Precision flyer initiator

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Apr 1999

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1999stin...0211362f&link_type=abstract

Technical Report, DE2001-9664; UCRL-JC-132115; DP0102032

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Propulsion System Configurations, Mars Sample Return Missions, Miniaturization, Hydrazines, Propellants

Scientific paper

A propulsion point design is presented for lifting geological samples from Mars. Vehicle complexity is kept low by choosing a monopropellant single stage. Little new development is needed, as miniature pump fed hydrazine has been demonstrated. Loading the propellant just prior to operation avoids structural, thermal, and safety constraints otherwise imposed by earlier mission phases. hardware mass and engineering effort are thereby diminished. The Mars liftoff mass is 7/8 hydrazine, 5% propulsion hardware, and 3% each for the payload and guidance.

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