CPC B64C 3/44 (2013.01) [B64C 3/26 (2013.01); B64C 9/18 (2013.01); B64C 2003/445 (2013.01)] | 9 Claims |
1. A morphing control surface system for an aircraft wing, the wing comprising an upper plane and a lower plane, comprising:
an upper flexible skin configured to be fixed to the wing in an extension of the upper plane of the wing;
a lower flexible skin configured to be movable in an extension of the lower plane of the wing via a plane-to-plane link, the lower flexible skin being fixed to the upper flexible skin along a trailing edge of the control surface;
at least one actuator configured to generate a displacement of the lower flexible skin with respect to the lower plane of the wing, and
the displacement of the lower flexible skin configured to cause a curvature of the upper flexible skin and a curvature of the lower flexible skin, the curvature of the upper flexible skin and the curvature of the lower flexible skin having a concavity oriented in a same direction,
wherein the upper flexible skin has a greater thickness in a zone situated at the trailing edge and in a zone situated at the fixing of the upper flexible skin to the upper plane of the wing than in a central zone situated between the zone situated at the trailing edge and the zone situated at the fixing; and
wherein a thickness ratio between the zone situated at the trailing edge and the central zone is between 2 and 3, and a thickness ratio between the zone situated at the fixing and the central zone is between 4 and 5.
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