A conventional Mercury sample return mission requires significant launch mass due to the large deltav required for the outbound and return trips, and the large mass of a planetary lander and ascent vehicle. Solar sailing can be used to reduce lander mass allocation by delivering the lander to a low, thermally safe orbit close to the terminator. Propellant mass is not an issue for solar sails so a sample can be returned relatively easily, without resorting to lengthy, multiple gravity assists. The initial Mercury sample return studies reported here were conducted under ESA contract ESTEC/16534/02/NL/NR, PI Colin McInnes, Technical Officer Peter Falkner. Updated solar sail capabilities were developed under the Ground System Demonstration program, funded by the NASA's In-Space Propulsion Technology (ISPT) Program.


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    Title :

    Mercury Sample Return using Solar Sails


    Contributors:

    Conference:

    Division for Planetary Sciences Meeting ; 2006 ; Pasadena, CA, United States


    Publication date :

    2006-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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