公开(公告)号：US20190291355A1

公开(公告)日：2019-09-26

申请号：US15935789

申请日：2018-03-26

Applicant: Bell Helicopter Textron Inc.

Inventor： Olivier Blanc

IPC: B29C65/48 ,  B29C65/00 ,  B29C70/34 ,  C09J5/04 ,  C09J7/38

Abstract: A method is provided in one example embodiment and may include assembling a first component and a second component together using, at least in part, a first adhesive film on the first component and a second adhesive film on the second component, wherein the first component and the second component are fully cured and the first adhesive film and the second adhesive film are at least partially uncured; and curing the first adhesive film and the second adhesive film to form a bonded structure.

公开(公告)号：US10421531B2

公开(公告)日：2019-09-24

申请号：US13685758

申请日：2012-11-27

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Ashok K. Agnihotri ,  Thomas W. Brooks

IPC: B64C13/00 ,  B64C27/56 ,  B64C13/04 ,  G05B19/042 ,  G05D1/08

Abstract: A system and method to modify a qualified actuator command with an unqualified actuator command modifier. The method includes creating a modified actuator command as the difference between the qualified actuator command and the unqualified actuator command and thereafter limiting the modified actuator command with an authority limiter. The system includes a qualified computer having an unqualified control law interfaced with an unqualified computer having a qualified control law.

公开(公告)号：US20190277392A1

公开(公告)日：2019-09-12

申请号：US15915699

申请日：2018-03-08

Applicant: Bell Helicopter Textron Inc.

Inventor： Colton Gilliland

IPC: F16H57/022 ,  B64D35/00

Abstract: A cam-locking system for use with a retractable driveshaft that includes a housing, a cam carrier located at least partially the housing, and a cam rotatably coupled to the cam carrier. Translation of the cam carrier along a central axis allows the cam to rotate into cooperative engagement with a catch recess on an interior surface of the housing, preventing the cam carrier from translating backwards, and thereby maintaining the retractable driveshaft in an engaged position. Further advancement of the cam carrier allows that cam to rotate into and unlocking gap in the interior surface of the housing, which enables the cam carrier to translate backwards along the central axis below the locked position, thereby disengaging the retractable driveshaft.

公开(公告)号：US20190276145A1

公开(公告)日：2019-09-12

申请号：US16421371

申请日：2019-05-23

Applicant: Bell Helicopter Textron Inc.

Inventor： John Richard McCullough ,  Paul K. Oldroyd

IPC: B64C27/605 ,  B64C29/00 ,  B64C27/54

Abstract: A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed. The rotor assembly includes a mast rotatable at the constant speed about a mast axis. A rotor hub is coupled to and rotatable with the mast. The rotor hub includes a plurality of spindle grips extending generally radially outwardly. Each of the spindle grips is coupled to one of a plurality of rotor blades and is operable to rotate therewith about a pitch change axis. A collective pitch control mechanism is coupled to and rotatable with the rotor hub. The collective pitch control mechanism is operably associated with each spindle grip such that actuation of the collective pitch control mechanism rotates each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.

公开(公告)号：US10408544B2

公开(公告)日：2019-09-10

申请号：US14282370

申请日：2014-05-20

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Doug Mueller ,  Brian S. Modrzejewski ,  Brad Ekstrom ,  Scott Gardner ,  David Elliott

IPC: F28D15/00 ,  F28D15/02 ,  B64C27/04 ,  B64D33/10

Abstract: A system and method to transfer heat energy through a composite structure. The system includes a heat pipe extending through a thickness of the composite material. The method includes extending a heat pipe through the composite material from a first surface exposed to the heat energy to a second surface exposed to airflow.

公开(公告)号：US20190263531A1

公开(公告)日：2019-08-29

申请号：US15906108

申请日：2018-02-27

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett KOOIMAN ,  George Ryan Decker ,  Michael Rinehart ,  Jeffrey Matthew Williams

IPC: B64D33/02 ,  F02C7/052 ,  B01D46/00

Abstract: An inlet barrier filter system for a tiltrotor aircraft comprising a filter duct extending from a filter to a filter outlet, a ram air duct extending from a ram air inlet to an engine where the filter duct connects to the ram air duct at the filter outlet, and a closure member movable between a first position blocking the ram air duct and a second position blocking the filter outlet. In use, the inlet barrier filter system provides for two mutually exclusive air flow paths, one for introducing ram air to the engine while closing off the filter and another air flow path for introducing filtered air to the engine while closing off the ram air duct.

公开(公告)号：US20190263504A1

公开(公告)日：2019-08-29

申请号：US15904763

申请日：2018-02-26

Applicant: Bell Helicopter Textron Inc.

Inventor： Yann Lavallee ,  Pasquale Spina

IPC: B64C13/06 ,  B64C13/04 ,  B64C13/14 ,  G05G9/047 ,  B64C27/56

Abstract: A cyclic stick for transmitting control commands to blades of a rotorcraft via at least one transmission member, including a grip configured for engagement with a pilot's hand, a control arm and at least one locking mechanism. The control arm has a bottom end configured for connection to the transmission member(s) and for rotational connection to a base support structure, and a top end pivotally connected to the grip. The control arm includes first and second arm portions pivotally connected to each other, the first arm portion defining the bottom end, the second arm portion defining the top end. The locking mechanism(s) selectively prevent a relative pivoting motion between the first and second arm portions and a relative pivoting motion between the second arm portion and the grip. A method of adjusting a position of a grip of a cyclic stick in a rotorcraft cabin is also discussed.

公开(公告)号：US20190248482A1

公开(公告)日：2019-08-15

申请号：US15892558

申请日：2018-02-09

Applicant: Bell Helicopter Textron Inc.

Inventor： Luke Dafydd Gillett

IPC: B64C27/57 ,  G05D1/08

Abstract: A rotorcraft including a main rotor, flight controls connected to the main rotor the main rotor, a plurality of engines connected to the main rotor and operable to drive the main rotor, a main rotor revolutions per minute (RPM) sensor, and a monitoring system operable to determine an engine failure of the plurality of engines. The monitoring system is further operable to engage an automated autorotation entry assist process in response to at least determining the engine failure and according to the measured main rotor RPM, where the automated autorotation entry assist process comprises the monitoring system generating one or more rotor RPM related commands according to at least a target main rotor RPM and the measured main rotor RPM, where the automated autorotation entry assist process further comprises controlling the one or more flight controls according to the one or more rotor RPM related commands.

公开(公告)号：US20190248469A1

公开(公告)日：2019-08-15

申请号：US15895192

申请日：2018-02-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Levi Charles HEFNER ,  Danielle Lynn MOORE ,  Dakota Charles EASLEY

IPC: B64C9/02 ,  B64C5/02 ,  B64C39/02 ,  B64C29/02

CPC classification number: B64C9/02 ,  B64C5/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/102 ,  B64C2201/108

Abstract: An example of an aerial vehicle includes a rudder removably connected to the aerial vehicle by a twist lock mechanism. The twist lock mechanism is biased in a locked position by an elastic member.

公开(公告)号：US10378978B2

公开(公告)日：2019-08-13

申请号：US15807958

申请日：2017-11-09

Applicant: Bell Helicopter Textron Inc.

Inventor： Ryan T. Ehinger ,  David R. Bockmiller

IPC: G01L3/02 ,  B64C27/57 ,  B64C27/32 ,  G01L3/10 ,  B64F5/60 ,  B64D35/00 ,  B64C29/00

Abstract: A method for calculating torque through a rotor mast of a propulsion system of a tiltrotor aircraft includes receiving the torque being applied through a quill shaft of the rotorcraft. The quill shaft is located between a fixed gearbox and a spindle gearbox, and the spindle gearbox is rotatable about a conversion access. The torque through the rotor mast is determined by using the torque through the quill shaft and the efficiency loss value between the quill shaft and the rotor mast.