公开(公告)号：US10815008B2

公开(公告)日：2020-10-27

申请号：US15662147

申请日：2017-07-27

Applicant: Bell Helicopter Textron Inc.

Inventor： Brent C. Ross ,  Kendall Goodman ,  Steven R. Ivans

IPC: G06F30/15 ,  B64F5/10 ,  B64C29/00 ,  B64F5/00 ,  B64C1/00

Abstract: A method for facilitating the design and manufacturing of a tiltrotor aircraft, including the steps of: determining a compatible mission data set; identifying lift propulsion module components for the compatible mission data set; determining compatible specifications; and generating a design for a lift propulsion module; wherein the lift propulsion module is configured to be connected to at least two different fuselages. There is also a method of designing a tiltrotor aircraft, comprising the step of modularizing a lift propulsion system, wherein the lift propulsion system is configured to be connected to at least two different fuselages. In another aspect, there is a tiltrotor aircraft including a fuselage; and a lift propulsion module, the lift propulsion module including a mounting surface; wherein the lift propulsion module is coupled to the fuselage on the mounting surface. Also included are methods of assembling and systems including a lift propulsion module.

公开(公告)号：US10814971B2

公开(公告)日：2020-10-27

申请号：US15949660

申请日：2018-04-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Dalton T. Hampton ,  Andrew Paul Haldeman ,  Aaron Alexander Acee ,  Matthew John Hill

IPC: B64C27/82 ,  B64C27/06

Abstract: Systems and methods include providing an aircraft with a tail rotor system having a tail rotor housing that forms a cambered airfoil between an upper cambered surface and a lower cambered surface of the tail rotor housing. The cambered airfoil design of the tail rotor housing is capable of providing sufficient lifting force of an aircraft to offload the tail rotor during forward flight, thereby eliminating the need for a traditional vertical stabilizer or fin. The tail rotor blades of the tail rotor system are disposed within an aperture in the tail rotor housing, which minimizes or preferably eliminates exposure of the tail rotor blades to edgewise airflow typically encountered during forward flight, thereby allowing rigid rotor hubs, both in-plane and out-of-plane, to be used in the tail rotor system while also reducing noise output of the tail rotor system.

公开(公告)号：US20200333228A1

公开(公告)日：2020-10-22

申请号：US16912934

申请日：2020-06-26

Applicant: Bell Textron Inc.

Inventor： Xiaoming Li ,  Bogdan R. Krasnowski ,  Robert A. Figueroa ,  Robert Wardlaw

IPC: G01N3/62 ,  G01N3/02 ,  G06F30/15

Abstract: A notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer; isolating the notch; and selectively etching the notch to provide an etched surface of the notch; wherein at least a portion of the re-melt material layer has been removed from the notch. In one aspect, there is provided a notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer, the specimen includes steel or an alloy thereof; isolating the notch; and selectively etching the notch with a first etching solution and a second etching solution to provide an etched surface on the notch; wherein at least a portion of the re-melt material layer has been removed from the notch.

公开(公告)号：US20200331216A1

公开(公告)日：2020-10-22

申请号：US16922831

申请日：2020-07-07

Applicant: Bell Textron Inc.

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

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

Abstract: In an aspect, there is a method of determining allowable defects for a composite component comprising identifying at least one wrinkle characteristic of a composite component wrinkle defect; making a first plurality of specimens each having a predetermined wrinkle defect representative of the composite component wrinkle defect; measuring each of the predetermined wrinkle defects in the first plurality of specimens for at least one performance metric to generate performance data; and generating an allowable wrinkle defect profile based on the performance data from the first plurality of specimens. In other aspects, there are methods of making a specimen with a predetermined wrinkle defect.

公开(公告)号：US10809281B2

公开(公告)日：2020-10-20

申请号：US16118283

申请日：2018-08-30

Applicant: Bell Helicopter Textron Inc.

Inventor： David W. Fuessel ,  Russel Mark Berkley

IPC: G01R1/04 ,  G01R31/00

Abstract: A support bracket for grounding a current sensor is disclosed. The support bracket comprises a first surface and a second surface. The first surface is electrically coupled to a current sensor to provide a current path to ground the current sensor. The second surface is physically coupled to the current sensor in order to support the current sensor.

公开(公告)号：US20200324883A1

公开(公告)日：2020-10-15

申请号：US16383161

申请日：2019-04-12

Applicant: Bell Helicopter Textron Inc.

Inventor： Michael Reaugh Smith ,  Frank B. Stamps ,  David E. Heverly, II

IPC: B64C27/00 ,  F16F7/10 ,  F16F13/26 ,  F16F13/22 ,  F16F15/027

Abstract: In some examples, an oscillatory pumping system comprises: one or more active piston, a fluid, and two motors. The one or more active piston is disposed in a channel fluidically coupling two fluid chambers. The passive piston has a frequency response operable to counteract a vibratory displacement. The fluid is disposed in the channel and the two fluid chambers. The two motors couple to the one or more active piston. The two motors are operable to selectively change the frequency response of the passive piston based on oscillating the one or more active piston.

公开(公告)号：US20200313209A1

公开(公告)日：2020-10-01

申请号：US16372341

申请日：2019-04-01

Applicant: Bell Helicopter Textron Inc.

Inventor： Joseph Dean Rainville ,  William Ben Johns

IPC: H01M8/04082 ,  F17C1/14 ,  H01M8/04089 ,  B64C39/02

Abstract: A tank configured to store a pressurized gas therein and carry a structural load between components of a vehicle.

公开(公告)号：US20200290749A1

公开(公告)日：2020-09-17

申请号：US16863798

申请日：2020-04-30

Applicant: Bell Textron Inc.

Inventor： Levi Bilbrey ,  Andrew Zahasky ,  Joshua Edler ,  Joseph Scott Drennan ,  Doug Fidler ,  Rares Halmagean

IPC: B64D43/00 ,  A42B3/30 ,  G06F3/01 ,  G01C23/00 ,  G08G5/00 ,  B64C13/18 ,  B64C13/22 ,  A42B3/04 ,  A42B3/22 ,  G06T19/00 ,  G02B27/01 ,  B64D11/06 ,  B64C13/04 ,  B64C1/06 ,  B64C1/18 ,  B64C1/40

Abstract: The present invention achieves technical advantages as a pilot and passenger seating. An aircraft employs a pilot seat, comprising a contoured structure having ergonomically formed and padded surfaces, with left and right arm supports that include an articulated control knob, movable in three rectangular axes and rotatable about a vertical axis to provide one or more aircraft steering functions for an aircraft, and a touch-sensitive control surface for controlling one or more power system components. A passenger seat, having a contoured structure, having ergonomically formed and padded surfaces, a headrest, a seat, a left support member, and a right support member are adapted to cradle a portion of a passenger's body to support the passenger during travel.

公开(公告)号：US20200290725A1

公开(公告)日：2020-09-17

申请号：US16732198

申请日：2019-12-31

Applicant: Bell Textron Inc.

Inventor： Chad Lewis Jarrett ,  Frank Bradley Stamps ,  Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Matthew Edward Louis ,  William Anthony Amante ,  Robert Vaughn ,  Joseph Richard Carpenter, JR.

IPC: B64C11/00 ,  B64C11/02 ,  B64D27/26

Abstract: An aircraft has a ducted thruster. The ducted thruster includes a duct having an inner wall, a stator hub disposed within the duct, a first stator extending along a first longitudinal axis between the inner wall and the stator hub, and a second stator. The second stator extends along a second longitudinal axis between the inner wall and the stator hub. The second longitudinal axis is either (1) substantially perpendicular to the first longitudinal axis or (2) substantially parallel to the first longitudinal axis and offset from the first longitudinal axis.

公开(公告)号：US10773798B2

公开(公告)日：2020-09-15

申请号：US15720626

申请日：2017-09-29

Applicant: Bell Helicopter Textron Inc.

Inventor： Andrew Paul Haldeman ,  Dalton T. Hampton ,  Bryan Marshall ,  Frank Bradley Stamps

IPC: B64C27/39 ,  B64C27/00 ,  B64C27/605 ,  B64C27/72 ,  B64C27/48 ,  B64C27/06

Abstract: An aircraft rotor assembly has a yoke and a plurality of rotor blade assemblies coupled thereto. Each of the rotor blade assemblies include a rotor blade, a bearing, and a blade grip coupling the rotor blade to the bearing. Each of the rotor blades is rotatable about a lead-lag axis, flap axis, and a pitch change axis, wherein all the axes intersect within the bearing. Adjacent pairs of rotor blade assemblies are coupled together via a damper assembly that is coupled to the pitch change axis of each of the rotor blade assemblies.