A variable chord, camber and span morphing wing and aircraft

Abstract

The application discloses a variable-chord, variable-camber and variable-span morphing wing and aircraft, and belongs to the technical field of morphing wing structure design. The wing rib comprises a variable-chord single cell structure and a variable-camber single cell structure, a plurality of variable-chord single cell structures are sequentially connected to form a wing rib main body, and the front end and the rear end of the wing rib main body are connected to the variable-camber single cell structure respectively. The variable-chord single cell structure comprises a first connecting frame composed of X-shaped connecting rods and V-shaped connecting rods, two X-shaped connecting rods are connected together side by side, the middle parts of the two X-shaped connecting rods jointly form a quadrilateral frame, the V-shaped connecting rod is located in the quadrilateral frame and connected to the middle parts of the corresponding X-shaped connecting rods at both ends, so that the middle part of the first connecting frame forms a special-shaped structure. The variable-camber single cell structure comprises a second connecting frame composed of horizontal connecting rods, wave-shaped connecting rods and reinforcing connecting rods. Two wave-shaped connecting rods are symmetrically distributed on the upper side and the lower side of the horizontal connecting rod, each wave-shaped connecting rod is connected to the horizontal connecting rod through the reinforcing connecting rod at each bending position, and the reinforcing connecting rod is inclined towards the free end of the variable-camber single cell structure. The wing has good rigidity, deformation accuracy and aerodynamic performance.

Description

Technical Field

[0001] This invention belongs to the field of morphing wing structure design technology, specifically a morphing wing and aircraft with variable chord length, camber, and span. Background Technology

[0002] Variant wings are designed to change the wing shape and thus the flight attitude of an aircraft by altering the wing's chord length, camber, and / or span, thereby adapting to different flight environments and achieving better aerodynamic performance.

[0003] For example, during high-speed flight in the cruise phase, drag can be reduced by decreasing the wing area through variable chord length, while lift can be provided by increasing the wing area during low-speed flight in the takeoff and landing phases. When performing specific missions or dealing with unexpected situations during flight, the wing alters the lift distribution of the aircraft through changes in camber, thereby improving the aircraft's maneuverability. When an aircraft needs to fly at lower speeds and for longer periods, such as long-range cruise or reconnaissance missions, the aircraft can increase lift and lift-to-drag ratio by increasing the wingspan, thus maintaining high flight efficiency and extending endurance. In situations requiring higher maneuverability and flexibility, such as takeoff, landing, and cruise, wind resistance is reduced by shortening the wingspan to improve the aircraft's agility. Furthermore, variable wingspan provides better storage and transport characteristics, making it easier for the aircraft to be stored and transported.

[0004] Patent application CN109515683A, published on March 26, 2019, discloses a deformable wing with variable chord length and camber. The wing includes a leading edge section, a mid-section, and a trailing edge section. Multiple sets of parallel deformable units are distributed within the mid-section. Each deformable unit contains a parallelogram structure. The wing's camber and chord length are varied by locking the lower triangle of the parallelogram structure to change the shape of the upper triangle, and by locking the upper triangle to change the shape of the lower triangle. This wing achieves both bending and variable chord length functionality through its parallelogram structure, eliminating the need for complex deformation operations and maintenance. Summary of the Invention

[0005] In view of the shortcomings of the prior art, the technical problem to be solved by the present invention is to provide a variant wing and aircraft with variable chord length, camber and span.

[0006] The present invention solves the aforementioned technical problem by adopting the following technical solution:

[0007] A variable wing with variable chord length, camber, and span, comprising ribs, spars, and skin, wherein the ribs are capable of elongation, shortening, and bending, and the spars are capable of elongation and shortening; characterized in that the ribs comprise variable chord length single-cell structures and variable camber single-cell structures, multiple variable chord length single-cell structures are sequentially connected to form the rib body, the front and rear ends of the rib body are respectively connected to the variable camber single-cell structures, and adjacent single-cell structures share a common substrate;

[0008] The variable chord length single cell structure includes a first connecting frame that defines the direction of expansion and contraction. The first connecting frame includes an X-shaped link and a V-shaped link. The two X-shaped links are connected side by side, and the middle parts of the two X-shaped links together form a quadrilateral frame. The V-shaped link is located inside the quadrilateral frame and its two ends are connected to the middle parts of the corresponding X-shaped links, so that the middle part of the first connecting frame forms an irregular structure.

[0009] The variable curvature single-cell structure includes a second connecting frame that restricts the bending direction. The second connecting frame includes a horizontal connecting rod, a wave-shaped connecting rod, and a reinforcing connecting rod. Two wave-shaped connecting rods are symmetrically distributed on the upper and lower sides of the horizontal connecting rod. Each bending part of the wave-shaped connecting rod is connected to the horizontal connecting rod through the reinforcing connecting rod, and the reinforcing connecting rod is inclined toward the free end of the variable curvature single-cell structure.

[0010] Furthermore, the wing spars include a first support plate, a second support plate, and a variable span drive unit; two second support plates are symmetrically distributed on both sides of the first support plate, and at least one variable span drive unit is connected to the first support plate in the middle and connected to the corresponding second support plate at both ends.

[0011] The variable span drive unit includes a variable span drive component, a first link, a second link, and gears. One end of each of the two first links is rotatably connected to one end of the first support plate via a connecting shaft. Gears are provided on the two connecting shafts, and the two gears mesh. The other ends of the two first links are rotatably connected to one end of the corresponding second link, and the other ends of the two second links are rotatably connected to one end of the corresponding second support plate. When the spar is in its original length state, the connected first and second links have a certain included angle. One end of each of the two variable span drive components is rotatably connected to the other end of the first support plate, and the other ends of each of the two variable span drive components are rotatably connected to the middle of the corresponding first link.

[0012] Furthermore, the irregular structure in the middle of the first connecting frame has three collinear sharp corners, two of which are in the same direction and the other is in the opposite direction.

[0013] Furthermore, the variable curvature single-cell structure also includes a variable curvature driving element and a second substrate. The left and right sides of the two second substrates are connected together by a second connecting frame. The two variable curvature driving elements are located on the upper and lower parts of the two second substrates, and the fixed end and telescopic end of the variable curvature driving elements are connected to the two second substrates respectively.

[0014] Furthermore, the variable curvature single-cell structure also includes a first connecting frame; two first connecting frames are located on the upper and lower sides of the two second substrates, and the two sharp corners of the irregular structure with the same direction are close to the free end of the variable curvature single-cell structure.

[0015] Furthermore, the variable chord length single cell structure also includes a variable chord length drive and a first substrate; the two first substrates are connected together by at least their opposite sides via a first connecting frame, and the fixed end and the telescopic end of the variable chord length drive are respectively connected to the center of the two first substrates.

[0016] An aircraft characterized in that it comprises the aforementioned variant wing with variable chord length, camber, and span.

[0017] Compared with the prior art, the beneficial effects of the present invention are:

[0018] The variable chord length single-cell structure and variable camber single-cell structure of this invention are mechanical superstructures. The irregular structure in the middle of the first connecting frame restricts the direction of deformation of the single-cell structure, giving the variable chord length and variable camber single-cell structures the special property of zero Poisson's ratio. At the same time, the second connecting frame of the variable camber single-cell structure provides directional restriction for the wing's camber, improving the accuracy of the chord length and camber of the wing, and also giving the morphing wing better aerodynamic performance. The first and second connecting frames are made of flexible materials with a certain stiffness, which improves the stiffness and deformation accuracy of the wing. Moreover, both the variable chord length and variable camber single-cell structures are hollow structures, making the overall weight of the wing lighter and increasing the endurance of the aircraft. This wing has three deformation functions: variable chord length, camber, and span, allowing the aircraft to change the wing shape when performing different flight missions to optimize the lift-to-drag ratio of the wing and improve flight performance and efficiency. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the overall structure;

[0020] Figure 2 This is a schematic diagram of the wing rib structure;

[0021] Figure 3 This is a schematic diagram of a variable string length single-cell structure;

[0022] Figure 4 This is a schematic diagram of the structure of the first connecting frame;

[0023] Figure 5 A schematic diagram of a single-cell structure with variable curvature;

[0024] Figure 6 This is a schematic diagram of the second connecting frame;

[0025] Figure 7 This is a schematic diagram of the wing beam structure;

[0026] In the figure, 100 - variable chord length single-cell structure; 200 - variable curvature single-cell structure; 300 - wing spars;

[0027] 101-First connecting frame; 102-Variable chord length drive; 103-First base plate; 201-Second connecting frame; 202-Variable curvature drive; 203-Second base plate; 301-First support plate; 302-Second support plate; 303-Variable extension drive; 304-First connecting rod; 305-Second connecting rod; 306-Gear;

[0028] 101-1, X-shaped link; 101-2, V-shaped link; 201-1, horizontal link; 201-2, wavy link; 201-3, reinforced link. Detailed Implementation

[0029] Specific embodiments are given below with reference to the accompanying drawings. These specific embodiments are only used to describe the technical solution of the present invention in detail, and are not intended to limit the scope of protection of this application.

[0030] On the one hand, the present invention provides a variant wing (hereinafter referred to as a wing) with variable chord length, camber, and span. Figures 1-7 The wing body comprises ribs, spars 300, and skin. The ribs include variable chord length single-cell structures 100 and variable camber single-cell structures 200. Multiple (two in this embodiment) variable chord length single-cell structures 100 are sequentially connected to form the rib body. Multiple variable camber single-cell structures 200 are sequentially connected to the front and rear ends of the rib body, respectively. Adjacent single-cell structures share a common substrate. In this embodiment, one variable camber single-cell structure 200 is connected to the front end of the rib body, and two variable camber single-cell structures 200 are connected to the rear end. The variable chord length single-cell structure 100 can extend and shorten along the rib length direction, thus achieving variable chord length of the wing. The variable camber single-cell structure 200 can bend, thus achieving variable camber of the wing.

[0031] The variable chord length single cell structure 100 includes a first connecting frame 101, a variable chord length driving member 102, and a first substrate 103; the two first substrates 103 are connected together by the first connecting frame 101 at least on opposite sides; the fixed end of the variable chord length driving member 102 is fixedly connected to the center of one of the first substrates 103, and the telescopic end is fixedly connected to the center of the other first substrate 103; the first connecting frame 101 is telescopically driven by the telescopic extension of the variable chord length driving member 102 to achieve the variable chord length of the wing.

[0032] The first connecting frame 101 includes an X-shaped connecting rod 101-1 and a V-shaped connecting rod 101-2; the two X-shaped connecting rods 101-1 are connected side by side, and the middle parts of the two X-shaped connecting rods 101-1 together form a quadrilateral frame. The V-shaped connecting rod 101-2 is located inside the quadrilateral frame and its two ends are fixedly connected to the middle parts of the corresponding X-shaped connecting rods 101-1, so that the middle part of the first connecting frame 101 forms an irregular structure with three sharp corners, and the three sharp corners are collinear, wherein two of the sharp corners are in the same direction and the other sharp corner is in the opposite direction. The direction of the sharp corner of the irregular structure plays a dominant role in restricting the extension and retraction direction of the first connecting frame 101.

[0033] The variable bending single-cell structure 200 includes a second connecting frame 201, a variable bending drive 202, and a second substrate 203. The left and right sides of the two second substrates 203 are connected together by the second connecting frame 201. The two variable bending drive 202 are located at the upper and lower parts of the two second substrates 203. The fixed end of the variable bending drive 202 is fixedly connected to one of the second substrates 203, and the telescopic end of the variable bending drive 202 is fixedly connected to the other second substrate 203 (the end of which is the free end of the variable bending single-cell structure). When the upper variable bending drive 202 extends and the lower variable bending drive 202 shortens, the variable bending single-cell structure 200 bends downward. When the upper variable bending drive 202 shortens and the lower variable bending drive 202 extends, the variable bending single-cell structure 200 bends upward. The second connecting frame 201 plays a dominant role in restricting the bending direction of the variable bending single-cell structure 200.

[0034] The variable bending single cell structure 200 also includes a first connecting frame 101; two first connecting frames 101 are located on the upper and lower sides of the two second substrates 203, and the two sharp corners of the irregular structure of the first connecting frame 101 are close to one side of the second substrate 203 connected to the telescopic end of the variable bending drive 202. The first connecting frame 101 is used to assist the bending deformation of the variable bending single cell structure 200.

[0035] The second connecting frame 201 includes a horizontal connecting rod 201-1, a wave-shaped connecting rod 201-2, and a reinforcing connecting rod 201-3. The two wave-shaped connecting rods 201-2 are symmetrically distributed on the upper and lower sides of the horizontal connecting rod 201-1. Each bent part of the wave-shaped connecting rod 201-2 is connected to the horizontal connecting rod 201-1 through the reinforcing connecting rod 201-3. The reinforcing connecting rod 201-3 is inclined toward the second substrate 203 connected to the telescopic end of the variable bending degree drive member 202, so that the second connecting frame 201 plays a dominant role in restricting the bending direction of the variable bending degree single cell structure 200.

[0036] The wing spars 300 includes a first support plate 301, a second support plate 302, and a variable span drive unit; the two second support plates 302 are symmetrically distributed on both sides of the first support plate 301, and the two second support plates 302 are fixedly connected to the corresponding wing ribs; at least one variable span drive unit is connected to the first support plate 301 in the middle and to the corresponding second support plate 302 at both ends, and the variable span drive unit achieves the variable span of the wing through its extension and retraction. The variable span drive unit includes a variable span drive component 303, a first connecting rod 304, a second connecting rod 305, and gears 306. One end of each of the two first connecting rods 304 is rotatably connected to one end of one side of the first support plate 301 via a connecting shaft. Gears 306 are respectively mounted on the two connecting shafts and mesh with each other. The other ends of each of the two first connecting rods 304 are rotatably connected to one end of a corresponding second connecting rod 305, and the other ends of each of the two second connecting rods 305 are rotatably connected to one end of a corresponding second support plate 302. When the spar 300 is at its original length, there is a certain angle between the connected first connecting rods 304 and second connecting rods 305, facilitating the extension of the variable span drive unit. The two variable-length drive members 303 are rotatably connected at one end to the other end of the first support plate 301, and at the other end to the middle of the corresponding first connecting rod 304. The two variable-length drive members 303 extend simultaneously to drive the two first connecting rods 304 to rotate around the first support plate 301, thereby pushing the two second connecting rods 305 to rotate, increasing the angle between the connected first connecting rods 304 and second connecting rods 305, thus realizing the extension of the variable-length drive unit. Conversely, the two variable-length drive members 303 retract simultaneously, decreasing the angle between the connected first connecting rods 304 and second connecting rods 305, thus realizing the retraction of the variable-length drive unit.

[0037] The two ribs are connected by a spars and wrapped together by a skin. The wing adopts an integral design, which improves the overall strength of the wing and makes the airfoil smoother during the wing transformation process, thus improving aerodynamic performance.

[0038] The aforementioned variable chord length drive 102, variable curvature drive 202, and variable span drive 303 can be hydraulic rods, pneumatic rods, or electric push rods. The first connecting frame 101 and the second connecting frame 201 are made of flexible materials with a certain rigidity, such as nylon or spring steel, to ensure the deformation function of the single-cell structure.

[0039] On the other hand, the present invention also provides an aircraft comprising the aforementioned variant wing with variable chord length, camber, and span.

[0040] The working principle and workflow of this invention are as follows:

[0041] The variable chord length driving component 102 drives the variable chord length single cell structure 100 to extend and shorten, thereby achieving the extension and shortening of the wing rib and realizing the purpose of variable chord length of the wing.

[0042] The camber of the cambered single-cell structure 200 is achieved by the cambered driving element 202. For a single cambered single-cell structure 200, when the upper cambered driving element 202 extends and the lower cambered driving element 202 shortens, the cambered single-cell structure 200 bends downward; when the upper cambered driving element 202 shortens and the lower cambered driving element 202 extends, the cambered single-cell structure 200 bends upward. The camberedness of the leading edge of the wing is achieved by the camberedness of the cambered single-cell structure 200 at the front end of the rib body, and the camberedness of the trailing edge of the wing is achieved by the camberedness of the cambered single-cell structure 200 at the rear end of the rib body.

[0043] Two variable span drive units 303 extend simultaneously, driving two first links 304 to rotate around the first support plate 301, which in turn pushes two second links 305 to rotate, increasing the angle between the connected first links 304 and second links 305, thus extending the variable span drive unit and increasing the wing span. Conversely, when the two variable span drive units 303 retract simultaneously, the angle between the connected first links 304 and second links 305 decreases, thus retracting the variable span drive unit and shortening the wing span, achieving the purpose of variable wing span.

[0044] The three deformation functions of the wing—chord length, camber, and span—are independent of each other, realizing the deformation function of the composite wing.

[0045] Any aspects not covered in this invention are applicable to existing technologies.

Claims

1. A variable wing with variable chord length, camber, and span, comprising ribs, spars, and skin, wherein the ribs are capable of elongation, shortening, and bending, and the spars are capable of elongation and shortening; characterized in that, The ribs include variable chord length single-cell structures and variable curvature single-cell structures. Multiple variable chord length single-cell structures are connected in sequence to form the rib body. The front and rear ends of the rib body are connected to the variable curvature single-cell structures respectively. Adjacent single-cell structures share a substrate. The variable chord length single cell structure includes a first connecting frame that defines the direction of expansion and contraction. The first connecting frame includes an X-shaped link and a V-shaped link. The two X-shaped links are connected side by side, and the middle parts of the two X-shaped links together form a quadrilateral frame. The V-shaped link is located inside the quadrilateral frame and its two ends are connected to the middle parts of the corresponding X-shaped links, so that the middle part of the first connecting frame forms an irregular structure. The variable curvature single-cell structure includes a second connecting frame that restricts the bending direction. The second connecting frame includes a horizontal connecting rod, a wave-shaped connecting rod, and a reinforcing connecting rod. Two wave-shaped connecting rods are symmetrically distributed on the upper and lower sides of the horizontal connecting rod. Each bending part of the wave-shaped connecting rod is connected to the horizontal connecting rod through the reinforcing connecting rod, and the reinforcing connecting rod is inclined toward the free end of the variable curvature single-cell structure.

2. A variable chord length, camber, and span variator wing according to claim 1, characterized in that, The wing spars include a first support plate, a second support plate, and a variable span drive unit; the two second support plates are symmetrically distributed on both sides of the first support plate, and the middle part of at least one variable span drive unit is connected to the first support plate, and both ends are connected to the corresponding second support plates. The variable span drive unit includes a variable span drive component, a first connecting rod, a second connecting rod, and gears; one end of each of the two first connecting rods is rotatably connected to one end of the first support plate via a connecting shaft, and gears are respectively provided on the two connecting shafts, and the two gears mesh; the other end of each of the two first connecting rods is rotatably connected to one end of the corresponding second connecting rod, and the other end of each of the two second connecting rods is rotatably connected to one end of the corresponding second support plate; when the spar is in its original length state, the connected first and second connecting rods have a certain included angle; one end of each of the two variable span drive components is rotatably connected to the other end of the first support plate, and the other end of each of the two variable span drive components is rotatably connected to the middle of the corresponding first connecting rod.

3. A variant wing with variable chord length, camber, and span according to claim 1 or 2, characterized in that, The irregular structure in the middle of the first connecting frame has three collinear sharp corners, two of which are in the same direction and the other is in the opposite direction.

4. A variant wing with variable chord length, camber, and span according to claim 3, characterized in that, The variable curvature single-cell structure also includes a variable curvature driving element and a second substrate. The left and right sides of the two second substrates are connected together by a second connecting frame. The two variable curvature driving elements are located on the upper and lower parts of the two second substrates, and the fixed end and telescopic end of the variable curvature driving elements are connected to the two second substrates respectively.

5. A variant wing with variable chord length, camber, and span according to claim 3 or 4, characterized in that, The variable curvature single cell structure also includes a first connecting frame; two first connecting frames are located on the upper and lower sides of the two second substrates, and the two sharp corners of the irregular structure with the same direction are close to the free end of the variable curvature single cell structure.

6. A variable chord length, camber, and span variator wing according to claim 1, characterized in that, The variable chord length single cell structure further includes a variable chord length drive and a first substrate; the two first substrates are connected together by at least two opposite sides via a first connecting frame, and the fixed end and the telescopic end of the variable chord length drive are respectively connected to the center of the two first substrates.

7. An aircraft, characterized in that, The aircraft comprises a variant wing with variable chord length, camber, and span as described in claim 1.

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