Collision monitoring algorithm for maneuvering spacecraft. 
  Discretizes orbit according to input time and anomaly vectors. Handles 
  high eccentricity and maneuvers input through acceleration vector.

   Since version 7.
  [prob, dMin, Shat, xhat] = CollisionMonAlg( y, t, M, nu, accel, aDiff, d )

   y      (6,m)   Relative state(s)
   t      (1,n)   Time vector [s]
   M      (1,n)   Mean anomaly vector
   nu     (1,n)   True anomaly vector
   accel   {m}    Accelerations due to maneuvers
   aDiff  (3,m)   Differential accelerations
   d        :     Algorithm data structure
                  .eRef          Eccentricity
                  .MRef          Mean anomaly
                  .initBounds    Error in measurement (6,1) [km, km/s]
                  .scalev        Sigma for measurement noise
                  .lenSC         Spacecraft length [m]
                  .Pmin          Probability of scalev
                  .Ssc           Spacecraft hard-body sphere
                  .S0            Initial ellipsoid

   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
  Reference: Mark Campbell, Collision Monitoring Within Satellite
  Clusters. IEEE Transactions on Control Systems Technology, Jan. 2005


Common: Control/C2DZOH
FormationFlying: Collision/CollProbSet
FormationFlying: Collision/DistantPtToEll
FormationFlying: EccDynamics/FFEccLinOrb
FormationFlying: Transformation/DeltaEl2Alfriend
FormationFlying: Transformation/DeltaElem2Hills
Math: Linear/Mag
Math: Trigonometry/UnwrapPhase
Math: Trigonometry/WrapPhase
Orbit: OrbitCoord/El2Alfriend
Orbit: OrbitMechanics/GVEDynamics
OrbitMiniToolbox: Support/M2Nu
SC: BasicOrbit/OrbRate