Computer Science – Performance
Scientific paper
Oct 2004
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.557e..33f&link_type=abstract
Proceedings of the 2nd International Conference on Green Propellants for Space Propulsion (ESA SP-557). 7-8 June 2004, Chia Lagu
Computer Science
Performance
Scientific paper
Liquid monopropellants and bipropellants have been for decades the choice for space propulsion applications due to their performance and reliability characteristics, in terms of steady and pulsed mode combustion, and mission duration. The current liquid monopropellants and bipropellants have a number of disadvantages, e.g. ability to produce toxic fumes, ability to produce explosive mixtures as a result of vapours coming in contact with air, their high reactivity, their cryogenic characteristics, their sensitiveness, their potential for detonating under specific temperature and pressure conditions, high adiabatic flame temperatures (in some cases can exceed 2573.15 K with direct consequences on the combustion chamber materials), a significant part of the combustion products are of a strongly oxidizing nature (similarly inducing stress on the combustion chamber materials), etc.. Hence, they comprise a high level of requirements that result in high cost of operation. Hydrazine is up to the present date considered the state-of-the-art liquid propellant for space applications, in terms of excellent performance, low flame temperature, reliable long lived catalyst system and the decomposition products generate a reducing atmosphere (as a consequence the requirements on the catalyst and the combustion chamber materials are less strict). A provisional ranking has been attempted on next generation liquid monopropellants as possible replacement for hydrazine on space applications. The conclusions of this work will be presented here.
Ford Matthew
Frota O.
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