| 摘要 |
The invention relates to a main leg intended to be used in the construction of a military aircraft with retractable landing gear. According to the invention, the leg comprises a damper (2) taking over the vertical shock which occurs upon the aircraft impact with the ground, which is articulated, at one end, with a body (1) and, at the other end, with a fork (3) supporting a wheel (5), where the body (1) is integral with a tab (6) provided with a bore (b) needed for the attachment to the aircraft structure and with a lever (7) for attaching the driving assembly, the damper (2) comprising two chambers (e and f), namely a hydraulic chamber and a pneumatic chamber, separated by a floating piston (10) sliding on a rod (12) inside a cylinder (11), the said rod (12) being integral with a throttle piston (20) provided with some calibrated orifices intended to permit communication with some other calibrated orifices provided within a throttle flange (21), the rod (12) sliding inside a piston rod (23) articulated with the flange (3) which, upon the aircraft impact with the ground, slides inside the cylinder (11) and makes the liquid pass from the lower part of the hydraulic chamber (f) to the upper part, through the calibrated orifices of the throttle piston (20), thereby generating nitrogen compression and expansion cycles, by means of the floating piston (10), until the balance is restored. |
