Name

CL_oe_kep2car — Keplerian to cartesian orbital elements

Calling Sequence

   [pos_car,vel_car[,jacob]] = CL_oe_kep2car(kep[,mu])
   
   

Description

  • Given the keplerien parameters [a,e,i,w,omega,M], this function computes the cartesien parameters [rx,ry,rz,vx,vy,vz] for an elliptic, hyperbolic or parabolic orbit.

    The transformation jacobian is optionally computed.

  • Last update : 29/11/2007

Parameters

kep:

keplerien parameters [a,e,i,w,omega,M] [m],[rad] (6xN)

mu :

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

pos_car:

satellite's cartesien position [rx,ry,rz] [m] (3xN)

vel_car:

satellite's cartesien velocity [vx,vy,vz] [m/s] (3xN)

jacob:

(optional) transformation jacobian d(rx,ry,rz,vx,vy,vz)/d(a,e,i,w,omega,M) (6x6xN)

Bibliography

1 CNES - MSLIB FORTRAN 90, Volume V (mv_kep_car)

See also

CL_oe_car2kep, CL_oe_kep2cirEqua

Authors

CNES - DCT/SB

Examples

// Example 1
kep=[24464560,0.7311,0.122138,3.10686,1.00681,0.048363]';
[pos_car,vel_car]=CL_oe_kep2car(kep);
[kep2]=CL_oe_car2kep(pos_car,vel_car);