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  Differential accelerations for spacecraft in formation assuming the
  worst case. 
  
  The relative accelerations are due to :
  1) Earth's Gravitational potential (geopotential)
  2) Atmospheric drag
  3) Sun 
  4) Moon
  4) Solar radiation pressure
  5) Linearization of equations of motion

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  Form: 
  [aDiff, aTerms] = WorstCasePerturbations( h, dR, mSC, Cd, Cr );
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  Inputs:
  -------
  h         (1)  altitude of (circular) orbit (km)
  dR        (1)  distance between the spacecraft (km)
  mSC       (1)  spacecraft mass (kg)
  Cd        (1)  drag coefficient
  Cr        (1)  reflectivity of s/c: 0.0 for translucent; 1.0 for black-body; 
                  2.0 for flat mirror 

  -------
  Outputs:
  --------
  aDiff     (1)  sum of all the terms (m/s/s)
  aTerms    (.)  data structure containing the individual differential
                 accelerations
            - J2     (3,1)  earth's oblateness  
            - drag   (3,1)  drag
            - sun    (3,1)  effect of sun
            - moon   (3,1)  effect of moon  
            - solar  (3,1)  solar radiation
            - linear (3,1)  linearization approximation error
              
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	 Code Author: This code was originally written by Mark Campbell and
	 modified by Bogdan Udrea as part of formation_flying code for TechSat-21. 
   Further modified and commited by Lavanya Swetharanyan 
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   Copyright 2004 Princeton Satellite Systems, Inc. All rights reserved.
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