| Predicate |
Object |
| assignee |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_bf53daf46ede52ed581c8fe8e7188669 |
| classificationCPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F03H1-0012
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F03H1-0037
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64G1-405
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64G1-409
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-76
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-42
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K99-00
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F03H1-0081
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F03H1-0093 |
| classificationIPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64G1-40
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F03H1-00 |
| filingDate |
2013-05-07-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_94742952fd5cdd0cf5e0432d472d2449
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_fdc647e61b6dd5a6af894a920ccf34f1
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_76e75d8eefb0b376c9ef26588c2d584f
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_c0d0a7af2e3a36e5d0bbbbe382d68df9
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_7274a28e48926625ec5bbd55b5c1a704
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_a56a95ad9fa8f35c43a97b1bc07f87eb
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_ad587d1cef3bd8433f158799bb3096d4
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_1c51f158a72c984e4890d2d0eb060b8a |
| publicationDate |
2015-07-30-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber |
US-2015210406-A1 |
| titleOfInvention |
Fuel-Free Spacecraft Propelling System Based on Spatial Atomic Oxygen and Propelling Method |
| abstract |
A fuel-free spacecraft propelling system having an open-ended outer cylinder of a propelling device and an atomic oxygen collecting device is disclosed. The latter is arranged at the forwardly-propelled front end of the outer cylinder and is hermetically connected with an RF generating device and an ion cyclotron wave heating device through a magnetic confinement device. A spiral wave discharge oxygen plasma inlet and a spiral wave discharge oxygen plasma outlet in the ion cyclotron wave heating device are respectively provided with another magnetic confinement device. The propulsion of the invention does not need to carry the propellant, which greatly reduces the launch costs, and enables a spacecraft to advantageously have an increased orbit life over existing spacecraft systems. |
| isCitedBy |
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-114135457-A
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-2022127022-A1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/RU-2741401-C1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/RU-2703854-C1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-2019168894-A1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-10793295-B2
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/EP-3232056-B1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-11708181-B2
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-10662930-B2 |
| priorityDate |
2012-05-22-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type |
http://data.epo.org/linked-data/def/patent/Publication |