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FOrbitMultiSpacecraft:

Path: CubeSat/Simulation

--------------------------------------------------------------------------
   Multispacecraft orbit model designed to work with ode113.

   You can include aerodynamic, radiation pressure and thrust models. Sun,
   earth, and moon perturbations are computed if the planet (Earth or
   Moon) is given. Uses SunV1 and MoonV1 for ephemeris. 
--------------------------------------------------------------------------
   Form:
      d = FOrbitMultiSpacecraft             % data structure
   xDot = FOrbitMultiSpacecraft( t, x, d )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   t                Time
   x       (7*n,1)  The state vector [r1;v1;m1;r2;v2;m2;...]
   d       (:)      Data structure array
                    .jD0                       (1,1)   Julian date at start

                    This is only needed for planetary disturbances
                    and if a gravity model is entered:

                    .planet                   (1,:)   Planet name, 'earth', 'moon'

                    These are optional:

                    .thrusterModel            (1,:)   Thrust function handle
                    .thrusterData             (.)     Thrust data structure
                    .opticalModel             (1,:)   Optical function handle
                    .aeroModel                (1,:)   Aero function handle
                    .surfData                 (.)     Surface data structure
                    .gravityModel             (.)     Gravity model structure

                    The following are only needed if you want J70, otherwise
                    AtmDens2 will be used.

                    .atm.aP                    (1,1)   Geomagnetic index 6.7 hours before the computation
                    .atm.f                     (1,1)   Daily 10.7 cm solar flux (e-22 watts/m^2/cycle/sec)
                    .atm.fHat                  (1,1)   81-day mean of f (e-22 watts/m^2/cycle/sec)
                    .atm.fHat400               (1,1)   fHat 400 days before computation date

   -------
   Outputs
   -------
   xDot    (7*n,1)  The state vector derivative [v1;r1Dot;m1Dot...]

--------------------------------------------------------------------------
   See also CubeSatEnvironment, ECIToPlanet, AGravityC, FOrbCart,
   PlanetaryAccelerations CubeSatRadiationPressure, CubeSatAero,
   CubeSatPropulsion
--------------------------------------------------------------------------

Children:

AeroUtils: AtmosphericCalculations/AtmDens2
AeroUtils: AtmosphericCalculations/AtmJ70
Common: Database/Constant
Common: Quaternion/QZero
Common: Time/JD2000
CubeSat: Utilities/CubeSatAttitude
Math: Linear/Mag
Math: Linear/Skew
Math: Linear/Unit
Orbit: OrbitMechanics/AGravityC
Orbit: OrbitMechanics/APlanet
SC: BasicOrbit/FOrbCart
SC: Ephem/ECIToPlanet
SC: Ephem/Eclipse
SC: Ephem/MoonV1
SC: Ephem/SunV1

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