Optimal design for a NEO tracking spacecraft formation

Maddock, Christie and Vasile, Massimiliano (2007) Optimal design for a NEO tracking spacecraft formation. In: IEEE Congress on Evolutionary Computing. IEEE, Paper 1728. ISBN 978-1-4244-1339-3

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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.

    Author(s):Maddock, Christie ORCID logoORCID: https://orcid.org/0000-0003-1079-4863 and Vasile, Massimiliano ORCID logoORCID: https://orcid.org/0000-0001-8302-6465
    Item type:Book Section
    ID code:39483
    Keywords:optimal design, near Earth objects, spacecraft formation flying, periodic orbit, Mechanical engineering and machinery, Motor vehicles. Aeronautics. Astronautics
    Subjects:Technology > Mechanical engineering and machinery
    Technology > Motor vehicles. Aeronautics. Astronautics
    Department:Faculty of Engineering > Mechanical and Aerospace Engineering
    Depositing user: Pure Administrator
    Date deposited:02 May 2012 15:01
    Last modified:05 Aug 2019 00:27
    URI:https://strathprints.strath.ac.uk/id/eprint/39483
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