초록 ▼

An aircraft door arrangement having a pivotable door for closing an aperture in the fuselage of an aircraft and selectively movable between closed and open positions by a linear actuating mechanism having a casing and a rod selectively extendable and retractable. An actuator mounting mounts the casi

An aircraft door arrangement having a pivotable door for closing an aperture in the fuselage of an aircraft and selectively movable between closed and open positions by a linear actuating mechanism having a casing and a rod selectively extendable and retractable. An actuator mounting mounts the casing between two elements of the primary structure of the aircraft. The rod is pivotally coupled to the door. The actuator mounting includes a rigid mounting component including three legs extending in a common plane together with the casing and the rotation axis and each having a first and a second longitudinal end. The first and second legs symmetrically extend from the casing at an angle at opposite sides thereof. Each of the second ends of the first and second legs is rotatably coupled on the rotation axis to another one of the spaced elements of the primary structure of the aircraft.

대표청구항 ▼

1. An aircraft door arrangement comprising a door hingedly mounted to the fuselage of an aircraft such that it is selectively pivotally movable into a closed position in which it closes an aperture in the fuselage and into an open position in which it provides access through the aperture,a linear ac

1. An aircraft door arrangement comprising a door hingedly mounted to the fuselage of an aircraft such that it is selectively pivotally movable into a closed position in which it closes an aperture in the fuselage and into an open position in which it provides access through the aperture,a linear actuating mechanism adapted to be operable for selectively moving the door between its open and closed positions, wherein the linear actuating mechanism comprises an elongate straight casing and a rod which is disposed in the casing and extends partially from a longitudinal end of the casing and which is selectively extendable and retractable by operating the linear actuating mechanism, andthe casing being mounted by an actuator mounting between and supported by two spaced elements of the primary structure of the aircraft such that it is pivotable about a rotation axis,wherein the longitudinal end of the rod extending from the casing is pivotally coupled to the door, such that upon extending the rod from the casing the door is moved into its open position and upon retracting the rod into the casing the door is moved into its closed position,the actuator mounting comprising a rigid mounting component comprising three elongate legs extending in a common plane together with the casing and the rotation axis and each having a first and a second longitudinal end, wherein the three elongate legs include a first leg and a second leg of equal length and shape and a third leg, and wherein each of the first and second legs is connected with its respective first end to the casing such that the first leg and the second leg symmetrically extend at an angle away from the casing at opposite sides thereof, and that loads acting on the casing upon operating the linear actuating mechanism are transferred to and along the first and second legs,the first end of the third leg is connected to the second end of the first leg and the second end of the third leg is connected to the second end of the second leg such that the third leg is connected between the second ends of the first and second legs, andeach of the second ends of the first and second legs is rotatably coupled on the rotation axis to another one of the spaced elements of the primary structure of the aircraft such that the mounting component is pivotable about the rotation axis. 2. The aircraft door arrangement according to claim 1, wherein the third leg supports the casing at a location spaced from the location at which the first ends of the first and second ends are connected to the casing, wherein the third leg is rigidly connected to the casing or wherein the third leg and the casing are floatingly connected such that they are movable with respect to each other in the longitudinal direction of the casing. 3. The aircraft door arrangement according to claim 1, wherein the casing is connected to the third leg such that the third leg supports the casing against movement in the direction of the rotation axis. 4. The aircraft door arrangement according to claim 2, wherein the casing is connected to the third leg in the middle between the first and second ends thereof. 5. The aircraft door arrangement according to claim 1, wherein the mounting component has mirror symmetry about a plane extending through the longitudinal axis of the casing and perpendicularly to the plane defined by the mounting component. 6. The aircraft door arrangement according to claim 1, wherein the first and second legs are straight or curved, and/or wherein the third leg is straight or curved. 7. The aircraft door arrangement according to claim 1, wherein the first ends of the first and second legs are rigidly connected to the casing. 8. The aircraft door arrangement according to claim 7, wherein the first and second legs are integrally formed in one piece with the casing, and/or the third leg is integrally formed in one piece with the casing. 9. The aircraft door arrangement according to claim 1, wherein the first ends of the first and second legs are connected and separated by a coupling component which is coupled to the casing. 10. The aircraft door arrangement according to claim 1, the first ends of the first and second legs are connected and separated by a coupling component which is coupled to the casing, and wherein the coupling component is or comprises a gimbal by which the first ends of the first and second legs are connected to the casing. 11. The aircraft door arrangement according to claim 1, wherein the linear actuating mechanism is a linear hydraulic, pneumatic or electrical actuator. 12. The aircraft door arrangement according to claim 1, wherein the rotation axis is oriented along the longitudinal axis of the aircraft. 13. The aircraft door arrangement according to claim 1, wherein the two spaced elements of the primary structure of the aircraft are two parallel cross beams. 14. The aircraft door arrangement according to claim 1, wherein the door is an access panel, flap, cargo door or gate. 15. An aircraft comprising an aircraft door arrangement according to claim 1.