Variable-elongation wing structure

Abstract

The invention discloses a variable-elongation wing structure which comprises a wing shell, a transmission assembly and a locking assembly, a composite corrugated skin is fixedly mounted in the middle of the wing shell, a wing rib is mounted in the wing shell, a mounting strip is mounted on the inner side of the wing rib, and a fixing plate is fixedly mounted in the middle of the mounting strip; and a hydraulic cylinder is mounted on the rear side of the front end of the fixed plate. The invention belongs to the technical field of wing structures, and aims to solve the problems that in the prior art, a driving system is too large in mass and high in complexity, and meanwhile, a wing cannot be locked in an auxiliary mode according to the stretching length in the stretching process. According to the technical effects, the extension change of the whole wing structure is achieved in a mode that the transmission assembly conducts power transmission, the complexity is reduced, meanwhile, the auxiliary locking function is achieved, and the phenomenon of displacement deviation of the adjusted extension due to the phenomena that the internal oil pressure of the hydraulic cylinder is unstable and the like is effectively prevented.

Description

Technical Field

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

[0002] Intelligent transformable aircraft can achieve the most optimized flight performance by changing its aerodynamic shape in different flight missions or different mission stages of the same mission, and has become an important development direction of aircraft technology. Large aspect ratio aircraft have good low-speed flight capabilities, strong endurance, and good take-off and landing performance, but their high-speed flight performance is poor; while small aspect ratio aircraft with poor low-speed flight performance have low total resistance and strong maneuverability when flying at high speeds, and have high-speed sprint capabilities. The small wingspan can also reduce parking space. The retractable and deformable wing aircraft combines the above characteristics. By controlling the retraction or extension of the outer wing within the main wing, the aspect ratio of the aircraft is greatly changed, so that the aerodynamic performance and the flight mission are optimally matched. It can be applied to large and medium-sized UAVs or cruise missiles that integrate reconnaissance and strike missions;

[0003] However, most of the telescopic deformation structures in the current variable-span wing structures mostly use gears and rack mechanisms and sliding mechanisms as drive systems; the drive system has too large a mass and is relatively complex, which leads to an increase in the weight of the wing and insufficient spanwise stiffness, which reduces the wing's load-bearing capacity and reliability; at the same time, the wing cannot be auxiliary-locked according to the extended length during the extension process. Therefore, the present invention provides a variable-span wing structure to solve the above problems. Summary of the invention

[0004] To this end, the present invention provides a variable-span wing structure to solve the problems that the existing drive system is too heavy and complex, and at the same time, the wing cannot be auxiliary locked according to the extended length during the extension process.

[0005] In order to achieve the above object, the present invention provides the following technical solutions:

[0006] According to a first aspect of the present invention, a variable-length wing structure comprises a wing shell, a transmission assembly and a locking assembly, wherein a composite corrugated skin is fixedly installed in the middle of the wing shell, a wing rib is installed inside the wing shell, a mounting strip is installed on the inner side of the wing rib, a fixing plate is fixedly installed in the middle of the mounting strip, a hydraulic cylinder is installed at the rear side of the front end of the fixing plate, and a piston rod is connected to the output end of the hydraulic cylinder;

[0007] A transmission assembly is installed on the outside of the piston rod, and mounting plates are installed on the outsides of both left and right ends of the transmission assembly. A rotating shaft is fixedly installed on the outside of one end of the transmission assembly, and a limiting wheel is fixedly arranged on the outside of the upper end of the rotating shaft.

[0008] A locking assembly located in the mounting plate is arranged on the inner side of the right end of the limiting wheel.

[0009] Furthermore, built-in beams are installed through the front and rear ends of the wing rib, and the left end of the built-in beam is fixedly installed inside the wing shell, and the right end of the built-in beam extends through and extends to the outside of the right end of the wing shell.

[0010] Furthermore, the rear end of the piston rod passes through the interior of the fixing plate, and the piston rod and the fixing plate are connected in a sliding manner.

[0011] Furthermore, the transmission assembly includes a fixed block, a first support plate and a connecting block. The fixed block is fixedly installed on the outside of the piston rod, and the first support plate is hingedly installed on the outside of the fixed block. Two groups of connecting blocks are arranged at the front end of the outer side of the piston rod.

[0012] Furthermore, fixing bolts are provided at the connection points of the two groups of connection blocks, and second support plates are respectively installed at the left and right ends of the connection blocks through hinges.

[0013] Furthermore, the length of the second support plate is greater than that of the first support plate, and one end of the second support plate away from the connecting block is connected to the mounting plate by a hinge.

[0014] Furthermore, a mounting groove is provided inside the connecting block, and an electromagnet is fixed inside the mounting groove by screws. A prefabricated groove is provided in the middle of the inner side of the piston rod, and the electromagnet extends to the inside of the prefabricated groove at one end close to the piston rod.

[0015] Furthermore, the locking assembly includes an installation cavity, an electric telescopic rod and a limit block. The installation cavity is opened inside the upper end of the mounting plate, and the electric telescopic rod is installed inside the installation cavity. The output end of the electric telescopic rod is fixedly installed with a limit block located on the inner side of the right end of the limit wheel.

[0016] Furthermore, a toothed structure is fixedly mounted at an equal angle on the outer side of the limiting wheel, and the limiting block is connected to the toothed structure in a snap-fit ​​manner, and the lower end of the limiting block extends to the inside of the mounting plate.

[0017] Furthermore, a connecting plate is fixedly installed on the outer side of one end of the fixing plate away from the piston rod, and the left and right ends of the mounting strip respectively extend to the inside of the connecting plate, and the mounting strip is respectively connected to the wing rib and the connecting plate in a sliding manner.

[0018] Compared with the prior art, the present invention has the following advantages:

[0019] 1. The piston rod and the transmission assembly are used to evenly transmit power, so as to better achieve the purpose of driving. The power transmission of the transmission assembly can realize the change of the span length of the entire wing structure, reduce the complexity, reduce the weight of the wing, and improve the spanwise stiffness and load-bearing capacity of the wing, thereby effectively improving the overall reliability;

[0020] 2. A toothed structure is fixedly installed at an equal angle on the outer side of the limiting wheel, and the limiting block is connected to the toothed structure by a snap-fitting manner. When the transmission assembly completes the adjustment of the wing span, the sensor is used to determine whether the limiting block is aligned with the gap of the toothed structure on the outer side of the limiting wheel. If aligned, the electric telescopic rod is started to extend the electric telescopic rod, drive the limiting block to move downward, and insert it into the gap of the toothed structure on the outer side of the limiting wheel, and snap-fit ​​with the limiting wheel and the limiting block in turn, so as to fix the limiting wheel and the rotating shaft, and effectively prevent the displacement deviation of the adjusted span due to the unstable internal oil pressure of the hydraulic cylinder;

[0021] 3. The end of the electromagnet close to the piston rod extends to the inside of the prefabricated groove. A magnetic strip is embedded and fixed inside the prefabricated groove. The magnetism of the electromagnet and the magnetic strip are opposite. After power is turned on, the electromagnet and the magnetic strip are magnetically connected to fix the position of the connecting block, thereby playing an auxiliary fixing role and further preventing the displacement deviation of the extension. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] 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.

[0023] Figure 1 A front cross-sectional view of a variable-span wing structure provided for some embodiments of the present invention.

[0024] Figure 2 A side cross-sectional view of a variable-span wing structure provided for some embodiments of the present invention.

[0025] Figure 3 A top view cross-sectional view of a variable span wing structure provided for some embodiments of the present invention.

[0026] Figure 4 A top view of the connection between a limiting wheel and a limiting block of a variable-length wing structure provided in some embodiments of the present invention.

[0027] Figure 5A top view cross-sectional view of the connection between a connecting block and an electromagnet of a variable-length wing structure provided in some embodiments of the present invention.

[0028] Figure 6 A variable-span wing structure provided in some embodiments of the present invention Figure 1 Enlarged view of point A in the middle.

[0029] Description of reference numerals:

[0030] 1. Wing shell; 2. Composite corrugated skin; 3. Wing rib; 4. Built-in beam; 5. Mounting strip; 6. Fixing plate; 7. Hydraulic cylinder; 8. Piston rod; 9. Fixing block; 10. First support plate; 11. Mounting plate; 12. Connecting block; 13. Second support plate; 14. Electromagnet; 15. Prefabricated groove; 16. Rotating shaft; 17. Limiting wheel; 18. Mounting cavity; 19. Electric telescopic rod; 20. Limiting block; 21. Connecting plate; 22. Fixing bolt; 23. Mounting groove. DETAILED DESCRIPTION

[0031] The present application is further described below in detail through specific embodiments in conjunction with the accompanying drawings.

[0032] like Figures 1 to 6 As shown, a variable-span wing structure in an embodiment of the first aspect of the present invention includes a wing shell 1, a transmission assembly and a locking assembly. A composite corrugated skin 2 is fixedly installed in the middle of the wing shell 1, and ribs 3 are installed inside the wing shell 1, which together constitute a wing structure. The composite corrugated skin 2 is a flexible structure for a variable wing, and it is composed of a composite corrugated plate, a composite thin plate and an elastomer layer.

[0033] The wing rib 3 serves as the lateral force-bearing frame of the wing. Its main function is to maintain the cross-sectional shape of the wing and ensure that the wing can maintain the designed aerodynamic shape under different flight conditions.

[0034] A mounting strip 5 is installed on the inner side of the rib 3, and a fixing plate 6 is fixedly installed in the middle of the mounting strip 5. A hydraulic cylinder 7 is installed on the rear side of the front end of the fixing plate 6, and a piston rod 8 is connected to the output end of the hydraulic cylinder 7. The mounting strip 5 and the fixing plate 6 play a good role in fixing and installing the hydraulic cylinder 7.

[0035] A transmission assembly is installed on the outside of the piston rod 8, and mounting plates 11 are installed on the outsides of the left and right ends of the transmission assembly. The transmission assembly includes a fixed block 9, a first support plate 10 and a connecting block 12. The fixed block 9 is fixedly installed on the outside of the piston rod 8, and the first support plate 10 is hingedly installed on the outside of the fixed block 9, and the end of the first support plate 10 away from the fixed block 9 forms a rotating structure with the mounting plate 11 through a rotating shaft 16. Two groups of connecting blocks 12 are arranged at the front end of the outer side of the piston rod 8.

[0036] When it is necessary to adjust the span of the wing, the hydraulic cylinder 7 is started to extend the piston rod 8 from the hydraulic cylinder 7. At this time, the piston rod 8 drives the fixing block 9 to move backward, so that the fixing block 9 rotates with the first support plate 10 through the hinge, thereby changing the inclination angle of the first support plate 10. At the same time, the first support plate 10 drives the rotating shaft 16 and the mounting plate 11 to rotate, thereby conveniently driving the two groups of mounting plates 11 to move in the direction close to the piston rod 8 to realize power transmission, and then conveniently bringing the two middle groups of wing ribs 3 closer together, thereby shortening the span of the wing. Conversely, the distance between the two middle groups of wing ribs 3 can be driven to become farther, thereby lengthening the span of the wing, thereby conveniently realizing the span change of the entire wing structure.

[0037] The rear end of the piston rod 8 passes through the interior of the fixed plate 6, and the piston rod 8 and the fixed plate 6 are connected in a sliding manner. The fixed plate 6 limits the piston rod 8 to ensure the smooth movement of the piston rod 8.

[0038] A fixing bolt 22 is provided at the connection of the two groups of connecting blocks 12, and the left and right ends of the connecting block 12 are respectively installed with a second support plate 13 through a hinge. The end of the second support plate 13 away from the connecting block 12 is connected to the mounting plate 11 through a hinge. Three groups of first support plates 10 are provided on the outside of the piston rod 8 from front to back, which is convenient for uniform transmission of power, so as to better achieve the purpose of driving.

[0039] The present invention realizes the span length change of the entire wing structure by means of power transmission through a transmission assembly, reduces the complexity, reduces the weight of the wing, improves the spanwise stiffness of the wing and the wing load-bearing capacity, thereby effectively improving the overall reliability.

[0040] The second support plate 13 is located outside the front end of the first support plate 10 of the middle group. When the first support plate 10 drives the mounting plate 11 to move toward the direction close to the piston rod 8, the second support plate 13 is respectively rotated with the mounting plate 11 and the connecting block 12 through hinges, so that the inclination angle thereof is changed, so as to provide auxiliary support for the mounting plate 11.

[0041] At the same time, the length of the second support plate 13 is greater than that of the first support plate 10, which can effectively ensure the movement trajectory of the connecting block 12, avoid the movement trajectory of the connecting block 12 being opposite to the above movement steps, and further ensure the uniformity of force.

[0042] A connecting plate 21 is fixedly installed on the outer side of one end of the fixing plate 6 away from the piston rod 8, and the left and right ends of the mounting strip 5 extend to the inside of the connecting plate 21 respectively. The mounting strip 5 is connected to the wing rib 3 and the connecting plate 21 in a sliding manner respectively. The wing rib 3 and the connecting plate 21 play a good role in limiting and supporting the mounting strip 5, so that the hydraulic cylinder 7 can be installed through the mounting strip 5 and the fixing plate 6. When the wing span changes, the mounting strip 5 can slide inside the wing rib 3 and the connecting plate 21 to ensure the overall stability.

[0043] Built-in beams 4 are installed through the front and rear ends of the wing rib 3, and the left end of the built-in beam 4 is fixedly installed inside the wing shell 1, and the right end of the built-in beam 4 extends through to the outside of the right end of the wing shell 1. When the whole is installed on both sides of the fuselage, the right end of the built-in beam 4 extends into the fuselage. At the same time, there is a certain space inside the fuselage to facilitate the storage of the built-in beam 4. When the wing span becomes shorter, the wing rib 3 and the built-in beam 4 slide. At this time, the built-in beam 4 extending to the outside of the right end of the wing shell 1 is stored in the fuselage, so as to reasonably support the leading edge of the wing through the built-in beam 4, thereby avoiding the phenomenon that the support effect becomes worse due to the adjustment of the span.

[0044] A rotating shaft 16 is fixedly installed on the outside of one end of the transmission assembly, and a limiting wheel 17 is fixedly arranged on the outside of the upper end of the rotating shaft 16, and a locking assembly located in the mounting plate 11 is arranged on the inner side of the right end of the limiting wheel 17. The locking assembly includes an installation cavity 18, an electric telescopic rod 19 and a limiting block 20. The installation cavity 18 is opened inside the upper end of the mounting plate 11, and the electric telescopic rod 19 is installed inside the installation cavity 18. The output end of the electric telescopic rod 19 is fixedly installed with a limiting block 20 located on the inner side of the right end of the limiting wheel 17. The installation cavity 18 plays a good installation role for the electric telescopic rod 19 and the limiting block 20, and a sensor is arranged inside the installation cavity 18.

[0045] A toothed structure is fixedly installed at an equal angle on the outer side of the limiting wheel 17, and the limiting block 20 is connected to the toothed structure in a snap-fitting manner. The lower end of the limiting block 20 extends to the inside of the mounting plate 11. When the transmission assembly completes the adjustment of the wing span, the sensor is used to determine whether the limiting block 20 is aligned with the gap in the toothed structure on the outer side of the limiting wheel 17. If aligned, the electric telescopic rod 19 is started to extend the electric telescopic rod 19, drive the limiting block 20 to move downward, and insert it into the gap in the toothed structure on the outer side of the limiting wheel 17, and snap-fit ​​with the limiting wheel 17 and the limiting block 20 in turn, so as to fix the limiting wheel 17 and the rotating shaft 16, and effectively prevent the hydraulic cylinder 7 from causing displacement deviation in the adjusted span due to unstable internal oil pressure and the like.

[0046] A mounting groove 23 is formed inside the connection block 12, and an electromagnet 14 is fixedly mounted inside the mounting groove 23 by screws, and a prefabricated groove 15 is formed in the middle of the inner side of the piston rod 8. When the connection block 12 slides forward on the outer side of the piston rod 8 driven by the second support plate 13, the force exerted on the mounting plate 11 is evenly transmitted to the piston rod 8, so as to further improve the supporting effect of the mounting plate 11.

[0047] The end of the electromagnet 14 close to the piston rod 8 extends to the inside of the prefabricated groove 15, and a magnetic strip is embedded and fixed inside the prefabricated groove 15. When the electromagnet 14 is energized, it will generate a magnetic field, which will attract the magnetic strip, so that the electromagnet 14 and the magnetic strip are magnetically connected. Since the connecting block 12 is connected to the magnetic strip, when the magnetic strip is attracted and fixed by the electromagnet 14, the position of the connecting block 12 will also be fixed.

[0048] If the sensor detects that the limit block 20 is not aligned with the gap of the outer tooth structure of the limit wheel 17, the electromagnet 14 is started. The magnetism of the electromagnet 14 is opposite to that of the magnetic strip. After power is turned on, the electromagnet 14 and the magnetic strip are magnetically connected to fix the position of the connecting block 12, thereby playing an auxiliary fixing role and further preventing the displacement deviation of the extension.

[0049] 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-span wing structure, comprising a wing shell (1), a transmission assembly and a locking assembly, characterized in that: A composite corrugated skin (2) is fixedly installed in the middle of the wing shell (1), and a wing rib (3) is installed inside the wing shell (1), a mounting strip (5) is installed on the inner side of the wing rib (3), and a fixing plate (6) is fixedly installed in the middle of the mounting strip (5), a hydraulic cylinder (7) is installed at the rear side of the front end of the fixing plate (6), and the output end of the hydraulic cylinder (7) is connected to a piston rod (8); A transmission assembly is installed on the outside of the piston rod (8), and mounting plates (11) are installed on the outsides of both left and right ends of the transmission assembly. A rotating shaft (16) is fixedly installed on the outside of one end of the transmission assembly, and a limiting wheel (17) is fixedly arranged on the outside of the upper end of the rotating shaft (16); A locking assembly located inside the mounting plate (11) is arranged on the inner side of the right end of the limiting wheel (17).

2. A variable-span wing structure according to claim 1, characterized in that: Internal beams (4) are installed through the front and rear ends of the wing rib (3), and the left end of the internal beam (4) is fixedly installed inside the wing shell (1), and the right end of the internal beam (4) extends through and extends to the outside of the right end of the wing shell (1).

3. A variable-span wing structure according to claim 2, characterized in that: The rear end of the piston rod (8) passes through the interior of the fixed plate (6), and the piston rod (8) and the fixed plate (6) are connected in a sliding manner.

4. The variable-span wing structure according to claim 1, characterized in that: The transmission assembly comprises a fixed block (9), a first support plate (10) and a connecting block (12); the fixed block (9) is fixedly mounted on the outer side of a piston rod (8), and the first support plate (10) is hingedly mounted on the outer side of the fixed block (9); and two groups of connecting blocks (12) are arranged at the outer front end of the piston rod (8).

5. The variable-span wing structure according to claim 4, characterized in that: A fixing bolt (22) is provided at the connection point of the two groups of connection blocks (12), and a second support plate (13) is respectively installed at the left and right ends of the connection block (12) through hinges.

6. A variable-span wing structure according to claim 5, characterized in that: The length dimension of the second support plate (13) is greater than the length dimension of the first support plate (10), and one end of the second support plate (13) away from the connecting block (12) is connected to the mounting plate (11) by hinge connection.

7. The variable-span wing structure according to claim 4, characterized in that: The connection block (12) is provided with a mounting groove (23) extending therethrough, and an electromagnet (14) is fixedly mounted inside the mounting groove (23) by means of screws. A prefabricated groove (15) is provided in the middle of the inner side of the piston rod (8), and one end of the electromagnet (14) close to the piston rod (8) extends into the inside of the prefabricated groove (15).

8. The variable-span wing structure according to claim 1, characterized in that: The locking assembly comprises a mounting cavity (18), an electric telescopic rod (19) and a limit block (20); the mounting cavity (18) is opened inside the upper end of the mounting plate (11), and the electric telescopic rod (19) is installed inside the mounting cavity (18); the output end of the electric telescopic rod (19) is fixedly mounted with a limit block (20) located inside the right end of the limit wheel (17).

9. The variable-span wing structure according to claim 8, characterized in that: A toothed structure is fixedly mounted at an equal angle on the outer side of the limiting wheel (17), and the limiting block (20) is connected to the toothed structure in a snap-fit ​​manner, and the lower end of the limiting block (20) extends to the interior of the mounting plate (11).

10. The variable-span wing structure according to claim 5, characterized in that: A connecting plate (21) is fixedly mounted on the outer side of one end of the fixing plate (6) away from the piston rod (8), and the left and right ends of the mounting strip (5) respectively extend to the inside of the connecting plate (21), and the mounting strip (5) is respectively connected to the wing rib (3) and the connecting plate (21) in a sliding manner.

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