AsteroidTrajectory:

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   Example problem from AIAA challenge.
   The asteroid in question should hit the Earth.
   Demonstrates an n-body gravity model using point masses. There is an 
   option to include the perturbations or to integrate with only the sun.  
   The perturbations bring the final position from an 883 Earth radii miss
   distance to only 5 radii. The perturbations include the major planets, 
   except Pluto, and the moon.

   Has a built-in RHS function combining ephemeris with gravity.
   The plots at the end can be replicated with the function output.

   Since version 7.
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   Form:
   [xPlot,tPlot,rEarth,rMars] = AsteroidTrajectory( perturbations )
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   Inputs
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   perturbations    (1,1)    1 to include perturbations, 0 otherwise

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Children:

Common: Database/Constant
Common: General/IsVersionAfter
Common: Graphics/Plot2D
Common: Graphics/Plot3D
Common: Time/Date2JD
Math: Linear/Mag
Orbit: OrbitMechanics/APlanet
OrbitMiniToolbox: Support/El2RV
SC: Ephem/PlanetPosJPL
SC: Ephem/SolarSysJPL