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Terminal guidance navigation for an asteroid impactor spacecraft

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dc.contributor.author Bhaskaran, Shyam
dc.contributor.author Kennedy, Brian
dc.date.accessioned 2013-12-10T23:01:57Z
dc.date.available 2013-12-10T23:01:57Z
dc.date.issued 2013-02-11
dc.identifier.citation 23rd AAS/AIAA Spaceflight Mechanics Meeting, Kauai, Hawaii, February 10-14 2013 en_US
dc.identifier.clearanceno 13-0547
dc.identifier.uri http://hdl.handle.net/2014/44056
dc.description.abstract Near Earth Asteroids could potentially cause a great deal of devastation if one were to impact the Earth. If such an asteroid were found, the next step would be to mitigate the threat by one of several options, the most viable of which is to deflect the asteroids trajectory such that it misses the Earth by hitting it at a very high velocity with a spacecraft. The technology to perform such a deflection has been demonstrated by the Deep Impact (DI) mission, which successfully collided with comet Tempel 1 in July 2005 using an onboard autonomous navigation system, called AutoNav, for the terminal phase of the mission. In this paper, we evaluate the ability of AutoNav to impact a wide range of scenarios that an deflection mission could encounter, varying parameters such as the approach velocity, phase angle, size of the asteroid, and the determination of spacecraft attitude. Using realistic Monte Carlo simulations, we tabulated the probability of success of the deflection as a function of these parameters, and find the highest sensitivity to be due the spacecraft attitude determination mode. We conclude with some recommendations for future work. en_US
dc.description.sponsorship NASA/JPL en_US
dc.language.iso en_US en_US
dc.publisher Pasadena, CA : Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2013 en_US
dc.subject asteroid deflection en_US
dc.subject autonomous navigation en_US
dc.title Terminal guidance navigation for an asteroid impactor spacecraft en_US
dc.type Presentation en_US


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