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 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.

The invention relates to a hinge (10) comprising a swivellable hinge part (12), a stationary hinge part (14) and a tensionable spring element (34), wherein the stationary hinge part (14) is designed with a first bearing (16) as well as a second bearing (18), wherein the bearings (16, 18) have swivel axes (S1, S2) that are offset to one another. According to the invention, the swivellable hinge part (12) is mounted on the stationary hinge part (14) via the first bearing (16) such that it can swivel about a swivel axis (S1), and the tensionable spring element (34) is arranged on the stationary hinge part (14) via the second bearing (18).

A negator spring tool for winding a negator spring output drum around a rotational axis includes: a pair of tool handles; and a tool disk having an outer edge which is generally circular except for a cutout. The tool disk is configured to be releasably attached to the output drum. The tool disk has a drum-facing side which includes protruding teeth protruding from the drum-facing side to engage radial spokes of the output drum. The outer edge of the tool disk includes handle slots which are spaced circumferentially. The distal end of each tool handle is insertable into a handle slot to rotate the tool disk around the rotational axis. The protruding teeth of the tool disk each having a T-shaped cross section, each T-shaped protruding tooth and the drum-facing side forming an I-shaped cross section having two opposite facing cavities on two opposite sides of the I-shaped cross section.

An actuator includes a piston assembly movably disposed within an assembly housing having a fixedly supported end and an opposing end that receives a movable piston assembly. The piston assembly includes a piston rod and an attached piston head having a fixed orifice as well as an orifice with a check valve to create rate control of the assembly. Hydraulic fluid is caused to move through the axially movable piston head based on compressive and tensile loads imparted to the assembly. A plurality of pre-loaded springs are configured to selectively provide pressure relief in the event the orifices of the piston become clogged, wherein the plurality of pre-loaded springs, such as disc springs, further provide an energy absorbing function of the assembly based on loading conditions.

A vertical take-off and landing (VTOL) aircraft provides transportation to users of a network system. The network system may include multiple aircraft or other types of vehicles to provide multi-model transportation. An aircraft may include a fuselage, a truss coupled to the fuselage, and multiple distributed electric propellers coupled to the truss. The distributed electric propellers may be positioned on at least two different planes. The fuselage may include a cabin having one or more seats for the passengers arranged in a configuration that has a compact footprint, provides legroom, provides visibility to surroundings of the aircraft, or facilitates convenient ingress or egress of passengers. The aircraft may open a port cabin door and starboard cabin door for simultaneous ingress or egress of passengers.

This application teaches a flush mount, quick inspection portal for aircraft. An object of the invention is to provide a flush inspection portal that will allow quick access into inspection areas. Another object of the invention is to reduce the number of man hours required for periodic inspection of aircraft. Another object of the invention is to reduce the number of man hours required for periodic inspections. Another object of this invention is to provide a flush inspection portal that is durable against extreme temperature changes and vibrations. Another object of the invention is to provide inspection portals that may replace cover plates as an after factory add on or in manufacturing.

A locking device for locking a first component to a second component, the device having: a catch element for fastening to the first or second component; a latching unit for fastening to the second or first component; the latching unit comprising a release element; and the release element can be moved between a rest position, which arranges the first latching body in the first latching recess of the catch element and in the receiving opening of the release element, and a release position, which releases the engagement between the first latching body and the first latching recess of the catch element.

A storage compartment for the overhead region of a passenger cabin of a passenger aircraft has a carrier which can be mounted in the passenger aircraft, and a pivoting part for receiving a storage item. The pivoting part is mounted on the carrier so as to be pivotable about a pivot axis in a pivoting region between an open position and a closing position. The storage compartment further contains a closing force module. The closing force module contains a switching module by which the closing force module can be brought into an active state or into a passive state. In the active state, a greater closing moment is brought about in the direction of the closing position on the pivoting part by the closing force module, at least in a partial region of the pivoting region, than in the passive state. The closing force module is configured free from electricity with respect to the generation of the closing moment and/or with respect to the switching over between the active state and passive state.

A locking mechanism for a door panel to be positioned within and out of blocking relationship with an opening. Mechanism includes a deadbolt rotatably connected to the wall and having a curved configuration and a locking bracket connected to the door panel. The locking bracket extends from the door panel in an angular direction with respect to a plane of door panel. With door panel in a closed position and deadbolt in a first position, the locking bracket extends through the curved configuration. Deadbolt is in blocking relationship with the locking bracket in a direction along a plane of the door panel and is not in blocking relationship in a direction along the locking bracket. With door panel in closed position, deadbolt is in a second position not in blocking relationship with the locking bracket permitting door panel to move in a direction along a plane of the door panel.