Combined high and low-thrust geostationary orbit insertion with radiation constraint

Macdonald, Malcolm and Owens, Steven Robert (2018) Combined high and low-thrust geostationary orbit insertion with radiation constraint. Acta Astronautica, 142. pp. 1-9. ISSN 0094-5765

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    Abstract

    The sequential use of an electric propulsion system is considered in combination with a high-thrust propulsion system for application to the propellant-optimal Geostationary Orbit insertion problem, whilst considering both temporal and radiation flux constraints. Such usage is found to offer a combined propellant mass saving when compared with an equivalent high-thrust only transfer. This propellant mass saving is seen to increase as the allowable transfer duration is increased, and as the thrust from the low-thrust system is increased, assuming constant specific impulse. It was found that the required plane change maneuver is most propellant-efficiently performed by the high-thrust system. The propellant optimal trajectory incurs a significantly increased electron flux when compared to an equivalent high-thrust only transfer. However, the electron flux can be reduced to a similar order of magnitude by increasing the high-thrust propellant consumption, whilst still delivering an improved mass fraction.

    Creators(s): Macdonald, Malcolm ORCID logoORCID: https://orcid.org/0000-0003-4499-4281 and Owens, Steven Robert;
    Item type:Article
    ID code:61999
    Keywords:orbit Insertion, radiation constraint, mission analysis, system analysis, hybrid propulsion, Mechanical engineering and machinery, Aerospace Engineering
    Subjects:Technology > Mechanical engineering and machinery
    Department:Faculty of Engineering > Mechanical and Aerospace Engineering
    Technology and Innovation Centre > Advanced Engineering and Manufacturing
    Depositing user: Pure Administrator
    Date deposited:11 Oct 2017 11:00
    Last modified:29 May 2020 00:46
    Related URLs:
    URI:https://strathprints.strath.ac.uk/id/eprint/61999
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