Circular equatorial to cartesian orbital elements
[pos,vel,jacob] = CL_oe_cireq2car(cireq [,mu])
Converts orbital elements adapted to near-circular near equatorial orbits to cartesian orbital elements.
The transformation jacobian is optionally computed.
See Orbital elements for more details.
Orbital elements adapted to near-circular near equatorial orbits [sma;ex;ey;ix;iy;L] [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 (See Orbital elements for more details) (6x6xN)
CNES - DCT/SB
// // Example 1 cireq = [7000.e3; 1e-4; 1e-4; 0.1; 0.2; %pi/2]; [pos,vel] = CL_oe_cireq2car(cireq); // Example 2 cireq = [7000.e3; 1e-4; 1e-4; 0.1; 0.2; %pi/2]; [pos,vel,jacob1] = CL_oe_cireq2car(cireq); [cireq2,jacob2] = CL_oe_car2cireq(pos,vel); cireq2 - cireq // zero jacob2 * jacob1 // identity |  |  |