FOrbitMultiSpacecraft:

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   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. Specify the
   atmospheric density model (for example: AtmJ70ToGround, AtmDens2) in
   the data structure

   Since version 8.
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   Form:
   xDot = FOrbitMultiSpacecraft( t, x, d )
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   Inputs
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   t                Time
   x       (7*n,1)  The state vector [r1;v1;m1;r2;v2;m2;...]
   d       (1,1)    Data structure
                    .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

                    These are optional

                    .thrustModel               (1,:)   Thrust function handle
                    .thrustData                (n)     Data structures for thrust model
                    .radiationPressureModel    (1,:)   Radiation pressure function handle
                    .radiationPressureData     (n)     Radiation pressure data
                    .aeroModel                 (1,:)   Aero function handle
                    .aeroData                  (n)     Aero data structure
                    .gravityModel              (1,1)   See AGravityCStruct

                    The following ais only needed if you don't have a gravity model

                    .mu                        (1,1)   Gravitational parameter

                    The following are only needed if you have an aero model

                    .atmModel               (1,:)   Atmospheric model function handle
                    .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

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

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Children:

Math: Linear/Mag
Orbit: OrbitMechanics/AGravityC
Orbit: OrbitMechanics/PlanetaryAccelerations
SC: BasicOrbit/FOrbCart
SC: Ephem/ECIToPlanet
SC: Ephem/Eclipse
SC: Ephem/SunV1