Bell Helicopter Textron Inc. Patente

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A rotorcraft (101) including a control element, a control sensor connected to the control element, where the control sensor is operable to generate trim data indicating a displacement of the control element in relation to a trim position of the control element, and a flight control computer (FCC) operable to monitor the trim data and determine an active detent state of the control element. The active detent state is one of an in-detent state (803), an out-of-detent state (813), and an in-transition state (807). The FCC is operable to buffer a transition of the active detent state from the in-detent state (803) to the out-of-detent state (813) using the in-transition state (807). The FCC provides a first flight management function when the active detent state is the in-detent state or the in-transition state, and provides a second flight management function when the active detent state is the out-of-detent state.

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An embodiment device (202) includes a clamp body (208) having a clamp opening (302), an extension opening (606) and a traverse block (312) having an internally threaded portion, a reaction plate (204) having a recess (406) in a first face at a first side of the reaction plate (204) and one or more pins (408) disposed in the recess (406) extending away from the first face, and further having an extension (402) extending along a long axis of the reaction plate (204) through the extension opening (606), and bearing blocks (308; 310) disposed on a second side of the reaction plate (204) opposite the first side, where the traverse block (312) is disposed between the bearing blocks (308; 310). An actuator (206) is aligned parallel to the long axis of the reaction plate (204) and extending through each of the bearing blocks (308; 310) and through the traverse block (312), and the actuator (206) has an eternally threaded portion engaged with the internally threaded portion of the clamp body (208).

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A fly-by-wire system for a rotorcraft includes a computing device having control laws. The control laws are operable to engage a roll command or a yaw command in response to deflection of a beep switch (402) of a pilot control assembly, wherein a roll angle for the roll command or a yaw rate for the yaw command is determined based on forward airspeed of the rotorcraft. The beep switch (402) may be disposed on a collective control (264a) of the pilot control assembly. The control laws are further operable to disengage the roll command or the yaw command in response to the beep switch (402) being returned from a deflected position to a neutral position. In representative aspects, the roll angle or the yaw rate may correspond to a standard rate turn (e.g.,3° per second).

A fairing (214a) is provided in one example embodiment and may include a first edge portion (220a) to provide a first clearance distance (222a) between the fairing (214a) and rotor flight controls (216) of a rotorcraft (100); a second edge portion (220b) to provide a second clearance distance (222b) between the fairing (214a) and the rotor flight controls (216) of the aircraft (100), wherein the second clearance distance (222b) is greater than the first clearance distance (222a); and a support structure (224) attached to the fairing (214a) below the second edge portion (220b). A rotorcraft (100) is provided in another example embodiment and may include a fairing (214a) in which the fairing (214a) can include a handhold portion (230) along an edge of the fairing (214a). The handhold portion (230) can include a handhold clearance distance between the handhold portion (230) and rotor flight controls (216) of the rotorcraft (100); and a support structure (224) attached to the fairing (214a) below the handhold portion (230).

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In one embodiment, an apparatus may comprise a rotor blade (300). The rotor blade (300) may comprise a plurality of blade segments (310); one or more attachment fittings for coupling the plurality of blade segments (310); and one or more actuators (330) for adjusting an orientation of the plurality of blade segments (310).

In an embodiment, a rotorcraft (101) includes: tail rotor blades (111); a tail rotor actuator (113) coupled to the tail rotor blades (111) such that the pitch of the tail rotor blades (111) varies according to a current extension of the tail rotor actuator (113); pilot flight controls electrically coupled to the tail rotor actuator (113); and a flight control computer (205) electrically coupled to the tail rotor actuator (113) and the pilot flight controls, the flight control computer (205) configured to: determine the current extension of the tail rotor actuator (113); determine whether the current extension of the tail rotor actuator (113) is within a margin of a maximum extension of the tail rotor actuator (113); and indicate a first warning to a pilot in response to the current extension of the tail rotor actuator (113) being within the margin of the maximum extension of the tail rotor actuator (113).

The disclosure provides a blocking door (160) that is pivotally disposed on a fixed nacelle (137, 139) of a tiltrotor aircraft (101) for pivoting between a stowed position (S) when a proprotor pylon (115, 117) is in the substantially horizontal position and a protective blocking position (B) in front of the proprotor pylon (115, 117) when the proprotor pylon (115, 117) is positioned in the non-horizontal position. In other aspects, there is provided a method of reducing infrared and/or radar signatures of rotorcraft with a rotatable proprotor (116, 118).

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In accordance with an embodiment of the present invention, a method of operating a rotorcraft (101) includes receiving a measured yaw rate from a yaw rate sensor or a measured lateral acceleration from a lateral acceleration sensor of the rotorcraft (101), 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 (123) of the rotorcraft (101).

A tiltrotor assembly (200) has a central hub (202) with a plurality of rotor blades (206) extending therefrom and is configured to rotate about a mast axis (204) to generate lift in a hover position. The central hub (202) is configured to rotate about a tilt axis (242) between the hover position and a forward-flight position such that rotation about the mast axis (204) generates forward thrust. The central hub (202) is surrounded by a segmented duct (216) that includes a thin rotatable inner ring (218) and a wide fixed outer ring (220). The inner ring (218) is configured to rotate with the central hub (202) about the tilt axis (242) leaving the wide outer ring (220) in a generally horizontal position.

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A rotorcraft (100) with a fly-by-wire system includes a computing device having control laws. The control laws are operable to engage a stabilization maneuver in response to a perturbation of an otherwise stable operating condition of the rotorcraft (100), thereby returning the rotorcraft (100) to the stable operating condition without requiring input from the pilot. One or more control laws are further operable to increase or decrease pitch angle, roll angle, yaw rate, or collective pitch angle. In representative aspects, perturbation of the stable operating condition may occur as a result of transient meteorological conditions ( e.g., wind shear, wind gust, turbulence) experienced by a rotorcraft (100) engaged in flight operations at airspeeds between o knots ( e.g., a hover) and about 60 knots. The control laws are further operable to permit the rotorcraft (100) to operate with Instrument Meteorological Conditions (IMC) approval at substantially all airspeeds within a normal flight envelope of the rotorcraft (100).

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A cooling apparatus (300) includes a shared cooling device (305) for one or more systems or components, and a plurality of primary cooling pathways. Each of the primary cooling pathways includes a transition duct (320, 325) and a fan (340, 345). The transition duct (320, 325) is in fluid communication with the shared cooling device (305). The fan (340, 345) is in fluid communication with the transition duct (320, 325).