CL_man_hohmannG

Description

• This function is deprecated.

  Replacement function: CL_man_dvHohmannG

• Computes the maneuvers of a generalized Hohmann transfer.

  This function computes the 2 velocity increments that transform an initial orbit defined by semi-major axis and eccentricity into a final orbit also defined by semi-major axis and eccentricity.

  The first velocity increment can be at the periapsis or apoapsis of the initial orbit, depending on the value of posman1.

  The second velocity increment is 180 degrees apart.

  delta_v is the sum of the norms of the velocity increments:

  delta_v = |dv1| + |dv2|

  The velocity increments are given in spherical coordinates in the "qsw" local orbital frame.

  anv1 is the true anomaly (on the initial orbit) at the location of the 1st velocity increment, and anv2 is the anomaly (on the intermediate orbit) at the location of the 2nd velocity increment.

  posman1 is used to define the location of the first maneuver.

  rotation defines whether the final orbit should have its line of apsides rotated 180deg relative to the initial orbit.

  

Parameters

ai :

Semi-major axis of initial orbit [m] (1xN or 1x1)

ei:

Eccentricity of initial orbit (1xN or 1x1)

af :

Semi-major axis of final orbit [m] (1xN or 1x1)

ef:

Eccentricity of final orbit (1xN or 1x1)

posman1:

(optional) Flag indicating the location of the first maneuver: 0 or "per" -> periapsis, 1 or "apo" -> apoapsis. Default is at the periapsis. (1xN or 1x1)

rotation:

(optional) Flag indicating whether the final orbit should have its perigee rotated 180deg relative to the initial orbit (0->no rotation, 1->rotation ; default is 0) (1xN or 1x1)

mu :

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

delta_v :

Total delta-v required = |dv1| + |dv2|. [m/s] (1xN)

dv1 :

First velocity increment in spherical coordinates in the "qsw" frame [lambda;phi;|dv|] [rad,rad,m/s] (3xN)

dv2 :

Second velocity increment in spherical coordinates in the "qsw" frame [lambda;phi;|dv|] [rad,rad,m/s] (3xN)

anv1:

True anomaly at the location of the first velocity increment (in the initial orbit). [rad] (1xN)

anv2:

True anomaly at the location of the second velocity increment (in the intermediate orbit). [rad] (1xN)

Authors

• CNES - DCT/SB

See also

• CL_man_biElliptic

• CL_man_hohmann

• CL_man_sma

Examples

// Maneuver at apogee, no rotation ai = 7200.e3; af = 7000.e3; ei = 0.1; ef = 0.1; [delta_v,dv1,dv2,anv1,anv2] = CL_man_hohmannG(ai,ei,af,ef,posman=1,rotation=0) // Check results : kep = [ai ; ei ; %pi/2 ; 0 ; 0 ; anv1]; kep1 = CL_man_applyDv(kep,dv1); kep1(6) = anv2; kep2 = CL_man_applyDv(kep1,dv2) // Maneuver at apogee, with rotation ai = 7200.e3; af = 7000.e3; ei = 0.1; ef = 0.1; [delta_v,dv1,dv2,anv1,anv2] = CL_man_hohmannG(ai,ei,af,ef,posman=1,rotation=1) // Check results : kep = [ai ; ei ; %pi/2 ; 0 ; 0 ; anv1]; kep1 = CL_man_applyDv(kep,dv1); kep1(6) = anv2; kep2 = CL_man_applyDv(kep1,dv2)