Articulated rotor systems with pitch independent damping
A proprotor system operable for use on a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom rela...
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| creator | Miller, Gary Stamps, Frank Bradley Parham, Jr., Thomas Clement Choi, Jouyoung Jason |
| description | A proprotor system operable for use on a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. Each of a plurality of spherical bearings couples one of the proprotor blades with the rotor hub. In addition, each of a plurality of lead-lag dampers couples one of the proprotor blades with the rotor hub, wherein each lead-lag damper is aligned with the pitch change axis of the respective proprotor blade, thereby providing pitch independent lead-lag damping. |
| format | Patent |
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The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. Each of a plurality of spherical bearings couples one of the proprotor blades with the rotor hub. In addition, each of a plurality of lead-lag dampers couples one of the proprotor blades with the rotor hub, wherein each lead-lag damper is aligned with the pitch change axis of the respective proprotor blade, thereby providing pitch independent lead-lag damping.</description><language>eng</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; BEARINGS ; BLASTING ; COSMONAUTICS ; ELEMENTS OR CRANKSHAFT MECHANISMS ; ENGINEERING ELEMENTS AND UNITS ; FLEXIBLE SHAFTS ; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS ; HEATING ; HELICOPTERS ; LIGHTING ; MEANS FOR DAMPING VIBRATION ; MECHANICAL ENGINEERING ; PERFORMING OPERATIONS ; ROTARY BODIES OTHER THAN GEARING ELEMENTS ; SHAFTS ; SHOCK-ABSORBERS ; SPRINGS ; THERMAL INSULATION IN GENERAL ; TRANSPORTING ; WEAPONS</subject><creationdate>2019</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20191029&DB=EPODOC&CC=US&NR=10457380B2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76290</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20191029&DB=EPODOC&CC=US&NR=10457380B2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Miller, Gary</creatorcontrib><creatorcontrib>Stamps, Frank Bradley</creatorcontrib><creatorcontrib>Parham, Jr., Thomas Clement</creatorcontrib><creatorcontrib>Choi, Jouyoung Jason</creatorcontrib><title>Articulated rotor systems with pitch independent damping</title><description>A proprotor system operable for use on a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. Each of a plurality of spherical bearings couples one of the proprotor blades with the rotor hub. In addition, each of a plurality of lead-lag dampers couples one of the proprotor blades with the rotor hub, wherein each lead-lag damper is aligned with the pitch change axis of the respective proprotor blade, thereby providing pitch independent lead-lag damping.</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>BEARINGS</subject><subject>BLASTING</subject><subject>COSMONAUTICS</subject><subject>ELEMENTS OR CRANKSHAFT MECHANISMS</subject><subject>ENGINEERING ELEMENTS AND UNITS</subject><subject>FLEXIBLE SHAFTS</subject><subject>GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS</subject><subject>HEATING</subject><subject>HELICOPTERS</subject><subject>LIGHTING</subject><subject>MEANS FOR DAMPING VIBRATION</subject><subject>MECHANICAL ENGINEERING</subject><subject>PERFORMING OPERATIONS</subject><subject>ROTARY BODIES OTHER THAN GEARING ELEMENTS</subject><subject>SHAFTS</subject><subject>SHOCK-ABSORBERS</subject><subject>SPRINGS</subject><subject>THERMAL INSULATION IN GENERAL</subject><subject>TRANSPORTING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2019</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZLBwLCrJTC7NSSxJTVEoyi_JL1IoriwuSc0tVijPLMlQKMgsSc5QyMxLSS1IBRJ5JQopibkFmXnpPAysaYk5xam8UJqbQdHNNcTZQze1ID8-tbggMTk1L7UkPjTY0MDE1NzYwsDJyJgYNQBWni8N</recordid><startdate>20191029</startdate><enddate>20191029</enddate><creator>Miller, Gary</creator><creator>Stamps, Frank Bradley</creator><creator>Parham, Jr., Thomas Clement</creator><creator>Choi, Jouyoung Jason</creator><scope>EVB</scope></search><sort><creationdate>20191029</creationdate><title>Articulated rotor systems with pitch independent damping</title><author>Miller, Gary ; Stamps, Frank Bradley ; Parham, Jr., Thomas Clement ; Choi, Jouyoung Jason</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US10457380B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2019</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>BEARINGS</topic><topic>BLASTING</topic><topic>COSMONAUTICS</topic><topic>ELEMENTS OR CRANKSHAFT MECHANISMS</topic><topic>ENGINEERING ELEMENTS AND UNITS</topic><topic>FLEXIBLE SHAFTS</topic><topic>GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS</topic><topic>HEATING</topic><topic>HELICOPTERS</topic><topic>LIGHTING</topic><topic>MEANS FOR DAMPING VIBRATION</topic><topic>MECHANICAL ENGINEERING</topic><topic>PERFORMING OPERATIONS</topic><topic>ROTARY BODIES OTHER THAN GEARING ELEMENTS</topic><topic>SHAFTS</topic><topic>SHOCK-ABSORBERS</topic><topic>SPRINGS</topic><topic>THERMAL INSULATION IN GENERAL</topic><topic>TRANSPORTING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>Miller, Gary</creatorcontrib><creatorcontrib>Stamps, Frank Bradley</creatorcontrib><creatorcontrib>Parham, Jr., Thomas Clement</creatorcontrib><creatorcontrib>Choi, Jouyoung Jason</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Miller, Gary</au><au>Stamps, Frank Bradley</au><au>Parham, Jr., Thomas Clement</au><au>Choi, Jouyoung Jason</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Articulated rotor systems with pitch independent damping</title><date>2019-10-29</date><risdate>2019</risdate><abstract>A proprotor system operable for use on a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. Each of a plurality of spherical bearings couples one of the proprotor blades with the rotor hub. In addition, each of a plurality of lead-lag dampers couples one of the proprotor blades with the rotor hub, wherein each lead-lag damper is aligned with the pitch change axis of the respective proprotor blade, thereby providing pitch independent lead-lag damping.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AEROPLANES AIRCRAFT AVIATION BEARINGS BLASTING COSMONAUTICS ELEMENTS OR CRANKSHAFT MECHANISMS ENGINEERING ELEMENTS AND UNITS FLEXIBLE SHAFTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HELICOPTERS LIGHTING MEANS FOR DAMPING VIBRATION MECHANICAL ENGINEERING PERFORMING OPERATIONS ROTARY BODIES OTHER THAN GEARING ELEMENTS SHAFTS SHOCK-ABSORBERS SPRINGS THERMAL INSULATION IN GENERAL TRANSPORTING WEAPONS |
| title | Articulated rotor systems with pitch independent damping |
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