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Mission maps for use in the choice of specific impulse for manned Mars missions [electronic resource].

Published:
Washington, D.C. : United States. Dept. of Energy, 1991.
Oak Ridge, Tenn. : Distributed by the Office of Scientific and Technical Information, U.S. Dept. of Energy.
Physical Description:
Pages: (10 pages) : digital, PDF file
Additional Creators:
United States. Department of Energy and United States. Department of Energy. Office of Scientific and Technical Information
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Summary:
The choice of engine concept for the initial manned missions to Mars should be driven by what can be feasibly built and flight qualified in the near term, and by the level of engine performance that is required for these missions. This paper addresses how mission requirements affect the choice of specific impulse, and consequently what values of the specific impulse best serve these missions. Broad mission surveys and sensitivity studies were performed to determine the specific impulse values that allow for fast transfer times and wide launch windows. We find that a specific impulse of around 1000 to 1200 sec is sufficient. Choosing an engine concept that has a higher specific impulse value is not justified for these missions because the modest reduction in propellant requirements and further widening of the launch windows does not compensate for the substantially greater technical risk. 3 refs., 8 figs.
Report Numbers:
E 1.99:egg-m-91094
E 1.99: aas--91-503
E 1.99: conf-9108126--2
conf-9108126--2
aas--91-503
egg-m-91094
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Note:
Published through SciTech Connect.
01/01/1991.
"egg-m-91094"
" aas--91-503"
" conf-9108126--2"
"DE92003273"
AAS/AIAA astrodynamics conference, Durango, CO (United States), 19-21 Aug 1991.
Madsen, W.W.; Neuman, J.E.; Olson, T.S.; Siahpush, A.S.
EG and G Idaho, Inc., Idaho Falls, ID (United States)
Funding Information:
AC07-76ID01570
View MARC record | catkey: 14079544