CL_man_dvIncSma

Description

• Computes the velocity increment needed to change the inclination and the semi major axis.

  The maneuver can be performed at the ascending or descending node only.

  The output argument dv is the velocity increment vector in the "qsw" local orbital frame.

  anv is the true anomaly at the maneuver position.

  The optional flag posman can be used to define the position of the maneuver (maneuver at ascending node, descending node).

  The optional flag icheck is used to enforce no checking on the final inclination value. If the targetted inclination is less than 0 or more than pi, the ascending node will rotate 180 degrees. If icheck is true, the right ascension of the ascending node is not changed by the maneuver.

  If the argument res is present and is equal to "s", all the output data are returned in a structure.

Parameters

ai :

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

ei :

Eccentricity (1xN or 1x1)

inci :

Initial inclination [rad] (1xN or 1x1)

pomi :

Argument of periapsis [rad] (1xN or 1x1)

af :

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

incf :

Final inclination [rad] (1xN or 1x1)

posman :

(optional) Flag specifying the position of the maneuver: 1 or "an" -> ascending node, -1 or "dn" -> descending node. Default is at the ascending node. (1xN or 1x1)

icheck:

(optional, boolean) Flag specifying if incf must be checked in the standard range for inclination values ([0, pi]). Default is %t. (1x1)

mu :

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

res :

(string, optional) Type of output: "d" or "s" for . Default is "d".

deltav :

Norm of velocity increment. [m/s] (1xN)

dv :

Velocity increment (in cartesian coordinates) in the "qsw" local frame [m/s] (3xN)

anv :

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

man :

Structure containing all the output data.

Authors

• CNES - DCT/SB

See also

• CL_man_dvInc

• CL_man_dvSma

Examples

// Typical transfer from GTO to GEO (at apogee = ascending node) rai = 42164.e3; // radius at apogee rpi = 6578.e3; // radius at perigee [ai, ei] = CL_op_rarp2ae(rai, rpi); inci = 7 * %pi/180; pomi = %pi; // apogee = ascending node af = 42164.e3; incf = 0; [deltav,dv,anv] = CL_man_dvIncSma(ai,ei,inci,pomi,af,incf,posman="an") // Check results: anm = CL_kp_v2M(ei,anv); // mean anomaly kep = [ai ; ei ; inci ; pomi ; 0 ; anm]; CL_man_applyDvKep(kep,dv)