Circular equatorial adapted to cartesian orbital elements
[pos_car,vel_car[,jacob]]=CL_oe_cirEqua2car(cir_equa[,mu])
Converts orbital elements adapted to near-circular near-equatorial orbits to position and velocity for an elliptic orbit.
The transformation jacobian is also optionally computed.
See Orbital elements for more details
orbital elements adapted to near-circular near-equatorial orbits [sma;ex;ey;ix;iy;pom+raan+anm] [m,rad] (6xN)
(optional) gravitational constant [m^3/s^2] (default value is %CL_mu)
position [X;Y;Z] [m] (3xN)
velocity [Vx;Vy;Vz] [m/s] (3xN)
(optional) transformation jacobian d(X,Y,Z,Vx,Vy,Vz)/d(sma,ex,ey,ix,iy,pom+raan+anm) (6x6xN)
1) CNES - MSLIB FORTRAN 90, Volume V (mv_cir_equa_car)
CNES - DCT/SB