| Predicate |
Object |
| assignee |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_ed71db03c3e1ff7d2b671bc10ef4bc65 |
| classificationCPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-42
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-62
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-56 |
| classificationIPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-42
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-56
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-62 |
| filingDate |
2018-03-16-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_43f16223fd15a953f7d7a5eeb5539c94 |
| publicationDate |
2019-09-19-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber |
WO-2019174741-A1 |
| titleOfInvention |
Rocket engine |
| abstract |
The present invention relates to a rocket engine for a rocket fuel having a working mass during the combustion of which a product with a dipole moment is produced. Said rocket engine comprises a combustion chamber, in particular having: a flame holder; a nozzle; and an electric-field-generating device with which an electric field can be applied at least in a region of the nozzle. |
| priorityDate |
2018-03-16-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type |
http://data.epo.org/linked-data/def/patent/Publication |