Rohr, Inc.

Imad D Ghandour

Timothy Gormley

Ken V Huynh

Jihad I Ramlaoui

Corey R Gloede

An assembly for an aircraft propulsion system includes a nacelle, at least one fan cowl actuator, at least one C-duct actuator, and a controller. The nacelle includes an outer structure including a fan cowl and a thrust reverser. The fan cowl includes at least one fan cowl door. The thrust reverser includes at least one C-duct door. The at least one fan cowl actuator is mounted to the at least one fan cowl door. The at least one C-duct actuator is mounted to the at least one C-duct door. The controller is configured to selectively direct electrical power from a power supply to (1) the fan cowl actuator electric motor to control a fan cowl position of the at least one fan cowl door and (2) the C-duct actuator electric motor to control a C-duct position of the at least one C-duct door.

Nacelle actuation and control assembly for an aircraft propulsion system

An aircraft nacelle is provided that includes a fan cowl, a thrust reverser translating sleeve, and a thrust reverser. The fan cowl and the sleeve are configured to circumferentially enclose an engine. The thrust reverser includes a thrust reverser actuation system (TRAS). The TRAS includes first and second actuators, and a portable manual drive unit (MDU). The first and second actuators are each configured to translate the sleeve linearly between stowed and deployed positions, and each has an actuator input drive port. The portable MDU has an MDU input drive port, an MDU output drive port, and a torque limiting device. The MDU output drive port is configured for engagement with the actuator input drive port. The portable MDU is configured for releasable engagement with the first actuator and for releasable engagement with the second actuator.

Thrust reverser manual drive system

An assembly is provided for an aircraft. This aircraft assembly includes a latch, a balk element and a fitting. The latch is movable between an unlocked position and a locked position. The balk element is rotatable between a balked position and an un-balked position. The balk element is configured to block the latch from moving to the locked position when the balk element is in the balked position. The fitting includes a keeper. The fitting is movable between an open position and a closed position. The fitting is configured to push the balk element into the un-balked position as the fitting moves into the closed position. The latch is configured to move to the locked position and engage the keeper when the fitting is in the closed position.

Balk device for door lock

A thrust reverser includes a frame, a track disposed on the frame, a carrier operatively coupled to the track, and a first reverser door operatively coupled to the carrier. The first reverser door is movable relative to the frame. The first reverser door is configured to move to a first position in response to the carrier moving with respect to the track in a first direction, and move to a second position in response to the carrier moving with respect to the track in a second direction.

Thrust reverser single degree of freedom actuator mechanism systems and methods

A method for deploying a thrust reverser includes translating a carrier along a track, transferring a first load between the carrier and a first reverser door in response to the carrier translating along the track, rotating the first reverser door between a closed position and an open position in response to the carrier translating along the track, transferring a second load between the carrier and a deployable fairing in response to the carrier translating along the track, and rotating the deployable fairing between a stowed position and a deployed position in response to the carrier translating along the track.

Thrust reverser actuation arrangement and deployable fairing systems and methods

An assembly for an aircraft includes a variable area inlet for an aircraft propulsion system. The variable area inlet extends along a longitudinal centerline. The variable area inlet includes an inlet structure, an inlet door, an inner inlet passage, and an outer inlet passage. The inlet door is configured to axially translate from a closed position to an open position along the longitudinal centerline. The inlet door is configured to close the outer inlet passage when the inlet door is in the closed position. The inlet door is configured to open the outer inlet passage when the inlet door is in the open position. The inner inlet passage extends into the variable area inlet from a leading edge of the inlet structure. The outer inlet passage extends through the inlet structure to the inner inlet passage.

Aircraft propulsion system with variable area

A thrust reverser may include a frame, a track disposed on the frame, a carrier operatively coupled to the track, and a first reverser door operatively coupled to the carrier. The first reverser door is movable relative to the frame, wherein the first reverser door is configured to move to a first position in response to the carrier moving with respect to the track in a first direction, and move to a second position in response to the carrier moving with respect to the track in a second direction.

A thrust reverser may include a frame, a track disposed on the frame, a carrier operatively coupled to the track, a first reverser door operatively coupled to the carrier, the first reverser door is movable relative to the frame, wherein the first reverser door is configured to move to a first position in response to the carrier moving with respect to the track in a first direction, and move to a second position in response to the carrier moving with respect to the track in a second direction, and a deployable fairing pivotally coupled to the frame, the deployable fairing operatively coupled to the carrier, wherein the deployable fairing is configured to move away from a central axis of the thrust reverser to provide clearance for the reverser door to rotate into a deployed position.

A lock mechanism for releasably securing a pivot door of a thrust reverser includes a frame, a blade housing connected to the frame, a blade member slidably disposed within the blade housing and configured to engage a lock fitting of the pivot door, an actuator configured to translate the blade member in a first direction with respect to the frame; a spring element configured to translate the blade member in a second direction with respect to the frame, and a loose-joint coupling configured to connect the actuator to the blade member.

Translating lock for pivot door thrust reverser

An assembly is provided for an aircraft propulsion system with an axial centerline. The assembly includes a translating sleeve, a sleeve actuator and a locking apparatus. The sleeve actuator is connected to the translating sleeve. The sleeve actuator is configured to move the translating sleeve along the axial centerline between a stowed position and a deployed position. The locking apparatus includes a lock and a lock actuator. The lock comprises a locking element. The lock actuator is configured to move the locking element between a locked position and an unlocked position. The locking element is configured to lock the translating sleeve in the stowed position when the locking element is in the locked position. A first portion of the locking apparatus axially overlaps the sleeve actuator along the axial centerline. A second portion of the locking apparatus does not axially overlap the sleeve actuator along the axial centerline.

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San Diego, CA, United States of America

Imad D Ghandour