The handle attachment includes a base portion that can be attached to a portion of a wall surface of a door, a flap portion that applies, as a result of a pulling operation, a pulling force to the door via the base portion, a flap rotation mechanism that rotatably connects the flap portion with respect to the base portion around a rotation axis, and a biasing member that biases the flap portion in a first rotation direction around the rotation axis with respect to the base portion. The flap portion includes a base end portion connected to the flap rotation mechanism and a distal end portion arranged at a position away from the flap rotation mechanism. The first rotation direction is a direction in which the distal end portion of the flap portion separates from the wall surface of the door.

A short term, autonomous, electrical power supply system, particularly an emergency short term, autonomous, electrical power supply system. Said system comprises an actuator with an electrical motor (14), an electrical generator (15) for driving said electrical motor (14) of said actuator, a turbine (13) in driving engagement with said electrical generator (15), an generator (7) of combustible, fluidic energy, a fluid line (10) from said generator (7) to said turbine (13), a control unit (5), and an igniter (9) arranged inside said generator (7) and controlled by said control unit (5).

An emergency opening device of an aircraft door including a tubular actuating member (2); a resilient compression device; a retaining member for retaining the tubular actuating member (2), having a retaining wire (12) which, when the tubular actuating member (2) is in the retracted position, is held taut between a first attachment (14, 17) and a second attachment (16, 18); a release device which includes a cutting member (22) for transversely cutting the retaining wire (12).

In one embodiment, an apparatus includes a collapsible workstation assembly to be used in a temporarily-mounted control system of an aircraft. The collapsible workstation assembly is mounted to a floor of the aircraft via one or more mounting plates and one or more adaptive floor plates. The collapsible workstation assembly includes a number of modules for display and user controls. Each of the modules are connected via hinges and hinge locks to be moved between a deployed position for use and a stowed position when not in use. The collapsible workstation assembly is further connected to an observer chair assembly and a temporary door plug.

In an example, method for locking/unlocking a structure is described. The method includes attaching a first end of a pawl to a support assembly, wherein the pawl comprises a shape memory alloy (SMA) element configured to transition between a first configuration and a second configuration, and wherein the pawl is attached to the support assembly such that a second end of the pawl is movable between a locked position that prevents a rotatable shaft from rotating and an unlocked position that allows the rotatable shaft to rotate, activating the SMA element, thereby causing the SMA element to take on the first configuration and move the second end of the pawl to the locked position, and deactivating the SMA element, thereby causing the SMA element to take on the second configuration and move the second end of the pawl from the locked position to the unlocked position.

A monitoring device for monitoring a movement profile of a user in the region of an actuating element of an aircraft or spacecraft, having at least one movement sensor which is configured to detect a first monitoring space of the monitoring device and at the same time a second monitoring space of the monitoring device which differs from the first monitoring space. Also a method for monitoring a movement profile of a user in the region of an actuating element of an aircraft or spacecraft, with: detection of a first monitoring space of the monitoring device by at least one movement sensor; and simultaneous detection of a second monitoring space, which is different from the first monitoring space, by the at least one movement sensor.

An aircraft electric door including a locking system for actuating a safety catch for locking the door, a system for moving the door between open and closed positions, and a single electric motor for actuating both the locking system and the system for moving the door.

A connecting mechanism between an aircraft door and a structure of the aircraft, a related aircraft and method are provided. The connecting mechanism includes an arm intended to be hinged on to the structure, a rotating connection between the door and the arm. The rotating connection may be disengaged from a connection configuration for connecting the door with the arm in an open position of the door, into an uncoupling configuration for uncoupling of the door from the arm, in a closed door position of the door.

A vertical takeoff and landing aircraft is described in which rotors can be disposed underneath the booms. This will allow for zero downward force resulting from thrust on the aircraft and therefore greater energy efficiency. Retractable doors can shield the rotors when not in use, decreasing drag during forward flight.

The invention relates to a method for locking a mobile element (101) of an aircraft, such as a hold door or a landing gear, the mobile element being moved between a deployed position and a closed or retracted position by means of an actuator (200) having a sliding stem (3) coupled to the mobile element, the stem being mounted so as to be able to slide in a body (1) of the actuator between an extended position corresponding to the deployed position of the mobile element and a withdrawn position corresponding to the closed or retracted position of the mobile element. The method of the invention comprises the step of positively blocking the sliding stem of the actuator in the withdrawn position.