Mars to orbit with pumped hydrazine.

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 st...

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Bibliographic Details
Corporate Authors: United States. Department of Energy. Office of the Assistant Secretary for Defense Programs
Lawrence Livermore National Laboratory
United States. Department of Energy. Office of Scientific and Technical Information
Language:English
Published: Livermore, Calif : Oak Ridge, Tenn. : Lawrence Livermore National Laboratory ; Distributed by the Office of Scientific and Technical Information, U.S. Department of Energy, 1999.
Subjects:
Online Access:
Physical Description:1.4 Megabytes pages.
Format: Electronic eBook

MARC

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245 0 0 |a Mars to orbit with pumped hydrazine. 
260 |a Livermore, Calif :  |b Lawrence Livermore National Laboratory ;  |a Oak Ridge, Tenn. :  |b Distributed by the Office of Scientific and Technical Information, U.S. Department of Energy,  |c 1999. 
300 |a 1.4 Megabytes pages. 
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500 |a Published through the Information Bridge: DOE Scientific and Technical Information. 
500 |c 04/27/1999. 
500 |a "UCRL-JC-132328" 
500 |a 35th Annual AIAA/ASME/SAE/American Society of Engineering Education Joint Propulsion Conference & Exhibit, Los Angeles, CA (US), 06/20/1999--06/23/1999. 
500 |a Whitehead, J C. 
500 |a Lawrence Livermore National Lab., CA (US) 
520 3 |a 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. 
538 |a Available via the World Wide Web. 
500 |a DOE Technical report ; UCRL-JC-132328 
500 |a Electronic resource. 
650 4 |a Design. 
650 4 |a Education. 
650 4 |a Hydrazine. 
650 4 |a Propulsion. 
650 4 |a Safety. 
650 4 |a Space Vehicles. 
650 0 |a Earth sciences.  |0 http://id.loc.gov/authorities/subjects/sh85040468 
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