http://rdf.ncbi.nlm.nih.gov/pubchem/patent/DE-2166904-A1
Outgoing Links
| Predicate | Object |
|---|---|
| assignee | http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_79f28c02b239c18b7c267c039ecb02a0 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-34 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-32 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-62 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-32 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-62 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-34 |
| filingDate | 1971-12-01-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationDate | 1976-07-08-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | DE-2166904-A1 |
| titleOfInvention | DRIVE SYSTEM FOR AIRCRAFT |
| abstract | Rocket motor for flight vehicle has a generator for the propellant gas, containers for latter gas and for an oxydant, a system for feeding propellant to a combustion chamber connected to a convergent-divergent propulsion nozzle (6) which is movable relative to the chamber in the direction of the nozzle axis. To this end the chamber has a cylindrical interior in which is axially slidingly supported a slide shoe or piston (46) having sealing rings (47) and constituting the upstream end of the nozzle. The nozzle position is set according to the fuel to be used. |
| isCitedBy | http://rdf.ncbi.nlm.nih.gov/pubchem/patent/WO-0079116-A1 |
| priorityDate | 1971-12-01-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
Total number of triples: 21.