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   Runs the collision monitoring algorithm. Propagates forward for a fixed time
   assuming no maneuvers. Calls CollisionMonAlg.
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   Form:
   [prob, dMin, xhat, Shat, t] = PredictCollision( d, jD, y );
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   ------
   Inputs
   ------
   d        :     Algorithm data structure
                  .hRef          Altitude of the reference orbit (km)
                  .eRef          Eccentricity
                  .MRef          Mean anomaly
                  .dR            Reference length of Hill's orbit (km)
                  .initBounds    Error in measurement (6,1)
                  .scalev        Sigma for measurement noise
                  .mSC           Spacecraft mass (kg)
                  .lenSC         Spacecraft length (m)
                  .diaSC         Spacecraft diameter (m)
                  .Cd            Drag coefficient
                  .Cr            Reflectivity of s/c: 0.0 for translucent; 
                                   1.0 for black-body; 2.0 for flat mirror
   jD      (1)    Epoch in Julian date
   y       (6,n)  Spacecraft relative state in Hill's frame (km, km/s)

   -------
   Outputs
   -------
   prob   {n}(1,:)     probability of collision    
   d      {n}(1,:)     minimum distance between spacecraft position ellipsoids
   xhat   {n}(6,:)     xhat, ellipsoid centers
   Shat   {n}(6,6,:)   Shat, ellipsoid size matrices
   t
 
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