Name

CL_man_applyDv — Modification of osculating orbital elements after a maneuver defined in QSW frame.

Calling Sequence

   kep_dv = CL_man_applyDv(kep,dv_local[,mu])
   
   

Description

  • This function evaluates the effect of an impulsive maneuver (instant change of velocity) on the orbital parameters. Orbit must be given as input in osculating keplerian parameters (kep) and position on orbit is defined by mean anomaly. This parameter is used to define the maneuver execution position because there is no orbit extrapolation.

    Maneuver is defined by its position (mean anomaly of kep) and its direction and modulus dv_local = [lambda;phi;norm] defined in the local orbital frame QSW with spheric coordinates : first parameter lambda is the in plane component (pi ~= towards planet and pi/2 = along velocity) second parameter phi is the out of plane component, positive towards the kinetic moment, third parameter is the norm

  • Last update : 15/2/2008

Parameters

kep:

osculating keplerian parameters of original orbit in inertial frame [m,rad] (6xN)

dv_local:

maneuver in spheric coordinates in satellite local frame QSW [lambda;phi;|dv|] [rad,rad,m/s] (3xN)

mu :

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

kep_dv:

osculating keplerian parameters of orbit in inertial frame after maneuver execution [m,rad] (6xN)

Authors

CNES - DCT/SB

See also

CL_fr_qswMat, CL_fr_inertial2qsw, CL_man_thrustDuration, CL_man_incRaanCirc, CL_man_hohmann, CL_man_biElliptic, CL_man_consumption, CL_man_hohmannG, CL_man_inclination