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公开(公告)号：JPH109341A
公开(公告)日：1998-01-13
申请号：JP35875496
申请日：1996-12-27
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： SEHGAL AJAY , COVINGTON CECIL E , YUCE MITHAT , MARSHALL BRYAN W
IPC: B64C27/51 , B64C27/00 , F16F15/12 , F16F15/133 , F16F15/121
Abstract: PROBLEM TO BE SOLVED: To provide a vibration absorbing device with which the weight compensates the vibration effectively in all five directions, i.e., ahead and aside in the plane, vertically, and in the pitching and rolling directions. SOLUTION: This vibration absorbing device concerned 20 is equipped with a mass member borne in the stationary state by intra-plane springs 36 at a certain spacing from a base plate 22, top plate, and spring holding structure 45. The mass member has a buffer surface contacting with a motion restrictor 30 for the base plate. The mass member, base plate, and top plate can be equipped with a passage 24 passing the axis 26. Adjustment of this vibration absorbing device can be made by varying the intra-plane spring (s), the degree of preliminary compression, and the size of the mass achieved through addition or removal of a mass adjusting weight.
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公开(公告)号：DE60201614T2
公开(公告)日：2005-10-06
申请号：DE60201614
申请日：2002-03-05
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： SEHGAL AJAY , ZIERER JOSEPH , COVINGTON CECIL E , BOYLE ERIC , HAYNIE DAVID
Abstract: The multi-bladed tail rotor assembly provides higher aerodynamic performance, damage tolerant design with 10,000-hour life expectancy, and which requires low maintenance through the use of composites and elastomerics. The tail rotor hub assembly includes two stacked yoke assemblies having multi-bladed teetering rotors, each mounted on a single drive mast. Each yoke assembly includes a yoke hub having a transverse bore therethrough, a bearing assembly disposed within the bore, and retention means for aligning and securing the bearing assembly within the bore. Each bearing assembly includes a trunnion portion having trunnion arms that extend outwardly from a trunnion body portion, and an elastomeric bearing disposed about each trunnion arm. The tail rotor assembly utilizes a composite twist strap flexure to accommodate collective pitch control integral with each rotor blade.
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公开(公告)号：CA2374652C
公开(公告)日：2009-12-08
申请号：CA2374652
申请日：2002-03-05
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： COVINGTON CECIL E , ZIERER JOSEPH , HAYNIE DAVID , BOYLE ERIC , SEHGAL AJAY
Abstract: A multi-bladed tail rotor assembly is disclosed that provides higher aerodynamic performance, damage tolerant design with 10,000-hour life expectancy, and which requires low maintenance through the use of composites and elastomerics. The tail rotor hub assembly includes two stacked yoke assemblies having multi-bladed teetering rotors, each mounted on a single drive mast. Each yoke assembly includes a yoke hub having a transverse bore therethrough, a bearing assembly disposed within th e bore, and retention means for aligning and securing the bearing assembly within th e bore. Each bearing assembly includes a trunnion portion having trunnion arms that extend outwardly from a trunnion body portion, and an elastomeric bearing disposed about each trunnion arm. The tail rotor assembly utilizes a composite twist strap flexure to accommodate collective pitch control integral with each rotor blade.
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公开(公告)号：CA2444000C
公开(公告)日：2007-09-25
申请号：CA2444000
申请日：2002-04-19
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： STAMPS FRANK B , SMITH MICHAEL R , COVINGTON CECIL E , MARSHALL BRYAN , SEHGAL AJAY
Abstract: A rotor system vibration absorber for use with a helicopter of other rotocra ft is disclosed in which spring forces are provided by a plurality of elongated rods (73) arranged in a selected pattern. The rods are coupled at one end to a fixed base (79) that is coupled to a rotor hub (55), and at the other end to a tuning weight (81).
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公开(公告)号：CA2369837C
公开(公告)日：2009-12-08
申请号：CA2369837
申请日：2002-01-30
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： STAMPS FRANK B , BRASWELL JAMES L JR , POPELKA DAVID A , COVINGTON CECIL E , BENNETT RICHARD L , COVINGTON CHARLES E , SETTLE THOMAS B JR
Abstract: An aircraft with a tilt rotor assembly comprising a craft body, a plurality of rotor blades which are subject to three modes of flight operation, a tilting mast coupling the plurality of rotor blades to the craft body and for selectively moving the plurality of rotor blades between the three modes of flight operation, a hub coupling the plurality of rotor blades to the tilting mast in a manner which transfers torque and thrust whi le allowing tilting of a rotor thrust vector, a main swashplate for tilting in response to operator input to control the direction of the rotor thrust vector, a plurality of pitch horns , each mechanically coupled to a particular one of the plurality of rotor blades and to the main swashplate, for communicating swashplate input to each of the plurality of rotor blades, a plurality of links coupling the main swashplate to the plurality of pitch horns, wherein each o f the plurality of pitch horns is mechanically coupled to a particular one of the plurality of rotor blades by one of the plurality of links in a particular position which yields a delta- 3 value which is not optimum, and a feedback swashplate and cooperating feedback links for receiving disk tilting input from the plurality of rotor blades during flight, and for supplying a mechanical input tothe main swashplate to compensate for the less than optimum delta-3 coupling between the plurality of pitch horns and the plurality of links. The three modes of flight include: (1) an airplane mode of flight with the plurality of rotor blades i n a rotor disk position which is substantially transverse to the craft body; (2) a helicopt er mode of flight with the plurality of rotor blades in a rotor disk position substantially parallel to the craft body with direction of flight being controlled by a rotor thrust vector; and (3) a transition mode of flight with the plurality of rotor blades moving between the rotor disk positions associated with the airplane mode of flight and the helicopter mode of fligh t.
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Patent Agency Ranking
公开(公告)号：DE60201614D1
公开(公告)日：2004-11-25
申请号：DE60201614
申请日：2002-03-05
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： SEHGAL AJAY , ZIERER JOSEPH , COVINGTON CECIL E , BOYLE ERIC , HAYNIE DAVID
Abstract: The multi-bladed tail rotor assembly provides higher aerodynamic performance, damage tolerant design with 10,000-hour life expectancy, and which requires low maintenance through the use of composites and elastomerics. The tail rotor hub assembly includes two stacked yoke assemblies having multi-bladed teetering rotors, each mounted on a single drive mast. Each yoke assembly includes a yoke hub having a transverse bore therethrough, a bearing assembly disposed within the bore, and retention means for aligning and securing the bearing assembly within the bore. Each bearing assembly includes a trunnion portion having trunnion arms that extend outwardly from a trunnion body portion, and an elastomeric bearing disposed about each trunnion arm. The tail rotor assembly utilizes a composite twist strap flexure to accommodate collective pitch control integral with each rotor blade.
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公开(公告)号：CA2374652A1
公开(公告)日：2002-09-06
申请号：CA2374652
申请日：2002-03-05
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： BOYLE ERIC , HAYNIE DAVID , ZIERER JOSEPH , COVINGTON CECIL E , SEHGAL AJAY
Abstract: A multi-bladed tail rotor assembly is disclosed that provides higher aerodynamic performance, damage tolerant design with 10,000-hour life expectancy, and which requires low maintenance through the use of composites and elastomerics. The tail rotor hub assembly includes two stacked yoke assemblies having multi-bladed teetering rotors, each mounted on a single drive mast. Each yoke assembly includes a yoke hub having a transverse bore therethrough, a bearing assembly disposed within th e bore, and retention means for aligning and securing the bearing assembly within th e bore. Each bearing assembly includes a trunnion portion having trunnion arms that extend outwardly from a trunnion body portion, and an elastomeric bearing disposed about each trunnion arm. The tail rotor assembly utilizes a composite twist strap flexure to accommodate collective pitch control integral with each rotor blade.
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公开(公告)号：CA2369837A1
公开(公告)日：2002-08-16
申请号：CA2369837
申请日：2002-01-30
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： BRASWELL JAMES L JR , STAMPS FRANK B , COVINGTON CECIL E , POPELKA DAVID A , COVINGTON CHARLES E , BENNETT RICHARD L , SETTLE THOMAS B JR
Abstract: An aircraft with a tilt rotor assembly comprising a craft body, a plurality of rotor blades which are subject to three modes of flight operation, a tilting mast coupling the plurality of rotor blades to the craft body and for selectively moving the plurality of rotor blades between the three modes of flight operation, a hub coupling the plurality of rotor blades to the tilting mast in a manner which transfers torque and thrust whi le allowing tilting of a rotor thrust vector, a main swashplate for tilting in response to operator input to control the direction of the rotor thrust vector, a plurality of pitch horns , each mechanically coupled to a particular one of the plurality of rotor blades and to the main swashplate, for communicating swashplate input to each of the plurality of rotor blades, a plurality of links coupling the main swashplate to the plurality of pitch horns, wherein each o f the plurality of pitch horns is mechanically coupled to a particular one of the plurality of rotor blades by one of the plurality of links in a particular position which yields a delta- 3 value which is not optimum, and a feedback swashplate and cooperating feedback links for receiving disk tilting input from the plurality of rotor blades during flight, and for supplying a mechanical input to the main swashplate to compensate for the less than optimum delta-3 coupling between the plurality of pitch horns and the plurality of links. The three modes of flight include: (1) an airplane mode of flight with the plurality of rotor blades i n a rotor disk position which is substantially transverse to the craft body; (2) a helicopt er mode of flight with the plurality of rotor blades in a rotor disk position substantially parallel to the craft body with direction of flight being controlled by a rotor thrust vector; and (3) a transition mode of flight with the plurality of rotor blades moving between the rotor disk positions associated with the airplane mode of flight and the helicopter mode of fligh t.
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公开(公告)号：AU6895291A
公开(公告)日：1991-06-13
申请号：AU6895291
申请日：1990-10-09
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： SCHELLHASE ERNST C , ANASTAS DAN , KEEFER PAUL E , COVINGTON CECIL E , ZIERER JOSEPH J , NEATHERY WILLIAM D
Abstract: Folding and folding locking apparatus for rotor blades that includes a power actuator for rotating the blades and locking means for securing the blade in the deployed position and securing the blades against rotation of the pitch angle during and when the blades are folded. The apparatus also provides for the complete fairing of the blades at their connections with the rotary drive hub and provides a powered door in the fairing that can be opened and closed to permit the quick and easy folding and redeployment of the blades.
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公开(公告)号：CA1209558A
公开(公告)日：1986-08-12
申请号：CA431061
申请日：1983-06-23
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： METZGER ROBERT W , NEATHERY WILLIAM D , REYES PETER A , TISDALE PATRICK R , COVINGTON CECIL E , BROEKHUIZEN WILLEM
Abstract: : The present invention relates to a soft inplane bearingless rotor which is to be rigidly mounted on a helicopter mast. The rotor is comprised of a unitary yoke which has a flat hub section adapted to be anchored to the end of the mast and has diametrically opposed blade-supporting arms which extend from the hub section. Each arm has a thin flapping section adjacent the hub section and a feathering section which extends from the flapping section. Blade attachments are located at the end of each of the arms. The arms include a plurality of fiber reinforced composite parallel ribs which extend span-wise with a predetermined inplane spacing. A blade is secured to each attachment with a cuff which extends inboard to the flapping section. A bearing structure interconnects the inboard end of the cuff and the flapping section and includes an inplane resilient structure for soft inplane restraint of the blade.
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