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dc.contributor.advisorCleary, David
dc.contributor.advisorRoss, I.M.
dc.contributor.authorElder, Jeffrey T
dc.date.accessioned2012-08-09T19:22:45Z
dc.date.available2012-08-09T19:22:45Z
dc.date.issued1997-06
dc.identifier.urihttp://hdl.handle.net/10945/8778
dc.descriptionApproved for public release; distribution is unlimiteden_US
dc.description.abstractAn analysis of the effects of small impulses on Earth impacting asteroids is presented. The analysis is performed using a numerical routine for an exact, two body, analytic solution. The solution is based on two dimensional, two body, Earth intersecting elliptical orbits. Given the asteroid eccentricity, time prior to impact and impulse magnitude and direction, an analysis of impulse to minimum separation distance is generated. Impulse times prior to impact from zero to a few orbits are considered. The analysis is presented as three dimensional plots of minimum separation distance as a function of impulse magnitude, direction, and time prior to impact. The general result is that for long lead times the optimal impulse occurs at the perihelia of the asteroid's orbit in the direction of the velocity vector, in the orbital plane. For short lead times the optimal impulse direction becomes more normal to the velocity vector, in the orbital plane, as the asteroid approaches the Earthen_US
dc.description.urihttp://archive.org/details/optimalimpulseco00elde
dc.language.isoeng
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.subject.lcshRENDEZVOUS TRAJECTORIESen_US
dc.titleOptimal impulse conditions for deflecting earth crossing asteroidsen_US
dc.description.serviceLieutenant, United States Navyen_US
etd.thesisdegree.nameM.S. in Applied Physicsen_US
etd.thesisdegree.nameM.S. in Astronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAstronautical Engineeringen_US
etd.thesisdegree.disciplineApplied Physicsen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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