| 摘要 |
<p>The invention pertains to a guiding mechanism (2) for moving a cargo door (L) into extended cargo door positions (A1, A2) in order to open and into a retracted cargo door position in order to close at least one section of an opening (T0) of a loading hatch (T) on a fuselage (R) of an aircraft (F), wherein a first structural component in the form of the cargo door (L) is pivotably supported on a second structural component in the form of the fuselage (R) on a front lateral edge (B1) by means of a pivot joint arranged in a pivoting axis (D) in order to assume the extended cargo door positions (A1, A2) on the loading hatch (T), and wherein the guiding mechanism (2) features:
– at least one actuator (30; 30a, 30b) for moving the cargo door (L) between a retracted position and a maximally extended cargo door position (A1, A2) that features: an actuator drive unit (31) and an actuating element (34) that can be moved relative to the actuator drive unit (31) and be coupled to a first coupling device (42a) on the first or second structural component (R, L),
– a supporting device (34a) arranged on the actuating element (34) in order to support the connecting element on a second connecting device (37) on the respectively other structural component, and
– a spring mechanism (38) that is arranged on the actuator (30; 30a, 30b) and designed for exerting a compressive force between the first and the second connecting device (32, 37) and makes available a compensation travel between the actuating element and the connecting element is available at an outer limit of the extended cargo door positions (A1, A2) relative to the respective actuating states of the actuating element (34),
as well as to an aircraft (F) with such a guiding mechanism (2) and a method for moving a cargo door (L) of an aircraft into extended cargo door positions (A1, A2).</p> |
