$LastChangedDate: 27-Juil-2011 $

# CL_man_applyDv

Effect of maneuver on orbital elements

## Calling Sequence

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

## Description

- 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).

- The orbital elements are the following:

## Parameters

kep:

  Initial (osculating) Keplerian elements [m,rad] (6xN)

dv_local:

  delta-V in spherical coordinates in the QSW local frame [lambda;phi;|dv|] [rad,rad,m/s] (3xN)

mu :

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

kep_dv:

  (Osculating) Keplerian elements including the effect of the maneuver [m,rad] (6xN)

## Authors

- CNES - DCT/SB

## See also

- CL_fr_qswMat

- CL_fr_inertial2qsw

## Examples

    // Manoeuvre : 7200km to 7000km :
    ai = 7200.e3;
    af = 7000.e3;
    [delta_v,dv1,dv2,anv1,anv2] = CL_man_hohmann(ai,af);

    // Check results using CL_man_applyDv:
    kep = [ai ; 0 ; %pi/2 ; 0 ; 0 ; anv1];
    kep1 = CL_man_applyDv(kep,dv1);
    kep1(6) = anv2;
    kep2 = CL_man_applyDv(kep1,dv2)