RHSOptimalFPA:

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   Compute the delta-V required to raise the orbit to altitude "hF".

   The first delta-v is applied at a point when the vehicle is at altitude
   "h0", velocity "v0", and flight path angle "gamma". The delta-v is
   applied along the original velocity vector at flight path angle "gamma"

   The first delta-v is computed so that the transfer orbit achieves
   apogee at altitude "hF".

   The second delta-v is applied at apogee of the transfer orbit, which is
   at altitude "hF". The flight path angle at this point is zero. The
   final velocity is the circular orbit velocity for this altitude. The
   delta-v is simply the difference between the circular orbit velocity
   and the transfer orbit velocity at its apogee.

   Since version 2015.1
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   Form:
   [dV,dV1,dV2,dVDrag] = RHSOptimalFPA( gamma, h0, hF, v0, bC )
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   ------
   Inputs
   ------
   gamma      (1,1)     Initial flight path angle (rad)
   h0         (1,1)     Initial altitude (km)
   hF         (1,1)     Final altitude for orbit (km)
   v0         (1,1)     Initial velocity (km/s)
   bC         (1,1)     Ballistic coefficient (kg/m^2). If not supplied,
                        drag is ignored;

   -------
   Outputs
   -------
   dV         (1,1)     Total delta-v, dV1 + dV2 + dVDrag (km/s)
   dV1        (1,1)     First delta-v at h0 (km/s)
   dV2        (1,1)     Second delta-v at hF (km/s)
   dVDrag     (1,1)     Approximate delta-v due to drag

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   See also BoostPhaseDeltaV, OrbitDrag
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Children:

LaunchVehicle: TSTO/BoostPhaseDeltaV
Orbit: OrbitMechanics/OrbitDrag