A variable camber adjustable ultrathin wing

Abstract

This utility model discloses an ultra-thin wing with variable camber adjustment, relating to the field of ultra-thin wing technology. It includes a structural plate, a support frame, an upper wing plate, a first adjustment frame, and an adjustment cable. An adjustment mechanism is provided on the side of the structural plate. The adjustment mechanism includes an upper wing plate, a first adjustment frame, a second adjustment frame, a third adjustment plate, and a fourth adjustment plate. The second adjustment frame is located at the bottom of the upper wing plate, the first adjustment frame is mounted on the side of the second adjustment frame, the third adjustment plate is mounted on the side of the first adjustment frame, and the fourth adjustment plate is mounted on the side of the third adjustment plate. The drive and adjustment mechanism ensures the accuracy and stability of the adjustment. Four symmetrically distributed drive blocks driven by a motor achieve micro-control of the adjustment cable through a first bolt and connecting blocks. The rotational connection design eliminates motion interference, ensuring precise transmission of the adjustment force, and the balanced adjustment force avoids excessive local deformation.

Description

Technical Field

[0001] This utility model relates to the field of ultra-thin wing technology, specifically an ultra-thin wing with adjustable camber. Background Technology

[0002] Ultrathin wings have significant advantages over conventional aircraft wings due to their smaller thickness ratio and larger aspect ratio: their thin profile can effectively suppress shape drag and transonic drag, while the larger aspect ratio can reduce the flow resistance of airflow on the wing surface when generating the same lift, thereby significantly reducing lift-induced drag; however, there are some issues in the existing technology that need to be optimized. For example, in a wing structure with application number CN202010784440.6, although the device is designed to reduce the probability of delamination or cracking at the joint between the upper and lower skins by fitting the leading edge patch onto the wing body through a groove and placing the joint between the upper and lower skins within the groove, the overall fixed structure makes it impossible to flexibly guide and adapt to changes in airflow stress points during actual use. This results in uneven stress distribution in some skin areas, making them prone to wear due to local stress concentration, and even causing cavitation, which in turn affects the aerodynamic performance and service life of the wing. Based on this, this solution proposes "an ultrathin wing with variable camber adjustment" to address the aforementioned problems. Utility Model Content

[0003] The purpose of this invention is to provide an ultra-thin wing with adjustable camber, addressing the problem mentioned in the background art that existing commercially available equipment cannot flexibly guide and adapt to changes in airflow stress points. This results in uneven stress distribution in some skin areas, making them prone to wear due to localized stress concentration, and even causing cavitation, thereby affecting the wing's aerodynamic performance and service life.

[0004] To achieve the above objectives, this utility model provides the following technical solution: a variable camber adjustable ultrathin wing, comprising a structural plate, a support frame, an upper wing plate, a first adjustment frame, and an adjustment cable; An adjustment mechanism is provided on the side of the structural plate. The adjustment mechanism includes an upper wing plate, a first adjustment frame, a second adjustment frame, a third adjustment plate, and a fourth adjustment plate. The second adjustment frame is located at the bottom of the upper wing plate, the first adjustment frame is installed on the side of the second adjustment frame, the third adjustment plate is installed on the side of the first adjustment frame, and the fourth adjustment plate is installed on the side of the third adjustment plate.

[0005] As a preferred technical solution of this utility model, the left side of the structural plate has a streamlined structure, and the cross-section of the structural plate is composed of multiple irregular triangles spliced ​​together, and there are four structural plates evenly distributed in total. The above technical solution features a streamlined structure on the left side of the structural plate, which effectively reduces air resistance, minimizes airflow separation, and improves the aerodynamic performance of the wing. Its cross-section is composed of multiple irregular triangles, which utilize the stability of triangles to reduce the weight of the wing while ensuring structural strength, meeting the requirements for lightweight ultra-thin wings. The four evenly distributed structural plates make the overall stress on the wing more balanced, avoid local stress concentration, and enhance the stability of the wing under complex working conditions.

[0006] As a preferred technical solution of this utility model, the support frame is fixedly connected to the side of the structural plate. The support frame has the same structure as the outer side of the structural plate. The support frame has a hollow structure inside and a through hole is opened on the right side of the support frame for the adjustment of the pull wire. By adopting the above technical solution, the support frame fixedly connected to the side of the structural plate is the same as the outer structure of the structural plate, which ensures the continuity of the overall aerodynamic shape of the wing and reduces airflow disturbance. The hollow structure inside the support frame reduces its own weight while providing installation space for the adjustment cable, making the structure more compact. The through hole opened on the right side of the support frame is specifically used for the adjustment cable, avoiding interference between the adjustment cable and other components and ensuring the smooth progress of the camber adjustment process.

[0007] As a preferred technical solution of this utility model, the support frame and the structural plate are of equal width, and the support frame and the structural plate are sandwiched together, with a pair of support frames fixedly connected between the two structural plates. By adopting the above technical solution, the support frame and the structural plate are of the same width, which increases the connection area between the two and improves the connection strength. The sandwich distribution structure between the support frame and the structural plate, as well as the pair of support frames fixedly connected between the two structural plates, form a stable composite structure, which enhances the overall rigidity and deformation resistance of the wing, and can better withstand the load generated by the airflow during flight, thus ensuring the structural stability of the wing.

[0008] As a preferred technical solution of this utility model, a motor is fixedly connected to the side of the structural plate, the output shaft of the motor is fixedly connected to one end of the drive block, a first bolt is threadedly connected to the bottom of the drive block, a connecting block is rotatably connected between the first bolt and the drive block, an adjustment cable is rotatably connected to the right side of the connecting block, and four drive blocks are symmetrically distributed between the structural plates. Using the above technical solution, the motor fixedly connected to the side of the structural plate provides power for the camber adjustment, and the fixed connection between the motor output shaft and the drive block ensures the effective transmission of power; the first bolt threaded below the drive block cooperates with the rotating connecting block to achieve precise control of the adjustment cable, which facilitates fine-tuning of the wing camber; the four symmetrically distributed drive blocks can adjust the wing from different positions, making the stress and deformation of each part of the wing more uniform, and improving the accuracy and stability of the camber adjustment.

[0009] As a preferred embodiment of this utility model, four adjustment wires are fixedly connected to the lower parts of the first adjustment frame, the second adjustment frame, the third adjustment plate, and the fourth adjustment plate, respectively. The first adjustment frame, the second adjustment frame, the third adjustment plate, and the fourth adjustment plate are all triangular structures. The upper parts of the first adjustment frame, the second adjustment frame, the third adjustment plate, and the fourth adjustment plate are fixedly connected to the upper wing plate. The upper wing plate is fixedly connected to the structural plate. The first adjustment frame, the second adjustment frame, the third adjustment plate, and the fourth adjustment plate are staggered. Using the above technical solution, the four adjustment cables are fixedly connected to the first adjustment frame, the second adjustment frame, the third adjustment plate, and the fourth adjustment plate, respectively, which can realize the independent or coordinated action of each adjustment component, so that the wing camber can be adjusted within a wide range to adapt to different flight conditions. The first adjustment frame, the second adjustment frame, the third adjustment plate, and the fourth adjustment plate adopt a triangular structure. Utilizing the stability of triangles, they can withstand greater forces and ensure the structural reliability during the adjustment process. Their upper parts are fixedly connected to the upper wing plate and are staggered, which makes the deformation of the upper wing plate smoother, avoids the impact of local abrupt changes on aerodynamic performance, and enhances the overall structural strength of the wing.

[0010] As a preferred embodiment of this utility model, the driving block is penetrated by the second bolt, and the driving blocks are synchronously driven by the second bolt. By adopting the above technical solution, the second bolt passes through the drive block and realizes synchronous drive between the drive blocks, ensuring the consistency of the action of each drive block, making the pulling amplitude of the adjustment cable the same, and avoiding uneven wing camber adjustment; synchronous drive also reduces the force difference between components, reduces the risk of component damage due to excessive local force, and improves the reliability and service life of wing camber adjustment.

[0011] Compared with the prior art, the beneficial effects of this utility model are: 1. The optimized structural design improves the overall performance. The left side of the structural panel is streamlined and the cross-section is spliced ​​with irregular triangles. With four evenly distributed settings, it not only reduces air resistance and optimizes aerodynamic performance, but also ensures structural strength while reducing weight by utilizing the stability of triangles, making the wing more evenly stressed. 2. The design of the support frame enhances practicality and stability. It is the same as the outer structure of the structural plate and has the same width, ensuring the continuity of the aerodynamic shape. The hollow structure achieves lightweighting and provides space for the adjustment cable. The through hole on the right side avoids cable interference. The sandwich distribution and symmetrical fixing method further improve the overall rigidity of the wing. 3. The drive and adjustment mechanism ensures the accuracy and stability of the adjustment. The four symmetrically distributed drive blocks driven by the motor realize the micro-control of the adjustment cable through the first bolt and connecting block. The rotation connection design eliminates motion interference, making the adjustment force transmission accurate and the balanced adjustment force avoids excessive local deformation. 4. The configuration of the adjustment components improves the flexibility and reliability of adjustment. The four adjustment cables correspond to the triangular adjustment frame and adjustment plate, respectively, enabling independent or coordinated adjustment. The staggered distribution and the design fixed to the upper wing plate make the deformation smoother. The synchronous drive achieved by the second bolt ensures the uniformity of adjustment and reduces the risk of component damage. Attached Figure Description

[0012] Figure 1 This is a side view of the structure of this utility model; Figure 2 This is a schematic diagram of the structure of the third and fourth adjusting plates of this utility model; Figure 3 This is a front view structural diagram of the structural plate of this utility model; Figure 4 This is a schematic diagram of the structural plate and upper wing plate of this utility model; Figure 5 This is a schematic diagram of the drive block and the first bolt structure of this utility model; Figure 6 This is a side view structural diagram of Embodiment 2 of the present utility model.

[0013] In the diagram: 1. Structural plate; 2. Support frame; 3. Upper wing plate; 4. First adjusting frame; 5. Second adjusting frame; 6. Third adjusting plate; 7. Fourth adjusting plate; 8. Drive block; 9. First bolt; 10. Connecting block; 11. Motor; 12. Second bolt; 13. Adjusting cable. Detailed Implementation

[0014] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0015] Please see Figure 1 - Figure 6 The present invention provides a novel technical solution: an ultra-thin wing with adjustable camber, embodiment one. For details, please refer to the following: Figure 1 - Figure 5It includes a structural plate 1, a support frame 2, an upper wing plate 3, a first adjusting frame 4, a second adjusting frame 5, a third adjusting plate 6, a fourth adjusting plate 7, a drive block 8, a first bolt 9, a connecting block 10, a motor 11, a second bolt 12, and an adjusting cable 13; An adjustment mechanism is provided on the side of the structural plate 1, which consists of an upper wing plate 3, a first adjustment frame 4, a second adjustment frame 5, a third adjustment plate 6, and a fourth adjustment plate 7. The second adjustment frame 5 is fixed to the bottom of the upper wing plate 3. The first adjustment frame 4 is installed laterally on the side of the second adjustment frame 5. The third adjustment plate 6 is mechanically connected to the side of the first adjustment frame 4. The fourth adjustment plate 7 is longitudinally connected to the side of the third adjustment plate 6, forming a spatially interlocking four-bar adjustment structure, which can flexibly realize the adjustment of the wing camber. The left side of structural plate 1 adopts a biomimetic fluid dynamics streamlined structure, which effectively reduces airflow resistance, suppresses airflow separation, and improves the aerodynamic efficiency of the wing during transonic flight. The cross section uses parametric modeling of irregular triangular mesh splicing, which greatly reduces weight while ensuring structural strength, meeting the lightweight requirements of aerospace structures. The four sets of structural plates 1 are symmetrically distributed at equal intervals, making the wing bending moment distribution more uniform and significantly reducing the stress concentration problem at the wing rib connection. The support frame 2 has the same width and outer profile as the structural plate 1. Aerodynamic continuity analysis using specialized software ensures aerodynamic smoothness of the wing surface, preventing additional aerodynamic drag. The support frame 2 employs a hollow truss structure internally, reducing its own weight while providing installation space for the adjustment cable 13. Motion interference simulation ensures that the adjustment cable 13 will not jam during swinging. The support frame 2 and structural plate 1 adopt a sandwich-type laminated structure, combining adhesive and riveting processes to enhance connection strength and form a stable box-type load-bearing structure. The power unit uses a high-power-density rare-earth permanent magnet synchronous motor 11. Professional simulations ensure that the temperature rise of the motor 11 is within a reasonable range during high-speed operation. The output shaft of the motor 11 is connected to the drive block 8 via a spline, which can effectively transmit power. It is combined with the first bolt 9 of the high-precision ball screw pair to achieve precise adjustment. The four symmetrically distributed drive units use a motion synchronization control algorithm to ensure the precise displacement of each adjustment point of the wing and ensure the smoothness of the aerodynamic shape during camber adjustment. The four sets of adjustment cables 13 are made of high-strength aerospace-grade aramid fiber composite material and equipped with a cable tension control system, which can adjust the tension as needed. The first adjustment frame 4, the second adjustment frame 5, the third adjustment plate 6, and the fourth adjustment plate 7 are all triangular rigid frame structures. Reliability analysis shows that their load-bearing capacity far exceeds the design load and meets aerospace strength standards. The adjustment components are arranged in a staggered spatial arrangement. Through multibody dynamics simulation, continuous curvature change of the upper wing plate 3 can be achieved, making the wing camber adjustment range sufficient to meet the aerodynamic requirements of the aircraft throughout the entire flight phase. This design integrates knowledge from multiple disciplines such as aerodynamics, structural mechanics and mechanical transmission, taking into account the aerodynamic performance of the wing, structural strength, adjustment accuracy and lightweight. Bench tests have verified that the adjustment system responds quickly and has excellent structural fatigue performance, effectively improving the aerodynamic adaptability and structural reliability of the aircraft.

[0016] Example 2 For details, please refer to the following: Figure 6 The difference between this embodiment and embodiment one is that the driving block 8 is penetrated by the second bolt 12, and the driving blocks 8 are driven synchronously by the second bolt 12. The second bolt 12 passes through the drive block 8 and realizes synchronous drive between the drive blocks 8, ensuring the consistency of the action of each drive block 8, making the pulling amplitude of the adjustment cable 13 the same, and avoiding uneven wing camber adjustment; synchronous drive also reduces the force difference between components, reduces the risk of component damage due to excessive local force, and improves the reliability and service life of wing camber adjustment.

[0017] This completes a series of tasks. The contents not described in detail in this specification are existing technologies known to those skilled in the art.

[0018] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A variable camber adjustable ultra-thin airfoil, comprising a structural plate (1), a support frame (2), a driving block (8) and an adjusting pull wire (13); characterized in that: The structural plate (1) is provided with an adjustment mechanism on its side. The adjustment mechanism includes an upper wing plate (3), a first adjustment frame (4), a second adjustment frame (5), a third adjustment plate (6), and a fourth adjustment plate (7). The second adjustment frame (5) is located at the bottom of the upper wing plate (3). The first adjustment frame (4) is installed on the side of the second adjustment frame (5). The third adjustment plate (6) is installed on the side of the first adjustment frame (4). The fourth adjustment plate (7) is installed on the side of the third adjustment plate (6).

2. The ultrathin wing with variable camber adjustment according to claim 1, characterized in that, The left side of the structural plate (1) is a streamlined structure, and the cross section of the structural plate (1) is made up of multiple irregular triangles spliced ​​together, and there are four structural plates (1) evenly distributed.

3. The ultrathin wing with variable camber adjustment according to claim 1, characterized in that, The structural plate (1) is fixedly connected to the support frame (2) on the side. The support frame (2) has the same structure as the outer side of the structural plate (1). The support frame (2) is hollow inside, and a through hole is opened on the right side of the support frame (2) for the adjustment pull line (13) to pass through.

4. The ultrathin wing with variable camber adjustment according to claim 1, characterized in that, The support frame (2) and the structural plate (1) are of equal width, and the support frame (2) and the structural plate (1) are sandwiched together. A pair of support frames (2) are fixedly connected between the two structural plates (1).

5. The ultrathin wing with variable camber adjustment according to claim 1, characterized in that, The structural plate (1) is fixedly connected to the side of the motor (11), the output shaft of the motor (11) is fixedly connected to one end of the drive block (8), the drive block (8) is threadedly connected to the bottom of the first bolt (9), the first bolt (9) and the drive block (8) are rotatably connected to the connecting block (10), the right side of the connecting block (10) is rotatably connected to the adjusting pull wire (13), and there are four drive blocks (8) symmetrically distributed between the structural plates (1).

6. The ultrathin wing with variable camber adjustment according to claim 1, characterized in that, The four adjustment wires (13) are fixedly connected to the lower part of the first adjustment frame (4), the second adjustment frame (5), the third adjustment plate (6), and the fourth adjustment plate (7), respectively. The first adjustment frame (4), the second adjustment frame (5), the third adjustment plate (6), and the fourth adjustment plate (7) are all triangular structures. The upper part of the first adjustment frame (4), the second adjustment frame (5), the third adjustment plate (6), and the fourth adjustment plate (7) is fixedly connected to the upper wing plate (3). The upper wing plate (3) is fixedly connected to the structural plate (1). The first adjustment frame (4), the second adjustment frame (5), the third adjustment plate (6), and the fourth adjustment plate (7) are staggered.

7. The ultrathin wing with variable camber adjustment according to claim 1, characterized in that, The drive block (8) is penetrated by the second bolt (12), and the drive blocks (8) are driven synchronously by the second bolt (12).

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