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公开(公告)号：USD798794S1
公开(公告)日：2017-10-03
申请号：US29564548
申请日：2016-05-13
Applicant: Bell Helicopter Textron Inc.
Designer： Carlos Alexander Fenny , Rohn Lee Olson , Andrew James Zahasky
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公开(公告)号：US20170096219A1
公开(公告)日：2017-04-06
申请号：US15383458
申请日：2016-12-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Dudley E. Smith , Cory M. Hitte , Bryan Marshall , Carlos Alexander Fenny
CPC classification number: B64C27/006 , B64C27/12 , B64D27/24 , B64D2027/026 , Y10T29/49117
Abstract: Embodiments refer generally to systems and methods for providing autorotative enhancement for helicopters using an autorotative assist unit coupled to the transmission of the helicopter. Methods of utilizing an autorotative assist unit as well as retrofitting an autorotative assist unit to an existing helicopter are also disclosed. By employing an autorotative assist unit, improved autorotation can be achieved without the need to increase the weight of the rotor.
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公开(公告)号：US20160059957A1
公开(公告)日：2016-03-03
申请号：US14934477
申请日：2015-11-06
Applicant: Bell Helicopter Textron Inc.
Inventor： Dudley E. Smith , Cory M. Hitte , Bryan Marshall , Carlos Alexander Fenny
CPC classification number: B64C27/006 , B64C27/12 , B64D27/24 , B64D2027/026 , Y10T29/49117
Abstract: Embodiments refer generally to systems and methods for providing autorotative enhancement for helicopters using an autorotative assist unit coupled to the transmission of the helicopter. Methods of utilizing an autorotative assist unit as well as retrofitting an autorotative assist unit to an existing helicopter are also disclosed. By employing an autorotative assist unit, improved autorotation can be achieved without the need to increase the weight of the rotor.
Abstract translation: 实施例总体上涉及用于使用耦合到直升机的传输的自动辅助单元来提供直升机的自动增强的系统和方法。 还公开了利用自动辅助单元以及将自动辅助单元改装到现有直升机的方法。 通过使用自动辅助单元，可以实现改进的自转，而不需要增加转子的重量。
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公开(公告)号：US20140263820A1
公开(公告)日：2014-09-18
申请号：US13834215
申请日：2013-03-15
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Dudley E. Smith , Cory M. Hitte , Bryan Marshall , Carlos Alexander Fenny
CPC classification number: B64C27/006 , B64C27/12 , B64D27/24 , B64D2027/026 , Y10T29/49117
Abstract: Embodiments refer generally to systems and methods for providing autorotative enhancement for helicopters using an autorotative assist unit coupled to the transmission of the helicopter. Methods of utilizing an autorotative assist unit as well as retrofitting an autorotative assist unit to an existing helicopter are also disclosed. By employing an autorotative assist unit, improved autorotation may be achieved without the need to increase the weight of the rotor.
Abstract translation: 实施例总体上涉及用于使用耦合到直升机的传输的自动辅助单元来提供直升机的自动增强的系统和方法。 还公开了利用自动辅助单元以及将自动辅助单元改装到现有直升机的方法。 通过使用自动辅助单元，可以实现改进的自转，而不需要增加转子的重量。
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公开(公告)号：US11053008B2
公开(公告)日：2021-07-06
申请号：US16161415
申请日：2018-10-16
Applicant: Bell Helicopter Textron Inc.
Inventor： Joseph Scott Drennan , Carlos Alexander Fenny , Michael John Ryan , John Richard Mccullough , Brett Rodney Zimmerman
Abstract: A parasite aircraft for airborne deployment and retrieve includes a wing; a fuselage rotatably mounted to the wing; a dock disposed on top of the fuselage and configured to receive a maneuverable capture device of a carrier aircraft; a pair of tail members extending from the fuselage; and a plurality of landing gear mounted to the wing. A method of preparing a parasite aircraft for flight includes unfolding an end portion of a wing; unfolding an end portion of a tail member of the parasite aircraft; and rotating a fuselage of the parasite aircraft so that the fuselage is perpendicular to the wing. A method of preparing a parasite aircraft for storage includes rotating a fuselage of the parasite aircraft to be parallel with a wing of the parasite aircraft; folding an end portion of the wing; and folding an end portion of a tail member of the parasite aircraft.
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Patent Agency Ranking
公开(公告)号：US10556680B2
公开(公告)日：2020-02-11
申请号：US15593458
申请日：2017-05-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Carlos Alexander Fenny , Rohn Lee Olson
IPC: B64C29/02 , B64D27/24 , B64C39/06 , B64C11/28 , B64C29/00 , B64C3/10 , B64C27/08 , B64C27/12 , B64D31/00 , B64C1/06 , B64C39/02 , B64C27/50 , B64C1/00 , B64D27/02
Abstract: The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.
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公开(公告)号：US20190389568A1
公开(公告)日：2019-12-26
申请号：US16013201
申请日：2018-06-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Carlos Alexander Fenny , Jouyoung Jason Choi
Abstract: An aircraft comprises a fuselage, one or more support structures connected to the fuselage, one or more engines or motors disposed within or attached to the one or more support structures or the fuselage, and a distributed propulsion system. The distributed propulsion system comprising two or more propellers symmetrically distributed in an array along the one or more support structures with respect to a center of gravity of the aircraft and operably connected to the one or more engines or motors, wherein each propeller has a rotation direction within a tilted plane of rotation, and a summation of horizontal force vectors created by the tilted plane of rotation of all the propellers is substantially zero when all the propellers are creating a substantially equal thrust magnitude. Movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the two or more propellers.
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公开(公告)号：US20190270516A1
公开(公告)日：2019-09-05
申请号：US15909246
申请日：2018-03-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric A. Sinusas , Erik John Oltheten , Carlos Alexander Fenny
Abstract: A propulsion system for a rotorcraft includes a first fan assembly including a plurality of first fan blades, a second fan assembly including a plurality of second fan blades and a drive system adapted to provide torque to the first and second fan blades. The first fan blades have a larger rotational inertia than the second fan blades. The second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft.
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公开(公告)号：US20190241251A1
公开(公告)日：2019-08-08
申请号：US15887664
申请日：2018-02-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Brady Garrett Atkins , Robert Paul Reynolds , Carlos Alexander Fenny , Charles Eric Covington
CPC classification number: F16K31/047 , F16K11/20
Abstract: Systems and methods include providing an aircraft with a direct drive dual-concentric valve (D3V) having a body, an outer secondary spool coaxially located within a bore of the body and linearly displaceable relative to the body, an inner primary spool coaxially located within a bore of the secondary spool and linearly displaceable relative to the secondary spool and the body, and multiple motor assemblies coupled to the primary spool that provide selective displacement of the primary spool or the secondary spool. Each motor assembly includes a clutching mechanism that selectively couples a motor of the motor assembly to and from the primary spool.
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公开(公告)号：US20190071173A1
公开(公告)日：2019-03-07
申请号：US16183035
申请日：2018-11-07
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Dewey Parsons , Carlos Alexander Fenny , Erik John Oltheten
IPC: B64C27/82
Abstract: The present invention includes an anti-torque assembly for a helicopter comprising a plurality of fixed blade pitch motors mounted on one or more pivots on the tail boom of the helicopter, wherein the plurality of fixed blade pitch motors on the one or more pivots are adapted to be oriented substantially in-plane with a tail boom of a helicopter during a first mode of operation that comprises a hover mode and wherein the fixed blade pitch motors are adapted to be oriented substantially off-plane from the tail boom of the helicopter during a second mode of helicopter operation that is different from the first mode.
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