Rohr, Inc.

Anthony Lacko

Michael R Aten

Sara Christine Crawford

Christian Soria

Song Chiou

David Edward Pierick

Frank Becker

Wentaur Eugene Chien

Antonio Pizzi

An aerostructure assembly that includes an aerostructure (e.g., a resin pressure molded structure) and a coupling assembly is disclosed. The aerostructure includes an outer shell and a female receiver located within an interior of the outer shell. The coupling assembly includes a coupling and a beam that extends from this coupling. The beam is disposed within the female receiver, including where at least part of the coupling is positioned beyond an open end of the outer shell. The shape of the female receiver may retain the aerostructure to the beam in at least one direction/dimension. One or more fasteners may be utilized to attach the aerostructure to the beam. The coupling may be formed from one or more metals, and in any case, accommodates attachment of the aerostructure assembly to a flight vehicle.

Resin pressure molded aerostructure with integrated metal coupling

An airfoil system is provided that includes an airfoil and an electric device. The airfoil includes a first exterior surface, a second exterior surface, a first airfoil segment and a second airfoil segment attached to the first airfoil segment. The airfoil extends widthwise between the first exterior surface and the second exterior surface. The first airfoil segment forms the first exterior surface. The second airfoil segment forms the second exterior surface. The electric device is embedded within the airfoil between the first airfoil segment and the second airfoil segment.

Airfoil system with embedded electric device

A hybrid electric powerplant can include an electric motor configured to convert electrical energy into kinetic energy to turn a propulsor, and a heat engine configured to convert a fuel into kinetic energy to turn the propulsor. The powerplant can include a firewall disposed around at least one of the electric motor or the heat engine to create an electric motor fire zone and a heat engine fire zone separate from the electric motor fire zone such that the electric motor is protected against a heat engine fire, and vice versa.

Firewall assemblies for hybrid electric aircraft powerplants

A nacelle is provided that includes an outer structure and an inner structure. The inner structure includes a support structure, a first core cowl and a second core cowl. The support structure includes a plurality of first hinges, a plurality of second hinges, a plurality of longitudinal rails and a plurality of crossover rails spaced longitudinally along and connected to the longitudinal rails. Each of the first hinges is connected to a respective one of the crossover rails at a first distal end of the respective crossover rail. Each of the second hinges is connected to a respective one of the crossover rails at a second distal end of the respective crossover rail. The first core cowl is pivotally mounted to the support structure by the first hinges. The second core cowl is pivotally mounted to the support structure by the second hinges.

Support structure for inner cowls of an aircraft propulsion system

An airfoil system is provided that includes an airfoil. This airfoil includes a first exterior surface, a second exterior surface, a first airfoil segment and a second airfoil segment. The airfoil extends widthwise between the first exterior surface and the second exterior surface. The first airfoil segment includes first composite material and a receptacle. A base of the receptacle is embedded within the first composite material. The second airfoil segment includes second composite material and a key. A base of the key is embedded within the second composite material. The key is mated with the receptacle thereby attaching the second airfoil segment to the first airfoil segment.

A translating inlet assembly may comprise a first inlet portion and a second portion configured to translate relative to the first portion. A track may be located in the first portion. A rail may be coupled to the second portion and configured to translate along the track. The rail and the track may form a load bearing component configured to transfer inertial loads experienced by the second portion. A first actuator may be operationally coupled to the rail and configured to drive the rail along the track.

Single track translating inlet

A thrust reverser is disclosed. The thrust reverser includes a frame, a first reverser door pivotally mounted to the frame, a second reverser door pivotally mounted to the frame and a hybrid exhaust duct. A first trailing edge of the first reverser door forms a portion of an exit plane of the thrust reverser and a second trailing edge of the second reverser door merges into the hybrid exhaust duct.

Hybrid pivot door thrust reversers

A sound attenuation device includes an acoustic panel having a first end and a second end spaced from the first end. The first end is configured for attachment to a first mount and the second end is configured for attachment to a second mount. The acoustic panel comprises a permeable skin and a septum, the septum having a length extending between the first end and the second end.

Acoustic panel with structural septum

An assembly is provided for an aircraft. This aircraft assembly includes an aircraft propulsion system and a pylon configured to mount the aircraft propulsion system to an airframe member. The pylon includes a first pylon structure and a second pylon structure. The first pylon structure is configured to mount to the airframe member. The second pylon structure is mounted to the aircraft propulsion system. The second pylon structure is configured to disconnect from the first pylon structure while mounted to the airframe member.

Segmented pylon for an aircraft propulsion system

An assembly is provided for an aircraft propulsion system. The assembly includes a tubular inner housing, a tubular outer housing and a bifurcation. The bifurcation includes a leading edge structure structurally connected to the inner housing and the outer housing.

Nacelle bifurcation with leading edge structure

A safety maintenance panel for a thrust reverser is provided. The thrust reverser may comprise one or more doors configured to actuate from a closed position to a deployed position. The safety maintenance panel may be located on the thrust reverser. The safety maintenance panel may comprise a safety pin configured to engage the door in the deployed position to at least partially limit movement of the door from the deployed position. In that respect, the safety pin may be inserted into a panel pin hole through the maintenance panel and a door pin hole through the door to lock the door into the deployed position.

Safety maintenance panel for a thrust reverser

A thrust reverser for a gas turbine engine includes a reverser door pivotally mounted to a frame, an exhaust duct translationally mounted to the frame and an actuator having an actuator rod connected to the reverser door and to the exhaust duct.

Translating nozzle for mixed flow turbofan engine

A nacelle is provided comprising, a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position, the translating sleeve comprising a slat cutout for clearance, and a slat door disposed at least partially in the slat cutout in response to the thrust reverser being in the stowed position, wherein the slat door is configured to move in response to the thrust reverser being in the deployed position to expose a portion of the slat cutout to accept a portion of a deployed forward wing slat.

Slat-thrust reverser clearance

An aircraft nacelle may comprise an inner fixed structure and an outer sleeve. The aircraft nacelle may comprise an O-duct thrust reverser. A drain gutter may be located in the inner fixed structure. The drain gutter may comprise a labyrinth configuration. The drain gutter may drain fluids in an aft direction through the inner fixed structure. The fluids may exit through a drain fin located at a station plane aft of the outer sleeve.

Nacelle fluid drain

An engine nacelle is provided and includes an outer fixed structure (OFS) assembly disposed about an inner fixed structure (IFS) barrel and a latch beam, which is separate from the IFS barrel along an entire length thereof. The latch beam includes forward and trailing ends directly and indirectly supportively coupled to the OFS assembly, respectively.

Growing community of inventors

San Diego, CA, United States of America

Anthony Lacko