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A MATLAB Script for Propagating Interplanetary Trajectories from Earth to Mars

A MATLAB Script for Propagating Interplanetary Trajectories from Earth to Mars

by

David Eagle (view profile)

 

Numerically integrate the orbital equations of motion of an Earth to Mars interplanetary trajectory.

obliq(t)
function y = obliq(t)

% function to compute mean obliquity of the ecliptic in arcseconds
% capitaine et al. (2003), astronomy and astrophysics 412, 567-586,
% expression from eq. (39) with obliquity at j2000.0 taken from
% eq. (37) or table 8

% input

%  t = tdb julian centuries

% output

%  y = mean obliquity of the ecliptic in arcseconds

% ported from NOVAS 3.0

%%%%%%%%%%%%%%%%%%%%%%%

y = (((( - 0.0000000434d0 * t ...
    - 0.000000576d0) * t ...
    + 0.00200340d0) * t ...
    - 0.0001831d0) * t ...
    - 46.836769d0) * t + 84381.406d0;

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