Circular to cartesian orbital elements
[pos,vel,jacob] = CL_oe_cir2car(cir [,mu])
Converts orbital elements adapted to near-circular orbits to cartesian orbital elements.
The transformation jacobian is optionally computed.
See Orbital elements for more details.
Orbital elements adapted to near-circular orbits [sma;ex;ey;inc;gom;pso] [m,rad] (6xN)
(optional) Gravitational constant. [m^3/s^2] (default value is %CL_mu)
Position vector [x;y;z] [m] (3xN)
Velocity vector [vx;vy;vz] [m/s] (3xN)
(optional) Transformation jacobian (See Orbital elements for more details) (6x6xN)
CNES - DCT/SB
// // Example 1 cir = [7000.e3; 0.1; 0.2; 1; 2; 3]; [pos, vel] = CL_oe_cir2car(cir); // Example 2 cir = [7000.e3; 0.1; 0.2; 1; 2; 3]; [pos, vel, jacob1] = CL_oe_cir2car(cir); [cir2, jacob2] = CL_oe_car2cir(pos, vel); cir2 - cir // => zero jacob2 * jacob1 // => identity |  |  |