A door arrangement for an aircraft comprising a door designed to close an aperture in an outer skin of the aircraft, and a articulated arm which is fixed by a first end to the door and which is designed to move the door in at least two translational directions and at least two rotational directions. An aircraft area with this door arrangement and an aircraft having such an aircraft area are furthermore provided. The aircraft area comprises a door aperture arranged in an outer skin of an aircraft, and a door arrangement. Here the door of the door arrangement may be designed to close the door aperture from an inside of the outer skin, and the articulated arm of the door arrangement may be fixed to the aircraft area.

Apparatus, systems, and methods for selectively locking and unlocking a passenger door. The apparatus includes a first shaft, having a first longitudinal centerline, and a member, connected to the first shaft. A handle is connected to the first shaft via the member, the handle being movable via rotation of the first shaft from a locked position and an unlocked position. A first protrusion extends from the handle and a latch crank is connected to the second shaft. A second protrusion extends from the latch crank and a linkage is connected between the latch crank and the member. When the handle in the locked position, the first protrusion is positioned adjacent to the second protrusion to prevent rotation of the second shaft. When the handle is in the unlocked position, the first protrusion is positioned away from the second protrusion to enable the second shaft to rotate.

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.

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).

There is provided a door mechanism comprising a door and a door closure mechanism for moving the door between a first, open, position and second, closed position. The door closure mechanism comprises a drive motor coupled to a drive screw, the drive screw having a first, right handed thread portion and a second, left handed thread portion, a first drive nut threadedly engaged with the first thread portion, a second drive nut threadedly engaged with the second thread portion, a first drive linkage pivotally coupled to the first drive nut at one end and to the door at a second, opposed end, and a second drive linkage pivotally coupled to the second drive nut at one end and to the door at a second, opposed end.

Methods, apparatus, systems and a vertical take-off and landing (VTOL) vehicle are provided. The VTOL vehicle includes: a fuselage having longitudinally a front section, a central section and a rear section; a first lifting surface comprising two wings respectively secured to opposite sides of the rear section of the fuselage; a second lifting surface comprising two wings respectively secured to opposite sides of the front section of the fuselage; where each wing comprises at least one engine module, each of the engine modules being pivotally coupled to the wing and each engine module being independently controlled for transitioning between a vertical mode of flight and a horizontal mode of flight.

An aircraft cabin section includes a door frame, which forms a door opening, a passenger door, which is arranged on the door frame and is configured to close the door opening, and a door insulation arrangement, which is larger in at least one direction than the door opening. The door insulation arrangement is produced from a textile which is heat-insulating and/or airflow-inhibiting. Furthermore, a corresponding door insulation arrangement and an aircraft having such an aircraft cabin section or such a door insulation arrangement are disclosed.

A lock module for a door in an aircraft has a lock with a blocking element and a non-self-locking drive for moving the blocking element. A blocking sensor detects a blocked position and an unblocked position of the blocking element. A control unit receives a blocking signal from the sensor and activates the drive based on the blocking signals of the blocking sensor(s). A module portion of the door leaf has at least the lock, the drive, and the blocking sensor structurally integrated therein. There is also described a door for the space with a lock module where the door leaf of the door contains the module portion, and a space of an aircraft which is closed by the door.

The present invention relates to a hybrid VTOL jet car comprising a light weight floatable chassis adapted for carrying a payload, a retractable tail section attached to a light weight floatable chassis at rear end adapted for stabilizing the hybrid VTOL jet car, a plurality of wheels at the bottom of the hybrid VTOL jet car, a plurality of retractable wings on the sides of light weight floatable chassis, adapted for manoeuvring the hybrid VTOL jet car. Disclosed embodiments further comprising a plurality of thrust-producing engines adapted for generating the thrust required for driving the hybrid VTOL jet car on a surface as well as in the air and a plurality of parachutes attached to the hybrid VTOL jet car to safely land the hybrid VTOL jet car under emergency.

An aircraft with a fuselage and at least one emergency exit system, the at least one emergency exit system including a jettisonable component that is accommodated and locked in an associated frame structure of the aircraft in normal operation mode to form a portion of the fuselage and that is releasable from the associated frame structure for being jettisoned from the aircraft in an emergency mode; and further including an emergency evacuation assistance device that is adapted to assist in an emergency evacuation of the aircraft via the associated frame structure in the emergency mode; wherein the emergency evacuation assistance device is attached to the jettisonable component such that the emergency evacuation assistance device is deployed by means of the jettisonable component when the jettisonable component is jettisoned from the aircraft in the emergency mode.