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% Two impulse optimal orbit transfer.
Computes the delta-v needed to go from a transfer orbit
to a final orbit with a plane change in two impulses.
Since version 1.
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Form:
[dv, dv1t, dvt2, et, theta] = Tfr2Imp( e1, a1, e2, a2, i1, i2, mu )
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Inputs
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e1 Eccentricity of the first orbit
a1 Semi-major axis of the first orbit
e2 Eccentricity of the final orbit
a2 Semi-major axis of the final orbit
i1 Initial inclination (deg)
i2 Final inclination (deg)
mu Gravitational parameter
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Outputs
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dv Total delta v
dv1t Delta v for first burn
dvt2 Delta v for second burn
et Eccentricity of second orbit
theta Angle of 2nd delta-v (deg)
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References: Kaplan, M., Modern Spacecraft Dynamics and Control, John
Wiley, pp. 87-91.
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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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