SYSTEM FOR RE-ENERGIZING STREAMFLOW IN CONTROL SURFACES OF AIRCRAFT

Abstract

A system for re-energizing streamflow in control surfaces of aircraft, comprising a panel provided with at least one aerodynamic element movable at least between a rest position, where the at least one aerodynamic element does not protrude from the panel, and a use position, where the at least one aerodynamic element protrudes from the panel, acting as a vortex generator. The at least one aerodynamic element is a die-cut portion of the panel that is hinged to a remainder of the panel.

Claims

1. A system for re-energizing streamflow in control surfaces of aircraft, comprising: a panel provided with at least one aerodynamic element movable at least between a rest position, where the at least one aerodynamic element does not protrude from the panel, and a use position, where the at least one aerodynamic element protrudes from the panel, acting as a vortex generator, wherein said at least one aerodynamic element is a die-cut portion of said panel that is hinged to a remainder of said panel.

2. The system for re-energizing streamflow in control surfaces of aircraft according to claim 1, wherein in the use position, the aerodynamic element defines a deflection angle with respect to the panel.

3. The system for re-energizing streamflow in control surfaces of aircraft according to claim 2, wherein said deflection angle is variable.

4. The system for re-energizing streamflow in control surfaces of aircraft according to claim 1, wherein the aerodynamic element comprises a fixed end joined to the panel, said fixed end defining a control line, and a movable end.

5. The system for re-energizing streamflow in control surfaces of aircraft according to claim 4, wherein the movable end has a pointed shape.

6. The system for re-energizing streamflow in control surfaces of aircraft according to claim 4, wherein the fixed end is divided in a plurality of sections.

7. The system for re-energizing streamflow in control surfaces of aircraft according to claim 1, wherein the aerodynamic element comprises at least one longitudinal slot.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0022] For a better understanding the above explanation and for the sole purpose of providing an example, some non-limiting drawings are included that schematically depict a practical embodiment.

[0023] FIG. 1 is a perspective of a portion of a wing of an aircraft, showing an aerodynamic element of the system according to the present invention placed between a control surface and a torsion box;

[0024] FIG. 2 is a perspective view of an aerodynamic element of the system according to the present in its rest position;

[0025] FIG. 3 is a perspective view of the aerodynamic element shown in FIG. 2 in its use position; and

[0026] FIGS. 4-6 are perspective view showing different positions of an aerodynamic element of the system according to the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0027] As shown in FIG. 1, the system according to the present invention is preferably used in a wing of an aircraft, in particular, in a zone between a control surface 10 and a torsion box 11, where a panel 1 is placed.

[0028] The panel 1 is made from a flexible material than can be curved during some phases of use of the aircraft and the panel 1 comprises at least one aerodynamic element 2, which can be placed passively, i.e., automatically, in its use position acting as a vortex generator or in its rest position, as will be described hereinafter.

[0029] The aerodynamic element 2 is a die-cut portion of the flexible panel 1, which is hinged to the rest of the panel 1, defining a fixed end 21 and a movable end 22.

[0030] The fixed end 21 defines a control line A, shown in FIG. 1, as a hinge axis, and the movable end 22 can be moved between the use and rest positions, defining a deflection angle with respect to the flexible panel 1.

[0031] As shown particularly in FIGS. 4-6, the deflection angle is variable depending on the use conditions.

[0032] The aerodynamic element 2 can also comprise at least one longitudinal slot 23, as shown particularly in FIG. 3, and its fixed end 21 can be divided in a plurality of sections, from which the longitudinal slot(s) 23 can be defined.

[0033] As shown in the Figures, the movable end 22 of the aerodynamic element 2 has preferably a pointed shaped, such as, e.g., an arrow shape, even though the movable end 22 can be made of any suitable shape.

[0034] The operation of the re-energizing streamflow system according to the present invention is very simple.

[0035] In certain conditions of the aircraft, e.g., in cruise conditions, the aerodynamic element(s) 2 is(are) in the rest position, i.e., hidden, not protruding from the panel 1.

[0036] In other conditions of the aircraft where the vortex generators are necessary, the aerodynamic element(s) is(are) in the use position, i.e., unhidden or protruding from the panel 1.

[0037] This change of position is made in a passive way, i.e., automatically due to the flexibility of the panel 1 and of the aerodynamic element(s) 2.

[0038] Therefore, as stated previously the system permits to hide and unhide the aerodynamic element(s) 2 in order to be used only when it is necessary, so the penalty at cruise conditions is avoided.

[0039] While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms comprise or comprising do not exclude other elements or steps, the terms a or one do not exclude a plural number, and the term or means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.