| 摘要 |
<p>1. Hydraulic directional valve for an aircraft servocontrol, for example the flaps (1) of air brakes of aircraft wings, comprising a plug (12) rotatably mounted in a fixed liner (13) housed in a body (15) and connected at one end (17) to a control device (18, 41, 42), and an annular sleeve (14) interposed rotatably between the plug (12) and the liner (13), bores (19, 23, 26; 27, 25, 21; 28, 24, 22), for the inlet under pressure and the outlet of a hydraulic fluid, which are formed in the liner (13) and in the sleeve (14), and passages (29a, 29b) on the periphery of the plug (12) to ensure the circulation of the hydraulic fluid from one bore (23) to the other (24, 25) of the liner (13) by passing through those of the sleeve (14) when the plug (12) rotates, characterised in that one end (14a) of the rotating sleeve (14) projects outside the body, on the side of the latter from which said end (17) of the plug already extends, and it rotates integrally with a lateral lever (32) associated with a position copying device comprising a feedback device (9; 32-34) capable of progressively returning the sleeve (14), by means of the above-mentioned lever, to its initial angular position with respect to the plug (12), after rotation of the latter through a predetermined angle.</p> |
