Name

CL_oe_cirEqua2car — Circular equatorial adapted to cartesien orbital elements

Calling Sequence

   [pos_car,vel_car[,jacob]]=CL_oe_cirEqua2car(cir_equa[,mu])
   
   

Description

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

    The transformation jacobian is also optionally computed.

  • Last update : 29/11/2007

Parameters

cir_equa:

circular equatorial adapted parameters [a,ex,ey,ix,iy,omega+w+M] [rad],[m] (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,ex,ey,ix,iy,omega+w+M) (6x6xN)

Bibliography

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

Authors

CNES - DCT/SB

See also

CL_oe_car2cirEqua, CL_oe_cir2car, CL_oe_car2cir

Examples

// Example 1
cir_equa=[42166.712;-7.9d-6;1.1d-4;1.2d-4;-1.16d-4;5.3];
[pos_car,vel_car,jacob1] = CL_oe_cirEqua2car(cirequa);
[cirequa2,jacob2] = CL_oe_car2cirEqua(pos_car,vel_car);