Effect of maneuver on orbital elements - DEPRECATED
kep_dv = CL_man_applyDv(kep,dv_local [,mu])
This function is deprecated.
Replacement function: CL_man_applyDvKep
Computes the effect of an impulsive maneuver (instantaneous velocity increment) on orbital elements.
The (osculating) orbit elements must be given at the time of maneuver as there is no orbit propagation.
The maneuver is defined by the components of the delta-V in the QSW local frame in spherical coordinates:
dv_local = [lambda;phi;dv] (lambda: in-plane angle (pi = towards planet and pi/2 ~ along velocity), phi: out-of-plane angle, positive towards the angular momentum vector (the angular momentum vector is perpendicular to the orbit plane and oriented according to the right hand rule), dv: norm of delta-V).
Initial (osculating) Keplerian elements [m,rad] (6xN)
delta-V in spherical coordinates in the QSW local frame [lambda;phi;|dv|] [rad,rad,m/s] (3xN)
(optional) Gravitational constant [m^3/s^2] (default is %CL_mu)
(Osculating) Keplerian elements including the effect of the maneuver [m,rad] (6xN)
CNES - DCT/SB