Abstract: A system may include a laser source, an acousto-optic modulator (AOM) coupled to the laser source, an atom trap, and at least one optical medium coupled between the AOM and the atom trap. Furthermore, at least one piezoelectric transducer may be coupled to the at least one optical medium, and a beam polarization controller may be coupled to the at least one piezoelectric transducer.

Abstract: Described herein are compositions composed of micronized placental components and pharmaceutical compositions thereof. The compositions have numerous medical applications. Methods for making and using the micronized compositions are also described herein.

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: 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: 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: A remodel nail plate and installation system for a remodel nail plate adapted to protect wires, other utility support cables, and/or plumbing pipes from damage. The remodel nail plate is for insertion between a wall stud and an outer wall that is already attached to the stud, as may be the case when remodeling a home. The nail plate includes a contact edge which may be contacted with a hammer, or interstitially with an installation tool. The remodel plate is adapted to be inserted by hammering, or otherwise inserting, a plate surface between the exterior wall and the stud alongside a retrofitted cable insertion, such as a power cable.

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: A locking apparatus with enhanced strength for use with a safe having a pivotably mounted door is provided. The locking apparatus includes a cam rotatably mounted to the door's rear wall and positioned within an internal cavity of the safe in the closed position, a plurality of arm members slidably mounted to the cam, and a shaft coupled to the cam. The shaft is maneuvered to rotate the cam in a first direction to permit the arm members to adjust to an extended position beyond a perimeter of the door within the safe's internal cavity, thereby locking the door in the closed position. The shaft is maneuvered to rotate the cam in a second direction to permit the arm members to adjust to a retracted position within the perimeter of the door, thereby unlocking the door and allowing pivotal movement of the door to the open position.