Bell Helicopter Textron Inc.

Hurst, TX, United States

Bell Helicopter Textron Inc.

Hurst, TX, United States

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Patent
Bell Helicopter Textron Inc. | Date: 2017-01-20

This description relates to a strapped windshield assembly for a rotorcraft. In some implementations, the rotorcraft includes an airframe, a windshield, and a plurality of independent straps connected to the airframe and the windshield, the straps operative to move independently with respect to one another. The independent movement of the straps allow relative movement of portions of the windshield in response to a strike. In some implementations, the straps are spaced every 4-6 inches along an edge of the windshield. In some implementations, the straps are over an edge of the windshield. The straps can have a modulus of elasticity of 8-12 millions of pounds per square inch (MSI). The windshield can include polycarbonate material.


Patent
Bell Helicopter Textron Inc. | Date: 2016-07-18

According to one embodiment, a flight control system includes a pilot control assembly and a flight control computer. The pilot control assembly can receive commands from a pilot. The flight control computer can receive, from the pilot control assembly, a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer can instruct, in response to the received pilot command, the flight control system to change a first operating condition of the flight control system based on an inherently-coupled relationship between the first flight characteristic and the second flight characteristic. The flight control computer can instruct, in response to the expected change to the second flight characteristic, the flight control system to change a second operating condition of the flight control system.


Patent
Bell Helicopter Textron Inc. | Date: 2017-01-26

A drive system for a tiltrotor aircraft includes a first gearbox rotatably mounted to the airframe and rotatable about a longitudinal axis to operate the tiltrotor aircraft between helicopter and airplane modes. A second gearbox extends generally normal to the longitudinal axis of the first gearbox. A common shaft, rotatable about the longitudinal axis, transfers torque from an output gear of the second gearbox to an input gear of the first gearbox. A support assembly couples the second gearbox to the airframe and includes a fixed joint proximate the longitudinal axis, a first directional reacting joint remote from the longitudinal axis providing a first radial growth degree of freedom to the second gearbox and a second directional reacting joint remote from the longitudinal axis providing a second radial growth degree of freedom to the second gearbox that is not parallel with the first radial growth degree of freedom.


Patent
Bell Helicopter Textron Inc. | Date: 2017-02-09

A mechanism for transitioning a tiltrotor aircraft between rotary and non rotary flight modes. The mechanism includes a gimbal lock positioned about a mast that is operable to selectively enable and disable a gimballing degree of freedom of a rotor assembly relative to the mast. A blade stop assembly, positioned about the mast, includes a plurality of arms having a radially contracted orientation and a radially extended orientation. A blade lock assembly is operably associated with each rotor blade assembly. Each blade lock assembly is operable to selectively enable and disable a folding degree of freedom and a pitching degree of freedom of the respective rotor blade assembly. A swash plate is operable to change the pitch of the rotor blade assemblies in the rotary flight mode and fold the rotor blade assemblies in the non rotary flight mode.


Patent
Bell Helicopter Textron Inc. | Date: 2017-02-07

A method of controlling an audio system includes generating a situation response model for a situation parameter, determining a situation parameter value, and at least one of (1) providing an audio system output as a function of the situation response model and the situation parameter value and (2) receiving an audio system input as a function of the situation response model and the situation parameter value.


Patent
Bell Helicopter Textron Inc. | Date: 2017-05-24

A system (230) includes an engine cover (124; 200) covering a side-facing rotorcraft engine (120) and having an opening (204) and an ice protection member (126; 210) mounted on the engine cover (124; 200) between the opening (204) and the engine (120), an area of the ice protection member (126; 210) smaller than an area of the opening (204). The ice protection member (126; 210) is configured to partially cover the opening (204) to prevent ice having a particular size from entering into the engine (120) and to allow air flow downstream into the engine (120).


Patent
Bell Helicopter Textron Inc. | Date: 2017-06-14

According to one embodiment, an aircraft features a fuselage (130), a wing member (150), and two fuselage beams (220a, 220b). The fuselage (130) features a first plurality of structural supports, a second plurality of structural supports, a first opening (132a) disposed between the first plurality of structural supports, and a second opening (132b) disposed between the second plurality of structural supports. The wing member (150) is disposed above the first opening (132a) and above the second opening (132b). The wing (150) features a plurality of ribs (152) including a first rib (152a) and a second rib (152b). The first fuselage beam (220a) couples the first rib (152a) of the wing member (150) to the fuselage (130) and has an elongated body portion extending across the first plurality of structural supports. The second fuselage beam (220b) couples the second rib (152b) of the wing member (150) to the fuselage (130) and features an elongated body portion extending across the second plurality of structural supports.


Patent
Bell Helicopter Textron Inc. | Date: 2017-06-21

The disclosure relates generally to flight control systems, and more specifically to an aircraft flight control system for allowing an augmentation system to have higher authorities, for example up to full authority, on an aircraft that has a mechanical flight control system. Embodiments include a flight control system for an aircraft, comprising: a first actuator; a first flight control computer having a first processor and a second processor for commanding the first actuator, wherein the first actuator compares commands from the first processor to commands from the second processor to find a first failure; a second actuator; and a second flight control computer having a first processor and a second processor for commanding the second actuator, wherein the second actuator compares commands from the first processor to commands from the second processor to find a second failure.


Patent
Bell Helicopter Textron Inc. | Date: 2017-07-19

The present application relates to a flight instrument (621) and method for providing visual economic operation of aircraft operations to an aircraft operator. The system and method provide a visual economic operation scale indicating at least one of: (i) a fuel efficiency; (ii) a rate of component wear or damage; (iii) a rate of maintenance inducing flight operation; (iv) a rate of component replacement inducing flight operation; (v) overall efficiency; and an indicator (623) moveable along the visual economic operation scale. A change in economic operation moves the indicator (623) along the visual economic operation scale so that a movement of the indicator (623) in a first direction represents an increase in economic operation of the aircraft, while a movement of the indicator (623) in a second direction represents a decrease in economic operation of the aircraft.


Patent
Bell Helicopter Textron Inc. | Date: 2017-04-03

A regime recognition system for an aircraft has a regime engine configured to identify a sub-regime performance of the aircraft only after having identified a top tier or top level regime performance that can include the sub-regime performance.

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