ROTOR BLADE SWASHPLATE-AXIS ROTATION AND GYROSCOPIC MOMENTS COMPENSATOR
An apparatus for compensating for spatial phase angle phase errors in the flapping angle oscillations of a rotor blade is diclosed. The apparatus receives a measured aircraft roll and a measured aircraft pitch. Gyroscopic moments resulting from these measured rolls and pitches are determined, and co...
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| creator | OSDER, STEPHEN, S |
| description | An apparatus for compensating for spatial phase angle phase errors in the flapping angle oscillations of a rotor blade is diclosed. The apparatus receives a measured aircraft roll and a measured aircraft pitch. Gyroscopic moments resulting from these measured rolls and pitches are determined, and compensating gyroscopic moments are then generated and summed with commanded pitch and roll accelerations. Flapping angle phase lags of the rotor blade swashplate are added to the summed signals to cancel any flapping angle phase leads, caused by changes in aircraft or rotor blade speed caused by installation configurations of the rotor blade swashplate.
Ce dispositif compense des erreurs de phase angulaire en phase spatiale survenant lors des oscillations d'angle de battement d'une pale de rotor. Il reçoit des informations concernant le roulis et le tangage mesurés pour une aéronef. Des moments gyroscopiques sont déterminés à partir de ces informations, et des moments gyroscopiques compensatoires sont ensuite générés et ajoutés aux accélérations commandées relatives à ce roulis et à ce tangage. Des retards de phase d'angle de battement, concernant le plateau cyclique des pales de rotor, sont additionnés aux signaux ajoutés pour annuler toute avance de phase d'angle de battement engendrée par des modifications de la vitesse de l'aéronef ou des pales de rotor s'expliquant par des configurations de montage concernant le plateau cyclique de pale de rotor. |
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Ce dispositif compense des erreurs de phase angulaire en phase spatiale survenant lors des oscillations d'angle de battement d'une pale de rotor. Il reçoit des informations concernant le roulis et le tangage mesurés pour une aéronef. Des moments gyroscopiques sont déterminés à partir de ces informations, et des moments gyroscopiques compensatoires sont ensuite générés et ajoutés aux accélérations commandées relatives à ce roulis et à ce tangage. Des retards de phase d'angle de battement, concernant le plateau cyclique des pales de rotor, sont additionnés aux signaux ajoutés pour annuler toute avance de phase d'angle de battement engendrée par des modifications de la vitesse de l'aéronef ou des pales de rotor s'expliquant par des configurations de montage concernant le plateau cyclique de pale de rotor.</description><edition>6</edition><language>eng ; fre</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; CONTROLLING ; COSMONAUTICS ; HELICOPTERS ; PERFORMING OPERATIONS ; PHYSICS ; REGULATING ; SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES ; TRANSPORTING</subject><creationdate>1997</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=19970612&DB=EPODOC&CC=WO&NR=9720736A2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=19970612&DB=EPODOC&CC=WO&NR=9720736A2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>OSDER, STEPHEN, S</creatorcontrib><title>ROTOR BLADE SWASHPLATE-AXIS ROTATION AND GYROSCOPIC MOMENTS COMPENSATOR</title><description>An apparatus for compensating for spatial phase angle phase errors in the flapping angle oscillations of a rotor blade is diclosed. The apparatus receives a measured aircraft roll and a measured aircraft pitch. Gyroscopic moments resulting from these measured rolls and pitches are determined, and compensating gyroscopic moments are then generated and summed with commanded pitch and roll accelerations. Flapping angle phase lags of the rotor blade swashplate are added to the summed signals to cancel any flapping angle phase leads, caused by changes in aircraft or rotor blade speed caused by installation configurations of the rotor blade swashplate.
Ce dispositif compense des erreurs de phase angulaire en phase spatiale survenant lors des oscillations d'angle de battement d'une pale de rotor. Il reçoit des informations concernant le roulis et le tangage mesurés pour une aéronef. Des moments gyroscopiques sont déterminés à partir de ces informations, et des moments gyroscopiques compensatoires sont ensuite générés et ajoutés aux accélérations commandées relatives à ce roulis et à ce tangage. Des retards de phase d'angle de battement, concernant le plateau cyclique des pales de rotor, sont additionnés aux signaux ajoutés pour annuler toute avance de phase d'angle de battement engendrée par des modifications de la vitesse de l'aéronef ou des pales de rotor s'expliquant par des configurations de montage concernant le plateau cyclique de pale de rotor.</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>CONTROLLING</subject><subject>COSMONAUTICS</subject><subject>HELICOPTERS</subject><subject>PERFORMING OPERATIONS</subject><subject>PHYSICS</subject><subject>REGULATING</subject><subject>SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES</subject><subject>TRANSPORTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>1997</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZHAP8g_xD1Jw8nF0cVUIDncM9gjwcQxx1XWM8AxWAMo5hnj6-yk4-rkouEcG-Qc7-wd4Oiv4-vu6-oUEKzj7-wa4-gU7Ak3gYWBNS8wpTuWF0twMCm6uIc4euqkF-fGpxQWJyal5qSXx4f6W5kYG5sZmjkbGRCgBAL_TLN0</recordid><startdate>19970612</startdate><enddate>19970612</enddate><creator>OSDER, STEPHEN, S</creator><scope>EVB</scope></search><sort><creationdate>19970612</creationdate><title>ROTOR BLADE SWASHPLATE-AXIS ROTATION AND GYROSCOPIC MOMENTS COMPENSATOR</title><author>OSDER, STEPHEN, S</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_WO9720736A23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre</language><creationdate>1997</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>CONTROLLING</topic><topic>COSMONAUTICS</topic><topic>HELICOPTERS</topic><topic>PERFORMING OPERATIONS</topic><topic>PHYSICS</topic><topic>REGULATING</topic><topic>SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES</topic><topic>TRANSPORTING</topic><toplevel>online_resources</toplevel><creatorcontrib>OSDER, STEPHEN, S</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>OSDER, STEPHEN, S</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>ROTOR BLADE SWASHPLATE-AXIS ROTATION AND GYROSCOPIC MOMENTS COMPENSATOR</title><date>1997-06-12</date><risdate>1997</risdate><abstract>An apparatus for compensating for spatial phase angle phase errors in the flapping angle oscillations of a rotor blade is diclosed. The apparatus receives a measured aircraft roll and a measured aircraft pitch. Gyroscopic moments resulting from these measured rolls and pitches are determined, and compensating gyroscopic moments are then generated and summed with commanded pitch and roll accelerations. Flapping angle phase lags of the rotor blade swashplate are added to the summed signals to cancel any flapping angle phase leads, caused by changes in aircraft or rotor blade speed caused by installation configurations of the rotor blade swashplate.
Ce dispositif compense des erreurs de phase angulaire en phase spatiale survenant lors des oscillations d'angle de battement d'une pale de rotor. Il reçoit des informations concernant le roulis et le tangage mesurés pour une aéronef. Des moments gyroscopiques sont déterminés à partir de ces informations, et des moments gyroscopiques compensatoires sont ensuite générés et ajoutés aux accélérations commandées relatives à ce roulis et à ce tangage. Des retards de phase d'angle de battement, concernant le plateau cyclique des pales de rotor, sont additionnés aux signaux ajoutés pour annuler toute avance de phase d'angle de battement engendrée par des modifications de la vitesse de l'aéronef ou des pales de rotor s'expliquant par des configurations de montage concernant le plateau cyclique de pale de rotor.</abstract><edition>6</edition><oa>free_for_read</oa></addata></record> |
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| subjects | AEROPLANES AIRCRAFT AVIATION CONTROLLING COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS PHYSICS REGULATING SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES TRANSPORTING |
| title | ROTOR BLADE SWASHPLATE-AXIS ROTATION AND GYROSCOPIC MOMENTS COMPENSATOR |
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