http://rdf.ncbi.nlm.nih.gov/pubchem/patent/FR-2606083-A1

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filingDate 1987-10-08-04:00^^<http://www.w3.org/2001/XMLSchema#date>
inventor http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_d17f5457360258b58f9551de5c4fdee0
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publicationDate 1988-05-06-04:00^^<http://www.w3.org/2001/XMLSchema#date>
publicationNumber FR-2606083-A1
titleOfInvention MULTIPLE FUEL AIRCRAFT AND PROPELLER SYSTEM
abstract PROPULSION SYSTEM AND METHOD INCLUDING A MEANS FOR COOLING THE LINING OF THE COMBUSTION CHAMBER AND OF THE THROAT OF A RUBBER SHELL 8 BY ENDOTHERMAL PYROLYSIS OF A HYDROCARBON PLACED IN A CHANNEL WHICH IS CONTIGUATED, BY SURROUNDING THEM. A MEANS IS PROVIDED FOR APPLYING A HIGH FLOW OF HEAT TO THE SEALS AS A RESULT OF THE COMBUSTION IN THE ROCKET SHELL, THE TEMPERATURE OF THE SEALS THEN EXCEEDING THEIR THERMAL LIMITS. A MEANS OF A CATALYST IS USED FOR LAPYROLYSIS. THE FUEL CROSSES THE CHANNEL; THE HEAT OF THE COMBUSTION IN THE CHAMBER IS TRANSMITTED BY RADIATION THROUGH THE GASKETS; AND THE HYDROCARBON IS HEATED TO A SUFFICIENT TEMPERATURE TO CAUSE ENDOTHERMAL PYROLYSIS IN THE CHANNEL. THE ENDOTHERMAL PYROLYSIS OF HYDROCARBIDE GIVES AN IMPROVED PRODUCT WHICH PRESENTS A HIGHER COMBUSTION SPEED, A HIGHER COMBUSTION TEMPERATURE AND RESULTS IN A PRODUCT WHOSE MOLECULAR MASS IS LOWER THAN THAT OF HYDROCARBIDE. APPLICATION TO ROCKET ENGINES, STATOREACTORS, ETC.
priorityDate 1986-10-14-04:00^^<http://www.w3.org/2001/XMLSchema#date>
type http://data.epo.org/linked-data/def/patent/Publication

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