An electro-mechanical unlocking device that includes a locking state, a holding state and an unlocking state. The unlocking device includes an arming solenoid and a holding solenoid. In the locking state the arming solenoid moves an arming assembly, which moves a crank and which moves a holding armature from a second position to a first position. In the holding state the holding solenoid is energized and the arming solenoid is de-energizing, which allows the arming armature to moves from the first position to the second position. In the unlocking state the holding solenoid is de-energized, which allows the holding armature and the arming link to move from the first position to the second position. In the locking and holding states a sear blocks the path of the striker and in the unlocking state the sear does not block the path of the striker.

A mobile machine includes a fuselage having at least one door, inside which is located a unit for processing measurements taken by at least one measurement device installed outside said fuselage. The system for communication between the processing unit and the measurement device includes a flex circuit that is affixed at least partially flat in the door corner between the door and the rim of the opening formed in the fuselage with which the door is associated and one of the ends, the internal end, of which is located inside the fuselage and the other, external, end of which is located outside. Since the flex circuit makes it possible to pass through the wall of the fuselage via the opening for doors, the need to make substantial modifications to the aircraft is avoided.

Disclosed is a method of forming a composite door. A precursor frame sheet, comprising flaps, is formed by cutting a prepreg sheet. The precursor frame sheet is draped over a door-forming tool, comprising a frame face and flap supports, non-parallel to the frame face, such that each of the flaps of the precursor frame sheet is geometrically complementary with a corresponding one of the flap supports. A composite frame is formed by curing the precursor frame sheet, draped over the door-forming tool, wherein the composite frame comprises a first rail and a second rail. The composite frame is separated from the door-forming tool. The composite frame, first composite edge fittings, second composite edge fittings, a first composite side beam, a second composite side beam, and a composite skin are interconnected. The first composite side beam comprises a first-beam base and two first-beam sides, non-parallel to the first-beam base, and connecting the first composite side beam to the composite frame comprises connecting a first one of the two first-beam sides to the first rail.

Disclosed is an aircraft piston assembly, having: a piston housing fluid port formed in a piston housing; a piston shaft, disposed within the piston housing, configured for translation in either forward or aft directions when fluid is respectively supplied to or removed from the piston housing; a screw shaft, disposed within the piston housing, that includes a first gear that rotates without translation while the piston shaft translates; and a slider, disposed within the piston housing, that includes a second gear, and that is configured for translation without rotation, wherein: the slider moves between a first position where the first gear and the second gear are separated from one another to allow the piston shaft to translate and a second position where the second gear surrounds the first gear so that the first and second gears are engaged with one another and the piston shaft is prevented from translating.

A system comprises a door including a latch assembly configured to latch the door to a doorframe in a closed position of the door. An latch actuator is operatively connected to the latch assembly to drive the latch assembly to latch and unlatch the door. A exterior touchless sensor operatively connected to the actuator to cause the actuator to unlatch the latch assembly upon receipt of touchless input from a user.

An isolation section assembly includes a section housing defining an interior space. The section housing includes a door with access to the interior space. The isolation section assembly includes an enclosure abutting the door. The airlock enclosure defines an interior airlock space. The interior airlock space is configured and adapted to be at a negative pressure relative to a cabin area. An air recirculation system in fluid communication with at least one of the interior space of the section housing or the interior airlock space.

A door damper assembly that includes a housing, a damper that includes a fixed end and a movable end disposed within the housing, a carriage assembly that is movable within the housing between a closed position and an open position, a claw assembly pivotably attached to the carriage assembly, and a spring positioned to bias the carriage assembly to the closed position. The movable end of the damper is secured to the carriage assembly. The claw assembly is movable with the carriage assembly between the closed position and the open position. The claw assembly is movable relative to the carriage assembly between a non-toggle position and a toggle position. The claw assembly includes a pin receiving space defined therein that defines a claw axis that is generally vertical when the claw is in the non-toggle position and not vertical when the claw assembly is in the toggle position.

A system may wirelessly supply electrical power to an aircraft cabin component which moves relative to another aircraft cabin component. A first aircraft cabin component may include a solid state electrical power transmitter having an induction loop. The second aircraft cabin component may include a solid state electrical power receiver having a receiving coil. When a power source is connected to the solid state electrical power transmitter, the induction loop creates an oscillating magnetic field which passes through the receiving coil and induces a flow of alternating current through the receiving coil which drives the load.

An aircraft including a support structure, an outer skin connected to the support structure, a first port extending through the outer skin and defining a first break in the support structure. The aircraft also includes a first receptacle attached to the support structure proximate the first port and defining a first opening, a ball-mounted sensor assembly received in the first receptacle and extending downward from the outer skin, a second port extending through the outer skin and defining a second break in the support structure, a second receptacle attached to the support structure proximate the second port and defining a second opening. A method of retrofitting an aircraft to accommodate a ball-mounted sensor assembly and a payload is also disclosed.

A lavatory door system for a vehicle, in particular an aircraft, with a lavatory door; a pneumatic actuator configured to open and close the lavatory door based on a differential pressure, wherein the pneumatic actuator is coupled to a vacuum toilet system of the vehicle to generate the differential pressure; and an operating interface configured to receive a user control operation and to selectively release the differential pressure from the vacuum toilet system for operation of the pneumatic actuator based on the received user control operation.