler's equation, Kozai orbit propagation - ECI version, Kozai orbit propagation - ECF version, Two-body orbital motion - Shepperd's method, Two-body orbital motion - Danby/Stumpff method, First-order equations of orbital motion (J2 gravity), Ephemeris of the planets - Meeus algorithm, Ephemeris of the Sun - LPPF algorithm, Ephemeris of the Moon - LPPF algorithm, Greenwich apparent sidereal time, Trig, vector and numerical analysis utility routines.
Submitted: Feb 29, 2000

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