Path: Orbit/OrbitMechanics
% Three impulse orbit transfer.
Computes the delta-v needed to go from a transfer orbit
to a final orbit with a plane change in three impulses.
Generally n should be as large as possible but this will
run into the law of diminishing returns and operational
constraints.
Since version 1.
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Form:
[dv, dv12, dv23, dv34, e2, e3, theta] = Tfr3Imp( e1, a1, e4, a4, n, i1, i4 ,mu )
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Inputs
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e1 Eccentricity of the first orbit
a1 Semi-major axis of the first orbit
e4 Eccentricity of the final orbit
a4 Semi-major axis of the final orbit
n Ratio of intermediate apogee to final apogee
i1 Initial inclination (deg)
i4 Final inclination (deg)
mu Gravitational parameter
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Outputs
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dv Total delta v
dv12 Delta v for first burn
dv23 Delta v for second burn
dv34 Delta v for third burn
e2 Eccentricity of second orbit
e3 Eccentricity of third orbit
theta Angle of 2nd delta-v (deg)
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References: Kaplan, M., Modern Spacecraft Dynamics and Control, John
Wiley, p. 87.
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Orbit: OrbitCoord/A2Apogee Orbit: OrbitCoord/A2Perige Orbit: OrbitCoord/RARP2E Common: General/DeBlankLT Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/PltStyle Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Math: Linear/DupVect
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