Variable-thickness wing structure

Abstract

The variable-thickness wing structure comprises a composite corrugated skin, a connecting rod assembly and a reinforcing plate, a fixing plate is fixedly arranged in the left side of the composite corrugated skin, a fixing frame is mounted on the outer side of the right end of the fixing plate, and a mounting plate is integrally and fixedly mounted on the right side of the fixing frame; an electric hydraulic rod is arranged in the middle of the left side of the mounting plate, and a connecting plate is fixedly mounted at the output end of the electric hydraulic rod; and a connecting rod assembly is mounted on the outer side of the connecting plate. The invention belongs to the technical field of wing structures, and aims at solving the problems that in the prior art, the thickness deformation degree of the upper side and the lower side cannot be accurately controlled at the same time, the limitation is large, and the supporting effect on the deformed composite corrugated skin is poor. The supporting device has the technical effects that the thickness deformation degree of the upper side and the lower side can be accurately controlled at the same time, the limitation of deformation is reduced, and the supporting effect on the deformed composite corrugated skin is improved.

Description

Technical Field

[0001] The invention relates to the technical field of wing structures, and in particular to a variable thickness wing structure. Background Art

[0002] The wing is the main structure for the aircraft to generate lift and control force, and its shape is an important factor in determining the aerodynamic characteristics of the aircraft. Therefore, most of the variant aircraft schemes at home and abroad choose deformable wings as deformable components. The wing section cut parallel to the symmetry plane of the wing is called the wing section, usually called the airfoil, which is a major factor in determining the aerodynamic characteristics of the wing. Research results show that increasing the relative thickness of the airfoil can increase the maximum lift coefficient accordingly. In addition, the relative thickness of the airfoil greatly affects the supersonic drag of the aircraft. When the aircraft flies at supersonic speed, its wave drag increases approximately in proportion to the square of the relative thickness of the airfoil. When designing an airfoil, its relative thickness is usually selected based on the empirical curve of the relationship between relative thickness and Mach number.

[0003] The concept of variable thickness wing is based on the relative thickness of the airfoil. By deforming the skin on the upper surface of the wing, the relative thickness of the wing is changed, thereby changing the aerodynamic characteristics of the wing. In the cruising state, the relative thickness of the wing is increased to ensure the lift coefficient of the aircraft, reduce fuel consumption, and increase the range; in the attack state, the relative thickness of the wing is reduced to reduce the superspeed wave resistance of the aircraft and improve the maneuverability of the aircraft.

[0004] For example, a variable thickness wing structure with a Chinese authorization publication number of CN 114291249 B discloses a wing structure with a simple and compact structure, high engineering practicality, and can effectively realize complex thickness changes of the upper and lower wing surfaces.

[0005] However, although most of the current variable thickness wing structures can achieve a certain degree of active deformation, they are unable to accurately control the deformation degree of the thickness of the upper and lower sides at the same time, and have great limitations, especially the inability to achieve distributed deformation function. At the same time, the support effect on the deformed composite corrugated skin is poor. Therefore, the present invention provides a variable thickness wing structure to solve the above problems. Summary of the invention

[0006] To this end, the present invention provides a variable thickness wing structure to solve the existing problem that the deformation degree of the thickness of the upper and lower sides cannot be accurately controlled at the same time, which has great limitations and the supporting effect of the deformed composite corrugated skin is poor.

[0007] In order to achieve the above object, the present invention provides the following technical solutions:

[0008] According to a first aspect of the present invention, a variable thickness wing structure comprises a composite corrugated skin, a connecting rod assembly and a reinforcement plate, wherein a fixing plate is fixedly arranged inside the left side of the composite corrugated skin, a fixing frame is installed outside the right end of the fixing plate, and a mounting plate is integrally fixedly installed on the right side of the fixing frame, an electric hydraulic rod is arranged in the middle of the left side of the mounting plate, and a connecting plate is fixedly installed at the output end of the electric hydraulic rod;

[0009] A connecting rod assembly is installed on the outer side of the connecting plate, and a connecting plate is installed on the outer side of the connecting rod assembly through a hinge, the connecting plate is adhesively fixed to the inner wall of the composite corrugated skin, and a wing rib is installed in the middle of the inner side of the composite corrugated skin;

[0010] A reinforcement plate is fixedly installed on the inner side of the connecting plate, and a front connecting rod is fixedly installed on the outer side of one end of the reinforcement plate, a rear connecting rod is fixedly installed on the outer side of the other end of the reinforcement plate, and the front end of the rear connecting rod is connected to the damper assembly located in the front connecting rod.

[0011] Furthermore, a leading edge is arranged at the inner left end of the composite corrugated skin, a trailing edge is installed at the inner right end of the composite corrugated skin, and a second support beam located in the wing rib is installed at the inner middle part of the composite corrugated skin.

[0012] Furthermore, the connecting rod assembly includes a first support rod, a second support rod and a third support rod, the right end of the first support rod is installed on the inner side of the outer side of the connecting plate by hinged rotation, two groups of second support rods are installed on the outer side of the first support rod by hinged rotation, and the left end of one group of second support rods is installed on the outer side of the mounting plate by hinged rotation.

[0013] Furthermore, two groups of third support rods are hingedly mounted on the outer side of the second support rod, and the left end of the third support rod is hingedly mounted on the outer side of one end of the connecting plate away from the composite corrugated skin.

[0014] Furthermore, both upper and lower ends of the wing rib are provided with groove structures matched with the connecting plate, and a second prefabricated through groove matched with the connecting plate is provided through the middle of the wing rib.

[0015] Furthermore, the connecting plate is connected to the wing rib in a sliding manner via a second prefabricated through groove, and a limiting plate located at the outer sides of the front and rear ends of the wing rib is fixedly installed in the middle of the connecting plate.

[0016] Furthermore, the reinforcing plate is symmetrically arranged front and back about the vertical center axis of the wing rib, and a ball is embedded on the lower side of one end of the reinforcing plate close to the wing rib, and a rolling groove matched with the ball is opened on the outer wall of the wing rib.

[0017] Furthermore, a first prefabricated through groove is formed inside both upper and lower ends of the wing rib, and both the front connecting rod and the rear connecting rod extend into the first prefabricated through groove, and the front end of the rear connecting rod extends into the interior of the front connecting rod.

[0018] Furthermore, first support beams are provided at both upper and lower ends of the right inner wall of the composite corrugated skin, and the lower end of the first support beam extends to the inner side of the outer side of the wing rib.

[0019] Furthermore, the reinforcement plate is located on the outside of the wing ribs, and the wing ribs are arranged at equal intervals inside the composite corrugated skin.

[0020] Compared with the prior art, the present invention has the following advantages:

[0021] 1. The electric hydraulic rod and the connecting plate drive the transmission assembly to change its angle, thereby realizing the transmission of motion, and then respectively exerting forces on the upper and lower connecting plates away from the wing ribs, which can simultaneously cause deformation of the upper and lower ends of the composite corrugated skin, so as to achieve the effect of simultaneously and accurately controlling the deformation degree of the thickness of the upper and lower sides. At the same time, it is convenient to control the elongation length of the electric hydraulic rod to achieve the adjustment of different thicknesses, thereby achieving the requirements of distributed large deformation, so that the overall structure has the advantages of simple structure and easy deformation.

[0022] 2. When the composite corrugated skin and the connecting plate deform and become thicker, the connecting plate drives the reinforcing plate to move synchronously in the direction away from the central axis of the wing rib. At this time, the ball rolls with the wing rib through the rolling groove, thereby ensuring the smooth movement of the reinforcing plate, so that the reinforcing plate can support the surrounding of the deformed composite corrugated skin, so that the composite corrugated skin is supported more evenly, which can ensure that the overall thickness changes evenly and continuously, and enhance the overall strength and stability of the wing;

[0023] 3. When the reinforcement plate moves, it drives the front connecting rod and the rear connecting rod to slide synchronously in the first prefabricated through groove. At the same time, the front connecting rod and the rear connecting rod are tightly connected under the action of the damper assembly, so that the two groups of reinforcement plates are located on the outside of the wing ribs and are tightly connected to the wing ribs respectively, so that the wing ribs can provide better support for the reinforcement plates, thereby facilitating further improving the supporting effect of the reinforcement plates on the connecting plates and the composite corrugated skin. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more intuitively illustrate the prior art and the present application, exemplary drawings are given below. It should be understood that the specific shapes and structures shown in the drawings should not generally be regarded as limiting conditions for implementing the present application; for example, those skilled in the art are capable of easily making conventional adjustments or further optimizations to the addition / reduction / attribution division, specific shapes, positional relationships, connection methods, and dimensional ratios of certain units based on the technical concepts and exemplary drawings disclosed in the present application.

[0025] Figure 1 A front cross-sectional view of a variable thickness wing structure provided for some embodiments of the present invention.

[0026] Figure 2 A side cross-sectional view of a variable thickness wing structure provided for some embodiments of the present invention.

[0027] Figure 3 A front cross-sectional view of the connection between a front connecting rod and a first prefabricated through groove of a variable thickness wing structure provided in some embodiments of the present invention.

[0028] Figure 4 A variable thickness wing structure provided in some embodiments of the present invention Figure 1 Enlarged view of point A in the middle.

[0029] Figure 5 A variable thickness wing structure provided in some embodiments of the present invention Figure 2 Enlarged view of point B in the middle.

[0030] Description of reference numerals:

[0031] 1. Composite corrugated skin; 2. Leading edge; 3. Trailing edge; 4. Fixed plate; 5. Fixed frame; 6. Mounting plate; 7. Electric hydraulic rod; 8. Connecting plate; 9. First support rod; 10. Second support rod; 11. Third support rod; 12. Connecting plate; 13. First support beam; 14. Second support beam; 15. Limiting plate; 16. Wing rib; 17. Reinforcement plate; 18. Front connecting rod; 19. Rear connecting rod; 20. Damper assembly; 21. First prefabricated through groove; 22. Ball; 23. Rolling groove; 24. Second prefabricated through groove. DETAILED DESCRIPTION

[0032] The present application is further described below in detail through specific embodiments in conjunction with the accompanying drawings.

[0033] like Figures 1 to 5 As shown, a variable thickness wing structure in an embodiment of the present invention includes: a composite corrugated skin 1, a connecting rod assembly and a reinforcement plate 17; a leading edge 2 is arranged at the inner left end of the composite corrugated skin 1, and a trailing edge 3 is installed at the inner right end of the composite corrugated skin 1, a rib 16 is installed at the inner middle part of the composite corrugated skin 1, a second support beam 14 located inside the rib 16 is installed at the inner middle part of the composite corrugated skin 1, and a first support beam 13 is arranged at both upper and lower ends of the right inner wall of the composite corrugated skin 1, which together constitute the overall wing structure.

[0034] The wing rib 16 is consistent with the shape of the airfoil and is arranged at equal intervals inside the composite corrugated skin 1. The first support beam 13 and the second support beam 14 are longitudinal members, and the lower ends of the second support beam 14 and the first support beam 13 extend to the outside of the wing rib 16 to prevent the first support beam 13 and the second support beam 14 from affecting the installation of the wing rib 16. At the same time, the wing rib 16 mainly bears most of the bending moment and shear force of the wing, ensuring the structural strength and stiffness of the wing, ensuring the strength and stability of the wing, and providing the necessary lift for the aircraft.

[0035] A fixing plate 4 is fixedly provided inside the left side of the composite corrugated skin 1, a fixing frame 5 is installed on the outer side of the right end of the fixing plate 4, screws are provided at the connection between the fixing plate 4 and the fixing frame 5, so as to facilitate the fixing and installation of the fixing frame 5, and a mounting plate 6 is integrally fixedly installed on the right side of the fixing frame 5, an electric hydraulic rod 7 is provided in the middle of the left side of the mounting plate 6, and a connecting plate 8 is fixedly installed on the output end of the electric hydraulic rod 7, the mounting plate 6 plays a good installation role for the electric hydraulic rod 7 and the connecting plate 8, so as to facilitate the installation of the electric hydraulic rod 7 and the connecting plate 8 inside the wing structure, and the electric hydraulic rod 7 provides a large driving load.

[0036] A connecting rod assembly is installed on the outer side of the connecting plate 8, and the connecting rod assembly includes a first support rod 9, a second support rod 10 and a third support rod 11. The right end of the first support rod 9 is installed on the inner side of the outer side of the connecting plate 8 by hinged rotation, and two groups of second support rods 10 are installed on the outer side of the first support rod 9 by hinged rotation, and the left end of a group of second support rods 10 is installed on the outer side of the mounting plate 6 by hinged rotation, and two groups of third support rods 11 are installed on the outer side of the second support rod 10 by hinged rotation, and the left end of the third support rod 11 is installed on the outer side of one end of the connecting plate 12 away from the composite corrugated skin 1 by hinged rotation, and the connecting rod assembly is installed in the gap between the connecting plate 8 and the connecting plate 12 by hinged rotation.

[0037] A connecting plate 12 is hingedly mounted on the outer side of the connecting rod assembly. The connecting plate 12 is bonded and fixed to the inner wall of the composite corrugated skin 1. The connecting plate 12 plays a good connecting role, facilitating the subsequent transmission of movement of the connecting rod assembly.

[0038] A second prefabricated through groove 24 matched with the connecting plate 8 is penetrated through the middle of the wing rib 16, and a limit plate 15 located on the outer side of the front and rear ends of the wing rib 16 is fixedly installed in the middle of the connecting plate 8. When the wing needs to be deformed, the electric hydraulic rod 7 is started to shorten the electric hydraulic rod 7 that was originally in an extended state, and drive the connecting plate 8 to move inside the composite corrugated skin 1. At this time, the connecting plate 8 is connected to the wing rib 16 in a sliding manner through the second prefabricated through groove 24. At the same time, the limit plate 15 limits the movement of the connecting plate 8, so as to ensure the stability of the movement of the connecting plate 8, and then facilitate the precise adjustment of the connecting rod assembly.

[0039] As the connecting plate 8 moves, the first support rod 9 rotates with the connecting plate 8 through the hinge, so that the inclination angle of the first support rod 9 changes and rotates with the two groups of second support rods 10 through the hinge, thereby driving the inclination angle of the second support rod 10 to rotate. As the second support rod 10 rotates, the two groups of third support rods 11 rotate with the second support rod 10 through the hinge, so that the inclination angle of the third support rod 11 changes, so that the two groups of third support rods 11 rotate with the connecting plate 12 through the hinge, respectively, to achieve motion transmission, and then generate forces on the upper and lower groups of connecting plates 12 away from the wing rib 16 respectively, which can cause the upper and lower ends of the composite corrugated skin 1 to deform at the same time, so as to adjust the thickness of the composite corrugated skin 1. At the same time, it is convenient to control the elongation length of the electric hydraulic rod 7 to achieve the adjustment of different thicknesses, thereby achieving the distributed large deformation requirements, and at the same time, the overall structure has the advantages of simple structure and easy deformation.

[0040] A reinforcing plate 17 is fixed on the inner side of the connecting plate 12 by screws. The reinforcing plate 17 is symmetrically arranged front and back about the vertical center axis of the wing rib 16, and a ball 22 is inlaid on the lower side of one end of the reinforcing plate 17 close to the wing rib 16. The outer wall of the wing rib 16 is provided with a rolling groove 23 adapted to the ball 22. When the composite corrugated skin 1 and the connecting plate 12 are deformed and thickened, the connecting plate 12 drives the reinforcing plate 17 to move synchronously in a direction away from the center axis of the wing rib 16. At this time, the ball 22 rolls with the wing rib 16 through the rolling groove 23, thereby ensuring the smoothness of the movement of the reinforcing plate 17; the reinforcing plate 17 can support the surrounding of the deformed composite corrugated skin 1, so that the composite corrugated skin 1 is subjected to a more uniform support force, which can ensure that the overall thickness changes evenly and continuously, thereby enhancing the overall strength and stability of the wing.

[0041] A front connecting rod 18 is fixedly installed on the outer side of one end of the reinforcement plate 17, and a rear connecting rod 19 is fixedly installed on the outer side of the other end of the reinforcement plate 17, and the front end of the rear connecting rod 19 is connected to the damper assembly 20 located in the front connecting rod 18, and the upper and lower ends of the wing rib 16 are penetrated by first prefabricated through grooves 21, and the front connecting rod 18 and the rear connecting rod 19 both extend into the first prefabricated through grooves 21, and the front end of the rear connecting rod 19 extends to the interior of the front connecting rod 18. The ends of the front connecting rod 18 and the rear connecting rod 19 away from the reinforcement plate 17 are both located in the first prefabricated through groove 21. When the reinforcement plate 17 moves, the two groups of reinforcement plates 17 drive the front connecting rod 18 and the rear connecting rod 19 to move synchronously, generating a tensile force on the damper assembly 20. When the reinforcement plate 17 stops moving, the damper assembly 20 rebounds, driving the front connecting rod 18 and the rear connecting rod 19 to be tightly connected, thereby making it easier for the reinforcement plate 17 and the wing rib 16 to be in a tightly connected state.

[0042] When the reinforcement plate 17 moves, it drives the front connecting rod 18 and the rear connecting rod 19 to slide synchronously in the first prefabricated through groove 21. At the same time, the front connecting rod 18 and the rear connecting rod 19 are tightly connected under the action of the damper assembly 20, so that the two groups of reinforcement plates 17 are located on the outside of the wing rib 16 and are tightly connected to the wing rib 16 respectively, so that the wing rib 16 can better support the reinforcement plate 17, thereby facilitating further improving the supporting effect of the reinforcement plate 17 on the connecting plate 12 and the composite corrugated skin 1.

[0043] A spring is arranged on the outer side of the damper assembly 20. Meanwhile, the expansion and contraction and stretching of the damper assembly 20 belong to the prior art and will not be described in detail here.

[0044] The upper and lower ends of the wing rib 16 are provided with groove structures adapted to the connecting plate 12 , so as to facilitate the installation of the connecting plate 12 on the inner side of the composite corrugated skin 1 without affecting the installation of the wing rib 16 .

[0045] The technical features of the above embodiments may be arbitrarily combined (as long as there is no contradiction in the combination of these technical features). To make the description concise, not all possible combinations of the technical features in the above embodiments are described; these embodiments that are not explicitly written should also be considered to be within the scope of this specification.

Claims

1. A variable thickness wing structure, comprising a composite corrugated skin (1), a connecting rod assembly and a reinforcement plate (17), characterized in that: A fixing plate (4) is fixedly arranged inside the left side of the composite corrugated skin (1), a fixing frame (5) is installed on the outer side of the right end of the fixing plate (4), and a mounting plate (6) is integrally fixedly installed on the right side of the fixing frame (5), an electric hydraulic rod (7) is arranged in the middle of the left side of the mounting plate (6), and a connecting plate (8) is fixedly installed on the output end of the electric hydraulic rod (7); A connecting rod assembly is installed on the outer side of the connecting plate (8), and a connecting plate (12) is installed on the outer side of the connecting rod assembly through a hinge, the connecting plate (12) is adhesively fixed to the inner wall of the composite corrugated skin (1), and a wing rib (16) is installed in the middle part of the inner side of the composite corrugated skin (1); A reinforcing plate (17) is fixedly mounted on the inner side of the connecting plate (12), and a front connecting rod (18) is fixedly mounted on the outer side of one end of the reinforcing plate (17), and a rear connecting rod (19) is fixedly mounted on the outer side of the other end of the reinforcing plate (17), and the front end of the rear connecting rod (19) is connected to a damper assembly (20) located in the front connecting rod (18).

2. A variable thickness wing structure according to claim 1, characterized in that: The composite corrugated skin (1) is provided with a leading edge (2) at the inner left end, and a trailing edge (3) is installed at the inner right end of the composite corrugated skin (1), and a second support beam (14) located inside the rib (16) is installed at the inner middle part of the composite corrugated skin (1).

3. A variable thickness wing structure according to claim 1, characterized in that: The connecting rod assembly comprises a first support rod (9), a second support rod (10) and a third support rod (11); the right end of the first support rod (9) is mounted on the inner side of the outer side of the connecting plate (8) by means of hinged rotation; two groups of second support rods (10) are mounted on the outer side of the first support rod (9) by means of hinged rotation; the left end of one group of the second support rods (10) is mounted on the outer side of the mounting plate (6) by means of hinged rotation.

4. A variable thickness wing structure according to claim 3, characterized in that: Two groups of third support rods (11) are hingedly mounted on the outer side of the second support rod (10), and the left end of the third support rod (11) is hingedly mounted on the outer side of one end of the connecting plate (12) away from the composite corrugated skin (1).

5. The variable thickness wing structure according to claim 1, characterized in that: The upper and lower ends of the wing rib (16) are provided with groove structures adapted to the connecting plate (12), and a second prefabricated through groove (24) adapted to the connecting plate (8) is provided through the middle of the wing rib (16).

6. A variable thickness wing structure according to claim 5, characterized in that: The connecting plate (8) is connected to the wing rib (16) in a sliding manner via a second prefabricated through groove (24), and a limiting plate (15) is fixedly installed in the middle of the connecting plate (8) and is located at the outer sides of the front and rear ends of the wing rib (16).

7. The variable thickness wing structure according to claim 1, characterized in that: The reinforcing plate (17) is arranged symmetrically front and rearward about the vertical center axis of the wing rib (16), and a ball (22) is embedded on the lower side of one end of the reinforcing plate (17) close to the wing rib (16), and a rolling groove (23) adapted to the ball (22) is opened on the outer wall of the wing rib (16).

8. The variable thickness wing structure according to claim 1, characterized in that: A first prefabricated through groove (21) is provided inside both upper and lower ends of the wing rib (16), and the front connecting rod (18) and the rear connecting rod (19) both extend into the first prefabricated through groove (21), and the front end of the rear connecting rod (19) extends into the interior of the front connecting rod (18).

9. The variable thickness wing structure according to claim 1, characterized in that: First support beams (13) are provided at both upper and lower ends of the right inner wall of the composite corrugated skin (1), and the lower end of the first support beam (13) extends to the inner side of the outer side of the wing rib (16).

10. The variable thickness wing structure according to claim 1, characterized in that: The reinforcing plates (17) are located outside the ribs (16), and the ribs (16) are arranged at equal intervals inside the composite corrugated skin (1).

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