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CL_man_hohmannG

Delta V for a generalized Hohmann transfer

Calling Sequence

[delta_v,dv1,dv2,anv1,anv2] = CL_man_hohmannG(ai,ei,af,ef [,posman1,rotation,mu])

Description

Parameters

ai :

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

ei:

Eccentricity of initial orbit (1xN)

af :

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

ef:

Eccentricity of final orbit (1xN)

posman1:

(optional) Flag indicating the location of the first maneuver (0->periapsis, 1->apoapsis; default is 0) (1xN)

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)

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

See also

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,1,0)
// 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,1,1)
// 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)
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