CL_oe_equin2car

Description

• Converts equinoctial orbital elements to cartesian orbital elements.

  The transformation jacobian is optionally computed.

  See Orbital elements for more details.

Parameters

equin:

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

mu :

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

pos:

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

vel:

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

jacob:

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

Authors

• CNES - DCT/SB

See also

• CL_oe_car2equin

• CL_oe_equin2kep

Examples

// // Example 1 equin = [7000.e3; 1e-4; 1e-4; 0.1; 0.2; %pi/2]; [pos,vel] = CL_oe_equin2car(equin); // Example 2 equin = [7000.e3; 1e-4; 1e-4; 0.1; 0.2; %pi/2]; [pos,vel,jacob1] = CL_oe_equin2car(equin); [equin2,jacob2] = CL_oe_car2equin(pos,vel); equin2 - equin // zero jacob2 * jacob1 // identity