This relates to changes in wing profiles. In order to make available an aerodynamic structure that can be variably adjusted and changed with respect to the wing profile, it is provided that an aerodynamic structure for a wing or rudder arrangement of an aircraft comprises a support structure and an
This relates to changes in wing profiles. In order to make available an aerodynamic structure that can be variably adjusted and changed with respect to the wing profile, it is provided that an aerodynamic structure for a wing or rudder arrangement of an aircraft comprises a support structure and an outer skin. The support structure comprises a fixed spar in the longitudinal direction, which extends from a root area to an outer end area. The support structure also comprises several adaptive framework segments in the transverse direction, which each consist of a plurality of strung together triangular compartments, which are formed by fixed-length guide elements and adjustable-length guide elements The framework segments are joined to the fixed spar. At least one side of a portion of the triangular compartments comprises one of the adjustable guide elements, so that the shape of the framework segments can be adjusted.
대표청구항▼
1. An aerodynamic structure for a wing or rudder arrangement of an aircraft, comprising: a support structure; andan outer skin;wherein the support structure comprises a fixed spar in the longitudinal direction, which extends from a root area to an outer end area;wherein the support structure compris
1. An aerodynamic structure for a wing or rudder arrangement of an aircraft, comprising: a support structure; andan outer skin;wherein the support structure comprises a fixed spar in the longitudinal direction, which extends from a root area to an outer end area;wherein the support structure comprises several adaptive framework segments in the transverse direction, each comprising a plurality of strung together triangular compartments that are formed by fixed-length guide elements and adjustable-length guide elements;wherein the framework segments are joined to the fixed spar;wherein at least one side of at least a portion of the triangular compartments comprises one of the adjustable-length guide elements, so that the shape of the framework segments can be adjusted;wherein the outer skin is held by the framework segments;wherein an outer contour of the aerodynamic structure can be changed at least in the transverse direction by adjusting the shape of the framework segments;wherein the adjustable-length guide elements are active actuating drives; andwherein the adjustable-length guide elements in the triangular compartments are arranged such that each triangular compartment comprises an adjustable-length guide element facing the outside, wherein the triangular compartments are arranged such that adjustable-length guide elements are provided on alternating upper and lower sides of the aerodynamic structure. 2. The aerodynamic structure of claim 1, wherein the framework segments are joined to the fixed spar transversely to its longitudinal direction in such a way as to provide triangular compartments on both sides of the spar. 3. The aerodynamic structure of claim 2, wherein it is provided that fixed-length guide elements are continuously strung together in the direction of the framework segment. 4. The aerodynamic structure of claim 1, wherein the spar forms a longitudinal beam, to which several framework segments are sequentially attached as transverse ribs. 5. The aerodynamic structure of claim 4, wherein several framework segments are arranged parallel to each other, and run parallel to the flight direction. 6. The aerodynamic structure of claim 5, wherein the aerodynamic structure forms a front edge on a longitudinal edge, and wherein the end area of the framework segments that faces the front edge is designed with a fixed, triangular compartment. 7. The aerodynamic structure of claim 6, wherein the fixed spar comprises a triangular cross section, and has three longitudinal edges, wherein the triangular cross section of the spar is integrated into the framework segments; andwherein it is provided that the fixed-length or adjustable-length guide elements be attached to the three longitudinal edges. 8. The aerodynamic structure of claim 7, wherein the outer skin can be shaped, and is attached to the framework segments at least partially via hold points by retaining elements; and wherein at least a portion of the retaining elements are designed as adaptive mounts, with which the location of the hold points in relation to the framework segments can be varied. 9. The aerodynamic structure of claim 8, wherein the adaptive mounts are adjustable-length hold members, with which the distance between the hold points and framework segments can be adjusted. 10. The aerodynamic structure of claim 9, wherein the outer skin consists of a single piece. 11. An aircraft, comprising: a fuselage structure;a wing assembly with at least one wing surface; anda tail unit with at least one control surface;wherein the wing assembly and tail unit are held on the fuselage structure; andwherein at least one wing surface and/or one control surface is designed with an aerodynamic structure comprising: a support structure; andan outer skin;wherein the support structure comprises a fixed spar in the longitudinal direction, which extends from a root area to an outer end area;wherein the support structure comprises several adaptive framework segments in the transverse direction, each comprising a plurality of strung together triangular compartments that are formed by fixed-length guide elements and adjustable-length guide elements;wherein the framework segments are joined to the fixed spar;wherein least one side of at least a portion of the triangular compartments comprises one of the adjustable-length guide elements, so that the shape of the framework segments can be adjusted;wherein the outer skin is held by the framework segments;wherein an outer contour of the aerodynamic structure can be changed at least in the transverse direction by adjusting the shape of the framework segments;wherein the adjustable-length guide elements are active actuating drives; andwherein the adjustable-length guide elements in the triangular compartments are arranged such that each triangular compartment comprises an adjustable-length guide element facing the outside, wherein the triangular compartments are arranged such that adjustable-length guide elements are provided on alternating upper and lower sides of the aerodynamic structure. 12. A method for adjusting an outer contour of an aerodynamic structure for a wing or rudder arrangement, which comprises the following steps: a) providing an aerodynamic structure for a wing or rudder arrangement of an aircraft; wherein the aerodynamic structure comprises a support structure and an outer skin; and wherein the support structure comprises a fixed spar in the longitudinal direction, which extends from a root area to an outer end area; and wherein the support structure comprises several adaptive framework segments in the transverse direction, each comprising a plurality of strung together triangular compartments, which are formed by fixed-length guide elements and adjustable-length guide elements; and wherein the framework segments are joined to the fixed spar, and the outer skin is held by the framework segments; and wherein at least one side of at least a portion of the triangular compartments comprises one of the adjustable-length guide elements, so that the framework segments have an adjustable shape; and wherein adjusting the shape of the framework segments makes it possible to vary the outer contour of the aerodynamic structure, at least in the transverse direction; and wherein the adjustable-length guide elements are active actuating drives; and wherein the adjustable-length guide elements in the triangular compartments are arranged such that each triangular compartment comprises an adjustable-length guide element facing the outside, wherein the triangular compartments are arranged such that adjustable-length guide elements are provided on alternating upper and lower sides of the aerodynamic structure;b) actively adjusting the adjustable-length guide elements; andc) changing the outer contour of the aerodynamic structure at least in the transverse direction. 13. An aerodynamic structure for a wing or rudder arrangement of an aircraft, comprising: a support structure; andan outer skin;wherein the support structure comprises a fixed spar in the longitudinal direction, which extends from a root area to an outer end area;wherein the support structure comprises several adaptive framework segments in the transverse direction, each comprising a plurality of strung together triangular compartments that are formed by fixed-length guide elements and adjustable-length guide elements;wherein the framework segments are joined to the fixed spar;wherein least one side of at least a portion of the triangular compartments comprises one of the adjustable-length guide elements, so that the shape of the framework segments can be adjusted;wherein the outer skin is held by the framework segments;wherein an outer contour of the aerodynamic structure can be changed at least in the transverse direction by adjusting the shape of the framework segments;wherein the framework segments are joined to the fixed spar transversely to its longitudinal direction in such a way as to provide triangular compartments on both sides of the spar;wherein the adjustable-length guide elements are active actuating drives; andwherein the adjustable-length guide elements in the triangular compartments are arranged such that each triangular compartment comprises an adjustable-length guide element facing the outside, wherein the triangular compartments are arranged such that adjustable-length guide elements are provided on alternating upper and lower sides of the aerodynamic structure.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (2)
Hemmelgarn, Christopher Douglas; Pelley, Bryan Michael, Passive adaptive structures.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.