http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-104903190-B
Outgoing Links
| Predicate | Object |
|---|---|
| classificationCPCAdditional | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64C2003-142 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/Y02T50-10 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B63B2035-009 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/Y02T70-5236 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64C3-26 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B63H9-061 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B63H9-04 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B63H9-06 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B63H9-08 |
| filingDate | 2013-11-25-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| grantDate | 2017-10-03-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationDate | 2017-10-03-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | CN-104903190-B |
| titleOfInvention | The wing and its application |
| abstract | This disclosure relates to a kind of wing.More specifically, many aspects of the present invention are related to the deformable wings that incrementally can be moved between neutral configuration and deformed configuration, wherein the wing takes reflexed camber airfoil cross sectional shape in deformed configuration.The wing includes the first aerofoil profile section and the second aerofoil profile section, their end is connected with each other at relative neutral leading edge and trailing edge or fixes and be spaced from each other along its length across the neutral mean camber line extended between neutral leading edge and trailing edge, to form the neutral aerofoil section of the wing.One or more actuators make the wing be deformed between neutral aerofoil section and reflexed camber aerofoil section, wherein the first and second aerofoil profile sections are elastic so that the wing is biased towards initial rest state.In order that reflexed camber aerofoil section is presented in aerofoil section, the Critical Buckling Loads of aerofoil profile section are more than the compression load that actuator makes the wing be deformed between neutral aerofoil section and reflexed camber aerofoil section and produced in aerofoil profile section.In use, two displacements on one of aerofoil profile section are made at least to generate compression load in such aerofoil profile section by actuator, deform the wing.The ability of such aerofoil profile section resistance compression load makes section use the shape with flex point, so that wing into reflexed camber aerofoil section. |
| priorityDate | 2012-11-28-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
Total number of triples: 21.