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celestlab >> Orbit properties > CL_op_eccVector3d

CL_op_eccVector3d

Eccentricity vector (3D)

Calling Sequence

[eccv] = CL_op_eccVector3d(pos, vel [, mu])

Description

Parameters

pos:

Satellite's position vector [m] (3xN or 3x1)

vel:

Satellite's velocity vector [m/s] (3xN or 3x1)

mu:

(optional) Gravitational constant. Default: %CL_mu. [m^3/s^2] (1x1). (1x1)

eccv :

Eccentricity vector (3xN)

Authors

Examples

// 1) Computation of eccentricity vector from Keplerian orbital elements
kep = [7.e6; 0.1; 1; 2; 3; 4];
eccv = kep(2) * CL_rot_rotVect(CL_rot_angles2quat([3, 1, 3], [kep(5); kep(3); kep(4)]), [1; 0; 0]);

// 2) Computation of eccentricity vector from position and velocity vectors
[pos, vel] = CL_oe_kep2car(kep);
CL_op_eccVector3d(pos, vel) - eccv // => 0

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