MissileTrajAnalysis

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   Analyze the trajectories for around-the-Earth missile launches.

   Simulates a ballistic missile trajectory and analyze the relationship
   between time of flight, initial velocity, initial flight path angle,
   maximum altitude.

   Simplifications made for this analysis:
     + Desired velocity is applied instantaneously -- no launch dynamics.
     + The rotation of the Earth is ignored
     + Atmospheric forces are ignored
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   Form:
   d = MissileTrajAnalysis( lla0, llaF, tFDes, dragOn )
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   Inputs
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   r               (3,1) Position vector in ECI frame
   n               (3,1) Normal vector in ECI frame

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   Outputs
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   R               (3,3) Rotation matrix from ECI to Orbital Plane

   See also: OrbNEl, OrbitalPlane
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