http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-H10503731-A
Outgoing Links
| Predicate | Object |
|---|---|
| classificationCPCAdditional | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64G1-402 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64G1-403 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64G1-002 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64G1-401 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-766 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64G1-14 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64G1-24 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64G1-00 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64G1-40 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-76 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64G1-14 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-42 |
| filingDate | 1995-07-25-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationDate | 1998-04-07-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | JP-H10503731-A |
| titleOfInvention | Two-stage launch vehicle and launch orbit method |
| abstract | (57) [Summary] A method of launching a two-stage rocket so that both stages (stages) of the two-stage rocket (20) can be collected at the launch point, and a flight path of the two-stage rocket (20). This can be achieved by launching the first stage (24) completely vertically so that when it burns out, the first stage (24) is located directly above the collection point. To maximize the effect of vertically lifting the stage, it is necessary to minimize the gravitational loss by setting the thrust / weight ratio of the first stage to 1.6. The high thrust / weight ratio burns out at about 100,000 feet in the atmosphere. The rocket therefore uses an engine that generates about 15% of the first stage sea level thrust at this altitude and burns the last 5% of fuel in 40 seconds. Disconnect at 200,000 feet. The second stage (24) uses a higher rated RL-10 engine (25), has a thrust / weight ratio of 1.45, and is capable of getting into orbit with a speed change of about 24,500 feet / second. The first stage (22) uses an air-inspired vertical lift engine (27) for recovery, and the second stage (24) utilizes a parawing (55). |
| isCitedBy | http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-2012030701-A http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-2014181030-A http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-2012530020-A |
| priorityDate | 1994-08-01-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
Total number of triples: 42.