Vane-type rotary hydraulic actuator device intended for driving an aircraft control surface

Rotary hydraulic actuator device comprising a vane (1, 21, 51, etc.) which is mounted rotatably and sealingly in a chamber (2;

• 34, 35, etc.) made in a body (3, 32, 74, etc.) and on the faces of which a hydraulic fluid pressure can be exerted, the vane being fixed mechanically to an element to be driven in rotation, characterized in that:
• the vane (2, 21, 51, etc.) comprises at least two parts (4, 5) extending radially on either side of its axis of rotation (XX), and these two parts are each movable in a chamber (8, 9;
• 55, 56, etc.) extending over an angular sector less than half a circumference, this chamber being divided into two compartments by the said part (4, 5;
• 52, 53;
• 67, 68);
• in that it is equipped with a hydraulic circuit for feeding fluid to the chambers (8, 9;
• 55, 56), which is designed so as to be capable of driving the vane (1, 21, 51, 66) in rotation in one direction or the other;
• and in that the vane (66) comprises two diametrically opposite radial parts (70) joined by means of a central piece (69) receiving a hub (71) which is fixed to the said rotating radial parts and in which is formed an axial recess receiving a shaft (73) fixed to the element to be driven and to the hub (71) the ends of the radial parts (70) and the hub (71) being in sealing sliding contact with the body (74) which surrounds the vane (66) and which has, on its periphery, two circumferential grooves (75, 76) each communicating, on the one hand, with hydraulic-fluid passage conduits, (77, 78, 84) made in a casing (79) containing the annular body (74) and the vane (66) and, on the other hand, with respective radial inlet perforations (81, 82) in the chambers (82, 88) and outlet perforations (86, 87) from the latter, which are made in the annular body (74), said circumferential grooves (75, 76) being located entirely within a radial extension of said radial parts (70).