CL_man_apsidesLine

Description

• This function is deprecated.

  Replacement function: CL_man_dvApsidesLine

• Computes the velocity increment needed to modify the line of apsides.

  The maneuver consists in making the orbit rotate in the orbit plane. Thus, only the argument of periapsis is changed; the semi major axis or the eccentricity are not.

  The output argument dv is the velocity increment expressed in spherical coordinates in the "qsw" local frame.

  anv is the true anomaly at the position of maneuver.

  posman can be used to define where the maneuver takes place.

Parameters

ai :

Initial semi major axis [m] (1xN or 1x1)

ei:

Initial eccentricity (1xN or 1x1)

pomi:

Initial argument of periapsis [rad] (1xN or 1x1)

pomf:

Final argument of periapsis [rad] (1xN or 1x1)

posman:

(optional) Flag specifying the maneuver location: 0 or "nper" -> near periapsis, 1 or "napo" -> near apoapsis. Default is close to the periapsis. (1xN or 1x1)

mu :

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

dv :

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

anv:

True anomaly at the position of the maneuver [rad] (1xN)

Authors

• CNES - DCT/SB

See also

• CL_man_biElliptic

• CL_man_hohmann

• CL_man_sma

• CL_man_hohmannG

• CL_man_inclination

Examples

ai = 7200.e3; ei = 0.1; pomi = 1; pomf = 1.1; [dv,anv] = CL_man_apsidesLine(ai,ei,pomi,pomf,posman=1) // Check results : anm = CL_kp_v2M(ei,anv); kep = [ai; ei; %pi/2; pomi; 0; anm]; kep1 = CL_man_applyDv(kep,dv)