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Mission Opportunities for the Flight Validation of the Kinetic Impactor Concept for Asteroid DeflectionThe kinetic impactor technique for deflecting near-Earth objects (NEOs), whereby a spacecraft is directed to collide with a NEO to alter its orbit via momentum transfer, is one of several proposed methods for defendingEarth against hazardous NEOs (asteroids and comets). In this paper we present detailed mission design concepts for a notionally feasible and aff ordable kinetic impactor flight validation mission deployed to a currently known near-Earth asteroid (NEA). Several filter steps are devised that utilize relevant criteria to optimally balance keyparameters, such as approach phase angle, estimated NEA diameter, relative velocity at intercept, and current NEA orbit knowledge, and produce refined lists of the most promising candidate target NEAs.
Document ID
20150007251
Acquisition Source
Jet Propulsion Laboratory
Document Type
Conference Paper
External Source(s)
Authors
Hernandez, Sonia
(Texas Univ. Austin, TX, United States)
Barbee, Brent W.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Bhaskaran, Shyam
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Getzandanner, Kenneth
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
May 4, 2015
Publication Date
April 15, 2013
Subject Category
Lunar And Planetary Science And Exploration
Astrodynamics
Meeting Information
Meeting: IAA Planetary Defense Conference
Location: Flagstaff, AZ
Country: United States
Start Date: April 15, 2013
End Date: April 19, 2013
Sponsors: International Academy of Astronautics
Distribution Limits
Public
Copyright
Other
Keywords
mission design
flight validation
trajectory optimization
kinetic impact
asteroid deflection

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