RHSLaunchVehicle3D:

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   The right hand side of a 3D launch model with gravity turn.
   
   Compute position, velocity and mass derivatives assuming a rotating
   spherical planet and an exponential atmosphere. The model can handle
   multiple stages. For each stage you add a fuel state to x. Thus a 3
   stage vehicle will have 9 states. Any planet that is included in
   AtmDens1 can be simulated.

   The data structure is the same as is used in RHSLaunchVehicle2D with the
   addition of mu and omegaE.

   Since version 1.0
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   Form:
   xDot = RHSLaunchVehicle3D( x, t, d )
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   Inputs
   ------
   x         (6+n,1)  [r v massFuel]
   t           (1,1)  Time (not used)
   d            (.)   Data structure
                      .rocket  (.)  Rocket model
                      .cDA    (1,:) Drag coefficient of each stage times area
                      .Rp     (1,1) Planet radius (km)
                      .planet (1,:) Planet name, may be empty for Earth
                      .omegaE (3,1) Earth rotation
                      .mu     (1å,1) Gravitational parameter

   -------
   Outputs
   -------
   xDot        (:,1)  State derivative

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	References:	Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
               pp. 207-211.
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Children:

AeroUtils: AtmosphericCalculations/AtmDens1
Math: Linear/Cross
Math: Linear/Mag
Math: Linear/Unit