Abstract: In an aircraft, the airframe includes a windshield frame, with an energy attenuating windshield corner support extending across a corner of the windshield frame. The energy attenuating windshield corner support is configured to deform upon an impact to a windshield disposed in the windshield frame. This energy attenuating windshield corner support may be shaped and/or sized to enable, and/or comprised of a material that enables, the aircraft windshield corner support to deform upon the impact to the windshield disposed in the windshield frame, attenuating energy of the impact to the windshield disposed in the windshield frame.

Abstract: Methods and systems for automated placement of composite material on a surface of a component, the composite material including unidirectional fibers, is provided. A set of fiber paths along the surface is established, the set of fiber paths comprising at least one ply, each ply comprising a respective plurality of fiber paths being substantially aligned with a respective direction. An isotropy factor for the component is determined based on the set of fiber paths, the isotropy factor being indicative of a distribution of the plurality of fiber paths on the surface. When the isotropy factor exceeds a predetermined threshold, a respective layer of composite material is applied to the surface of the component using an automated fiber placement machine and for each of the at least one ply, wherein the unidirectional fibers of the composite material are applied along the set of fiber paths.

Abstract: Methods and systems for recovering sulfur dioxide from a Claus unit process emissions stream are provided. The method comprises the steps of generating a process emissions stream from a thermal oxidizer or other combustion device, introducing the emissions stream to an SO2 removal system, introducing the SO2 rich stream from the SO2 removal system to a CO2 removal system, and introducing an enriched SO2 stream back to the Claus unit. The SO2 removal system can include one or more SO2 selective membranes. The CO2 removal system can include one or more CO2 selective membranes.

Abstract: In an aircraft, the airframe includes a windshield frame, with an energy attenuating windshield corner support extending across a corner of the windshield frame. The energy attenuating windshield corner support is configured to deform upon an impact to a windshield disposed in the windshield frame. This energy attenuating windshield corner support may be shaped and/or sized to enable, and/or comprised of a material that enables, the aircraft windshield corner support to deform upon the impact to the windshield disposed in the windshield frame, attenuating energy of the impact to the windshield disposed in the windshield frame.

Abstract: Methods are provided for reducing the quantity of acid gas reinjected into a reservoir by partial CO2 removal processes. The methods include acid gas removal, acid gas enrichment, generation of a CO2 rich stream and an H2S rich stream, and reinjection of the H2S rich stream into the reservoir. The acid gas enrichment can be performed by a solvent-based acid gas enrichment unit, a membrane-based acid gas enrichment unit, or a combination of a solvent-based acid gas enrichment unit a and membrane-based acid gas enrichment unit. The system includes an acid gas removal unit, one or more acid gas enrichment units, and an acid gas reinjection compressor. The acid gas enrichment unit can be a solvent-based acid gas enrichment unit, a membrane-based acid gas enrichment unit, or a solvent-based acid gas enrichment unit and a membrane-based acid gas enrichment unit.

Abstract: According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy attenuating portion. The energy attenuating portion includes first and second edge sections separated by an adaptable section. The adaptable section may be rigid in a first range of directions and compressible in a second range of directions.

Abstract: Layers of plies of composite material are laid on a convex tool surface. A first layer is placed with a first ply of a first section having a gap edge adjacent a gap edge of a first ply of a second section, the edges being parallel and a contraction distance from each other. A second layer is placed with a second ply of the first section having a gap edge adjacent a gap edge of a second ply of the second section, the edges being parallel and a contraction distance from each other, the second ply of the second section overlapping onto the first ply of the first section by a splice distance. Consolidation and curing cause contraction of the layers toward the tool, allowing the adjacent gap edges of each layer to be in close proximity or in contact after moving toward each other during the contraction.

Abstract: A modal restraint system for an occupant of a seat of an aircraft. The modal restraint system includes a strap feeder unit and a strap selectively retractable into and extendable from the strap feeder unit. The strap feeder unit is adapted to switch between a plurality of modes including an unfixed mode and a fixed mode. The strap is extendable from and retractable into the strap feeder unit in the unfixed mode. The strap is substantially unextendable from the strap feeder unit in the fixed mode. The strap feeder unit is in the unfixed mode by default. The strap feeder unit is operable to switch from the unfixed mode to the fixed mode in response to a precautionary event including detection of an operational parameter that is beyond a predetermined threshold, thereby reducing freedom of movement of the occupant relative to the seat.

Abstract: According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy attenuating portion. The energy attenuating portion includes first and second edge sections separated by an adaptable section. The adaptable section may be rigid in a first range of directions and compressible in a second range of directions.

Abstract: A retractable cargo hook for aircraft is described. The cargo hook comprises a torsion spring allowing rotatable attachment to an aircraft body. An optional recessed portion of the aircraft body can house and receive the cargo hook. This can protect interior components from crashes which can push the cargo hook into the aircraft fuselage, damaging components.

Abstract: Methods and systems for recovering sulfur dioxide from a Claus unit process emissions stream are provided. The method comprises the steps of generating a process emissions stream from a thermal oxidizer or other combustion device, introducing the emissions stream to an SO2 removal system, introducing the SO2 rich stream from the SO2 removal system to a CO2 removal system, and introducing an enriched SO2 stream back to the Claus unit. The SO2 removal system can include one or more SO2 selective membranes. The CO2 removal system can include one or more CO2 selective membranes.

Abstract: According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy absorbing assembly. The energy absorbing assembly includes first and second portions and a retractable section. The retractable section may be at least partially affixed to the first portion and is configured to enable displacement of the second portion of the stabilizer with respect to the first portion.

Abstract: Methods are provided for reducing the quantity of acid gas reinjected into a reservoir by partial CO2 removal processes. The methods include acid gas removal, acid gas enrichment, generation of a CO2 rich stream and an H2S rich stream, and reinjection of the H2S rich stream into the reservoir. The acid gas enrichment can be performed by a solvent-based acid gas enrichment unit, a membrane-based acid gas enrichment unit, or a combination of a solvent-based acid gas enrichment unit a and membrane-based acid gas enrichment unit. The system includes an acid gas removal unit, one or more acid gas enrichment units, and an acid gas reinjection compressor. The acid gas enrichment unit can be a solvent-based acid gas enrichment unit, a membrane-based acid gas enrichment unit, or a solvent-based acid gas enrichment unit and a membrane-based acid gas enrichment unit.

Abstract: An emulsion separation device including a plurality of inclined plates, a buoyancy device, and an electric field generation system. Also disclosed are systems and methods for the separation of an emulsion into a continuous aqueous phase and a continuous oil phase. The systems may include: a vessel having an emulsion inlet, a continuous aqueous phase outlet, and a continuous oil phase outlet. A separation device may be disposed in the vessel, the separation device including: a plurality of inclined plates and a buoyancy device configured to maintain the plurality of inclined plates between the continuous aqueous phase and the continuous oil phase. An electric field generation system may also be provided and configured to expose the emulsion to an electric field.

Abstract: A rotorcraft includes a substantially rigid structural body. The structural body has an internal cavity and an aperture extending entirely through the structural body. The rotorcraft further includes at least one of a tail boom and a fuselage. The rotorcraft further includes a propulsion device disposed at least partially within the internal cavity and at least partially within the aperture. The propulsion device is carried by the structural body so that forces are transferred from the propulsion device to at least one of the tail boom and the fuselage via the structural body.

Abstract: According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy attenuating portion. The energy attenuating portion includes first and second edge sections separated by an adaptable section. The adaptable section may be rigid in a first range of directions and compressible in a second range of directions.

Abstract: A process for recovering a noncondensable gas from a gaseous mixture, the method comprising the steps of: supplying a gaseous mixture comprising a noncondensable component; supplying a sweep gas comprising a condensable component; introducing the gaseous mixture and the sweep gas to a swept membrane stage to obtain a retentate stream and a mixed permeate stream, the mixed permeate stream comprising at least a portion of the condensable component and at least a portion of the noncondensable component; introducing the mixed permeate stream to a vapor-liquid separator and subjecting the mixed permeate stream to thermodynamic conditions sufficient to condense most of the condensable component into a liquid, and obtain a raw noncondensable component stream, wherein the raw noncondensable component stream is enriched in the noncondensable component; and introducing the raw noncondensable component to a concentration unit to obtain a noncondensable component product stream enriched in the noncondensable component.

Abstract: A modal restraint system for an occupant of a seat of an aircraft. The modal restraint system includes a strap feeder unit and a strap selectively retractable into and extendable from the strap feeder unit. The strap feeder unit is adapted to switch between a plurality of modes including an unfixed mode and a fixed mode. The strap is extendable from and retractable into the strap feeder unit in the unfixed mode. The strap is substantially unextendable from the strap feeder unit in the fixed mode. The strap feeder unit is in the unfixed mode by default. The strap feeder unit is operable to switch from the unfixed mode to the fixed mode in response to a precautionary event including detection of an operational parameter that is beyond a predetermined threshold, thereby reducing freedom of movement of the occupant relative to the seat.

Abstract: A windowed structure includes a body having a frame with an outer wall extending between a first end and a second end. An inner wall extends from the outer wall. The inner wall is connected to the outer wall at the first end to define a proximal joint of the body delimiting a window opening extending through the body. A window element covers the window opening and defines an outer window surface and an inner window surface. The window element has an overlap segment overlaying the outer wall and attached thereto. An unobstructed portion of the window element is defined between the overlap segment and is unobstructed by the frame between the proximal joint.

Abstract: A modal restraint system for an occupant of a seat of an aircraft having a mechanical failure sensor includes a strap feeder unit and a strap selectively retractable into and extendable from the strap feeder unit. The strap is positionable adjacent to the occupant. The strap feeder unit is adapted to switch between a plurality of modes including an unfixed mode and a fixed mode. The strap is extendable from and retractable into the strap feeder unit in the unfixed mode. The strap is substantially unextendable from the strap feeder unit in the fixed mode. The strap feeder unit is in the unfixed mode by default. The strap feeder unit is operable to switch to the fixed mode in response to a precautionary event including detection of an aircraft mechanical failure by the mechanical failure sensor, thereby reducing freedom of movement of the occupant relative to the seat.