An aircraft safety lifesaving system, disclosing an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land; a damping and buffering mechanism provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body. A safety cabin is provided at the top of the aircraft body, and a deceleration device in the safety cabin is ejected in an emergency to assist the aircraft body to decelerate; the damping and buffering mechanism extends below the wheel body, and the damping and buffering mechanism contacts with the ground first.

An aircraft safety lifesaving system, which includes an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land; a damping and buffering mechanism is provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body.

A hatch locking device for an aircraft hatch includes an eccentric bush which can be connected to a hatch bulkhead of the aircraft hatch panel, an inner lining which is introduced into the eccentric bush and has a bolt receptacle which is oriented centrally along a bolt receptacle axis for receiving a locking bolt, a conical pressing sleeve in the inner lining, a conical clamping sleeve, the outer conical shell face of which is in displaceable engagement with an inner conical shell face of the conical pressing sleeve, and the inner cylindrical shell face of which is flush with the outer wall of the bolt receptacle, and linear actuators which are mounted on in each case two opposite sides of the conical pressing sleeve in the inner lining and are designed to displace the conical pressing sleeve along the bolt receptacle axis with respect to the conical clamping sleeve.

An assembly for arming/disarming a slide of an airplane door according to the invention comprises a system with two releasable connection mechanisms (2) linked with the door (1) and a cabin floor of the airplane, each mechanism (2) comprising a releasable connector (21b) secured to the door (1), extending at right angles to the floor on each side of a door bottom, and an anchor fitting (22b) fixed to the cabin floor. Each connector (21b) is equipped with an elastic centering element (70) and a locking/unlocking grab (25b) on the corresponding anchor fitting (22b), the connectors (21b) being linked by a girt bar (5). Each grab (25b) being rotationally mobile, one of the grabs (25b) is driven by a single command (5; 25b) which drives the other grab in rotation via the girt bar (5).

An emergency exit system comprising a first primary structure frame, a second primary structure frame extending substantially parallel to the first primary structure frame, a door opening arranged between the first primary structure frame and the second primary structure frame, and a door shiftable substantially parallel to the first primary structure frame and the second primary structure frame between a closed position and an open position. In the closed position, the door closes the door opening. In the open position, the door opens up the door opening. At least one of the primary structure frames comprises a primary structure guide element for guiding the door when the door is shifted between the closed position and the open position.

A seal is disclosed having a pair of side walls, a base extending between the side walls, a first concave surface extending inwardly from one of the side walls, a second concave surface extending inwardly from the other side wall, and a convex surface extending between the first concave and second concave surface to form a rounded peak having an apex. The seal has a seal width defined between the seal side walls, and a seal height defined between the apex of the rounded peak and the base. The width is at least twice the height of the seal. The seal is located in a channel recess of a first component opposite a second component to seal between the first component and the second component, the channel recess having a floor and a height defined between the floor and a surface of the first component in which the channel recess is formed.

The invention relates to an aircraft door having a support arm (6) connected to a support forearm (9) by a first pivot connection (7) about a first pivot axis (8), the support forearm (9) being connected to the leaf (5) by a second pivot connection (10) about a second pivot axis (11) parallel to the first pivot axis (8). The support arm (6) is connected to the door frame (4) by two hinges (13, 14) each having a pivot (26, 27) for rotating the support arm (6) about a third pivot axis (12) which is parallel to the first pivot axis (8) and to the second pivot axis (11), this pivot (26, 27) being connected to the door frame (4) by an attachment (22, 23) that is translatably adjustable in two directions (35, 37, 43, 47) orthogonal to one another and orthogonal to the third pivot axis (12).

The present disclosure is directed to a bi-fold door system, apparatus, or device including a first panel, a second panel, and a center post. When in a fully closed position, the bi-fold door limits access to a lavatory on an aircraft, and, alternatively, when in a fully opened position, the bi-fold door allows or provides access to the lavatory on the aircraft. When in the closed position, a user within the lavatory may lock the bi-fold door in the closed position by stepping on a foot pedal at an interior of the bi-fold door. The foot pedal mechanically cooperates with a lock rod and an escapement mechanism the user stepping on the foot pedal moves the lock rod from a retracted position to an extended position locking the bi-fold door in the closed position. To exit the lavatory, the user may unlock the bi-fold door utilizing the foot pedal and then interact with a hands-free actuation mechanism to move the bi-fold door from the closed position to the opened position. When in the opened position, the bi-fold door may be held open for a selected period of time such that the user may exit the lavatory without physically contacting the bi-fold door.

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.

An apparatus comprises a composite sandwich panel, a seal, and a hinge. The composite sandwich panel has a first edge in a first over-crush edge region, wherein a thickness of the composite sandwich panel decreases within the first over-crush edge region in a direction towards the first edge. The seal is bonded to the first over-crush edge region of the composite sandwich panel and extending past the first edge. The hinge is connected to the composite sandwich panel such that an axis of rotation of the hinge is positioned over the first over-crush edge region of the composite sandwich panel.