| 摘要 |
<p>The invention relates to an aircraft control surface (1), in particular for an aircraft supporting surface (2), comprising a primary control surface (6) including a hinge pin (10) and a secondary control surface (7) including a hinge pin (11), whereby the secondary control surface (7) rotates by means of the hinge pin thereof (11) in relation to the primary control surface (6). The secondary control surface (7) only occupies part of the span of the primary control surface (6), with the length of the secondary control surface (7) along the hinge pin (11) thereof being significantly less than the length of the primary control surface (6) along the hinge pin (10) of same. In addition, the width or chord of the secondary control surface (7) narrows along the axis of the hinge pin (11) thereof towards the tip of the supporting surface (2) according to a tapering law designed expressly to adapt the torsional rigidity distribution along the span of the supporting surface (2) to the corresponding aerodynamic load distribution, while the effective curvature distribution owing to the deflection of the control surface (1) is such that it increases the aerodynamic stalling angle of attack of the supporting surface (2).</p> |
