CL_oe_car2kep

Description

• Converts cartesian orbital elements to classical Keplerian orbital elements.

  The transformation jacobian is optionally computed.

  See Orbital elements for more details.

Parameters

pos:

Position vector [x;y;z] [m] (3xN)

vel:

Velocity vector [vx;vy;vz] [m/s] (3xN)

mu :

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

kep:

Classical Keplerian orbital elements [sma;e;inc;pom;raan;M] [m,rad] (6xN)

jacob:

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

Authors

• CNES - DCT/SB

See also

• CL_oe_kep2car

Examples

// Example 1 pos = [7000.e3; 1000.e3; -500.e3]; vel = [1.e3; 2.e3; 7e3]; kep = CL_oe_car2kep(pos, vel); // Example 2 pos = [7000.e3; 1000.e3; -500.e3]; vel = [1.e3; 2.e3; 7e3]; [kep, jacob1] = CL_oe_car2kep(pos, vel); [pos2, vel2, jacob2] = CL_oe_kep2car(kep); pos2 - pos // => zero vel2 - vel // => zero jacob2 * jacob1 // => identity