http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-2007192221-A
Outgoing Links
| Predicate | Object |
|---|---|
| assignee | http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_657f8fe5931a3364fda9ccca712ad398 |
| classificationCPCAdditional | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F05D2260-202 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-42 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-64 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-82 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-972 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-64 |
| filingDate | 2007-01-10-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor | http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_a851da4346620a72284831380c52d079 http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_dcdca998189d83fc400180f1f54e7cfc |
| publicationDate | 2007-08-02-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | JP-2007192221-A |
| titleOfInvention | Acoustic cavity manifold for rocket engine, rocket engine and method for improving specific thrust efficiency of rocket engine |
| abstract | Provided is a thruster for attitude control and direction change that improves specific thrust efficiency without increasing the heat load of the combustion device or degrading the performance of the natural dual propellant combustion device. A reinforcing gas supply device includes an acoustic cavity manifold mounted between an outer edge of an injector face and a combustion chamber. The reinforcing gas supply device 24 injects the reinforcing gas from the reinforcing gas tank 26 through the acoustic cavity manifold 30 into the combustion chamber 12. By injection of the reinforcing gas, a boundary layer is formed between the combustion gas flow and the chamber wall 14, the thermal load on the chamber wall 14 is reduced, and the specific thrust of the rocket engine 10 is improved. As the reinforcing gas, an active element such as hydrogen or an inert element such as helium can be used. Thereby, the specific thrust efficiency can be improved without reducing the performance. [Selection] Figure 4B |
| isCitedBy | http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-2009085159-A |
| priorityDate | 2006-01-19-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
Total number of triples: 27.