Name

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

  • This function computes inclination and RAAN maneuver for circular orbits:

    dv is the velocity increment required given in spherical coordinates in the QSW frame : 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

    arg_lat is the argument of latitude of the maneuver.

  • Last update : 21/02/2007

Parameters

sma :

semi-major axis of orbit [m] (1xN)

inci:

inclination of initial orbit [rad] (1xN)

raani:

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

incf:

inclination of final orbit [rad] (1xN)

raanf:

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

mu :

(optionnal) 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)