CL_oe_cirEqua2car

Description

• This function is deprecated.

  Replacement function: CL_oe_cireq2car

  "cirEqua" orbital elements are identical to "cireq" orbital elements except that ix=2*sin(i/2)*cos(raan) and iy=2*sin(i/2)*sin(raan)

• Converts orbital elements adapted to near-circular near-equatorial orbits to position and velocity for an elliptic orbit.

  The transformation jacobian is also optionally computed.

  See Orbital elements for more details

Parameters

cir_equa:

orbital elements adapted to near-circular near-equatorial orbits [sma;ex;ey;ix;iy;pom+raan+anm] [m,rad] (6xN)

mu :

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

pos_car:

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

vel_car:

velocity [Vx;Vy;Vz] [m/s] (3xN)

jacob:

(optional) transformation jacobian (See Orbital elements for more details) (6x6xN)

Bibliography

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

Authors

• CNES - DCT/SB

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(cir_equa); [cirequa2,jacob2] = CL_oe_car2cirEqua(pos_car,vel_car);