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 ![]() | Item type: | Article |
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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: | 01 Jan 2021 12:20 |
Related URLs: | |
URI: | https://strathprints.strath.ac.uk/id/eprint/61999 |
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