公开(公告)号：US10752349B2

公开(公告)日：2020-08-25

申请号：US16173064

申请日：2018-10-29

Applicant: Bell Helicopter Textron Inc.

Inventor： Andrew Paul Haldeman ,  Zachary Edwin Dailey ,  Aaron Alexander Acee ,  Dalton T. Hampton

IPC: B64C27/605 ,  B64C27/06 ,  B64C27/00 ,  B64C13/04 ,  B64C13/40 ,  B64C27/72

Abstract: An exemplary rotorcraft includes a power train with an engine coupled to a gearbox, a main rotor blade having a mast coupled to the power train, a control input linkage in communication between a pilot input device and the main rotor blade configured to communicate a control input force from the pilot input device to the main rotor blade, and a counterweight system in connection with the control input linkage and the power train to apply a centrifugal force to the control input linkage.

公开(公告)号：US10752346B2

公开(公告)日：2020-08-25

申请号：US15787093

申请日：2017-10-18

Applicant: Bell Helicopter Textron Inc.

Inventor： Andrew Paul Haldeman ,  Dalton T. Hampton ,  Frank Bradley Stamps ,  John Lloyd ,  Gilberto Morales

IPC: B64C27/51 ,  B64C27/00

Abstract: A rotor assembly has a composite driveshaft extending between a transmission and a yoke for providing torque from the transmission to the yoke to cause rotation of the yoke and a plurality of rotor blade assemblies attached thereto. The rotor hub also has a composite static mast coupled to the yoke and a frame. The static mast being configured to carry the lift and thrust forces from the yoke to the frame.

公开(公告)号：US10752335B2

公开(公告)日：2020-08-25

申请号：US15886655

申请日：2018-02-01

Applicant: Bell Helicopter Textron Inc.

Inventor： Michael Reaugh Smith

IPC: B64C1/32 ,  B64C1/14

Abstract: An emergency escape window for a rotorcraft includes a window frame, a window pane set inside the window frame, a plurality of pins connecting the window frame to the fuselage of the rotorcraft, and a release mechanism having at least one actuator connected to a respective pin and constructed to retract the pin from the window frame. The escape window can then be pivoted away and/or completely detached from the fuselage in the event of an emergency to allow occupants to safely exit the rotorcraft. The disclosure also relate to a method of operating an emergency escape window for a rotorcraft and to a rotorcraft having an emergency escape window.

公开(公告)号：US10752332B2

公开(公告)日：2020-08-25

申请号：US15665627

申请日：2017-08-01

Applicant: Bell Helicopter Textron Inc.

Inventor： Jon Damon Bennett ,  Joshua Allan Edler

IPC: B64D29/00 ,  B64D29/02 ,  B64D29/04 ,  B64D29/08 ,  B64C7/00 ,  B64C7/02 ,  B64C1/38 ,  B64C1/14 ,  B64D29/06 ,  B64C27/04 ,  B64C1/06

Abstract: One example of a fairing for a rotorcraft includes an outer mold line portion (OML portion) and a bearing portion extending from the OML portion. The OML portion provides at least a portion of an outer mold line of the rotorcraft. Both the OML portion and the bearing portion shield a portion of a structural member. The bearing portion can protect the portion of the structural member from damage resulting from foot traffic associated with accessing an area nearby the structural member.

公开(公告)号：US10745120B2

公开(公告)日：2020-08-18

申请号：US16547003

申请日：2019-08-21

Applicant: Bell Helicopter Textron Inc.

Inventor： Gary Miller ,  Frank B. Stamps

IPC: B64C27/33 ,  B64C27/605 ,  B64C29/00

Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, an adapter ring, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the swashplate and the adapter ring, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the swashplate and the adapter ring, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

公开(公告)号：US10744727B2

公开(公告)日：2020-08-18

申请号：US15464822

申请日：2017-03-21

Applicant: Bell Helicopter Textron Inc.

Inventor： Michael Burnett ,  Wei-Yueh Lee ,  Michael Dearman

IPC: B29C70/54 ,  B29C70/56 ,  G01M5/00 ,  G01N3/08 ,  B29C70/32 ,  G01N3/02 ,  G01N3/04 ,  G06F30/23 ,  B29C70/30 ,  B29K105/00

Abstract: In a first aspect, there is a method of making a specimen with a predetermined wrinkle defect, the steps including orienting a composite material around a layup tool at a wrap angle to form a closed loop; and generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of determining allowable defects for a composite component.

公开(公告)号：US10730624B2

公开(公告)日：2020-08-04

申请号：US15593607

申请日：2017-05-12

Applicant: Bell Helicopter Textron Inc.

Inventor： Carlos Alexander Fenny ,  Rohn Lee Olson ,  Andrew James Zahasky

IPC: B64C39/06 ,  B64C27/08 ,  B64C11/28 ,  B64C27/50 ,  B64C29/00 ,  B64C3/10 ,  B64C27/12 ,  B64D27/24 ,  B64D31/00 ,  B64C29/02 ,  B64C1/06 ,  B64C39/02 ,  B64C1/00 ,  B64D27/02

Abstract: An aircraft capable of vertical takeoff and landing and stationary flight includes a distributed airframe coupled to a modular fuselage. The modular fuselage has a longitudinal axis substantially parallel to a rotational axis of three or more propellers. The modular fuselage includes a rear module substantially disposed within a perimeter of the distributed airframe, a front module removably connected to the rear module and substantially aligned with the longitudinal axis. One or more engines or motors are disposed within or attached to the distributed airframe or fuselage. The three or more propellers are proximate to a leading edge of the distributed airframe, distributed along the distributed airframe, and operably connected to the one or more engines or motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight.

公开(公告)号：US20200239152A1

公开(公告)日：2020-07-30

申请号：US16262059

申请日：2019-01-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Joseph Dean Rainville

IPC: B64D33/08 ,  H01M8/04007 ,  B64C27/28 ,  B64C27/20 ,  B64C27/26

Abstract: A thermal management system includes a plurality of passages through a leading edge of a component of an aircraft. The thermal management system is configured to circulate coolant from a heat source through the plurality of passages in order to maximize heat transfer from the coolant to the airflow passing over the leading edge.

公开(公告)号：US20200239149A1

公开(公告)日：2020-07-30

申请号：US16257750

申请日：2019-01-25

Applicant: Bell Helicopter Textron Inc.

Inventor： Joseph Dean Rainville

IPC: B64D27/24 ,  H01M8/04537 ,  H01M8/04858 ,  H01M8/04664 ,  B64C27/04 ,  B64D41/00

Abstract: A stack fuel cell array featuring paired fuel-cell systems combined to generate 540 VDC for a rotorcraft. Power from the hydrogen-based fuel cells is provided to the rotorcraft. A rated electrical load of the rotorcraft helps determine how many paired fuel-cell systems are needed during any fuel-cell systems failures. Each of the paired fuel-cell systems is coupled to an electrical load of the rotorcraft. The system detects any fuel cell failures and removes other working fuel cells as needed to balance the electrical system.

公开(公告)号：US10723472B2

公开(公告)日：2020-07-28

申请号：US15627393

申请日：2017-06-19

Applicant: Bell Helicopter Textron Inc.

Inventor： Brent Scannell ,  Thomas Mast ,  Sarah R. Villanueva

IPC: B64D29/06 ,  B64D41/00 ,  B64F5/40 ,  B64C7/02 ,  E05C17/12 ,  B64C27/04 ,  B64C27/06

Abstract: One example of a cowling assembly for a rotorcraft includes a stationary fairing affixed to an airframe of the rotorcraft, an articulated fairing hinged on the stationary fairing for articulation relative to the stationary fairing between a closed position, a first partially open maintenance position and a second fully open maintenance position. The articulated fairing is supported in the first maintenance position by a for example gas-charged strut and is releasably locked in the second maintenance position against the stationary fairing by a locking mechanism. The locking mechanism includes a latch blade disposed on the stationary fairing and a latch arranged on the articulated fairing, wherein a latch pin engages with a hole or recess in the latch blade when the latch blade extends through a slot in the articulated fairing.