Code covered by the BSD License  

Highlights from
B-Plane Coordinates

B-Plane Coordinates

by

 

MATLAB script that demonstrates the calculation of b-plane coordinates.

oeprint1(mu, oev)
function oeprint1(mu, oev)

% print six classical orbital elements,
% argument of latitude and orbital period in days

% input

%  mu      = gravitational constant (km**3/sec**2)
%  oev(1)  = semimajor axis (kilometers)
%  oev(2)  = orbital eccentricity (non-dimensional)
%            (0 <= eccentricity < 1)
%  oev(3)  = orbital inclination (radians)
%            (0 <= inclination <= pi)
%  oev(4)  = argument of perigee (radians)
%            (0 <= argument of perigee <= 2 pi)
%  oev(5)  = right ascension of ascending node (radians)
%            (0 <= raan <= 2 pi)
%  oev(6)  = true anomaly (radians)
%            (0 <= true anomaly <= 2 pi)

% Orbital Mechanics with Matlab

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

rtd = 180 / pi;

% unload orbital elements array

sma = oev(1);
ecc = oev(2);
inc = oev(3);
argper = oev(4);
raan = oev(5);
tanom = oev(6);

arglat = mod(tanom + argper, 2.0 * pi);

if (sma > 0.0)
    period = 2.0 * pi * sma * sqrt(sma / mu) / 86400.0d0;
else
    period = 9.9999999999e99;
end

% print orbital elements

fprintf ('\n      sma (km)        eccentricity     inclination (deg)    argper (deg)');

fprintf ('\n %12.10e  %12.10e  %12.10e  %12.10e \n', sma, ecc, inc * rtd, argper * rtd);

if (sma > 0.0)
    
    fprintf ('\n     raan (deg)     true anomaly (deg)   arglat (deg)       period (days)');
    
    fprintf ('\n %12.10e  %12.10e  %12.10e  %12.10e \n', raan * rtd, tanom * rtd, arglat * rtd, period);

else
    
    fprintf ('\n     raan (deg)     true anomaly (deg)   arglat (deg)');
 
    fprintf ('\n %12.10e  %12.10e  %12.10e \n', raan * rtd, tanom * rtd, arglat * rtd);
    
end




Contact us