Tfr2Imp:

Path: Orbit/OrbitMechanics

% 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
   ------
   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

   -------
   Outputs
   -------
   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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Children:

Orbit: OrbitCoord/A2Apogee
Orbit: OrbitCoord/A2Perige
Orbit: OrbitCoord/RARP2E

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