Name

CL_man_apsidesLine — Delta V for a maneuver to modify line of apsides

Calling Sequence

   [dv,anv] = CL_man_apsidesLine(ai,ei,pomi,pomf[,posman[,mu]])
   
   

Description

  • This function computes the velocity impulsion needed for a maneuver to modify the line of apsides. Maneuver consists to modify the argument of periapsis in the orbit plan. Semi major axis and eccentricity are not modified.

    Output dv is the impulsion required 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.

    posman can be used to define maneuver execution point (0-> next to periapsis, 1->next to apoapsis, default is 0)

  • Last update : 13/2/2008

Parameters

ai :

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

ei:

initial orbit eccentricity (1xN)

pomi:

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

pomi:

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

posman:

(optional) flag to indicate maneuver execution point (0-> next to periapsis, 1->next to apoapsis, default is 0) (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_inclination

Examples

// Maneuver at apogee
ai = 7200.e3;
ei = 0.1;
pomi = CL_deg2rad(65);
pomf = CL_deg2rad(85);
[dv,anv] = CL_man_apsidesLine(ai,ei,pomi,pomf,1)
// Check results :
anm = CL_kp_v2M(ei,anv);
kep = [ai ; ei ; %pi/2 ; pomi ; 0 ; anm];
kep1 = CL_man_applyDv(kep,dv)