公开(公告)号：US20190375506A1

公开(公告)日：2019-12-12

申请号：US16004159

申请日：2018-06-08

Applicant: Bell Helicopter Textron Inc.

Inventor： Jeremy Robert Chavez ,  Brent Chadwick Ross

IPC: B64D7/06

Abstract: Embodiments are directed to an aircraft, such as a tiltrotor, having an internal payload storage area. A rotatable deployment system is mounted within the payload storage area. The rotatable deployment system comprises a frame that is configured to rotate between a stowed position and a deployment position. Two extendible arms are attached to the frame, wherein each extendible arm is configured to move in opposite directions between a retracted position and a plurality of extended positions. Each extendible arm has a fixed end and a moving end. A payload mounting point on each moving end. The payload mounting point allows a payload to pan and tilt in azimuth and elevation.

公开(公告)号：US20190351995A1

公开(公告)日：2019-11-21

申请号：US15981525

申请日：2018-05-16

Applicant: Bell Helicopter Textron Inc.

Inventor： Jillian Samantha Alfred ,  Christopher M. Bothwell

IPC: B64C13/18 ,  B64D31/06 ,  B64C13/04

Abstract: In an embodiment, a rotorcraft includes: a rotor system; a sensor; a flight control device; and a flight control computer (FCC) coupled to the rotor system, the sensor, and the flight control device, the FCC configured to: determine a rotation speed of the rotor system; select a first aeroservoelasticity filter configuration from a plurality of aeroservoelasticity filter configurations according to the rotation speed of the rotor system, the aeroservoelasticity filter configurations being predetermined configurations corresponding to different rotation speeds of the rotor system; receive a signal from the sensor; filter the signal according to the first aeroservoelasticity filter configuration; and adjust the flight control device according to the filtered signal.

公开(公告)号：US10479495B2

公开(公告)日：2019-11-19

申请号：US15483652

申请日：2017-04-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Kirk L. Groninga ,  Daniel B. Robertson ,  Matthew E. Louis

IPC: B64C27/82 ,  B64C27/06 ,  F04D17/04 ,  F04D25/16 ,  F04D27/00 ,  F04D29/42

Abstract: In one aspect, there is provided an aircraft, including a fuselage having a longitudinal axis extending from a front portion through an aft portion; first and second tail members extending from the aft portion; a first cross-flow fan system rotatably mounted to the first tail member; and a second cross-flow fan system rotatably mounted to the second tail member. The first and second cross-flow fan systems are configured to provide a forward thrust vector and an anti-torque vector on the aircraft. The first and second cross-flow fan systems can have a rotational axis oriented generally vertically. In another aspect, there is an aircraft including a fuselage having a front portion and a tail portion; and a cross-flow fan system supported by the tail portion. Embodiments include a cross-flow fan system retrofittable onto an aircraft and methods for retrofitting an aircraft with a cross-flow fan system.

公开(公告)号：US10472082B2

公开(公告)日：2019-11-12

申请号：US15463879

申请日：2017-03-20

Applicant: Bell Helicopter Textron Inc.

Inventor： Joseph Daniel Leachman

IPC: F16L55/168 ,  B64D37/00 ,  B64C27/64 ,  F16L55/07 ,  F16L23/16 ,  B64C1/14 ,  F02M25/08 ,  B64C27/605 ,  B64C27/82 ,  F02M37/00

Abstract: An embodiment fluid recovery structure includes a body having an interior cavity, ports integrally joined to first walls of the body and having port walls that extend away from the body, with each of the ports having a port opening that is contiguous with the interior cavity, and a drain structure integrally joined to a second wall of the body and having a drain hole that extends from the interior cavity through the drain structure.

公开(公告)号：US20190337629A1

公开(公告)日：2019-11-07

申请号：US15967831

申请日：2018-05-01

Applicant: Bell Helicopter Textron Inc.

Inventor： Colton James GILLILAND ,  Mark Alan PRZYBYLA ,  Eric Stephen OLSON

IPC: B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  B64C29/00

Abstract: An exemplary tiltrotor aircraft with a hybrid drive system includes a first propulsion system having a first engine and a first supplemental driver operably coupled to a first proprotor that is operable between a helicopter mode and an airplane mode and a second propulsion system having a second engine and a second supplemental driver operably coupled to a second proprotor that is operable between a helicopter mode and an airplane mode.

公开(公告)号：US10464689B2

公开(公告)日：2019-11-05

申请号：US15677885

申请日：2017-08-15

Applicant: Bell Helicopter Textron Inc.

Inventor： Rodney Keith Hale

IPC: B64D45/00 ,  G01N29/46 ,  G07C5/00 ,  G01N29/04 ,  G01N29/14 ,  B64F5/60 ,  G07C5/08 ,  B64C27/12

Abstract: A method, system, and device for diagnosing an anomaly of a monitored component in a drive train, the method including: obtaining original data based on samples of a tachometer signal; processing the original data to obtain rotational information; processing the original data to produce a sine spectrum; determining complex magnitudes of the sine spectrum; removing dominate torsional mode residuals from the complex magnitudes of the sine spectrum to produce a frequency spectrum; and determining a condition indicator from the frequency spectrum.

公开(公告)号：US20190329867A1

公开(公告)日：2019-10-31

申请号：US15963516

申请日：2018-04-26

Applicant: Bell Helicopter Textron Inc.

Inventor： Kyle Thomas CRAVENER ,  Glenn SHIMEK

IPC: B64C11/28 ,  B64C29/00 ,  B64C3/56 ,  B64C11/30 ,  B64C11/06 ,  F16C17/02

Abstract: A folding rotor blade assembly for an aircraft a yoke, an inboard beam coupled to the yoke, an inboard centrifugal force bearing coupled to the inboard beam, a grip coupled to the inboard beam, an outboard bearing housing coupled to the grip, and a rotor blade pivotally coupled to the grip by a blade fold bolt that is positioned outboard of the outboard bearing housing.

公开(公告)号：US10457417B2

公开(公告)日：2019-10-29

申请号：US16171672

申请日：2018-10-26

Applicant: Bell Helicopter Textron Inc.

Inventor： Erik John Oltheten ,  Thomas Wayne Brooks

IPC: G08B23/00 ,  B64D45/08 ,  B64D43/02 ,  B64D45/00

Abstract: Embodiments are directed to flight instrument warnings that are configured to automatically adjust a low airspeed warning band on an airspeed indicator based on available torque margin and radar altimeter height. Warnings may be presented on a primary flight display or on flight instruments when a low airspeed band is entered.

公开(公告)号：US10457388B2

公开(公告)日：2019-10-29

申请号：US15398919

申请日：2017-01-05

Applicant: Bell Helicopter Textron, Inc.

Inventor： Gary Miller ,  Frank B. Stamps

IPC: B64C27/35 ,  B64C27/48 ,  B64C27/33 ,  B64C27/54 ,  B64C27/51

Abstract: An aircraft rotor assembly has a central yoke and a plurality of rotor blades coupled to the yoke for rotation with the yoke about an axis, each blade having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the yoke, each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Lead and lag motion of each blade is opposed by a biasing force that biases the associated blade toward the neutral position, and the biasing force is selected to achieve a first in-plane frequency of greater than 1/rev for each blade.

公开(公告)号：US20190323596A1

公开(公告)日：2019-10-24

申请号：US15961370

申请日：2018-04-24

Applicant: Bell Helicopter Textron Inc.

Inventor： Eric Stephen OLSON ,  David BOCKMILLER

IPC: F16H57/04

Abstract: An exemplary passive oil system includes a reservoir housing configured in operation to rotate around a rotational axis, the reservoir housing defining a reservoir between a top wall, a bottom wall, innermost side, and an outer sidewall; and an outlet positioned adjacent the outer sidewall to discharge a lubrication fluid contained in the reservoir in response to the reservoir housing rotating around the rotational axis.