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A pivoting panel for an aircraft and to a composite support piece for this kind panel. The support piece (17) is arranged as a part of the frame structure of the panel (3). The support piece has an extension portion (23) to which an actuator connection fitting (7) of an actuator (4) can be fastened.

A pivoting panel for an aircraft and to a composite support piece for this kind panel. The support piece (17) is arranged as a part of the frame structure of the panel (3). The support piece has an extension portion (23) to which an actuator connection fitting (7) of an actuator (4) can be fastened. The extension portion (23) distributes the forces to the structures of the panel (3).

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What is claimed is: 1. A pivoting panel for an aircraft, comprising: a first surface plate and a second surface plate; a front spar at a front edge of the panel and a rear spar at a rear edge of the panel; a frame structure arranged into a space defined by the surface plates and the spars; at least

What is claimed is: 1. A pivoting panel for an aircraft, comprising: a first surface plate and a second surface plate; a front spar at a front edge of the panel and a rear spar at a rear edge of the panel; a frame structure arranged into a space defined by the surface plates and the spars; at least two hinges arranged on a front edge portion of the panel; and at least one actuator connection fitting to which an actuator is connectable for pivoting the panel in relation to the hinges, wherein the frame structure comprises at least one support piece made of a composite material; the support piece comprises at least an extension portion; the position of the extension portion is arranged to correspond to that of the actuator connection fitting; and the extension portion is provided with a first surface and a second surface, the first surface being attached to an inner surface of the first surface plate of the panel and the second surface of the extension portion being attached to an inner surface of the second surface plate, whereby during assembly the support piece is arranged as an integral part of the panel; and wherein the support piece further comprises a first branch and a second branch arranged inside the space defined by the surface plates and the spars, and at a distance from each other, the distance between outermost ends of the branches being greater than that between innermost ends of the first and second branches thereby forming a structure having an inverted V-shape. 2. A panel according to claim 1, wherein the actuator connection fitting has a fastening flange; and surface areas of the first surface and the second surface of the extension portion are greater than a surface area of the fastening flange of the actuator connection fitting. 3. A panel according to claim 1, wherein the actuator connection fitting has a fastening flange; and the surface areas of the first surface and the second surface of the extension portion are at least twice as large as a surface area of the fastening flange of the actuator connection fitting. 4. A panel according to claim 1, wherein the extension portion has a wedge-shaped cross-section; and the extension portion is arranged into a wedge-shaped space in the trailing edge of the panel. 5. A panel according to claim 1, wherein the support piece comprises a first branch and a second branch extending from the extension portion to the front edge portion of the panel at a first distance; the first and second branches are arranged at a second distance from one another and having first and second ends; the branches are coupled from their first ends to a first edge of the extension portion; the second ends of the branches extend to the front edge portion of the panel; and the second ends of the first branch and the second branch are provided with hinges attached thereto, the support piece thus being arranged to form a uniform fastening part for fastening both the actuator connection fitting and the hinges. 6. A panel according to claim 5, wherein the first or second surface plate has an opening. 7. A panel according to claim 6, wherein the opening is between the first and second branches of the support piece. 8. A panel according to claim 5, wherein the first and second branches of the support piece are fastened to the first and second surface plates. 9. A panel according to claim 1, wherein the frame structure of the panel comprises a plurality of longitudinal supports between the surface plates; the longitudinal supports comprise two lateral flanges with a vertical flange between them; the lateral flanges are attached to the surface plates; and the front end of the longitudinal support is attached to the front spar and the rear end thereof to the rear spar. 10. A panel according to claim 1, wherein the frame structure of the panel comprises at least one cellular structure between the surface plates. 11. A panel according to claim 1, wherein the panel is entirely made of a composite material; and the composite material comprises at least one reinforcing fiber and at least one polymer matrix. 12. A pivoting panel for an aircraft, comprising: a first surface plate and a second surface plate; a front spar at a front edge of the panel and a rear spar at a rear edge of the panel; a frame structure arranged into a space defined by the surface plates and the spars; at least two hinges arranged on a front edge portion of the panel; and at least one actuator connection fitting to which an actuator is connectable for pivoting the panel in relation to the hinges, and wherein the frame structure comprises at least one support piece made of a composite material; the support piece comprises at least an extension portion; the position of the extension portion is arranged to correspond to that of the actuator connection fitting; the extension portion is provided with a first surface and a second surface, the first surface being attached to an inner surface of the first surface plate of the panel and the second surface of the extension portion being attached to an inner surface of the second surface plate, whereby during assembly the support piece is arranged as an integral part of the panel; and the cross-section of the extension portion is wedge-shaped; and the extension portion is arranged into a wedge-shaped space proximate a trailing edge of the panel opposite the front edge. 13. A pivoting panel for an aircraft, comprising: a first surface plate and a second surface plate; a front spar at the front edge of the panel and a rear spar at the rear edge of the panel; a frame structure arranged into a space defined by the surface plates and the spars; at least two hinges arranged on the front edge portion of the panel; and at least one actuator connection fitting to which an actuator is connectable for pivoting the panel in relation to the hinges, wherein the frame structure comprises at least one support piece made of a composite material; the support piece comprises at least an extension portion; the position of the extension portion is arranged to correspond to that of the actuator connection fitting; the extension portion is provided with a first surface and a second surface, the first surface being attached to an inner surface of the first surface plate of the panel and the second surface of the extension portion being attached to an inner surface of the second surface plate, whereby during assembly the support piece is arranged as an integral part of the panel; the support piece further comprises an elongated first branch and an elongated second branch arranged inside the space defined by the surface plates and the spars, and extending from the extension portion to the front edge portion of the panel at a first distance; the first and second branches are arranged at a second distance from one another thereby forming an open space therebetween and having first and second ends; the branches are coupled from their first ends to the first edge of the extension portion; the second ends of the branches extend to the front edge portion of the panel; and the second ends of the first branch and the second branch are provided with hinges attached thereto, the support piece thus being arranged to form a uniform fastening part for fastening both the actuator connection fitting and the hinges. 14. A pivoting panel for an aircraft, comprising: a first surface plate and a second surface plate; a front spar at a front edge of the panel and a rear spar at a rear edge of the panel; a frame structure arranged into a space defined by the surface plates and the spars; at least two hinges arranged on a front edge portion of the panel; and at least one actuator connection fitting to which an actuator is connectable for pivoting the panel in relation to the hinges, and wherein the frame structure comprises at least one support piece made of a composite material; the support piece comprises at least an extension portion and branches arranged inside the space defined by the surface plates and the spars; the position of the extension portion is arranged to correspond to that of the actuator connection fitting and at a distance from the front spar towards the rear edge of the panel; and the extension portion is provided with a first surface and a second surface, the first surface being attached to an inner surface of the first surface plate of the panel and the second surface of the extension portion being attached to an inner surface of the second surface plate, whereby during assembly the support piece is arranged as an integral part of the panel. 15. A pivoting panel for an aircraft, comprising: a first surface plate and a second surface plate; a front spar at a front edge of the panel and a rear spar at a rear edge of the panel; a frame structure arranged into a space defined by the surface plates and the spars; at least two hinges arranged on a front edge portion of the panel; and at least one actuator connection fitting to which an actuator is connectable for pivoting the panel in relation to the hinges, and wherein the frame structure comprises at least one support piece made of a composite material; the support piece comprises at least an extension portion; the position of the extension portion is arranged to correspond to that of the actuator connection fitting at a shorter distance from the rear spar compared to a distance from the front spar; and the extension portion is provided with a first surface and a second surface, the first surface being attached to an inner surface of the first surface plate of the panel and the second surface of the extension portion being attached to an inner surface of the second surface plate, whereby during assembly the support piece is arranged as an integral part of the panel. 16. A pivoting panel for an aircraft, comprising: a first surface plate and a second surface plate; a front spar at a front edge of the panel and a rear spar at a rear edge of the panel; a frame structure arranged into a space defined by the surface plates and the spars; at least two hinges arranged on a front edge portion of the panel; and at least one actuator connection fitting to which an actuator is connectable for pivoting the panel in relation to the hinges, and wherein the frame structure comprises at least one support piece made of a composite material; the support piece comprises at least an extension portion; the position of the extension portion is arranged to correspond to that of the actuator connection fitting; and the extension portion is provided with a first surface and a second surface, the first surface being attached to an inner surface of the first surface plate of the panel and the second surface of the extension portion being attached to an inner surface of the second surface plate, whereby during assembly the support piece is arranged as an integral part of the panel; wherein the support piece further comprises a first branch and a second branch arranged at a distance from each other, the distance between outermost ends of the branches being greater than that between innermost ends of the first and second branches thereby forming a structure having an inverted V-shape, and wherein the support piece and the front spar form a substantially triangular support piece between the actuator connection fitting and the hinges. 17. A pivoting panel for an aircraft, comprising: a first surface plate and a second surface plate; a front spar at a front edge of the panel and a rear spar at a rear edge of the panel; at least two hinges arranged on a front edge portion of the panel; and an actuator connection fitting to which an actuator is connectable for pivoting the panel in relation to the hinges, the actuator connection fitting being secured on an outer surface of the first surface plate at a distance from the front edge of the panel; wherein the surface plates and the spars house therewithin a frame structure comprising an extension portion and first and second branches arranged below the actuator connection fitting to support the actuator connection fitting thereon. 18. A pivoting panel according to claim 17, wherein the surface plates and the spars form a sealed box-type structure.