Abstract: A nacelle inlet structure for an engine includes a composite inlet lip defining a leading edge of a nacelle of the engine.

Abstract: A thrust reverser of a nacelle may include an translating sleeve and an inner fixed structure a pressure relief assembly. A pressure relief mechanism may include a pressure relief door coupled via a hinge and a latch to the inner fixed structure. Alternatively, a pressure relief door may be coupled to a frame via a hinge and a latch to the inner fixed structure. The pressure relief assembly may limit deflections between the thrust reverser and the pylon in response to a burst duct. The pressure relief door may release from the latch automatically in response to an over pressurization event.

Abstract: A magnetic fire seal for a nacelle may comprise an exterior surface configured to form a sealing interface and an interior surface opposite the exterior surface. A fire-resistant material may be disposed between the exterior surface and the interior surface. A magnet may be located at the interior surface proximate the sealing interface. A portion of the fire-resistant material may be located between the magnet and the exterior surface.

Abstract: The present disclosure provides an inlet assembly for a nacelle. The inlet assembly may comprise an inlet, a lip skin coupled to the inlet, the lip skin and the inlet forming a duct, and an inner duct skin situated between the inlet and the lip skin, the inner duct skin separating the duct by defining a first chamber and a second chamber.

Abstract: A catch assembly is provided that includes a keeper, a guide and a catch. The catch includes a catch mount, a catch arm and a catch hook. The catch arm is cantilevered from the catch mount. The catch arm extends longitudinally away from the catch mount to a distal end of the catch. The catch hook is connected to the catch arm at the distal end. The catch is configured to bias the catch hook against the guide. The catch hook is configured to slide longitudinally along the guide from a first position to a second position where the catch hook engages the keeper.

Abstract: A nacelle may include a pylon and a thrust reverser having an inner fixed structure. A locking mechanism may automatically engage and prevent relative movement between thrust reverser halves. A bumper may be coupled to the inner fixed structure. The locking mechanism may limit deflections between the thrust reverser and the pylon in response to a burst duct. A locking mechanism in the inner fixed structure may include a pressure relief door and an arrestor which hooks onto a retaining bar in a pylon bracket. The locking mechanism may allow the thrust reverser halves to be opened for access to the engine.

Abstract: A diaphragm latch may comprise a housing, a diaphragm disposed in the housing, a pin coupled to the diaphragm, an opening in the housing, and a pin aperture disposed in the first side, wherein the pin extends from the pin aperture. The diaphragm may be configured to move in response to a pressure being communicated through the opening, and the pin may be configured to at least one of extend or retract from the pin aperture in response to the diaphragm moving. The diaphragm latch may passively couple an inner fixed structure (IFS) to an intermediate case (IMC) during an overpressure event.

Abstract: A system is provided that includes an assembly adapted to support a first body relative to a second body. An elastomeric body is configured with a mounting aperture for receiving the first body. The elastomeric body includes a first protrusion and a second protrusion. A frame wraps about a perimeter of the elastomeric body. The frame is configured with a first window and a second window. The first protrusion extends through the first window to a distal end of the first protrusion. The second protrusion extends through the second window to a distal end of the second protrusion. Spring elements are adapted to mount to the second body. The elastomeric body is disposed between the first and the second spring elements such that the first spring element engages the distal end of the first protrusion and the second spring element engages the distal end of the second protrusion.

Abstract: Acoustically treated components and methods of acoustic treating are provided. The acoustically treated components include a structural fitting having a first surface and a second surface, wherein the first surface defines a flow path and includes a plurality of perforations passing through the structural fitting from the first surface to the second surface, at least one non-structural acoustic treatment member installed on the second surface, a first end of the at least one non-structural acoustic treatment member attached to the second surface such that a cellular structure of the at least one non-structural acoustic treatment member aligns with the plurality of perforations, and a cover attached on a second end of the at least one non-structural acoustic treatment member such that an acoustic chamber is defined between the cover and the cellular structure and open to the flow path.

Abstract: A thermally protected attachment system is provided. A device including a cover hingeably coupled to a thermal blanket is provided. The thermal blanket and cover may be configured to insulate a cavity defined by the interior of the thermal blanket and the cover in response to the cover being in a closed position. The thermal blanket may be coupled to a thermal protection panel of an aircraft.

Abstract: Latch housing assemblies, latch hook assemblies, and latch assemblies are disclosed. Various disclosed latch housing assemblies include a latch pin coupled to an inner housing, and an outer housing having an inner surface coupled to an outer surface of the inner housing via at least one of a fuse pin and a spring. Various disclosed latch hook assemblies include a latch hook coupled to a latch housing, a weak point in the latch housing disposed between an inboard mount and an outboard mount, and a catch member mounted to the inboard mount and the outboard mount. Various disclosed latch assemblies include a latch housing, a bolt, and a deformable bushing at least partially surrounding the bolt, the deformable bushing configured to deform about a radius in response to a compressive load of about 1,000 lbf to about 3,000 lbf.

Abstract: Latch housing assemblies, latch hook assemblies, and latch assemblies are disclosed. Various disclosed latch housing assemblies include a latch pin coupled to an inner housing, and an outer housing having an inner surface coupled to an outer surface of the inner housing via at least one of a fuse pin and a spring. Various disclosed latch hook assemblies include a latch hook coupled to a latch housing, a weak point in the latch housing disposed between an inboard mount and an outboard mount, and a catch member mounted to the inboard mount and the outboard mount. Various disclosed latch assemblies include a latch housing, a bolt, and a deformable bushing at least partially surrounding the bolt, the deformable bushing configured to deform about a radius in response to a compressive load of about 1,000 lbf to about 3,000 lbf.

Abstract: A thermal blanket system is provided on an aircraft component to protect the component, for example, from engine heat. The component has a latch half attached thereto, which is also covered by the thermal blanket system. In some scenarios, the latch half may need to be detached from the component because the latch was stuck closed. The thermal blanket system includes a portion thereof which overlaps the latch half and breaks away from the remainder of the thermal blanket system when the latch half is detached.

Abstract: Acoustically treated components and methods of acoustic treating are provided. The acoustically treated components include a structural fitting having a first surface and a second surface, wherein the first surface defines a flow path and includes a plurality of perforations passing through the structural fitting from the first surface to the second surface, at least one non-structural acoustic treatment member installed on the second surface, a first end of the at least one non-structural acoustic treatment member attached to the second surface such that a cellular structure of the at least one non-structural acoustic treatment member aligns with the plurality of perforations, and a cover attached on a second end of the at least one non-structural acoustic treatment member such that an acoustic chamber is defined between the cover and the cellular structure and open to the flow path.

Abstract: A structural panel for an aircraft nacelle may comprise a first skin, a second skin, and a core sandwiched between them. One of the skins may comprise regions of different thicknesses. The regions of different thicknesses may be separated by a ramp, in which the number of composite plies in the first skin varies. A slope of the ramp may vary across the ramp to prevent disbonding of the core from the skin at the base of the ramp.

Abstract: A nacelle may include a pylon and a thrust reverser having an inner fixed structure. A locking mechanism may automatically engage and prevent relative movement between thrust reverser halves. A bumper may be coupled to the inner fixed structure. The locking mechanism may limit deflections between the thrust reverser and the pylon in response to a burst duct. A locking mechanism in the inner fixed structure may include a pressure relief door and an arrestor which hooks onto a retaining bar in a pylon bracket. The locking mechanism may allow the thrust reverser halves to be opened for access to the engine.

Abstract: A nacelle may include a pylon and a thrust reverser having an inner fixed structure. A locking mechanism may automatically engage and prevent relative movement between thrust reverser halves. A bumper may be coupled to the inner fixed structure. The locking mechanism may limit deflections between the thrust reverser and the pylon in response to a burst duct. A locking mechanism in the inner fixed structure may include a pressure relief door and an arrestor which hooks onto a retaining bar in a pylon bracket. The locking mechanism may allow the thrust reverser halves to be opened for access to the engine.

Abstract: A seal comprising a generally acorn shaped cross-sectional profile is described herein. The seal may be configured for use between two generally adjoining and/or nearly adjoining surfaces. The seal may be used to eliminate a gap or rubbing between a plurality of surfaces. The seal may have a non-circular cross-sectional interior profile.

Abstract: A composite component may be coupled to an aluminum component with a plurality of fasteners. An expansion strap may be located between the composite component and the aluminum component. The expansion strap may have a coefficient of thermal expansion which is greater than the coefficient of thermal expansion of the composite component, and less than the coefficient of thermal expansion of the aluminum component. A first set of fasteners may be inserted through the composite component, the expansion strap, and the aluminum component. A second set of fasteners may be inserted through the composite component and the expansion strap. The expansion strap may decrease stress in the composite component at the fastener locations.

Abstract: A structural panel for an aircraft nacelle may comprise a first skin, a second skin, and a core sandwiched between them. One of the skins may comprise regions of different thicknesses. The regions of different thicknesses may be separated by a ramp, in which the number of composite plies in the first skin varies. A slope of the ramp may vary across the ramp to prevent disbonding of the core from the skin at the base of the ramp.