Koaxiale Übersetzungs-/Zentriernaben-Unteranordnung für Rotoranordnung
An integrated spline/cone seat subassembly (190) for an unmanned aerial vehicle (10) having a rotor assembly (100) that includes ducted, counter-rotating rotors (200, 202), comprising:a rotor shaft (128R or 130R) having an axis, said rotor shaft (128R or 130R) includinga primary shaft portion (192)...
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| creator | CYCON, JAMES P MILLEA, F KOHLHEPP, W |
| description | An integrated spline/cone seat subassembly (190) for an unmanned aerial vehicle (10) having a rotor assembly (100) that includes ducted, counter-rotating rotors (200, 202), comprising:a rotor shaft (128R or 130R) having an axis, said rotor shaft (128R or 130R) includinga primary shaft portion (192) having a first diameter (D1),an end shaft portion (194) having a second diameter (D2) and having a plurality of shaft splines (198) extending radially outwardly therefrom, anda conic transition portion (196) intermediate said primary and end shaft portions (192, 194), said conic transition portion (196) making a predetermined angle (β) with respect to said axis of said rotor shaft (128R or 130R); anda rotor hub (204) having a centerline (212), said rotor hub (204) having a shaft aperture (206) having a plurality of hub splines (208) extending radially inwardly therefrom;said plurality of hub splines (208) and said plurality of shaft splines (198) being interleaved in combination to provide a rotational interlock between said rotor hub (204) and said rotor shaft (128R or 130R) in the rotor assembly (100); characterized in thateach of said hub splines (208) having an outwardly tapered lower portion (210) that makes a predetermined angle (θ) with respect to said centerline (212); andsaid predetermined angle (θ) of said outwardly tapered lower portions (210) of said hub splines (208) being equal to said predetermined angle (β) of said conic transition portion (196) of said rotor shaft (128R or 130R) wherein said tapered lower portions (210) of said hub splines (208) abuttingly engage and are mechanically supported by said conic transition portion (196) of said rotor shaft (128R or 130R) in the rotor assembly (100). |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_DE69332506TT2</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>DE69332506TT2</sourcerecordid><originalsourceid>FETCH-epo_espacenet_DE69332506TT23</originalsourceid><addsrcrecordid>eNrjZPDwzk-syEzMSVU4PCcptag4taSqNC-9WFc_KjWvpCgztSgvMSk1Tzc0ryS1KDEvvyglDyitkHZ4T5FCUH5JPkKMh4E1LTGnOJUXSnMzKLm5hjh76KYW5MenFhckJqfmpZbEu7iaWRobG5kamIWEGBkTpQgASk43kw</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Koaxiale Übersetzungs-/Zentriernaben-Unteranordnung für Rotoranordnung</title><source>esp@cenet</source><creator>CYCON, JAMES P ; MILLEA, F ; KOHLHEPP, W</creator><creatorcontrib>CYCON, JAMES P ; MILLEA, F ; KOHLHEPP, W</creatorcontrib><description>An integrated spline/cone seat subassembly (190) for an unmanned aerial vehicle (10) having a rotor assembly (100) that includes ducted, counter-rotating rotors (200, 202), comprising:a rotor shaft (128R or 130R) having an axis, said rotor shaft (128R or 130R) includinga primary shaft portion (192) having a first diameter (D1),an end shaft portion (194) having a second diameter (D2) and having a plurality of shaft splines (198) extending radially outwardly therefrom, anda conic transition portion (196) intermediate said primary and end shaft portions (192, 194), said conic transition portion (196) making a predetermined angle (β) with respect to said axis of said rotor shaft (128R or 130R); anda rotor hub (204) having a centerline (212), said rotor hub (204) having a shaft aperture (206) having a plurality of hub splines (208) extending radially inwardly therefrom;said plurality of hub splines (208) and said plurality of shaft splines (198) being interleaved in combination to provide a rotational interlock between said rotor hub (204) and said rotor shaft (128R or 130R) in the rotor assembly (100); characterized in thateach of said hub splines (208) having an outwardly tapered lower portion (210) that makes a predetermined angle (θ) with respect to said centerline (212); andsaid predetermined angle (θ) of said outwardly tapered lower portions (210) of said hub splines (208) being equal to said predetermined angle (β) of said conic transition portion (196) of said rotor shaft (128R or 130R) wherein said tapered lower portions (210) of said hub splines (208) abuttingly engage and are mechanically supported by said conic transition portion (196) of said rotor shaft (128R or 130R) in the rotor assembly (100).</description><edition>7</edition><language>ger</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; BEARINGS ; BLASTING ; BRAKES ; CLUTCHES ; COMBUSTION ENGINES ; COMBUSTION ENGINES IN GENERAL ; COSMONAUTICS ; COUPLINGS FOR TRANSMITTING ROTATION ; ELEMENTS OR CRANKSHAFT MECHANISMS ; ENGINEERING ELEMENTS AND UNITS ; FLEXIBLE SHAFTS ; GEARING ; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS ; HEATING ; HELICOPTERS ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; INTERNAL-COMBUSTION PISTON ENGINES ; 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>2003</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=20030710&DB=EPODOC&CC=DE&NR=69332506T2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20030710&DB=EPODOC&CC=DE&NR=69332506T2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>CYCON, JAMES P</creatorcontrib><creatorcontrib>MILLEA, F</creatorcontrib><creatorcontrib>KOHLHEPP, W</creatorcontrib><title>Koaxiale Übersetzungs-/Zentriernaben-Unteranordnung für Rotoranordnung</title><description>An integrated spline/cone seat subassembly (190) for an unmanned aerial vehicle (10) having a rotor assembly (100) that includes ducted, counter-rotating rotors (200, 202), comprising:a rotor shaft (128R or 130R) having an axis, said rotor shaft (128R or 130R) includinga primary shaft portion (192) having a first diameter (D1),an end shaft portion (194) having a second diameter (D2) and having a plurality of shaft splines (198) extending radially outwardly therefrom, anda conic transition portion (196) intermediate said primary and end shaft portions (192, 194), said conic transition portion (196) making a predetermined angle (β) with respect to said axis of said rotor shaft (128R or 130R); anda rotor hub (204) having a centerline (212), said rotor hub (204) having a shaft aperture (206) having a plurality of hub splines (208) extending radially inwardly therefrom;said plurality of hub splines (208) and said plurality of shaft splines (198) being interleaved in combination to provide a rotational interlock between said rotor hub (204) and said rotor shaft (128R or 130R) in the rotor assembly (100); characterized in thateach of said hub splines (208) having an outwardly tapered lower portion (210) that makes a predetermined angle (θ) with respect to said centerline (212); andsaid predetermined angle (θ) of said outwardly tapered lower portions (210) of said hub splines (208) being equal to said predetermined angle (β) of said conic transition portion (196) of said rotor shaft (128R or 130R) wherein said tapered lower portions (210) of said hub splines (208) abuttingly engage and are mechanically supported by said conic transition portion (196) of said rotor shaft (128R or 130R) in the rotor assembly (100).</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>BEARINGS</subject><subject>BLASTING</subject><subject>BRAKES</subject><subject>CLUTCHES</subject><subject>COMBUSTION ENGINES</subject><subject>COMBUSTION ENGINES IN GENERAL</subject><subject>COSMONAUTICS</subject><subject>COUPLINGS FOR TRANSMITTING ROTATION</subject><subject>ELEMENTS OR CRANKSHAFT MECHANISMS</subject><subject>ENGINEERING ELEMENTS AND UNITS</subject><subject>FLEXIBLE SHAFTS</subject><subject>GEARING</subject><subject>GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS</subject><subject>HEATING</subject><subject>HELICOPTERS</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>INTERNAL-COMBUSTION PISTON ENGINES</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>2003</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZPDwzk-syEzMSVU4PCcptag4taSqNC-9WFc_KjWvpCgztSgvMSk1Tzc0ryS1KDEvvyglDyitkHZ4T5FCUH5JPkKMh4E1LTGnOJUXSnMzKLm5hjh76KYW5MenFhckJqfmpZbEu7iaWRobG5kamIWEGBkTpQgASk43kw</recordid><startdate>20030710</startdate><enddate>20030710</enddate><creator>CYCON, JAMES P</creator><creator>MILLEA, F</creator><creator>KOHLHEPP, W</creator><scope>EVB</scope></search><sort><creationdate>20030710</creationdate><title>Koaxiale Übersetzungs-/Zentriernaben-Unteranordnung für Rotoranordnung</title><author>CYCON, JAMES P ; MILLEA, F ; KOHLHEPP, W</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_DE69332506TT23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>ger</language><creationdate>2003</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>BEARINGS</topic><topic>BLASTING</topic><topic>BRAKES</topic><topic>CLUTCHES</topic><topic>COMBUSTION ENGINES</topic><topic>COMBUSTION ENGINES IN GENERAL</topic><topic>COSMONAUTICS</topic><topic>COUPLINGS FOR TRANSMITTING ROTATION</topic><topic>ELEMENTS OR CRANKSHAFT MECHANISMS</topic><topic>ENGINEERING ELEMENTS AND UNITS</topic><topic>FLEXIBLE SHAFTS</topic><topic>GEARING</topic><topic>GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS</topic><topic>HEATING</topic><topic>HELICOPTERS</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>INTERNAL-COMBUSTION PISTON ENGINES</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>CYCON, JAMES P</creatorcontrib><creatorcontrib>MILLEA, F</creatorcontrib><creatorcontrib>KOHLHEPP, W</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>CYCON, JAMES P</au><au>MILLEA, F</au><au>KOHLHEPP, W</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Koaxiale Übersetzungs-/Zentriernaben-Unteranordnung für Rotoranordnung</title><date>2003-07-10</date><risdate>2003</risdate><abstract>An integrated spline/cone seat subassembly (190) for an unmanned aerial vehicle (10) having a rotor assembly (100) that includes ducted, counter-rotating rotors (200, 202), comprising:a rotor shaft (128R or 130R) having an axis, said rotor shaft (128R or 130R) includinga primary shaft portion (192) having a first diameter (D1),an end shaft portion (194) having a second diameter (D2) and having a plurality of shaft splines (198) extending radially outwardly therefrom, anda conic transition portion (196) intermediate said primary and end shaft portions (192, 194), said conic transition portion (196) making a predetermined angle (β) with respect to said axis of said rotor shaft (128R or 130R); anda rotor hub (204) having a centerline (212), said rotor hub (204) having a shaft aperture (206) having a plurality of hub splines (208) extending radially inwardly therefrom;said plurality of hub splines (208) and said plurality of shaft splines (198) being interleaved in combination to provide a rotational interlock between said rotor hub (204) and said rotor shaft (128R or 130R) in the rotor assembly (100); characterized in thateach of said hub splines (208) having an outwardly tapered lower portion (210) that makes a predetermined angle (θ) with respect to said centerline (212); andsaid predetermined angle (θ) of said outwardly tapered lower portions (210) of said hub splines (208) being equal to said predetermined angle (β) of said conic transition portion (196) of said rotor shaft (128R or 130R) wherein said tapered lower portions (210) of said hub splines (208) abuttingly engage and are mechanically supported by said conic transition portion (196) of said rotor shaft (128R or 130R) in the rotor assembly (100).</abstract><edition>7</edition><oa>free_for_read</oa></addata></record> |
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| subjects | AEROPLANES AIRCRAFT AVIATION BEARINGS BLASTING BRAKES CLUTCHES COMBUSTION ENGINES COMBUSTION ENGINES IN GENERAL COSMONAUTICS COUPLINGS FOR TRANSMITTING ROTATION ELEMENTS OR CRANKSHAFT MECHANISMS ENGINEERING ELEMENTS AND UNITS FLEXIBLE SHAFTS GEARING GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INTERNAL-COMBUSTION PISTON ENGINES 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 | Koaxiale Übersetzungs-/Zentriernaben-Unteranordnung für Rotoranordnung |
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