| 主权项 |
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, and the 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. |
