Variant wing capable of actively regulating and controlling chord length and thickness

Abstract

The invention discloses a morphing wing capable of actively regulating and controlling chord length and thickness. The morphing wing comprises a front edge section, a wing body, a telescopic driving part, a rear edge section and a skin, the wing body is connected with the front edge section and the rear edge section, and the multiple telescopic driving pieces are embedded in the wing body; the wing body comprises a plurality of wing body units arrayed in the extension direction, each wing body unit is formed by arraying a plurality of anisotropic cubic superstructures in the chord length direction, the thickness direction and the extension direction, and inclined protrusions of special-shaped connecting pieces at the corresponding vertex positions of adjacent cubic cell elements of the adjacent anisotropic cubic superstructures in the chord length direction and the thickness direction are connected. The special-shaped connecting pieces at the corresponding vertex positions of the adjacent cubic cells of the adjacent anisotropic cubic superstructures in the extension direction are combined to form a cross-cell special-shaped connecting piece, and the wing body has the negative Poisson's ratio characteristic in the chord length and thickness directions and has the zero Poisson's ratio characteristic in the extension direction. The wing can stretch out and draw back in the chord length direction and the thickness direction at the same time, the stretching length is kept unchanged, and the diversified application requirements of the aircraft are met.

Description

Technical Field

[0001] The present invention belongs to the technical field of variant wing structure design, and in particular relates to a variant wing capable of actively regulating chord length and thickness. Background Art

[0002] The complex flight environment poses multi-dimensional challenges to aircraft performance, and different flight phases have different requirements for lift-to-drag ratio and aerodynamic characteristics. The morphing wing is designed to optimize the aircraft's aerodynamic performance by dynamically adjusting the wing configuration and flight attitude to adapt to multi-mission scenarios. For example, during the cruise phase, the wing area is increased by varying the chord length to increase lift and extend flight time; by increasing the relative thickness of the wing, a high lift coefficient is maintained, fuel consumption is reduced, and range is increased. During the accelerated flight phase, the wing area is reduced by varying the chord length to reduce drag and enhance aircraft agility; by reducing the relative thickness of the wing, supersonic shock wave drag is reduced and maneuverability is improved.

[0003] The invention application, published on April 15, 2025, with publication number CN119821657A, discloses a variable-thickness wing structure comprising a composite corrugated skin, a connecting rod assembly, and a reinforcement plate. A fixing plate is fixedly disposed within the left interior of the composite corrugated skin. A fixing bracket is mounted on the right outer end of the fixing plate, and a mounting plate is integrally fixedly mounted on the right side of the fixing bracket. An electric hydraulic rod is disposed in the middle portion of the left side of the mounting plate, and a connecting plate is fixedly mounted on the output end of the electric hydraulic rod. A connecting rod assembly is mounted on the outer side of the connecting plate. This variable-thickness wing structure can simultaneously precisely control the degree of deformation of the upper and lower thicknesses, reducing deformation limitations and improving the support effect of the deformed composite corrugated skin. Although this wing structure can achieve a certain degree of active deformation, it cannot deform in the chord direction. The change in wing area is significantly limited, limiting the ability to adjust the lift-drag and aerodynamic characteristics at different speeds and failing to meet the adjustment requirements of the variable-thickness wing in different flight phases. Summary of the Invention

[0004] In view of the deficiencies of the prior art, the technical problem to be solved by the present invention is to provide a variant wing that can actively adjust the chord length and thickness.

[0005] The present invention solves the technical problem by adopting the following technical solutions:

[0006] A variant wing capable of actively regulating chord length and thickness comprises a leading edge section, a wing body, a telescopic drive element, a trailing edge section, and a skin. The wing body connects the leading edge section and the trailing edge section, a plurality of telescopic drive elements are embedded in the wing body, a fixed end of each telescopic drive element is connected to the leading edge section, and a telescopic end is connected to the trailing edge section. The skin is applied to the outside of the leading edge section, the wing body, and the trailing edge section.

[0007] The wing-body includes a plurality of wing-body units arrayed along the span direction, each wing-body unit being composed of a plurality of anisotropic cubic superstructures arrayed along the chord length, thickness and span directions, respectively. The inclined protrusions of the special-shaped connectors at the corresponding vertex positions of adjacent cubic cells of adjacent anisotropic cubic superstructures along the chord length and thickness directions are connected, and the special-shaped connectors at the corresponding vertex positions of adjacent cubic cells of adjacent anisotropic cubic superstructures along the span direction are merged to form a cross-cell special-shaped connector. The wing-body has negative Poisson's ratio characteristics in the chord length and thickness directions, and has zero Poisson's ratio characteristics in the span direction.

[0008] Furthermore, the anisotropic cubic superstructure is composed of four cubic cells arrayed in the chord length and thickness directions. The cubic cells include special-shaped connectors, inclined links and diamond-shaped structural members. Short straight rods are provided at each vertex position of the diamond-shaped structural members. The six diamond-shaped structural members are located on the six faces of the cubic cell. Adjacent diamond-shaped structural members share the short straight rods at adjacent vertex positions. The two ends of the short straight rod at the vertex position of each diamond-shaped structural member are respectively connected to an inclined link, and the three adjacent inclined links are connected together through special-shaped connectors.

[0009] Furthermore, the special-shaped connecting part is composed of four protrusions connected together, one of which is an inclined protrusion, and the other three are standard protrusions. The angle between each of the three standard protrusions is 90°. The standard protrusion is connected to the inclined connecting rod. The inclined protrusion is located in the xoz or yoz plane of the spatial rectangular coordinate system and the angle with the horizontal direction is greater than 0° and less than 45°.

[0010] Furthermore, the cross-cell special-shaped connector has four standard protrusions and one inclined protrusion, wherein two standard protrusions are collinear and respectively connected to an inclined connecting rod, and the remaining two standard protrusions are coplanar and respectively connected to two inclined connecting rods.

[0011] Compared with the prior art, the present invention has the following beneficial effects:

[0012] The wing has a negative Poisson's ratio in the chord and thickness directions, and a zero Poisson's ratio in the span direction. This limits the overall deformation direction of the wing, allowing the wing to expand and contract simultaneously in the chord and thickness directions, allowing the wing to maintain a constant span while changing its chord and thickness, and to adjust the wing area and thickness to a greater extent, achieving precise control of the wing's aerodynamic shape. By collaboratively controlling the chord and thickness of the wing, multi-dimensional active control of the aerodynamic performance of the variant aircraft is achieved to meet its diverse application needs. Specifically, by changing the wing thickness, the lift-drag characteristics and aerodynamic characteristics are optimized, while by adjusting the chord length, the wing area is changed to further adapt to the lift-drag ratio requirements at different speeds. Through the linkage deformation mechanism of thickness and area, the aerodynamic efficiency of the variant aircraft in different flight phases is jointly improved.

[0013] The anisotropic cubic superstructure requires very little drive load to produce rotational deformation, allowing it to rapidly respond to the displacement loads generated by the expansion and contraction of the telescopic actuators, ensuring the wing's rapid deformation response. The anisotropic cubic superstructure incorporates a greater number of rods, resulting in higher stiffness and strength, ensuring stability during chord length and thickness variations and improving the wing's load-bearing capacity. The porous structure of the anisotropic cubic superstructure reduces the overall weight of the wing, thereby increasing the aircraft's endurance. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0015] Figure 2 A cross-sectional view of the overall structure of the present invention;

[0016] Figure 3 is a side view of the wing body of the present invention;

[0017] Figure 4 Schematic diagram of the structure of the anisotropic cubic superstructure of the present invention;

[0018] Figure 5 Schematic diagram of an array of anisotropic cubic superstructures along the lengthwise direction of the present invention;

[0019] Figure 6 Schematic diagram of the structure of the cubic cell of the present invention;

[0020] Figure 7 It is a structural schematic diagram of the special-shaped connector of the present invention;

[0021] Figure 8 Graph showing the deformation process of the anisotropic cubic superstructure of the present invention along the chord length and thickness directions;

[0022] Figure 9 FIG4 is a diagram showing the deformation process of the anisotropic cubic superstructure of the present invention along the extension direction;

[0023] In the figure, 1-leading edge section; 2-wing body; 3-telescopic drive member; 4-trailing edge section; 5-skin; 21-skin connector; 22-anisotropic cubic superstructure; 221-special-shaped connector; 222-inclined connecting rod; 223-diamond-shaped structural member; 221-1, standard protrusion; 221-2, inclined protrusion. DETAILED DESCRIPTION

[0024] Specific embodiments are given below in conjunction with the accompanying drawings. The specific embodiments are only used to introduce the technical solutions of the present invention in detail and are not intended to limit the scope of protection of the present application.

[0025] The present invention provides a variant wing (hereinafter referred to as wing, see Figures 1 to 9 ), including a leading edge section 1, a wing-body 2, a telescopic drive member 3, a trailing edge section 4 and a skin 5; wherein, the wing-body 2 connects the leading edge section 1 and the trailing edge section 4, a plurality of telescopic drive members 3 are embedded in the wing-body 2, the fixed end of each telescopic drive member 3 is fixedly connected to the leading edge section 1, and the telescopic end is fixedly connected to the trailing edge section 4, and the skin 5 is laid on the outside of the leading edge section 1, the wing-body 2 and the trailing edge section 4 to form the aerodynamic shape of the wing; the wing-body 2 has a negative Poisson's ratio characteristic in the chord length and thickness directions, and a zero Poisson's ratio characteristic in the span direction, and the telescopic drive member 3 drives the wing-body 2 to extend or shorten simultaneously along the chord length and thickness directions while keeping the span unchanged, thereby realizing variable chord length and thickness of the wing.

[0026] The wing-body 2 includes a plurality of wing-body units arrayed along the span direction, and the wing-body units are connected to the skin 5 through a skin connector 21; each wing-body unit is composed of a plurality of anisotropic cubic superstructures 22 arrayed along the chord length, thickness and span directions, and the adjacent cubic cells of the adjacent anisotropic cubic superstructures 22 along the chord length and thickness directions are connected by the inclined protrusions 221-2 of the special-shaped connectors 221 at the corresponding vertex positions. Due to the setting of the inclined protrusions 221-2, under the action of the telescopic drive member 3, the cubic cells rotate and deform around the inclined protrusions 221-2, so that the anisotropic The anisotropic cubic superstructure 22 gradually shrinks inward or expands outward, so that the wing has a negative Poisson's ratio characteristic in the chord length and thickness directions, ensuring that the wing can be extended or shortened simultaneously in the chord length and thickness directions, realizing active regulation of the chord length and thickness; the special-shaped connectors 221 at the corresponding vertex positions of adjacent cubic cells of adjacent anisotropic cubic superstructures 22 along the span direction are merged to form a cross-cell special-shaped connector, so that the wing has a zero Poisson's ratio characteristic in the span direction, so that the wing does not deform in the span direction, and the span remains fixed while the chord length and thickness are changed.

[0027] The anisotropic cubic superstructure 22 is composed of four cubic cells arrayed in the chord length and thickness directions. The inclined protrusions 221-2 of the special-shaped connectors 221 at the corresponding vertices of adjacent cubic cells are connected. The cubic cell includes special-shaped connectors 221, inclined connecting rods 222, and diamond-shaped structural members 223. Each vertex of the diamond-shaped structural members 223 is equipped with a short straight rod. Six diamond-shaped structural members 223 are located on the six faces of the cubic cell. Adjacent diamond-shaped structural members 223 share the short straight rods at adjacent vertices. Each of the short straight rods at the vertex of each diamond-shaped structural member 223 is connected to an inclined connecting rod 222 at each end. The inclined connecting rods 222 are inclined outward relative to the diamond-shaped structural member 223. Three adjacent inclined connecting rods 222 are connected together by special-shaped connectors 221. In other words, a special-shaped connector 221 is provided at each of the eight vertices of the cubic cell.

[0028] The special-shaped connecting member 221 is composed of four protrusions connected together, one of which is an inclined protrusion 221-2, and the other three are standard protrusions 221-1. The three standard protrusions 221-1 are respectively connected to the inclined connecting rod 222, and the angle between the three standard protrusions 221-1 is 90°, which is equivalent to the three standard protrusions 221-1 being respectively along the three axes of the spatial rectangular coordinate system; the inclined protrusion 221-2 is located in the xoz or yoz plane of the spatial rectangular coordinate system, and the angle with the horizontal direction is greater than 0° and less than 45°.

[0029] The cross-cell special-shaped connector has four standard protrusions and one inclined protrusion, wherein two standard protrusions are collinear and respectively connected to one inclined link 222 , and the remaining two standard protrusions are coplanar and respectively connected to two inclined links 222 .

[0030] In order to verify the deformation characteristics of the anisotropic cubic superstructure 22, a finite element simulation is performed on a structure formed by sixteen anisotropic cubic superstructures 22 (two arrays each along the chord length and thickness direction, and four arrays along the span direction). The wall thickness of all cubic cells remains unchanged, and a compressive load along the chord length direction is applied to them, as shown in Figure 2. Figure 8 、 9 As shown, the driving load required for the anisotropic cubic superstructure 22 to produce rotational deformation is very small. The cubic cells first produce rotational deformation around the inclined protrusion 221-2 and gradually shrink inward, so that the anisotropic cubic superstructure 22 has negative Poisson's ratio characteristics in the chord length and thickness directions, thereby enabling the wing body 2 to simultaneously extend or shrink along the chord length and thickness directions, realizing controlled deformation of the wing with variable chord length and thickness; and the anisotropic cubic superstructure 22 has greater stiffness and strength in the span direction. The length of the cubic cells in the span direction remains unchanged, so that the anisotropic cubic superstructure 22 exhibits zero Poisson's ratio characteristics in the span direction, realizing maintaining a fixed span while changing the chord length and thickness.

[0031] The working principle and workflow of the present invention are as follows:

[0032] This wing can actively control its chord length and thickness to meet the aerodynamic performance requirements of the aircraft during different flight phases. When the telescopic actuator 3 contracts, the anisotropic cubic superstructure 22 can rapidly respond to the displacement load generated by the contraction of the telescopic actuator 3, gradually contracting the anisotropic cubic superstructure 22 in the chord and thickness directions, thereby simultaneously reducing the chord length and thickness. Conversely, when the telescopic actuator 3 extends, the anisotropic cubic superstructure 22 gradually expands outward in the chord and thickness directions, simultaneously increasing the chord length and thickness. This exhibits a negative Poisson's ratio in these directions, while the anisotropic cubic superstructure 22 has higher stiffness and strength in the span direction. The anisotropic cubic superstructure 22 does not deform in the span direction, exhibiting a zero Poisson's ratio in the span direction. This allows the wing 2 to maintain a fixed span while changing its chord length and thickness, achieving the purpose of variable chord length and thickness. The two deformation functions of the wing, variable chord length and variable thickness, occur simultaneously, which changes the wing area to a greater extent and can meet the requirements of lift-to-drag ratio and aerodynamic characteristics in different flight stages.

[0033] Any matters not described in the present invention are applicable to the prior art.

Claims

1. A variant wing capable of actively regulating chord length and thickness, comprising a leading edge section, a wing body, a telescopic drive element, a trailing edge section, and a skin; the wing body connects the leading edge section and the trailing edge section, a plurality of telescopic drive elements are embedded in the wing body, a fixed end of each telescopic drive element is connected to the leading edge section, and a telescopic end is connected to the trailing edge section, and the skin is applied to the outside of the leading edge section, the wing body, and the trailing edge section; characterized in that: The wing-body includes a plurality of wing-body units arrayed along the span direction, each wing-body unit being composed of a plurality of anisotropic cubic superstructures arrayed along the chord length, thickness and span directions, respectively. The inclined protrusions of the special-shaped connectors at the corresponding vertex positions of adjacent cubic cells of adjacent anisotropic cubic superstructures along the chord length and thickness directions are connected, and the special-shaped connectors at the corresponding vertex positions of adjacent cubic cells of adjacent anisotropic cubic superstructures along the span direction are merged to form a cross-cell special-shaped connector. The wing-body has negative Poisson's ratio characteristics in the chord length and thickness directions, and has zero Poisson's ratio characteristics in the span direction.

2. The variant wing capable of actively adjusting chord length and thickness according to claim 1, characterized in that: The anisotropic cubic superstructure is composed of four cubic cells arrayed in the chord length and thickness directions. The cubic cell includes a special-shaped connector, an inclined connecting rod and a diamond-shaped structural member. A short straight rod is provided at each vertex position of the diamond-shaped structural member; six diamond-shaped structural members are located on the six faces of the cubic cell, and adjacent diamond-shaped structural members share the short straight rods at adjacent vertex positions. The two ends of the short straight rod at the vertex position of each diamond-shaped structural member are respectively connected to an inclined connecting rod, and three adjacent inclined connecting rods are connected together by a special-shaped connector.

3. The variant wing capable of actively adjusting chord length and thickness according to claim 2, characterized in that: The special-shaped connecting piece consists of four protrusions connected together, one of which is an inclined protrusion, and the other three are standard protrusions. The angle between the three standard protrusions is 90°. The standard protrusion is connected to the inclined connecting rod. The inclined protrusion is located in the xoz or yoz plane of the spatial rectangular coordinate system and the angle with the horizontal direction is greater than 0° and less than 45°.

4. The variant wing capable of actively adjusting chord length and thickness according to claim 2 or 3, characterized in that: The cross-cell special-shaped connector has four standard protrusions and one inclined protrusion, wherein two standard protrusions are collinear and respectively connected to an inclined connecting rod, and the remaining two standard protrusions are coplanar and respectively connected to two inclined connecting rods.

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