| Predicate |
Object |
| assignee |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_8f6fd8a92f55dca0f111bd7c5858ae83 |
| classificationCPCAdditional |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64G1-002 |
| classificationCPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-766
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64G1-401
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-60
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-94
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-566 |
| classificationIPCAdditional |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64G1-00 |
| classificationIPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-60
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-76
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-94
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64G1-40
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-56 |
| filingDate |
2001-03-16-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| grantDate |
2002-12-31-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_bfc4b980eeddef0b0b519984ed0d1878 |
| publicationDate |
2002-12-31-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber |
US-6499696-B1 |
| titleOfInvention |
Rocket engine with reduced thrust and stagable venting system |
| abstract |
A rocket having a rocket engine vent system for a rocket engine is disclosed. The rocket engine vent system includes at least one rocket engine vent system conduit having a pair of vent apertures that are disposed on opposite sides of this conduit (i.e., disposed in opposing relation). A diverter with a pair of vanes is disposed within this rocket engine vent system conduit. One diverter vane projects toward one of the vent apertures, while the other diverter vane projects toward the other vent aperture. Two separate and discrete fluid flows are thereby directed out of the rocket engine vent system conduit in at least generally opposite directions, which significantly reduces the thrust to which the rocket engine is exposed when venting rocket fuel therefrom under high pressure conditions. |
| isCitedBy |
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-8720181-B1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-101539072-B
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-6702050-B1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-10023329-B1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-8812179-B1 |
| priorityDate |
2001-03-16-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type |
http://data.epo.org/linked-data/def/patent/Publication |