CL_man_sma

Description

• This function is deprecated.

  Replacement function: CL_man_dvSma

• Delta-v required to change the semi major axis by one maneuver at the peripasis or apoapsis.

  The output argument dv is the delta-V in spherical coordinates in the "qsw" local orbital frame.

  anv is the true anomaly at the position of the maneuver.

• Note: The results are set to %nan if the targeted semi major-axis is unreachable.

Parameters

ai :

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

ei:

Initial eccentricity (1xN or 1x1)

af :

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

posman:

(optional) Flag specifying the position of the maneuver: 0 or "per" -> periapsis, 1 or "apo" -> apoapsis. Default is at 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" frame [lambda;phi;|dv|] [rad,rad,m/s] (3xN)

anv:

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

Authors

• CNES - DCT/SB

See also

• CL_man_biElliptic

• CL_man_hohmann

• CL_man_hohmannG

Examples

ai = 7200.e3; af = 7000.e3; ei = 0.1; [dv,anv] = CL_man_sma(ai,ei,af) // Check results : kep = [ai ; ei ; %pi/2 ; 0 ; 0 ; anv]; kep1 = CL_man_applyDv(kep,dv)