A system may include a door installed within a vehicle. The system may further include an electronically actuated linear actuator latch mechanism (a) installed in or on the door or (b) installed within the vehicle in proximity to the door. The electronically actuated linear actuator latch mechanism may be configured to cause the door to be in a latched state and to cause the door to be in an unlatched state.

Fixed-wing short-takeoff-and-landing aircraft and related methods. The aircraft comprise an airframe comprising a rear wing assembly and a forward wing assembly positioned forward of the rear wing assembly, a rear plurality of blowing rotor assemblies operatively coupled to the rear wing assembly that are configured to blow air across the rear wing assembly to induce lift in the rear wing assembly, and a forward plurality of blowing rotor assemblies that are operatively coupled to the forward wing assembly and configured to blow air across the forward wing assembly to induce lift in the forward wing assembly. The methods comprise inducing lift in a forward wing assembly by blowing air across the forward wing assembly with a forward plurality of blowing rotor assemblies and inducing lift in a rear wing assembly by blowing air across a rear wing assembly with a rear plurality of blowing rotor assemblies.

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.

Systems and methods are provided for trimming and installation. One embodiment is a system for cutting out portions of a fuselage section. The system includes an Inner Mold Line (IML) tool comprising an inner gripping element configured to apply suction to a portion of the fuselage section, and further comprising an outer gripping element configured to apply suction to an area surrounding the portion, an Outer Mold Line (OML) tool configured to operate a cutter to cut the portion out from the fuselage section while suction is applied to the portion and to the area surrounding the portion, and a track that is disposed between the IML tool and the OML tool, wherein the fuselage section is configured to be pulsed in a process direction along the track, such that the fuselage section remains disposed between the IML tool and the OML tool when pulsed in the process direction.

Methods and structures are disclosed. An example method includes: rotating a tubular mandrel about a longitudinal axis of the tubular mandrel; depositing a composite material on an inner surface of the tubular mandrel to form a composite tubular member on the inner surface of the tubular mandrel; inserting and expanding an inner expandable mandrel within the composite tubular member to cause the inner expandable mandrel to press the composite tubular member against the inner surface of the tubular mandrel; curing the composite tubular member; removing the inner expandable mandrel; placing a frame within the composite tubular member; and removing the tubular mandrel so as to obtain the composite tubular member with the frame placed therein.

A tank that may be used in combination with an actuating means such as a pneumatic door actuator includes a first, inner, enclosure positioned and enclosed within a second, outer, enclosure, to provide an enclosed chamber between the inner enclosure and outer enclosure. The pressure in the chamber may be measured with a gauge that does not extend into the inner enclosure. The measured pressure may then be monitored and compared in order to detect a change in pressure and thereby also detect a leak through a wall from the inner enclosure. The tank may also be used to inflate and/or deploy an emergency evacuation slide in an aircraft.

An aircraft door mechanism includes an aircraft structure (14) delimiting an opening (24); an aircraft door (26) movable between a position closing off the opening (24) and a released position of the opening (24); and a guide system (28) for moving the door (26) between the closed off and released positions. The guide system (28) includes a main rail (46) that is fixed relative to the structure and a main carriage (48) mechanically connected to the door (26) and able to slide on the main rail (46) during the movement between said closed off and released positions. The main rail (46) is positioned between the door (26) and the structure during at least part of the movement of the door (26) between said closed off and released positions.

A device includes a drive link coupled to an actuator and a first link coupled to the drive link, the first link and the drive link forming a first pivot point. The device also includes a second link coupled to the first link and a support shaft coupled to second link. The second link and the first link form a second pivot point and the second link is configured to rotate about the support shaft. The device further includes a third link coupled to the second link and includes a fourth link coupled to third link and coupled to a door assembly. The third link and the second link form a third pivot point, and the fourth link and the third link form a fourth pivot point. When the door assembly is in an open position, the support shaft, the third pivot point, and the fourth pivot point are aligned.

Cradle assemblies for supporting a door for uninstalling and/or installing the door to a fuselage of an aircraft, and arrangements and methods for the same are provided. In one example, a cradle assembly includes a first contoured board and a second contoured board that is spaced apart from the first contoured board. The first and second contoured boards are cooperatively configured to support outer sections of a first door. A third contoured board is configured to be selectively positioned adjacent to and extending higher than the first contoured board to support a first outer section of a second door that has a different outer shape than the first door. The third contoured board is contoured to substantially match the first outer section of the second door. The cradle assembly is configured to be positioned proximate to the fuselage.

A hydrogen accumulation control system for monitoring and controlling leaked hydrogen within an interior space, in particular of an aircraft, includes a hydrogen detection system installed within the interior space to detect the presence of gaseous hydrogen in the interior space and to provide occurrence data on the detected hydrogen within the interior space, a system control configured to assess the occurrence data and to determine and initiate a remedial procedure for reduction of the detected hydrogen within the interior space, and a venting system configured to vent the interior space from the detected hydrogen according to the remedial procedure.