AsteroidOrbitDemo:

% Example orbit propagation problem from an AIAA student challenge.
   The asteroid in question should hit the Earth.
   Demonstrates an n-body gravity model. There is an option to 
   include the perturbations or to integrate with only the sun. The 
   perturbations bring the final position from an 1174 Earth radii miss distance
   to only 5 radii. The integration runs for a fixed amount of time using
   ode113, so it is possible that there is an even closer pass within a day
   of the endpoint.

   Since version 7.
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  See also AsteroidTrajectory
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%
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   Copyright (c) 2006. Princeton Satellite Systems, Inc. All rights reserved.
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Children:

Sail: Missions/AsteroidTrajectory