Name

CL_man_inclination — Delta V for an inclination maneuver

Calling Sequence

   [dv,anv] = CL_man_inclination(ai,ei,inci,pomi,incf[,posman[,mu]])
   
   

Description

  • This function computes the velocity increment needed for an inclination maneuver. Maneuver consists to rotate the orbit plan around the line of apsides, executing the maneuver at a node.

    Output dv is the velocity increment given in spheric coordinates in 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

    anv is the true anomaly of maneuver execution point in radians.

    Optional flag posman can be used to define maneuver execution point (1->ascending node, -1->descending node, 0->point of optimal cost)

  • Last update : 13/2/2008

Parameters

ai :

initial orbit semi major axis [m] (1xN)

ei:

initial orbit eccentricity (1xN)

inci :

initial orbit inclination [rad] (1xN)

pomi:

initial orbit argument of periapsis [rad] (1xN)

incf :

final orbit desired inclination [rad] (1xN)

posman:

(optional) flag to indicate maneuver execution point (1->ascending node, -1->descending node, 0->point of optimal cost, default is ascending node) (1xN)

mu :

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

dv :

velocity impulsion required in spheric coordinates in QSW frame [lambda;phi;|dv|] [rad,rad,m/s] (3xN)

anv:

true anomaly of maneuver execution point [rad] (1xN)

Authors

CNES - DCT/SB

See also

CL_man_biElliptic, CL_man_hohmann, CL_man_sma, CL_man_hohmannG, CL_man_apsidesLine

Examples

ai = 7200.e3;
ei = 0.1;
inci = CL_deg2rad(65);
pomi = CL_deg2rad(110);
incf = CL_deg2rad(70);
[dv,anv] = CL_man_inclination(ai,ei,inci,pomi,incf,0)
// Check results :
anm = CL_kp_v2M(ei,anv);
kep = [ai ; ei ; inci ; pomi ; 0 ; anm];
kep1 = CL_man_applyDv(kep,dv)