Effect of maneuver on orbital elements
kep_dv = CL_man_applyDvKep(kep,dv [,dv_frame,mu])
Computes the effect of an impulsive maneuver (instantaneous velocity increment) on keplerian orbital elements.
The (osculating) orbital elements must be given at the time of maneuver as there is no orbit propagation.
The maneuver is defined by the components of the velocity increment one local frame (default is "qsw").
Initial (osculating) Keplerian elements [m,rad] (6xN)
Velocity increment (in cartesian coordinates) in the local frame [m/s] (3xN)
Local frame in which dv is defined. Default is "qsw"
(optional) Gravitational constant [m^3/s^2]. Default is %CL_mu
(osculating) Keplerian elements with the effect of the maneuver included [m,rad] (6xN)
CNES - DCT/SB
// Manoeuvre : 7200km to 7000km : ai = 7200.e3; af = 7000.e3; [deltav,dv1,dv2,anv1,anv2] = CL_man_dvHohmann(ai,af); // Check results: // NB: here, true anomaly = mean anomaly kep = [ai ; 0 ; %pi/2 ; 0 ; 0 ; anv1]; kep1 = CL_man_applyDvKep(kep,dv1,dv_frame="qsw"); kep1(6) = anv2; kep2 = CL_man_applyDvKep(kep1,dv2,dv_frame="qsw") |  |  |