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: 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: 2017-04-05

An emergency lighting system (ELS) 200, 500, 800 for an aircraft 100 has a capacitor 206, a light emitting diode (LED) 220, 222 selectively powered by the capacitor, and at least one of a photoluminescent sign 242 and a photoluminescent panel 242, 244 configured to receive light emitted from the LED.


Patent
Bell Helicopter Textron Inc. | Date: 2017-02-01

A method of providing power information in a rotorcraft, the rotorcraft having a powerplant. The method comprising calculating a real-time power required and calculating a real-time power available, and orienting power required and power available indicators on a power safety instrument, the position of the power required indicator being dependent upon the calculated power required, and the position of the power available indicator being dependent upon the calculated power available.


Patent
Bell Helicopter Textron Inc. | Date: 2017-02-08

A rotorcraft rotor blade assembly (100) includes an upper skin portion (104) extending substantially a full span of the rotor blade assembly (100) and a lower skin portion (106) extending substantially the full span of the rotor blade assembly (100). Each of the upper skin portion (104) and the lower skin portion (106) is configured to carry at least substantially 30% of rotor blade assembly (100) loads.


Patent
Bell Helicopter Textron Inc. | Date: 2017-04-05

A vibration control system 200 for a rotorcraft 100 includes at least one of an integrated actuator 208 and an intermediate actuator 210 associated with a first source of vibration, a sensor configured to sense vibration from the first source of vibration, a dedicated actuator 212 configured for association with a fuselage 106, and a controller 204 configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator.


Patent
Bell Helicopter Textron Inc. | Date: 2017-01-11

A rotorcraft rotor blade (400) assembly includes a stub spar (402) extending less than a full span of the rotor blade assembly (400). An upper skin portion (404) extends substantially the full span of the rotor blade assembly (400). A lower skin portion (406) extends substantially the full span of the rotor blade assembly (400). The stub spar (402) is positioned between the upper skin portion (404) and the lower skin portion (406).


Patent
Bell Helicopter Textron Inc. | Date: 2017-04-05

An emergency lighting system (ELS) 200, 500, 800 for an aircraft 100 has a capacitor 206, at least one of an onboard power system 116 and a ground power unit 118 configured to charge the capacitor, and a light emitting diode (LED) 220, 222 selectively powered by the capacitor.


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: 2017-09-13

An aircraft rotor assembly (217) has a central hub (221) and a plurality of rotor blades (215) coupled to the hub (221) for rotation with the hub (221) about an axis (242), each blade (215) having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade (215) is formed by a flexure (219) coupling the associated blade (215) to the hub (221). Each pivot is a radial distance from the axis (242) and allows for in-plane lead-lag motion of the associated blade (215) relative to the hub (221), each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Elastic deformation of the flexure (219) produces a biasing force for biasing the associated blade (215) 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 (215).

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