Abstract: Ingestible devices can directly deliver therapeutic agents to desired tissue(s) of the GI tract of a subject, such as the submucosa, the mucosa, and/or the mucus layer of the GI tract, and methods of using the same. The ingestible devices can deliver therapeutic agents in a safe, effective, and reliable manner. The disclosure also provides pharmaceutical compositions for use in methods of treating a disease or condition in a subject in need thereof.

Abstract: According to one aspect, a power storage system may include an enclosure, and one or more modules disposed in the enclosure. Each of the one or more modules may include a plurality of electrochemical cells electrically coupled to one another, each one of the plurality of electrochemical cells including an oxygen evolution electrode (OEE), an anode, a gas diffusion electrode (GDE), an electrolyte, and a vessel and, within the vessel, the OEE, the anode, and the GDE at least partially immersed in the electrolyte.

Abstract: According to an aspect, an electrochemical cell may include a vessel, at least two instances of an anode assembly, at least two instances of an oxygen evolution electrode (OEE), and a gas diffusion electrode (GDE). In the vessel, the GDE may be disposed between mirrored arrangements of the at least two instances of the OEE and the at least two instances of the anode assembly.

Abstract: An aircraft system for an aircraft is disclosed having a controller that is configured, during a take-off procedure, to initiate, prior to receiving a command to retract a landing gear, automatic opening of a landing gear bay door associated with the landing gear from a closed position towards an open position, on the basis of a determination, made when a speed of the aircraft is determined by the controller to be equal to or greater than a first threshold speed, that a one engine inoperative condition is met.

Abstract: An aircraft system for an aircraft, the aircraft system including a controller configured, during a take-off procedure, to determine that a one engine inoperative condition is met and determine that a predetermined take-off criterion is met. The controller is configured, on the basis of a determination that the one engine inoperative condition is met, and prior to receiving a command to retract a landing gear of the aircraft, to initiate automatic opening of a landing gear bay door associated with the landing gear from a closed position towards an open position when the controller determines that the predetermined take-off criterion is met, and inhibit the automatic opening when the controller determines that the predetermined take-off criterion is not met.

Abstract: An aircraft door controller 100 including a receiver 110 configured to receive a command 14 to move an aircraft door between an open position and a closed position relative to a door frame. The aircraft door controller 100 is configured to not store the command 14 when power to move the aircraft door between the open position and the closed position relative to the door frame is unavailable.

Abstract: A hang tab and product tag assembly comprising a first panel, a second panel, and a third panel. The first panel includes an aperture configured to engage with a retention mechanism, the second panel includes an aperture that is configured to adjust to different dimensions.

Abstract: A tooling installation system having unique tools which provide an external force directly to the sleeve end of a faster to create a bulb on the sleeve of the fastener is provided. The system provides external forces directly to the sleeve end of the fastener deforming a portion of the sleeve radially outward and onto the structure prior to swaging a second portion of the sleeve radially inward onto the pin. Additionally, the system controls formation of the sleeve by capturing an external portion of the sleeve creating a cavity between the tool and the structure for achieving proper bulb formation during installation prior to swage. The system also provides specific forces to the head of the pin and the head of the sleeve to insure proper seating of the fastener head against the structure inducing residual compressive stresses within the structure, thus improving mechanical properties such as fatigue life of the structure.

Abstract: A hang tab and product tag assembly comprising a first panel, a second panel, and a third panel. The first panel includes an aperture configured to engage with a retention mechanism, the second panel includes an aperture that is configured to adjust to different dimensions.

Abstract: An aircraft door controller 100 including a receiver 110 configured to receive a command 14 to move an aircraft door between an open position and a closed position relative to a door frame. The aircraft door controller 100 is configured to not store the command 14 when power to move the aircraft door between the open position and the closed position relative to the door frame is unavailable.

Abstract: A method for displaying an item includes providing a hang tab and product tag assembly including a first panel, a second panel, and a third panel. The method includes inserting at least a portion of the item through an aperture of the second panel; stretching the second panel to change a size of the aperture and allowing the aperture to conform to dimensions of the portion of the item; inserting at least a portion of a retention mechanism through an aperture of the first panel; and suspending the first panel from the retention mechanism such that the first panel extends at a first angle relative to the second panel, and such that the second panel extends at a second angle relative to the third panel.

Abstract: The present invention provides a landing gear assembly for an aircraft landing gear, the assembly comprising a steering mechanism for steering at least one wheel of the landing gear, a deployment mechanism for moving a leg of the landing gear between a stowed position and a deployed position, and an actuator arranged to actuate both the steering mechanism and the deployment mechanism. The invention also provides an aircraft landing gear, an aircraft and methods of operating an aircraft landing gear.

Abstract: A hang tab and product tag assembly including a first panel, a second panel, and a. The first panel includes an aperture configured to engage with a retention mechanism, and the second panel includes an aperture that is configured to adjust to different dimensions.

Abstract: A hang tab and product tag assembly comprising a first panel, a second panel, and a third panel. The first panel includes an aperture configured to engage with a retention mechanism, the second panel includes an aperture that is configured to adjust to different dimensions.

Abstract: A tooling installation system having unique tools which provide an external force directly to the sleeve end of a faster to create a bulb on the sleeve of the fastener is provided. The system provides external forces directly to the sleeve end of the fastener deforming a portion of the sleeve radially outward and onto the structure prior to swaging a second portion of the sleeve radially inward onto the pin. Additionally, the system controls formation of the sleeve by capturing an external portion of the sleeve creating a cavity between the tool and the structure for achieving proper bulb formation during installation prior to swage. The system also provides specific forces to the head of the pin and the head of the sleeve to insure proper seating of the fastener head against the structure inducing residual compressive stresses within the structure, thus improving mechanical properties such as fatigue life of the structure.

Abstract: A self-integrating insert sleeve assembly, comprising an insert sleeve and an expander pin, for insertion into an aperture of a work piece is provided. Upon installation, the insert sleeve component is incrementally expanded by interaction with the pin, and secured to the aperture of the work piece, such that the resulting aperture of the installed insert sleeve has a predetermined diameter, and the resulting structure now contains compressive residual stresses. Thus, the installed insert sleeve may be employed as a hole repair solution, allowing for the installation of an original size fastener per structural design within a damaged and reconditioned aperture, or simply for enhanced structural fatigue life. The installation of this insert sleeve may be done through various manners, including pull type, push type, and blind type installation processes.

Abstract: The present invention provides a landing gear assembly for an aircraft landing gear, the assembly comprising a steering mechanism for steering at least one wheel of the landing gear, a deployment mechanism for moving a leg of the landing gear between a stowed position and a deployed position, and an actuator arranged to actuate both the steering mechanism and the deployment mechanism. The invention also provides an aircraft landing gear, an aircraft and methods of operating an aircraft landing gear.

Abstract: An actuator is arranged to move an aircraft component such as a landing gear leg, flap or aileron between a first position and a second position, net load from external forces acting on the aircraft component tending to drive it towards the first position. The actuator comprises a threaded screw and a threaded nut. A main prime mover is configured to apply torque to the screw or nut acting in opposition to the net load under normal operating conditions. An emergency prime mover is configured to apply torque to the screw or nut acting in the same sense as the net load under emergency operating conditions in which the interface between the nut and the screw has become partially jammed to the extent that the component cannot be moved from the second position to the first position by operation of the net load alone.

Abstract: A linear actuator has a housing, a piston slideable within the housing along a slide axis, a first shaft rotatable about a first axis substantially perpendicular to the slide axis, a second shaft rotatable about a second axis parallel to the slide axis, in which the second shaft and the piston are engaged to convert rotational motion of the second shaft into linear motion of the piston, and in which the first shaft and the second shaft are engaged by a ball-worm gear.

Abstract: An actuator is arranged to move an aircraft component such as a landing gear leg, flap or aileron between a first position and a second position, net load from external forces acting on the aircraft component tending to drive it towards the first position. The actuator comprises a threaded screw and a threaded nut. A main prime mover is configured to apply torque to the screw or nut acting in opposition to the net load under normal operating conditions. An emergency prime mover is configured to apply torque to the screw or nut acting in the same sense as the net load under emergency operating conditions in which the interface between the nut and the screw has become partially jammed to the extent that the component cannot be moved from the second position to the first position by operation of the net load alone.