CL_oe_car2cireq

Description

• Converts cartesian orbital elements to orbital elements adapted to near-circular near-equatorial orbits.

  The transformation jacobian is optionally computed.

  See Orbital elements for more details.

Parameters

pos:

position [X;Y;Z] [m] (3xN)

vel:

velocity [Vx;Vy;Vz] [m/s] (3xN)

mu :

(optional) Gravitational constant. [m^3/s^2] (default value is %CL_mu)

cireq:

Orbital elements adapted to near-circular orbits [sma;ex;ey;ix,iy;L] [m,rad] (6xN)

jacob:

(optional) Transformation jacobian (See Orbital elements for more details) (6x6xN)

Authors

• CNES - DCT/SB

See also

• CL_oe_cireq2car

• CL_oe_car2kep

Examples

// Example 1 pos = [7000.e3;1000.e3;-500.e3]; vel = [1.e3;2.e3;7e3]; cireq = CL_oe_car2cireq(pos,vel); // Example 2 pos = [7000.e3;1000.e3;-500.e3]; vel = [1.e3;2.e3;7e3]; [cireq,jacob1] = CL_oe_car2cireq(pos,vel); [pos2,vel2,jacob2] = CL_oe_cireq2car(cireq); pos2 - pos // zero vel2 - vel // zero jacob2 * jacob1 // identity