Abstract: A system for mounting an engine on an aircraft. The system includes a lower forward element, lateral linkages, an upper forward element, and an aft element. The lower forward element couples a forward portion of an engine core with a lower forward portion of a pylon. The linkages extend laterally between the lower forward element and the forward portion of the engine core. The upper forward element couples an outer portion of the fan case with an upper portion of the pylon. The aft element is spaced aftwardly apart from the lower and upper forward elements, and couples an aft portion of the engine core to an aft portion of the pylon. The system reacts all major moments acting on the engine, and the system does not extend beyond an outer periphery of the fan case, which eliminates the need for or minimizes the height of an aerodynamic fairing.

Abstract: A method of manufacturing a multi-sided or otherwise relatively three-dimensional formed structure for, e.g., an aerospace vehicle. A relatively planar base structure is constructed using a first construction technique. Features (e.g., ribs) are incorporated into the base structure using a second construction technique (e.g., additive or subtractive manufacturing) to create an intermediate structure. The intermediate structure is folded along fold-lines or otherwise physically formed to create the formed structure, such that some of the features are located within an internal space defined by the formed structure. Joints between the sides of the formed structure are welded, fastened, or otherwise secured. Separately constructed additional elements (e.g., bulkheads) may be incorporated into the structure. A closeout element may be added to the formed structure to further define and close the internal space. Throughout the process, the structures, features, and elements may be refined to desired tolerances.

Abstract: A cascade assembly for a thrust reverser of an aircraft engine. The cascade broadly comprises a number of vanes formed of a pliable material and shiftable between a collapsed position when the thrust reverser is in a stowed configuration and a distended position when the thrust reverser is in a deployed configuration to redirect fan duct flow in a reverse thrust flow opening created by the thrust reverser.

Abstract: A method of manufacturing a multi-sided or otherwise relatively three-dimensional formed structure for, e.g., an aerospace vehicle. A relatively planar base structure is constructed using a first construction technique. Features (e.g., ribs) are incorporated into the base structure using a second construction technique (e.g., additive or subtractive manufacturing) to create an intermediate structure. The intermediate structure is folded along fold-lines or otherwise physically formed to create the formed structure, such that some of the features are located within an internal space defined by the formed structure. Joints between the sides of the formed structure are welded, fastened, or otherwise secured. Separately constructed additional elements (e.g., bulkheads) may be incorporated into the structure. A closeout element may be added to the formed structure to further define and close the internal space. Throughout the process, the structures, features, and elements may be refined to desired tolerances.

Abstract: An assembly for reacting a thrust load from an engine, the assembly comprising a frame, a pin, an evener bar, and left and right thrust links. The frame includes an upper pin interface and a lower pin interface. The pin extends through the upper pin interface and the lower pin interface and includes an upper end and a lower end. The evener bar engages the lower end of the pin below the lower pin interface and connects the left and right thrust links to the pin. The pin is configured to react the thrust load at the lower pin interface and the upper pin interface thereby forming a distributed force couple between the lower pin interface and the upper pin interface.

Abstract: An aircraft propulsion system configured to be supported from an aircraft wing having a leading edge and opposing upper and lower surfaces. The aircraft propulsion system broadly comprises an engine having a core, a fan case, and a nacelle including a plurality of access panels, and an attachment assembly for securing the engine to the aircraft wing. The attachment assembly broadly comprises an upper support section including a number of spars and a number of ribs connected between the spars, a lower support section, and an aft section. The attachment assembly aerodynamically melds the nacelle and the aircraft wing together via the upper support section so that air flowing over the engine flows over the aircraft wing along the upper surface and air flowing laterally alongside the nacelle flows under the aircraft wing along the lower surface.

Abstract: A cascade assembly for a thrust reverser of an aircraft engine. The cascade broadly comprises a number of vanes formed of a pliable material and shiftable between a collapsed position when the thrust reverser is in a stowed configuration and a distended position when the thrust reverser is in a deployed configuration to redirect fan duct flow in a reverse thrust flow opening created by the thrust reverser.

Abstract: A cascade assembly for a thrust reverser of an aircraft engine. The cascade broadly comprises a number of vanes formed of a pliable material and shiftable between a collapsed position when the thrust reverser is in a stowed configuration and a distended position when the thrust reverser is in a deployed configuration to redirect fan duct flow in a reverse thrust flow opening created by the thrust reverser.

Abstract: A system for mounting an engine on an aircraft. The system includes a lower forward element, lateral linkages, an upper forward element, and an aft element. The lower forward element couples a forward portion of an engine core with a lower forward portion of a pylon. The linkages extend laterally between the lower forward element and the forward portion of the engine core. The upper forward element couples an outer portion of the fan case with an upper portion of the pylon. The aft element is spaced aftwardly apart from the lower and upper forward elements, and couples an aft portion of the engine core to an aft portion of the pylon. The system reacts all major moments acting on the engine, and the system does not extend beyond an outer periphery of the fan case, which eliminates the need for or minimizes the height of an aerodynamic fairing.

Abstract: A cascade assembly for a thrust reverser of an aircraft engine. The cascade broadly comprises a number of vanes formed of a pliable material and shiftable between a collapsed position when the thrust reverser is in a stowed configuration and a distended position when the thrust reverser is in a deployed configuration to redirect fan duct flow in a reverse thrust flow opening created by the thrust reverser.

Abstract: An assembly for reacting a thrust load from an engine, the assembly comprising a frame, a pin, an evener bar, and left and right thrust links. The frame includes an upper pin interface and a lower pin interface. The pin extends through the upper pin interface and the lower pin interface and includes an upper end and a lower end. The evener bar engages the lower end of the pin below the lower pin interface and connects the left and right thrust links to the pin. The pin is configured to react the thrust load at the lower pin interface and the upper pin interface thereby forming a distributed force couple between the lower pin interface and the upper pin interface.

Abstract: An engine support mount including an airframe structure having a first anchor surface and a length extending along an x-axis, with a second axis defined perpendicularly to the x-axis. A support member is fixed to the airframe structure and defines a first aperture and a second aperture. A mounting assembly includes an elongated arm and first and second primary attachment assemblies respectively attaching the arm to the support member at the first and second apertures, the arm having a second anchor surface. A moment arm reduction feature includes a lug fixed to one of the anchor surfaces and a corresponding fastener fixed to the other of the anchor surfaces. The first anchor surface is positioned on the airframe structure outside of the first and second apertures, and the second anchor surface is positioned on the arm outside of the first and second attachment assemblies.

Abstract: A method of manufacturing a multi-sided or otherwise relatively three-dimensional formed structure for, e.g., an aerospace vehicle. A relatively planar base structure is constructed using a first construction technique. Features (e.g., ribs) are incorporated into the base structure using a second construction technique (e.g., additive or subtractive manufacturing) to create an intermediate structure. The intermediate structure is folded along fold-lines or otherwise physically formed to create the formed structure, such that some of the features are located within an internal space defined by the formed structure. Joints between the sides of the formed structure are welded, fastened, or otherwise secured. Separately constructed additional elements (e.g., bulkheads) may be incorporated into the structure. A closeout element may be added to the formed structure to further define and close the internal space. Throughout the process, the structures, features, and elements may be refined to desired tolerances.

Abstract: An aircraft engine nacelle spoiler assembly including a number of spoilers and actuators. Each spoiler has a drag surface and a nacelle connection point. The spoilers are shiftable via the actuators between a stowed position and a deployed position such that the drag surfaces are substantially parallel with the direction of relative wind when the spoilers are stowed and exposed to the relative wind when the spoilers are deployed.

Abstract: A system for mounting an engine on an aircraft. The system includes a lower forward element, lateral linkages, an upper forward element, and an aft element. The lower forward element couples a forward portion of an engine core with a lower forward portion of a pylon. The linkages extend laterally between the lower forward element and the forward portion of the engine core. The upper forward element couples an outer portion of the fan case with an upper portion of the pylon. The aft element is spaced aftwardly apart from the lower and upper forward elements, and couples an aft portion of the engine core to an aft portion of the pylon. The system reacts all major moments acting on the engine, and the system does not extend beyond an outer periphery of the fan case, which eliminates the need for or minimizes the height of an aerodynamic fairing.

Abstract: An engine support mount including an airframe structure having a first anchor surface and a length extending along an x-axis, with a second axis defined perpendicularly to the x-axis. A support member is fixed to the airframe structure and defines a first aperture and a second aperture. A mounting assembly includes an elongated arm and first and second primary attachment assemblies respectively attaching the arm to the support member at the first and second apertures, the arm having a second anchor surface. A moment arm reduction feature includes a lug fixed to one of the anchor surfaces and a corresponding fastener fixed to the other of the anchor surfaces. The first anchor surface is positioned on the airframe structure outside of the first and second apertures, and the second anchor surface is positioned on the arm outside of the first and second attachment assemblies.

Abstract: A nacelle mounted above a wing of an aircraft. A support structure on the nacelle above the pylon resists forces in different directions, and includes door supports allowing the door to be opened upwardly. A retaining structure on the pylon below the nacelle resists forces in different directions, and includes a fixed support track and multiple keepers. Each keeper includes a first end which slides within the channel, and a second end which engages a latch on the closed door. A pylon below the nacelle supports the nacelle and an engine in the nacelle above the wing, increases aerodynamic efficiency, and may include a side spar for supporting the engine from the side. A fire seal assembly includes a depressor surface and a fire seal, and the latter does not contact the former until the door is almost closed, so that compression is substantially direct and scrubbing is reduced.

Abstract: An inlet for a nacelle and an AM system and method for manufacturing the inlet having fewer discontinuities on the exterior surface to achieve a smoother flow over the inlet. The inlet includes an annular lip-cowl and a supporting framework. The AM system includes a support structure providing a form, and AM heads for depositing materials onto the form, with the materials subsequently hardening to become the lip-cowl. The support structure may have an upright or inverted orientation, is rotatable, and may be tiltable. Components may protrude from the form to be incorporated into the lip-cowl. The AM heads are mounted on moveable arms and are computer-controlled to deposit the material onto the form, and may be moveable along a radial axis to accommodate an asymmetrical portion of the form. The AM system may further include one or more machining heads for subtractively machining the deposited material.

Abstract: An aircraft engine attachment assembly having a wing section, an engine pylon, upper secondary attachment links, lateral load attachment links, and a number of fuse pins. The engine pylon is mounted to the front end of the wing section so that the engine pylon is not restricted by a minimum structural depth. The wing section, engine pylon, upper secondary attachment links, and lateral load links form primary and secondary attachment joints configured to form alternate load paths if one of the joints fails. The wing section and engine pylon include knuckle-off geometries for promoting mechanical fusing of the fuse pins during high energy dynamic events.

Abstract: An aircraft engine nacelle spoiler assembly including a number of spoilers and actuators. Each spoiler has a drag surface and a nacelle connection point. The spoilers are shiftable via the actuators between a stowed position and a deployed position such that the drag surfaces are substantially parallel with the direction of relative wind when the spoilers are stowed and exposed to the relative wind when the spoilers are deployed.