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Patent Agency Ranking
公开(公告)号：EP3495260A1
公开(公告)日：2019-06-12
申请号：EP18208692.6
申请日：2018-11-27
Applicant: Bell Helicopter Textron Inc.
Inventor： BRAND, Albert G. , ISAAC, Mark Loring , STAMPS, Frank Bradley , MUELLER, Russell Lee
Abstract: A dual rotor propulsion system (200, 300) for a tiltrotor aircraft (10, 100) having VTOL and forward flight modes. The dual rotor propulsion system (200, 300) includes an engine (202, 302) operable to provide an input torque to a transmission (206, 306) that, responsive thereto, generates an output torque. A first output shaft (214a, 314a) is coupled to the transmission (206, 306) and is operable to receive a first portion of the output torque. A first rotor assembly (216a, 316a) is coupled to and rotatable with the first output shaft (214a, 314a). A second output shaft (214b, 314b) is coupled to the transmission (206, 306) and is operable to receive a second portion of the output torque. A second rotor assembly (216b, 316b) is coupled to and rotatable with the second output shaft (214b, 314b). In operation, the first and second rotor assemblies (216a, 316a, 216b, 316b) rotate coaxially, the first rotor assembly (216a, 316a) is a different diameter than the second rotor assembly (216b, 316b) and the first rotor assembly (216a, 216b) is stoppable and foldable in the forward flight mode.
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公开(公告)号：EP3486168B1
公开(公告)日：2020-01-29
申请号：EP18195578.2
申请日：2018-09-19
Applicant: Bell Helicopter Textron Inc.
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公开(公告)号：EP3486168A1
公开(公告)日：2019-05-22
申请号：EP18195578.2
申请日：2018-09-19
Applicant: Bell Helicopter Textron Inc.
IPC: B64C27/26 , B64C27/28 , B64C29/00 , B64C39/08 , G05D1/08 , B64C15/12 , B64C27/30 , B64C27/08 , B64C11/28
Abstract: A quad tiltrotor aircraft (10, 100, 200) has a longitudinally extending fuselage (12, 312) with forward and aft stations (14, 314; 16, 318). A forward wing (18, 320) having first and second outboard ends extends laterally from the forward station (14, 314). An aft wing (20, 324) having first and second outboard ends extends laterally from the aft station (16, 318). First and second forward rotors (26a, 26b, 112a, 112b, 212a, 212b, 330a, 330b) are respectively coupled proximate the first and second outboard ends of the forward wing (18, 320) and are tiltable relative to the forward wing (18, 320) between vertical lift and forward thrust orientations. First and second aft rotors (36a, 36b, 120a, 120b, 220a, 220b, 342a, 342b) are respectively coupled proximate the first and second outboard ends of the aft wing (20, 324) and are tiltable relative to the aft wing (20, 324) between vertical lift and forward thrust orientations. The forward rotors (26a, 26b, 112a, 112b, 212a, 212b, 330a, 330b) are higher disk-loading rotors than the aft rotors (36a, 36b, 120a, 120b, 220a, 220b, 342a, 342b). The aft rotors (36a, 36b, 120a, 120b, 220a, 220b, 342a, 342b) are foldable in the forward flight mode to provide extended range for the quad tiltrotor aircraft (10, 100, 200).
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公开(公告)号：EP3178737B1
公开(公告)日：2018-02-14
申请号：EP16202514.2
申请日：2016-12-06
Applicant: Bell Helicopter Textron Inc.
CPC classification number: B64C1/26 , B64C1/1423 , B64C3/187 , B64C29/0033
Abstract: According to one embodiment, an aircraft features a fuselage (130), a wing member (150), and two fuselage beams (220a, 220b). The fuselage (130) features a first plurality of structural supports, a second plurality of structural supports, a first opening (132a) disposed between the first plurality of structural supports, and a second opening (132b) disposed between the second plurality of structural supports. The wing member (150) is disposed above the first opening (132a) and above the second opening (132b). The wing (150) features a plurality of ribs (152) including a first rib (152a) and a second rib (152b). The first fuselage beam (220a) couples the first rib (152a) of the wing member (150) to the fuselage (130) and has an elongated body portion extending across the first plurality of structural supports. The second fuselage beam (220b) couples the second rib (152b) of the wing member (150) to the fuselage (130) and features an elongated body portion extending across the second plurality of structural supports.
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公开(公告)号：EP3178737A1
公开(公告)日：2017-06-14
申请号：EP16202514.2
申请日：2016-12-06
Applicant: Bell Helicopter Textron Inc.
CPC classification number: B64C1/26 , B64C1/1423 , B64C3/187 , B64C29/0033
Abstract: According to one embodiment, an aircraft features a fuselage (130), a wing member (150), and two fuselage beams (220a, 220b). The fuselage (130) features a first plurality of structural supports, a second plurality of structural supports, a first opening (132a) disposed between the first plurality of structural supports, and a second opening (132b) disposed between the second plurality of structural supports. The wing member (150) is disposed above the first opening (132a) and above the second opening (132b). The wing (150) features a plurality of ribs (152) including a first rib (152a) and a second rib (152b). The first fuselage beam (220a) couples the first rib (152a) of the wing member (150) to the fuselage (130) and has an elongated body portion extending across the first plurality of structural supports. The second fuselage beam (220b) couples the second rib (152b) of the wing member (150) to the fuselage (130) and features an elongated body portion extending across the second plurality of structural supports.
Abstract translation: 根据一个实施例，飞行器具有机身（130），翼构件（150）和两个机身梁（220a，220b）。 机身130具有第一多个结构支撑件，第二多个结构支撑件，设置在第一多个结构支撑件之间的第一开口132a和设置在第二多个结构支撑件之间的第二开口132b） 。 翼构件（150）设置在第一开口（132a）的上方并位于第二开口（132b）的上方。 机翼（150）具有包括第一肋（152a）和第二肋（152b）的多个肋（152）。 第一机身梁（220a）将翼构件（150）的第一肋（152a）联接到机身（130）并且具有延伸穿过第一多个结构支撑件的细长主体部分。 第二机身梁（220b）将翼构件（150）的第二肋（152b）联接到机身（130）并且具有延伸穿过第二多个结构支撑件的细长主体部分。
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