<< CL_oe_car2cirEqua Coordinates and frames CL_oe_cir2car >>

CelestLab >> Coordinates and frames > CL_oe_car2kep

CL_oe_car2kep

Cartesian to keplerian orbital elements

Calling Sequence

[kep[,jacob]] = CL_oe_car2kep(pos_car,vel_car[,mu])

Description

Parameters

pos_car:

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

vel_car:

velocity [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;ecc;inc;pom;raan;anm] [m,rad] (6xN)

jacob:

(optional) transformation jacobian d(sma,ecc,inc,pom,raan,anm)/d(X,Y,Z,Vx,Vy,Vz) (6x6xN)

Bibliography

See also

Authors

Examples

// Example 1 : elliptical orbit
pos = [-26655.e3 ; 29881.e3 ; 0];
vel = [-1125 ; -1122 ; 195];
[kep,jacob] = CL_oe_car2kep(pos,vel)
[pos2,vel2,jacob2] = CL_oe_kep2car(kep);
jacob*jacob2 // = identity
[pos2-pos ; vel2-vel]

// Example 2 : hyperbolic orbit
pos = [0; 6933.e3; 0];
vel = [0; 0; 12739.];
[kep,jacob] = CL_oe_car2kep(pos,vel)
[pos2,vel2,jacob2] = CL_oe_kep2car(kep);
jacob*jacob2 // = identity
[pos2-pos ; vel2-vel]
<< CL_oe_car2cirEqua Coordinates and frames CL_oe_cir2car >>