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  • Symmetrically Laden Motorised Momentum Exchange tethers for a continuous Earth Moon payload exchange

    Paper number

    IAC-06-D4.3.03

    Author

    Mr. Christopher Murray, University of Glasgow, United Kingdom

    Coauthor

    Prof. Matthew Cartmell, University of Glasgow, United Kingdom

    Year

    2006

    Abstract
    A permanent Moon base will require an efficient and reliable method of transporting materials from the Earth to the Moon and vice versa.  Conventional chemical propulsion is not the most cost effective method of supply for the construction and maintenance of a Moon base.  Using symmetrically laden motorised momentum exchange tethers in orbit about the Earth and Moon and by passing payload’s between them will allow for a low cost and reliable method of transfer. Although the initial setup of the Earth Moon transfer system would initially be more costly than a single transfer to the Moon using chemical propulsion the cost of transfers would considerably reduce overall costs after a few round trips in comparison with chemical propulsion.
    
    This paper focuses on the technical and logistical requirements necessary for the setup of a continuous Earth Moon payload exchange system.  Initially a payload is launched from a Motorised Momentum Exchange tether at Earth onto a lunar trajectory.  At the Moon the payload is captured by another motorised momentum exchange tether and is subsequently rotated round and placed onto the lunar surface.  At this point a payload from the Moon, picked up when the incoming payload was captured to conserve tether symmetry, is released onto an Earth bound trajectory and is subsequently captured by the tether at Earth.  This system uses no other form of propulsion other than the tethers themselves.
    
    Such a system would allow for the supply of essential materials to the Moon and would allow for the return of materials mined from the Moon. The Earth Moon transfer is well within the capabilities of the tether system and an extension of this may allow for the setup of an Earth Mars payload exchange system.
    
    Abstract document

    IAC-06-D4.3.03.pdf