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CL_man_dvIncSma

Inclination + semi-major axis maneuver (uncontrolled eccentricity)

Calling Sequence

[deltav, dv, anv] = CL_man_dvIncSma(ai, ei, inci, pomi, af, incf [[, posman, icheck, mu, res="d"]])
man = CL_man_dvIncSma(ai, ei, inci, pomi, af, incf [[, posman, icheck, mu, res="s"]])

Description

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 "an". (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. Default is %CL_mu [m^3/s^2] (1x1)

res :

(string, optional) Type of output: "d" or "s" for . Default is "d". (1x1)

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

See also

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_kp_apsConvert("ra", rai, "rp", rpi, ["sma", "ecc"]);
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)

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