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http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K7-10
filingDate 1975-09-04-04:00^^<http://www.w3.org/2001/XMLSchema#date>
grantDate 1982-07-13-04:00^^<http://www.w3.org/2001/XMLSchema#date>
inventor http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_af1c5af53e2995c92eb29b447c50f246
publicationDate 1982-07-13-04:00^^<http://www.w3.org/2001/XMLSchema#date>
publicationNumber US-4338783-A
titleOfInvention Two-stage hypersonic ramjet
abstract A two-stage ramjet engine including an aft end, ejectable, boost stage-combustor/nozzle assembly for initially accelerating from low-to-mid-supersonic launching speeds to high supersonic speeds, and mounted in a tandem arrangement immediately aft of a separate, forward end-cruise stage-combustor/nozzle assembly positioned directly behind an inlet-diffuser section for subsequently further accelerating from high supersonic to hypersonic speeds after ejecting the entire boost stage.
isCitedBy http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-2009158745-A1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-8381528-B2
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-2006112674-A1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-8955791-B2
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-5853143-A
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/RU-2686567-C2
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/FR-2574480-A1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-2013299626-A1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-8528341-B2
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-7328571-B2
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-2017144761-A1
priorityDate 1975-09-04-04:00^^<http://www.w3.org/2001/XMLSchema#date>
type http://data.epo.org/linked-data/def/patent/Publication

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Total number of triples: 34.