Optimal design for a NEO tracking spacecraft formation

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Abstract

The following paper presents the design and methodology for developing an optimal set of spacecraft orbits for a NEO tracking mission. The spacecraft is designed to fly in close formation with the asteroid, avoiding the nonlinear gravity field produced by the asteroid. A periodic orbit is developed, and the initial conditions are optimized by use of a global optimizer for constrained nonlinear problems. The asteroid Apophis (NEO 2004 MN4) was used as the case study
due the potential impact with Earth in 2036, and the need for more accurate ephemerides.
Original languageEnglish
Title of host publicationIEEE Congress on Evolutionary Computing
PublisherIEEE
PagesPaper 1728
Number of pages8
ISBN (Print)978-1-4244-1339-3
DOIs
Publication statusPublished - 25 Sept 2007
EventIEEE Congress on Evolutionary Computation (CEC) - Singapore
Duration: 25 Sept 200728 Sept 2007

Conference

ConferenceIEEE Congress on Evolutionary Computation (CEC)
CitySingapore
Period25/09/0728/09/07

Keywords

  • optimal design
  • near Earth objects
  • spacecraft formation flying
  • periodic orbit

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