Inclination and RAAN maneuver for circular orbits
[dv,arg_lat]=CL_man_incRaanCirc(sma,inci,raani,incf,raanf [,mu])
Computes the dv needed for an inclination and RAAN change for a circular orbit.
dv is the velocity increment vector (in spherical coordinates) in the QSW frame : [lambda; phi; norm], where lambda: angle between the radius vector and the projection of dv on the orbit plane, phi: angle between dv and its projection on the orbit plane, norm = |dv|.
arg_lat is the argument of latitude of the maneuver.
Semi-major axis [m] (1xN)
Initial inclination [rad] (1xN)
Initial right ascension of ascending node [rad] (1xN)
Final inclination [rad] (1xN)
Final right ascension of ascending node [rad] (1xN)
(optional) Gravitational constant. [m^3/s^2] (default value is %CL_mu)
Velocity increment in spherical coordinates in the QSW frame [lambda;phi;|dv|] [rad;rad;m/s] (3xN)
Argument of latitude of the maneuver [rad] (1xN)
CNES - DCT/SB