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21.发明公开
公开(公告)号：EP3409586A1
公开(公告)日：2018-12-05
申请号：EP18174173.7
申请日：2018-05-24
Applicant: Bell Helicopter Textron Inc.
Inventor： HALDEMAN, Andrew , SINUSAS, Eric , STAMPS, Frank Bradley
CPC classification number: B64D27/24 , B60L53/12 , B64C27/06 , B64C27/12 , B64C27/82 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8254 , B64D2027/026 , B64D2221/00 , H02P3/04 , H02P3/14
Abstract: The present invention includes a system and method for slowing the rotation of a rotor (902) using, for example, rotor brake system (900) for a rotorcraft (906) comprising: one or more generators connected to a main rotor gearbox (914); an electric distributed anti-torque system (924) mounted on a tail boom (108) of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.
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公开(公告)号：EP3318489B1
公开(公告)日：2018-09-26
申请号：EP17193869.9
申请日：2017-09-28
Applicant: Bell Helicopter Textron Inc.
Inventor： STAMPS, Frank Bradley , GONZALEZ, Eric Ricardo
CPC classification number: B64C27/605 , B64C11/28 , B64C27/10 , B64C27/12 , B64C27/50 , B64C39/024
Abstract: An aircraft (10) has a fuselage (28), a first rotor assembly (36) having a first rotor hub (38) and first rotor blades (40a, 40b, 40c) pivotably coupled to the first rotor hub (38) and a second rotor assembly (56) having a second rotor hub (58) and second rotor blades (60a, 60b, 60c) pivotably coupled to the second rotor hub (58). The first (40a, 40b, 40c) and second (60a, 60b, 60c) rotor blades have deployed configurations extending generally radially from the fuselage (28) and stowed configurations extending generally parallel with the fuselage (28). A sequencing cam (90), positioned between the first (38) and second (58) rotor hubs, is coupled to the second rotor blades (60a, 60b, 60c). The sequencing cam (90) has a retracted orientation when the second rotor blades (60a, 60b, 60c) are in the stowed configuration and an extended orientation when the second rotor blades (60a, 60b, 60c) are in the deployed configuration in which the sequencing cam (90) props support arms (42a, 42b, 42c) of the first rotor blades (40a, 40b, 40c) preventing transition of the first rotor blades (40a, 40b, 40c) from the deployed configuration to the stowed configuration.
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公开(公告)号：EP3366583A1
公开(公告)日：2018-08-29
申请号：EP17208612.6
申请日：2017-12-19
Applicant: Bell Helicopter Textron Inc.
Inventor： CHOI, Jouyoung Jason , ROBERTSON, Daniel Bryan , GRONINGA, Kirk Landon , STAMPS, Frank Bradley , LOUIS, Matthew Edward
CPC classification number: B64C39/005 , B64C3/14 , B64C3/32 , B64C23/02 , B64C27/26 , B64C27/28 , B64C27/52 , B64C29/0033 , B64C39/003 , B64C2003/143 , B64D27/12 , B64D27/26 , B64D2027/262 , Y02T50/12
Abstract: A tiltrotor aircraft (10) has a fuselage (12) and a wing (18) having upper and lower surfaces (18a-b) with a plurality of channels (56a-d) extending therebetween, each with a cycloidal rotor (28a-h) mounted therein. At least two pylon assemblies (22a-b) are rotatably coupled to the wing (18) to selectively operate the tiltrotor aircraft (10) between helicopter and airplane flight modes. Each pylon assembly (22a-b) includes a mast (54) and a proprotor assembly (24a-b) operable to rotate with the mast (54) to generate thrust. At least one engine (40) provides torque and rotational energy to the proprotor assemblies (24a-b) and the propulsion assemblies. Each of the cycloidal rotors (28a-h) has a plurality of blades (108) that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor (28a-h) is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.
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公开(公告)号：EP3323720A1
公开(公告)日：2018-05-23
申请号：EP17192413.7
申请日：2017-09-21
Applicant: Bell Helicopter Textron Inc.
Inventor： CHOI, Jouyoung Jason , MILLER, Gary , RAUBER, Richard Erler , PARHAM, Thomas Clement, Jr. , EWING, Alan Carl , STAMPS, Frank Bradley
CPC classification number: B64C29/0033 , B64C27/28 , B64C27/41 , B64C27/473 , B64C27/51 , B64C27/52 , B64C27/54 , B64C2027/4736
Abstract: A proprotor system (100; 200; 300; 400) for tiltrotor aircraft (10) having a helicopter mode and an airplane mode. The proprotor system includes a hub (102; 202; 302; 404) and a plurality of proprotor blades (112; 212; 312; 402) coupled to the hub (102; 202; 302; 404) such that each proprotor blade (112; 212; 312; 402) is operable to independently flap relative to the hub and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev.
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公开(公告)号：EP1883758A1
公开(公告)日：2008-02-06
申请号：EP06738784.5
申请日：2006-03-17
Applicant: Bell Helicopter Textron Inc.
Inventor： STAMPS, Frank Bradley , SMITH, Michael, Reaugh , LEE, Taeoh
Abstract: A vibration isolator for connecting a first body and a second body includes a housing having a first chamber (22) , a second chamber (26) , and a port (24) connecting the first chamber (22) to the second chamber (26) and permitting fluid (34) to flow between the first chamber (22) and the second chamber (26). The first and second chambers (22), (26) and the port (24) defining a fluid reservoir (27) . The isolator (10) includes a gas-to-fluid accumulator (30) in fluid communication with the fluid reservoir (27) through a first one-way valve (140) and a second one-way valve (142) . The first one-way valve (140) allows fluid (34) to pass only from the fluid reservoir (27) to the accumulator (30) and the second one-way valve (142) allows fluid (34) to pass only from the accumulator (30) to the fluid reservoir (27). At least one of the first and second one-way valves (140), (142) being preloaded to a predetermined force to permit fluid flow through the at least one-way valve (140), (142) only when fluid pressure exceeds the predetermined force.
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Patent Agency Ranking
公开(公告)号：EP3366583B1
公开(公告)日：2019-07-17
申请号：EP17208612.6
申请日：2017-12-19
Applicant: Bell Helicopter Textron Inc.
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公开(公告)号：EP3421353A1
公开(公告)日：2019-01-02
申请号：EP18167038.1
申请日：2018-04-12
Applicant: Bell Helicopter Textron Inc.
Inventor： PARHAM, Jr., Thomas Clement , BOSWORTH, Jeffrey , MILLER, Gary , STAMPS, Frank Bradley , CHOI, Jouyoung Jason , OLDROYD, Paul K. , RAUBER, Richard Erler , SEIFERT, Michael Scott
Abstract: A wing airframe (36, 100, 222) for a wing (18, 102, 200) of a tiltrotor aircraft (10) includes a wing airframe coreassembly (110, 206) and a wing skin assembly (24, 118, 202) disposed on the wing airframe core assembly. The wing skin assembly (118, 202) includes an outer skin (52, 130, 208) and a damping sublayer (50, 128, 204), the damping sublayer interposed between the outer skin and the wing airframe core assembly (110, 206). The tiltrotor aircraft (10) includes a pylon assembly (30a, 30b) subject to aeroelastic movement during forward flight. The wing (18, 102, 200) is subject to deflection in response to the aeroelastic movement of the pylon assembly (30a, 30b). The damping sublayer (50, 128, 204) reduces the deflection of the wing (18, 102, 200), thereby stabilizing the wing during forward flight.
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公开(公告)号：EP3345830A1
公开(公告)日：2018-07-11
申请号：EP17182195.2
申请日：2017-07-19
Applicant: Bell Helicopter Textron Inc.
Inventor： STAMPS, Frank Bradley , SUTTON, Drew Alan
CPC classification number: B64C27/72 , B64C27/43 , B64C27/48 , B64C27/59 , B64C27/78 , B64C27/82 , B64C2027/8227
Abstract: The present invention includes a rotor hub system (200), comprising: a teetering rotor hub (204, 206) disposed about a mast (202), the teetering rotor hub (204, 206) comprising: a first (208) and a second (218) yoke; each connected to a set of rotor blades (210, 212, 220, 222), wherein the second set of rotor blades (220, 222) and the first set of rotor blades (210, 212) are disposed in a common plane, but the first (208) and the second (218) yoke do not come in contact.
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公开(公告)号：EP3333074A1
公开(公告)日：2018-06-13
申请号：EP17195818.4
申请日：2017-10-10
Applicant: Bell Helicopter Textron Inc.
Inventor： PARHAM Jr., Thomas Clement , CHOI, Jouyoung Jason , MILLER, Gary , STAMPS, Frank Bradley , RAUBER, Richard Erler
Abstract: A soft-in-plane proprotor system (100) for a tiltrotor aircraft (10) having a helicopter mode and an airplane mode. The proprotor system (100) includes a hub (102), a plurality of proprotor blades (104) and a plurality of loop yokes (120), each coupling one of the proprotor blades (104) with the hub (102) and each including first (204) and second (206) longitudinal sections extending between inboard (208) and outboard (210) arcuate sections and a bearing assembly (118) disposed between the inboard (208) and outboard (210) arcuate sections of each loop yoke (120). Each bearing assembly (118) includes a flapping bearing (122) disposed generally within the inboard arcuate section (208) of the respective loop yoke (120) and coupled to the hub (102), a lead-lag damper (128) coupled to the hub (108), a centrifugal force bearing (138) disposed generally within the outboard arcuate section (210) of the respective loop yoke (120) and a blade anchor (130) coupled between the lead-lag damper (128) and the centrifugal force bearing (138). The blade anchor (130) is also coupled to the respective proprotor blade (104).
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公开(公告)号：EP3290338A1
公开(公告)日：2018-03-07
申请号：EP17163295.3
申请日：2017-03-28
Applicant: Bell Helicopter Textron Inc.
IPC: B64C29/02
Abstract: A tail sitter aircraft (10) includes a fuselage (12) having a forward portion (14) and an aft portion (16). The forward portion (14) of the fuselage (12) includes first and second rotor stations (18, 20). A first rotor assembly (22) is positioned proximate the first rotor station (18). A second rotor assembly (24) is positioned proximate the second rotor station (20). A tailboom assembly (26) extends from the aft portion (16) of the fuselage (12). The tailboom assembly (26) includes a plurality of landing members (28). In a vertical takeoff and landing mode of the aircraft (10), the first and second rotor assemblies (22, 24) rotate about the fuselage (12) to provide vertical thrust. In a forward flight mode of the aircraft, the first rotor assembly (22) rotates about the fuselage (12) to provide forward thrust and the second rotor assembly (24) is non-rotatable about the fuselage (12) forming wings to provide lift.
Abstract translation: 尾部维护飞机（10）包括具有前部（14）和后部（16）的机身（12）。 机身（12）的前部（14）包括第一和第二转子站（18,20）。 第一转子组件（22）靠近第一转子站（18）定位。 第二转子组件（24）位于第二转子站（20）附近。 尾梁组件（26）从机身（12）的后部（16）延伸。 尾杆组件（26）包括多个着陆构件（28）。 在飞机（10）的垂直起飞和着陆模式中，第一和第二转子组件（22,24）围绕机身（12）旋转以提供垂直推力。 在飞机的向前飞行模式中，第一转子组件（22）围绕机身（12）旋转以提供向前的推力，并且第二转子组件（24）围绕机身（12）不可旋转，从而形成机翼以提供升力 。
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