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.

Abstract: The present disclosure provides a composition for use in drilling fluids comprising an adsorbing substrate that is loaded with a hydrophobic liquid. In one aspect, the hydrophobic liquid comprises a base oil, an emulsifier, a rheology modifier, a viscosifier, a quaternary amine or a mixture thereof. The composition may be combined with an oil-based or hydrocarbon continuous phase, and an aqueous dispersed phase to form a non-aqueous phase invert emulsion for use in drilling applications.

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: A vehicle underbody including a rear underbody structure, a rear differential, a sub-frame, and a traction battery is provided. The rear differential is mounted to the rear underbody structure. The sub-frame is mounted to the rear underbody structure rearward of the rear differential. The traction battery is mounted between the rear underbody structure and the sub-frame. A base portion of the traction battery defines a base portion plane that does not extend through the rear differential. The sub-frame may include at least two reinforcement members each having a ramp-shaped end extending toward the rear differential. The sub-frame may include a rear lateral member and a trailer hitch mount extending rearwardly therefrom. One of the reinforcement members and the trailer hitch mount may be aligned in parallel with a central longitudinal axis defined by the rear underbody structure.

Abstract: A vehicle underbody including a rear underbody structure, a rear differential, a sub-frame, and a traction battery is provided. The rear differential is mounted to the rear underbody structure. The sub-frame is mounted to the rear underbody structure rearward of the rear differential. The traction battery is mounted between the rear underbody structure and the sub-frame. A base portion of the traction battery defines a base portion plane that does not extend through the rear differential. The sub-frame may include at least two reinforcement members each having a ramp-shaped end extending toward the rear differential. The sub-frame may include a rear lateral member and a trailer hitch mount extending rearwardly therefrom. One of the reinforcement members and the trailer hitch mount may be aligned in parallel with a central longitudinal axis defined by the rear underbody structure.

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 exemplary traction battery assembly includes, among other things, a battery pack and a securing assembly. The securing assembly secures the battery pack to a structure of the vehicle. The securing assembly is disposed along a horizontally facing side of the battery pack and is configured to move from a first position to a second position in response to a load to permit movement of the battery pack relative to the vehicle structure.

Abstract: An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module.

Abstract: A prefetch optimizer tool for an information handling system (IHS) may improve effective memory access time by controlling both hardware prefetch operations and software prefetch operations. The prefetch optimizer tool selectively disables prefetch instructions in an instruction sequence of interest within an application. The tool measures execution times of the instruction sequence of interest when different prefetch instructions are disabled. The tool may hold hardware prefetch depth constant while cycling through disabling different prefetch instructions and taking corresponding execution time measurements. Alternatively, for each disabled prefetch instruction in the instruction sequence of interest, the tool may cycle through different hardware prefetch depths and take corresponding execution time measurements at each hardware prefetch depth.

Abstract: An aircraft nacelle having a fixed structure fixed relative to an aircraft pylon, a translating thrust reverser sleeve translatable aftward, relative to the fixed structure, and a translating variable area fan nozzle (VAFN) panel translatable aftward, relative to the translating thrust reverser sleeve. The nacelle may also include a VAFN actuator mounted on the translating thrust reverser sleeve and a VAFN drive unit attached to the fixed structure. The VAFN drive unit may be coupled to drive the VAFN actuator via first and second coupling components when the translating thrust reverser sleeve is stowed. When the translating thrust reverser sleeve is deployed, the first and second coupling components may decouple, disconnecting the VAFN drive unit from the VAFN actuator.

Abstract: An assembly and method for attaching an engine pylon to an aircraft wing. The method may include attaching a first forward wing-mounted fitting to the pylon at a first side of the pylon between upper and lower spars of the pylon and attaching a second forward wing-mounted fitting to the pylon at a second side of the pylon between the upper and lower spars of the pylon. The second side of the pylon is located opposite of the first side of the pylon. Mechanical attachment devices may be inserted through holes on the sides of the pylon aligned with holes formed through the forward wing-mounted fittings. The mechanical attachment devices may be made of steel and the forward wing-mounted fittings may be made of composite or aluminum material.

Abstract: Disclosed are devices, apparatus, and methods for directly infusing one or more materials into a bone of a patient. More particularly, devices, apparatus and methods are provided for direct intra-bone infusion, wherein intra-bone pressure is continuously monitored and adjusted during infusion such that intra-bone pressure does not exceed levels of systemic blood pressure. Such devices, apparatus and methods are particularly suitable for use in performing bone marrow transplants.

Abstract: An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module.

Abstract: A prefetch optimizer tool for an information handling system (IHS) may improve effective memory access time by controlling both hardware prefetch operations and software prefetch operations. The prefetch optimizer tool selectively disables prefetch instructions in an instruction sequence of interest within an application. The tool measures execution times of the instruction sequence of interest when different prefetch instructions are disabled. The tool may hold hardware prefetch depth constant while cycling through disabling different prefetch instructions and taking corresponding execution time measurements. Alternatively, for each disabled prefetch instruction in the instruction sequence of interest, the tool may cycle through different hardware prefetch depths and take corresponding execution time measurements at each hardware prefetch depth.

Abstract: An aircraft pylon is disclosed, the pylon including a strut, a modular fluid containment structure and a modular firewall. The strut presents an open structure and connects an aircraft external element to the aircraft. The fluid containment structure is associated with a fluid transfer component, wherein the fluid containment structure contains escaped fluid from the fluid transfer component and channels the escaped fluid away from the aircraft. Both the fluid containment component and the firewall are modular and separable from the strut.

Abstract: An assembly and method for attaching an engine pylon to an aircraft wing. The method may include attaching a first forward wing-mounted fitting to the pylon at a first side of the pylon between upper and lower spars of the pylon and attaching a second forward wing-mounted fitting to the pylon at a second side of the pylon between the upper and lower spars of the pylon. The second side of the pylon is located opposite of the first side of the pylon. Mechanical attachment devices may be inserted through holes on the sides of the pylon aligned with holes formed through the forward wing-mounted fittings. The mechanical attachment devices may be made of steel and the forward wing-mounted fittings may be made of composite or aluminum material.