Name

CL_oe_car2cirEqua — Cartesien to circular equatorial adapted orbital elements

Calling Sequence

   [cir_equa[,jacob]]=CL_oe_car2cirEqua(pos_car,vel_car[,mu])
   
   

Description

  • Given cartesien position and velocity vectors, this function computes the circular equatorial adapted parameters [a,ex,ey,ix,iy,omega+w+M] for an elliptic orbit.

    The transformation jacobian is optionally computed.

  • Last update : 29/11/2007

Parameters

pos_car:

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

vel_car:

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

mu :

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

cir_equa:

circular equatorial adapted parameters [a,ex,ey,ix,iy,omega+w+M] [rad],[m] (6xN)

jacob:

(optional) transformation jacobian d(rx,ry,rz,vx,vy,vz)/d(a,ex,ey,ix,iy,omega+w+M) (6x6xN)

Bibliography

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

Authors

CNES - DCT/SB

See also

CL_oe_cirEqua2car, CL_oe_car2cir, CL_co_car2sph, CL_co_car2ell, CL_oe_car2kep

Examples

// Example 1
pos_car=[-29536113;30329259;-100125];
vel_car=[-2194;-2141;-8];
[cirequa,jacob1] = CL_oe_car2cirEqua(pos_car,vel_car);
[pos_car2,vel_car2,jacob2] = CL_oe_cirEqua2car(cirequa);