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公开(公告)号：EP3708499A1
公开(公告)日：2020-09-16
申请号：EP20152387.5
申请日：2020-01-17
Applicant: Bell Helicopter Textron Inc.
Inventor： ACEE, Aaron Alexander , HALDEMAN, Andrew Paul , SINUSAS, Eric Albert , LAVALLEE, Yann , BRAND, Albert G.
Abstract: An exemplary electric distributed propulsion system (600) includes two or more rotors (612a-d) that are individually controlled by the rotational speed of associated motors (611a-d), an input control (626) connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic (624) connected to the input control (626) and the associated motors (611a-d), the logic (624) for controlling speed and direction of the two or more rotors (612a-d) to achieve the desired net thrust and to avoid a motor speed condition.
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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：EP3406521B1
公开(公告)日：2019-06-19
申请号：EP17185863.2
申请日：2017-08-11
Applicant: Bell Helicopter Textron Inc.
Inventor： CARR, Matthew R. , LOUIS, Matthew E. , GRONINGA, Kirk L. , ROBERTSON, Daniel B. , STAMPS, Frank B. , BRAND, Albert G. , SINUSAS, Eric A.
IPC: B64C27/82
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公开(公告)号：EP3241756A1
公开(公告)日：2017-11-08
申请号：EP16172307.7
申请日：2016-05-31
Applicant: Bell Helicopter Textron Inc.
Inventor： PERYEA, Martin , SMITH, Michael Reaugh , HAMELWRIGHT Jr., Douglas , BRAND, Albert G. , PLAGIANOS, Nicholas J. , EMRICH, Joshua , CARR, Timothy
IPC: B64D37/04
Abstract: A rotorcraft (10) includes a fuselage (16) having a fuel tank receiving assembly (24) with a fuel tank (28) positioned therein. The fuel tank (28) including a plurality of interconnected fuel bags operable to contain liquid fuel. A network of straps is disposed about the fuel tank (28) forming a restraint assembly (130; 172; 182; 202). The network of straps includes at least one perimeter strap (132, 134, 136, 138, 140) extending at least partially about at least two fuel bags and at least one surrounding strap (142, 144, 146) extending at least partially about the at least two fuel bags. The at least one perimeter strap (132, 134, 136, 138, 140) has at least two intersections (156, 158) with the at least one surrounding strap (142, 144, 146).
Abstract translation: 一种旋翼飞行器（10）包括具有燃料箱接收组件（24）的机身（16），燃料箱（28）位于其中。 燃料箱（28）包括多个可操作以容纳液体燃料的互连燃料箱。 围绕形成约束组件（130; 172; 182; 202）的燃料箱（28）设置有网带。 所述带的网络包括至少一个周边带（132,134,136,138,140），所述至少一个周边带至少部分地围绕至少两个燃料袋延伸，所述至少一个周围带（142,144,146）至少部分地围绕 至少两个燃料袋。 所述至少一个周边带（132,134,136,138,140）具有与所述至少一个周围带（142,144,146）的至少两个交叉点（156,158）。
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公开(公告)号：EP3406521A1
公开(公告)日：2018-11-28
申请号：EP17185863.2
申请日：2017-08-11
Applicant: Bell Helicopter Textron Inc.
Inventor： CARR, Matthew R. , LOUIS, Matthew E. , GRONINGA, Kirk L. , ROBERTSON, Daniel B. , STAMPS, Frank B. , BRAND, Albert G. , SINUSAS, Eric A.
IPC: B64C27/82
CPC classification number: B64C27/82 , B64C2027/8245 , B64C2027/8254 , F04D17/16 , F04D29/462
Abstract: In one embodiment, a rotorcraft (100) comprises a fuselage (110), a tail boom (202), a rotor system (120), and a centrifugal blower system (200). The centrifugal blower system (200) comprises a centrifugal blower (204) configured to generate thrust using an airflow, wherein the centrifugal blower (204) is located within the tail boom (202). The centrifugal blower system (200) also comprises a plurality of ducts configured to control the thrust generated by the centrifugal blower (204), wherein the plurality of ducts is located on a portion of the tail boom (202) surrounding the centrifugal blower (204), and wherein the plurality of ducts comprises one or more adjustable ducts configured to vary a size of an associated duct opening.
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公开(公告)号：EP3241756B1
公开(公告)日：2018-08-01
申请号：EP16172307.7
申请日：2016-05-31
Applicant: Bell Helicopter Textron Inc.
Inventor： PERYEA, Martin , SMITH, Michael Reaugh , HAMELWRIGHT Jr., Douglas , BRAND, Albert G. , PLAGIANOS, Nicholas J. , EMRICH, Joshua , CARR, Timothy
IPC: B64D37/04
Abstract: A rotorcraft (10) includes a fuselage (16) having a fuel tank receiving assembly (24) with a fuel tank (28) positioned therein. The fuel tank (28) including a plurality of interconnected fuel bags operable to contain liquid fuel. A network of straps is disposed about the fuel tank (28) forming a restraint assembly (130; 172; 182; 202). The network of straps includes at least one perimeter strap (132, 134, 136, 138, 140) extending at least partially about at least two fuel bags and at least one surrounding strap (142, 144, 146) extending at least partially about the at least two fuel bags. The at least one perimeter strap (132, 134, 136, 138, 140) has at least two intersections (156, 158) with the at least one surrounding strap (142, 144, 146).
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