| Predicate |
Object |
| assignee |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_657f8fe5931a3364fda9ccca712ad398 |
| classificationCPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K1-10
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K1-36
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-78
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K3-06
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C3-32
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-84 |
| classificationIPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-84
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-78 |
| filingDate |
2007-02-08-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_fff4a2d5b3413e2ba7f7a67b9414bbea |
| publicationDate |
2007-08-22-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber |
EP-1820955-A2 |
| titleOfInvention |
Integrated airbreathing and non-airbreathing engine system |
| abstract |
An engine assembly includes a gas-turbine engine having a tailcone portion (130) and a bypass duct (126), a rocket engine combustion assembly (132, 134) located at the tailcone portion (130) of the gas-turbine engine, and a movable nozzle segment subassembly (102) that is selectively engageable with the gas-turbine engine bypass duct (126) in an open position and with the rocket engine combustion assembly in a closed position. |
| isCitedBy |
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-106499544-A
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-106499544-B
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/WO-2020052910-A1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/RU-2648480-C2
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-109408993-A
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-11661908-B2 |
| priorityDate |
2006-02-15-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type |
http://data.epo.org/linked-data/def/patent/Publication |