$LastChangedDate: 27-Juil-2011 $

# CL_man_incRaanCirc

Inclination and RAAN maneuver for circular orbits

## Calling Sequence

       [dv,arg_lat]=CL_man_incRaanCirc(sma,inci,raani,incf,raanf [,mu])

## Description

- 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.

## Parameters

sma :

  Semi-major axis [m] (1xN)

inci:

  Initial inclination [rad] (1xN)

raani:

  Initial right ascension of ascending node [rad] (1xN)

incf:

  Final inclination [rad] (1xN)

raanf:

  Final right ascension of ascending node [rad] (1xN)

mu :

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

dv :

  Velocity increment in spherical coordinates in the QSW frame [lambda;phi;|dv|] [rad;rad;m/s] (3xN)

arg_lat:

  Argument of latitude of the maneuver [rad] (1xN)

## Authors

- CNES - DCT/SB

## Examples

    sma = 7200.e3;
    inci = CL_deg2rad(111);
    raani = CL_deg2rad(12);
    incf = CL_deg2rad(108);
    raanf = CL_deg2rad(15);
    [dv,arg_lat]=CL_man_incRaanCirc(sma,inci,raani,incf,raanf)
    kep = [sma*ones(inci);zeros(inci);inci;zeros(inci);raani;arg_lat];
    kep1 = CL_man_applyDv(kep,dv)