公开(公告)号：US20180334260A1

公开(公告)日：2018-11-22

申请号：US15597886

申请日：2017-05-17

Applicant: Bell Helicopter Textron Inc.

Inventor： Brent Scannell ,  Jean Pierre Paradis ,  Thomas Mast

IPC: B64D29/08 ,  B64D29/06 ,  B64D41/00

CPC classification number: B64D29/08 ,  B64C1/1446 ,  B64D29/06 ,  B64D41/00

Abstract: An example cowling for a rotorcraft is hinged on a stationary part of an airframe of the rotorcraft and is pivotable from a closed position into a first partially open position and thereafter into a second fully open position. The example cowling includes a rod articulated on the cowling and having a free end configured to releasably engage with the airframe to hold the cowling in the first position; and at least one handhold attached to an exterior surface of the cowling, wherein the at least one handhold has a substantially straight section that in the fully open position rests on a top portion of the airframe so as to more evenly distribute the weight of the cowling on the airframe.

公开(公告)号：US20180329430A1

公开(公告)日：2018-11-15

申请号：US15594393

申请日：2017-05-12

Applicant: Bell Helicopter Textron Inc.

Inventor： Christopher Mike Bothwell ,  Jillian Samantha Alfred ,  Sung Kyun Kim ,  Marko Vuga ,  Matthew Hendricks ,  Mark Wasikowski ,  Thomas Parham ,  Michael Reaugh Smith

IPC: G05D1/08 ,  B64C27/82 ,  B64C27/04 ,  B64C27/57

CPC classification number: G05D1/0858 ,  B64C27/001 ,  B64C27/04 ,  B64C27/57 ,  B64C27/82 ,  G05D1/0825

Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes receiving a measured yaw rate from a yaw rate sensor or a measured lateral acceleration from a lateral acceleration sensor of the rotorcraft, filtering the measured yaw rate or the measured lateral acceleration using a filter to form a filtered measured yaw rate or a filtered measured lateral acceleration, and regulating a yaw rate or a lateral acceleration of the rotorcraft based on the measured yaw rate or the measured lateral acceleration. The filter includes a bandpass characteristic or a notch characteristic, and the filtering is configured to reduce lateral vibrations caused by airflow in a tail section of the rotorcraft

公开(公告)号：US20180327108A1

公开(公告)日：2018-11-15

申请号：US15593956

申请日：2017-05-12

Applicant: Bell Helicopter Textron Inc.

Inventor： Angel David Rosado

IPC: B64D41/00 ,  B64C1/12

CPC classification number: B64D41/00 ,  B64C1/12 ,  B64C2001/0072 ,  B64D33/04 ,  B64D2041/002 ,  F02C7/20 ,  F05D2220/50 ,  F05D2260/30

Abstract: A mounting assembly for mounting a portion of an engine exhaust duct in an opening of an airframe panel aircraft, including a peripheral flange disposed on the portion of the exhaust duct, and at least one mounting member having an outer peripheral flange portion for connection to the airframe panel and having an inner peripheral flange portion with at least one compliant isolator member to receive the peripheral flange of the exhaust duct in a manner that suspends the exhaust duct in the opening away from the airframe panel and accommodates thermal expansion and contraction of the exhaust duct relative to the airframe panel. Embodiments include a method of mounting an engine exhaust duct in an opening of an outer airframe panel of an aircraft.

公开(公告)号：US20180327086A1

公开(公告)日：2018-11-15

申请号：US15594588

申请日：2017-05-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Jaret F. Burgess ,  Frank Bradley Stamps

IPC: B64C27/32 ,  B64C27/605 ,  B64C29/00 ,  B64C27/06 ,  F16C19/06

CPC classification number: B64C27/32 ,  B64C27/06 ,  B64C27/605 ,  B64C29/0033 ,  F16C19/06 ,  F16C2326/43

Abstract: An aircraft rotor assembly has a yoke with at least two arms extending therefrom. The yoke is attached to a mast through a constant-velocity joint, thereby permitting axial tilt of the yoke relative to the mast. Each arm of the yoke includes an axisymmetric elastomeric bearing with a spherical central member and two opposite partially-spherical members attached to the central member. Each axisymmetric bearing cooperates with a cup and a bracket. Each cup is attached to one of the yoke arms and each bracket is attached to a blade cuff.

公开(公告)号：US20180327078A1

公开(公告)日：2018-11-15

申请号：US15593241

申请日：2017-05-11

Applicant: Bell Helicopter Textron Inc.

Inventor： Brendan P. Lanigan ,  Joshua R. O'Neil

IPC: B64C5/02 ,  B64C27/06 ,  B64C27/82

CPC classification number: B64C5/02 ,  B64C27/06 ,  B64C27/82 ,  B64C2003/142 ,  B64C2027/8272 ,  B64C2027/8281

Abstract: In one embodiment, a horizontal stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a horizontal orientation. The airfoil structure comprises a leading edge, a trailing edge, a top surface, and a bottom surface. Moreover, the airfoil structure is cambered, wherein a camber of the airfoil structure forms a concave slope on the top surface and a convex slope on the bottom surface.

公开(公告)号：US20180297685A1

公开(公告)日：2018-10-18

申请号：US15488217

申请日：2017-04-14

Applicant: Bell Helicopter Textron Inc.

Inventor： Carl May ,  James D. Hethcock, JR. ,  John R. McCullough

IPC: B64C1/12 ,  B32B3/12 ,  B32B5/18 ,  B32B5/24

Abstract: An aircraft includes a composite structure, comprising an outer skin formed from a composite material and having a first thickness, an inner skin formed from a composite material and having a second thickness, the second thickness being greater than the first thickness, and a core structure positioned between the inner and outer skins to increase bending stiffness of the composite structure. During use a structural load carried by the inner skin exceeds a structural load carried by the outer skin.

公开(公告)号：US20180290742A1

公开(公告)日：2018-10-11

申请号：US15972448

申请日：2018-05-07

Applicant: Bell Helicopter Textron Inc.

Inventor： Paul K. Oldroyd ,  John Richard McCullough

IPC: B64C29/00 ,  B64C1/32 ,  B64C27/08 ,  B64C39/02 ,  B64D25/12 ,  B64D27/24

CPC classification number: B64C29/0033 ,  B64C1/32 ,  B64C27/08 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/108 ,  B64D25/12 ,  B64D27/24 ,  B64D27/26

Abstract: A propulsion assembly for an aircraft includes a housing having a gimbal coupled thereto that is operable to tilt about first and second axes. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades. The rotor assembly is rotatable with the output drive of the electric motor in a rotational plane to generate thrust having a thrust vector with a direction. The first axis of the gimbal is orthogonal to the second axis of the gimbal. Actuation of the gimbal tilts the propulsion system relative to the housing to change the rotational plane of the rotor assembly relative to the housing, thereby controlling the direction of the thrust vector within a thrust vector cone.

公开(公告)号：US10094751B2

公开(公告)日：2018-10-09

申请号：US15079946

申请日：2016-03-24

Applicant: Bell Helicopter Textron Inc.

Inventor： Xiaoming Li ,  Bogdan R. Krasnowski

IPC: G01N3/08 ,  G01N3/32

Abstract: A method of determining damage tolerance allowables in a specimen, the method includes applying a cyclic load to a specimen until a first crack emanates from a notch in the specimen, the cyclic load having a maximum load and a minimum load. The method also includes applying a subsequent cyclic load to the specimen until the first crack grows to form a second crack emanating from the first crack, the subsequent cyclic load having the same maximum load but a greater minimum load.

公开(公告)号：US10093415B1

公开(公告)日：2018-10-09

申请号：US15464084

申请日：2017-03-20

Applicant: Bell Helicopter Textron Inc.

Inventor： Robert Lee Fortenbaugh ,  Jillian Samantha Alfred ,  Luke Dafydd Gillett

IPC: B64C27/57 ,  G05D1/08 ,  G05D1/02 ,  B64C27/605 ,  B64C27/82 ,  B64C13/50

Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes operating the rotorcraft in a heading control mode that includes activating a yaw channel path of a heading controller and deactivating a roll channel path of the heading controller when a speed of the rotorcraft is less than a first speed threshold or a heading error is less than a heading error threshold, and activating the roll channel path of the heading controller and deactivating the yaw channel path of the heading controller when the speed of the rotorcraft is greater than a second speed threshold and the heading error is not less than the heading error threshold.

公开(公告)号：US20180265186A1

公开(公告)日：2018-09-20

申请号：US15459781

申请日：2017-03-15

Applicant: Bell Helicopter Textron Inc.

Inventor： Christopher Edward Foskey ,  Frank Bradley Stamps ,  Michael Reaugh Smith

IPC: B64C27/00 ,  B64C27/10 ,  B64C27/82 ,  B64C27/22

CPC classification number: B64C27/001 ,  B64C27/10 ,  B64C27/22 ,  B64C27/82 ,  B64C2027/002 ,  B64C2027/8236 ,  B64C2027/8281

Abstract: A vibration isolation system for an advancing blade concept rotorcraft having a pylon assembly and an airframe. The vibration isolation system includes one or more pylon links each having first and second ends with the first end coupled to the pylon assembly and the second end coupled to the airframe. Each pylon link includes a vibration isolator, such as a Liquid Inertia Vibration Eliminator unit, that is interposed between the pylon assembly and the airframe. The vibration isolator system is operable to reduce or eliminate transmission of the pylon assembly vibration to the airframe.