| 摘要 |
<p>The landing gear (10) comprises a strut (12) having an upper portion (12a) arranged to be mechanically coupled to an aircraft and a lower portion (12b) movably mounted with respect to the upper portion, a bogie beam (14) pivotally coupled to the lower portion of the strut, a bogie control linkage (20, 22, 24) mechanically coupled to the bogie at a first connection point and to the strut at a second connection point, the bogie control linkage comprising an actuator (24) which includes a locking system (24a) operable to inhibit its actuation, a sensor linkage (26) mechanically coupled to the lower portion of the strut and arranged to change between a first condition and a second condition in accordance with movement of the upper portion of the strut relative to the lower portion of the strut, and an actuator control apparatus (28, 30, 32) arranged to operate the locking system when the sensor linkage is in the first condition and arranged not to operate the locking system when the sensor linkage is in the second condition. The two conditions are provided by a pivot (27) between two torque links (26a, b) for the strut (12) passing across a marker T between respective sectors (S1, S2) about a pivot (25) of one of the torque links with its respective strut portion (12a, b).</p> |
