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@skulumani
Created September 25, 2018 15:48
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matlab documentation
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Purpose:
% - Function that loads planetary constant values for AAE532 class
%
% Inputs:
% - none
%
% Outpus:
% - constants - structure that holds constants for sol system divided
% by body
% - rot_per - axial rotational period in rev/day
% - radius - mean equatorial radius in km
% - mu - graviational parameter in km^3/sec^2
% - orbit_sma - semi-major axis of orbit in km
% - orbit_per - period of orbit in sec
% - orbit_ecc - eccentricity of orbit
% - orbit_inc - inclination of orbit in deg
% - mass - body mass (derived from mu and G) in kg
% - G - universal graviational constant in km^3/kg*sec^2
%
% Dependencies:
% - none
%
% Author:
% - Shankar Kulumani 1 Sept 2012
% - list revisions
% - Shankar Kulumani 19 Sept 2012
% - added distance conversions
% - added time conversions
% - Shankar Kulumani 30 Oct 2012
% - added semiparamter to constants
%
% References
% - planetary_constants.pdf (from AAE532 supplements)
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