Intelligent airfoil and rotor

Abstract

This application provides an intelligent airfoil and rotor. The intelligent airfoil includes: an I-beam 6, a U-shaped tube 5, a crossbeam 7, a flexible skin 4, and a fuel medium 9. The crossbeam 7 is located in the middle of the entire airfoil, and its center coincides with the center of gravity of the entire airfoil. The flexible skin 4 is arranged along the outer contour of the entire intelligent airfoil. The airfoil space within the flexible skin 4 and the first layer of U-shaped tubes 5, and outside the crossbeam 7 and the first layer of U-shaped tubes 5, is filled using I-beams 6. The gap space outside the I-beams 6 is filled with fuel medium 9. The I-beam 6 includes an I-beam 1 and two flexible half-tubes 2. N I-beams constitute three combination types: a crisscrossing combination 8, a longitudinal arrangement combination 10, and a transverse arrangement combination 11. The U-shaped tube 5 includes a U-shaped beam 3 and one flexible half-tube 2. The flexible half-tubes of both the I-beam and the U-shaped tube are filled with fuel medium. The flexible half-tube 2 includes an arc-shaped edge and a right-angled edge.

Description

Technical Field

[0001] This invention patent belongs to the field of aviation, specifically relating to an intelligent airfoil and rotor. Background Technology

[0002] Airfoil refers to the cross-sectional shape of an aircraft wing or tail. Variations in the airfoil of an aircraft wing or helicopter rotor can affect the lift and drag coefficients to varying degrees. Studying and applying the precise laws governing the impact of airfoil variations on lift and drag coefficients allows for the pre-planned modification of an aircraft's lift or drag as needed. It can also improve stall characteristics and maintain optimal flight performance according to changes in environment and mission. For example, extending flaps downwards and rearwards increases lift, while flipping spoilers upwards increases drag.

[0003] Currently, there are three main methods for changing airfoil shape: ① Changing the airfoil through the action of rigid, separate structures, such as ailerons and flaps, which are widely used in various aircraft; ② Changing the airfoil through pre-set adjustment mechanisms, such as trailing edge trimmers on helicopter rotor blades; ③ Setting up an actuating mechanism inside the wing, which actuates the flexible skin to change the airfoil, currently mostly in the experimental stage or applied to lightweight model aircraft. The first and second technologies are very mature, but they can only change the airfoil in a single direction, limiting them to relatively simple flight modes. The third method, which only sets up an actuating mechanism inside the wing, has two major drawbacks: first, it can only change the airfoil curvature, not the airfoil area; second, the existence of "cavities" inside the wing, i.e., the space made up to accommodate the movement of the actuating mechanism, becomes a region with reduced stiffness, which, under aerodynamic effects, affects the maintenance of the skin's smoothness, thus affecting aerodynamic characteristics. Summary of the Invention

[0004] This application provides an intelligent airfoil and rotor that can change the lift or drag of an aircraft as needed according to a pre-designed plan, and can also improve stall characteristics, maintaining optimal flight status at all times according to changes in environment and mission.

[0005] In a first aspect, this application provides a smart airfoil, the smart airfoil comprising: an I-beam 6, a U-shaped tube 5, a crossbeam 7, a flexible skin 4, and a fuel medium 9, wherein:

[0006] The crossbeam 7 is located in the middle of the entire airfoil, and the center of the crossbeam 7 coincides with the center of gravity of the entire airfoil; the flexible skin 4 is arranged on the outer contour of the entire intelligent airfoil; the airfoil space inside the flexible skin 4 and the first layer of concave tubes 5 above it, and outside the crossbeam 7 and the first layer of concave tubes 5 above it, is filled with I-beams 6; the gap space outside the I-beams 6 is filled with fuel medium 9; the I-beam 6 includes an I-beam 1 and two flexible half-tubes 2; N I-beams 6 constitute three combination types, namely, a longitudinal and transverse evenly distributed combination 8, a longitudinal arrangement combination 10, and a transverse arrangement combination 11; the concave tube 5 includes a concave beam 3 and one flexible half-tube 2; the interior of the flexible half-tube 2 of the I-beam 6 and the concave tube 5 is filled with fuel medium 9; the flexible half-tube 2 includes curved edges and right-angled edges;

[0007] A pressure mechanism is used to fill the interior of the flexible half-tube 2 with fuel medium 9. By controlling the combination valve, different amounts of fuel medium 9 are filled into the flexible half-tube 2 in different areas of the airfoil, causing the flexible half-tube 2 in different areas of the airfoil to expand and deform to different degrees and in different directions. By controlling the expansion and deformation of the I-tube 6 and the U-tube 5 in different areas of the intelligent airfoil, the intelligent change of the airfoil is realized.

[0008] Furthermore, the right-angled side of the flexible semi-tube 2 is bonded to both sides of the I-beam 1. The diameter of the arc-shaped side is 14mm in the unexpanded state, and the wall thickness is 0.5mm in the unexpanded state.

[0009] Furthermore, the right-angled side of the flexible semi-tube 2 is bonded to the inside of the concave beam 3. The diameter of the arc-shaped side is 14mm in the unexpanded state, and the wall thickness is 0.5mm in the unexpanded state.

[0010] Furthermore, the crisscrossing arrangement combination 8 is a combination of 3*3 I-beams 6 arranged in a crisscross pattern, the vertical arrangement combination 10 is a combination of 2*3 I-beams 6 arranged in a vertical column, and the horizontal arrangement combination 11 is a combination of 2*3 I-beams 6 arranged in a horizontal column.

[0011] Furthermore, when the fuel medium 9 inside the flexible half-pipe 2 is pressurized and expands, the flexible half-pipe 2 can only expand in the direction of the arc-shaped edge.

[0012] Furthermore, the height of the cross beam 7 is nine-tenths of the airfoil thickness, the length of the cross beam 7 is nine-tenths of the airfoil chord length, and the thickness of the cross beam 7 is one-tenth of the airfoil thickness.

[0013] Furthermore, the first layer inside the flexible skin 4 is laid using a concave tube 5 to adapt to the angle, and the first layer of the cross beam 7 is laid using a concave tube 5.

[0014] Furthermore, both the I-beam 1 and the U-beam 3 are rigid structures, and all edges are chamfered.

[0015] Secondly, this application provides a helicopter rotor, characterized in that the helicopter rotor adopts the aforementioned intelligent airfoil.

[0016] In summary, the technical advantages of the intelligent airfoil and rotor provided in this application are as follows:

[0017] 1. This invention mainly uses the combination of two key components, the I-beam tube 6 and the concave tube 5, to achieve intelligent airfoil transformation. The design is ingenious, the logic is simple, and it is easy to control.

[0018] 2. This invention uses only a few structures: I-beams 6, U-beams 5, flexible skin 4, and crossbeams 7. The dimensional design is simple and easy to manufacture. Fuel oil is used as the filling medium, which is readily available and can also be used as fuel for aircraft when necessary.

[0019] 3. Through extensive computer simulations and experiments, the desired airfoil can be obtained, and rapid changes between various airfoils can be achieved. This invention has significant potential for airfoil design. Attached Figure Description

[0020] Figure 1 A cross-sectional view of an intelligent airfoil provided in this application;

[0021] Figure 2 A schematic diagram of an I-beam and a U-shaped tube for an intelligent airfoil provided in this application;

[0022] Among them, 1-I-beam, 2-flexible half-pipe, 3-U-beam, 4-flexible skin, 5-U-pipe, 6-I-beam, 7-cross beam, 8-vertical and transverse evenly distributed combination, 9-fuel medium, 10-vertical arrangement combination, 11-transverse arrangement combination. Detailed Implementation

[0023] The present invention aims to design an intelligent airfoil that can change its curvature and area in a predetermined direction by manual or algorithmic control. Its core method is to use the most readily available fuel on the aircraft as the best flexible medium, and to intelligently control the directional change of the fuel volume inside the wing to drive the flexible skin 4 to change in a predetermined direction, thereby causing the curvature, chord length, shape and area of ​​the airfoil to change in a predetermined direction.

[0024] like Figure 1 As shown, this application provides an intelligent airfoil comprising: an I-beam 6, a U-shaped tube 5, a crossbeam 7, a flexible skin 4, and a fuel medium 9, wherein:

[0025] The crossbeam 7 is located in the middle of the entire airfoil, and its center coincides with the center of gravity of the entire airfoil. The flexible skin 4 is arranged on the outer contour of the entire smart airfoil. The airfoil space inside the flexible skin 4 and the first layer of U-shaped tubes 5 above it, and outside the crossbeam 7 and the first layer of U-shaped tubes 5 above it, is filled with H-shaped tubes 6. The gap space outside the H-shaped tubes 6 is filled with fuel medium 9. The H-shaped tube 6 includes an H-beam 1 and two flexible half-tubes 2. N H-shaped tubes 6 constitute three combination types, namely, a longitudinally and transversely evenly distributed combination 8, and a longitudinally arranged combination 10. The airfoil is arranged in a horizontal row, and the concave tube 5 includes a concave tube 3 and a flexible half tube 2. The flexible half tube 2 of both the I-tube 6 and the concave tube 5 is filled with fuel medium 9. The flexible half tube 2 is filled with fuel medium 9 using a pressure mechanism. By controlling the combination valve, different amounts of fuel medium 9 are filled into the flexible half tube 2 in different areas of the airfoil, so that the flexible half tube 2 in different areas of the airfoil expands and deforms to different degrees and in different directions. By controlling the expansion and deformation of the I-tube 6 and the concave tube 5 in different areas of the intelligent airfoil, the intelligent change of the airfoil is realized.

[0026] Specifically, such as Figure 2 As shown, the I-beam 1 is 10mm high, 10mm wide, and 1mm thick. The right-angled part of the flexible semi-tube 2 is bonded to both sides of the I-beam 1. The diameter of the arc-shaped part is 14mm in the unexpanded state, and the wall thickness is 0.5mm in the unexpanded state.

[0027] Specifically, such as Figure 2 As shown, the concave beam 3 is 6mm high, 10mm wide, and 1mm thick. The right-angled part of the flexible semi-tube 2 is bonded to the inside of the concave beam 3. The diameter of the arc-shaped part in the unexpanded state is 14mm, and the wall thickness in the unexpanded state is 0.5mm.

[0028] It should be noted that the I-beam tube 6 is generally arranged longitudinally or laterally inside the airfoil. The U-shaped tube 5 can be arranged at any angle and laid on the attachment inside the airfoil, generally with the bottom of the long side of the U-shaped tube 5 as the laying surface.

[0029] Specifically, both I-beam 1 and U-beam 3 are rigid structures, and all edges are chamfered.

[0030] It should be noted that the purpose of the chamfering is to prevent scratching the flexible structure of the half-tube.

[0031] More specifically, when the fuel medium 9 inside the flexible half-pipe 2 is pressurized and expands, the flexible half-pipe 2 can only expand in the direction of the arc-shaped edge.

[0032] It is understandable that this invention utilizes this structural characteristic to achieve directional changes in the airfoil.

[0033] Specifically, the height, length, and thickness of the crossbeam 7 are determined based on the overall dimensions of the airfoil.

[0034] Preferably, the height of the cross beam 7 is nine-tenths of the airfoil thickness, the length of the cross beam 7 is nine-tenths of the airfoil chord length, and the thickness of the cross beam 7 is one-tenth of the airfoil thickness.

[0035] Specifically, the cross beam 7 is a rigid structure, and its main function is to maintain the rigidity of the entire wing.

[0036] Specifically, the first layer inside the flexible skin 4 is laid using a concave tube 5 at an appropriate angle, mainly to better maintain the outer contour of the airfoil.

[0037] Specifically, the first layer of the cross beam 7 is laid with concave tubes 5, mainly to better protect the I-beams 6 in the middle of the airfoil and provide a good deformation environment.

[0038] Specifically, the crisscrossing combination 8 is a combination of 3*3 I-beams 6 arranged in a crisscross pattern. This combination is mainly arranged in areas within the airfoil where the difference in longitudinal and transverse deformation is not significant, such as the area near the origin of the cross beam 7.

[0039] Specifically, the longitudinal arrangement combination 10 is a combination of 2*3 I-beams arranged in 6 longitudinal columns. This combination is mainly arranged in places where the longitudinal deformation of the airfoil is required to be large, such as the upper and lower ends of the airfoil.

[0040] Specifically, the horizontal arrangement combination 11 is a combination of 2*3 I-beams arranged in horizontal rows. This combination is mainly arranged in places where the lateral deformation of the airfoil is required to be large, such as the left and right ends of the airfoil.

[0041] Key features of the smart airfoil provided in this application:

[0042] 1. I-beam 1 is 10mm high, 10mm wide, and 1mm thick. In its unexpanded state, the diameter of the curved edge is 14mm, and the wall thickness is 0.5mm. 2. U-beam 3 is 6mm high, 10mm wide, and 1mm thick. The right-angled edge of flexible semi-tube 2 is bonded to the inside of U-beam 3. In its unexpanded state, the diameter of the curved edge is 14mm, and the wall thickness is 0.5mm.

[0043] 2. Both the I-beam 1 and the U-beam 3 are rigid structures, and all edges are chamfered to prevent scratching the flexible structure of the half-pipe. When the fuel medium 9 inside the flexible half-pipe 2 is pressurized and expands, the flexible half-pipe 2 can only expand in the direction of the arc edge. This invention utilizes this characteristic of the structure to achieve directional changes in the airfoil.

[0044] 3. There are three main types of I-beam tube 6 combinations: longitudinal and transverse crisscrossing combination 8, longitudinal arrangement combination 10, and transverse arrangement combination 11. These are respectively suitable for places where the longitudinal and transverse deformation is not significantly different within the airfoil (such as the area near the coordinate origin of the cross beam 7), places where the longitudinal deformation requirement is large within the airfoil (such as the upper and lower ends of the airfoil), and places where the transverse deformation requirement is large within the airfoil (such as the left and right ends of the airfoil).

[0045] 4. Principle of Intelligent Airfoil Transformation: A pressure mechanism is used to fill the flexible semi-tube 2 with fuel medium 9. By controlling a combination valve to fill different areas of the flexible semi-tube 2 within the airfoil with different amounts of fuel medium 9, the flexible semi-tube 2 in different areas of the airfoil can undergo expansion and deformation to varying degrees and directions. Primarily controlling the longitudinal and lateral expansion and deformation in different areas of the airfoil, intelligent airfoil transformation can be achieved under certain logical control. Through extensive computer simulations and experiments, the desired airfoil can be obtained, and rapid transformation between various airfoils can be realized.

[0046] The technical effects of the intelligent airfoil provided in this application are as follows:

[0047] 1. This invention mainly uses the combination of two key components, the I-beam tube 6 and the concave tube 5, to achieve intelligent airfoil transformation. The design is ingenious, the logic is simple, and it is easy to control.

[0048] 2. This invention uses only a few structures: I-beams 6, U-beams 5, flexible skin 4, and crossbeams 7. The dimensional design is simple and easy to manufacture. Fuel oil is used as the filling medium, which is readily available and can also be used as fuel for aircraft when necessary.

[0049] 3. The desired airfoil can be obtained through extensive computer simulations and experiments, and rapid changes between various airfoils can be achieved. This invention has significant potential for airfoil design.

Claims

1. A smart airfoil, characterized in that, The intelligent airfoil includes: an I-beam (6), a U-beam (5), a crossbeam (7), a flexible skin (4), and a fuel medium (9), wherein: The cross beam (7) is located in the middle of the entire airfoil, and the center of the cross beam (7) coincides with the center of gravity of the entire airfoil; the flexible skin (4) is arranged on the outer contour of the entire smart airfoil; the airfoil space inside the flexible skin (4) and the first layer of concave tubes (5) above it, and outside the cross beam (7) and the first layer of concave tubes (5) above it, is filled with I-beams (6) in combination, and the gap space outside the I-beams (6) is filled with fuel medium (9); the I-beam (6) includes an I-beam (1) and two flexible half tubes (2); N I-beams (6) constitute three combination types, namely, the longitudinal and transverse crisscross evenly distributed combination (8), the longitudinal arrangement combination (10), and the transverse arrangement combination (11); the concave tube (5) includes a concave sub-beam (3) and one flexible half tube (2); the interior of the flexible half tube (2) of the I-beam (6) and the concave tube (5) is filled with fuel medium (9); the flexible half tube (2) includes an arc edge and a right angle edge; The pressure mechanism is used to fill the interior of the flexible half tube (2) with fuel medium (9). By controlling the combination valve, different amounts of fuel medium (9) are filled into the flexible half tube (2) in different areas of the airfoil, so that the flexible half tube (2) in different areas of the airfoil expands and deforms to different degrees and in different directions. By controlling the expansion and deformation of the I-shaped tube (6) and the concave tube (5) in different areas of the intelligent airfoil, the intelligent change of the airfoil is realized.

2. The intelligent airfoil according to claim 1, characterized in that, The right-angled part of the flexible half-tube (2) is bonded to both sides of the I-beam (1). The diameter of the arc-shaped part is 14mm in the unexpanded state, and the wall thickness is 0.5mm in the unexpanded state.

3. The intelligent airfoil according to claim 1, characterized in that, The right-angled part of the flexible semi-tube (2) is bonded to the inside of the concave beam (3). The diameter of the arc-shaped part is 14mm in the unexpanded state, and the wall thickness is 0.5mm in the unexpanded state.

4. The intelligent airfoil according to claim 1, characterized in that, The crisscrossing evenly distributed combination (8) is a combination of 3*3 I-beams (6) arranged in a crisscross pattern. The vertical arrangement combination (10) is a combination of 2*3 I-beams (6) arranged vertically, and the horizontal arrangement combination (11) is a combination of 2*3 I-beams (6) arranged horizontally.

5. The intelligent airfoil according to claim 1, characterized in that, When the fuel medium (9) inside the flexible half tube (2) is pressurized and expanded, the flexible half tube (2) can only expand in the direction of the arc edge.

6. The smart airfoil according to claim 1, characterized in that, The height of the cross beam (7) is nine-tenths of the airfoil thickness, the length of the cross beam (7) is nine-tenths of the airfoil chord length, and the thickness of the cross beam (7) is one-tenth of the airfoil thickness.

7. The smart airfoil according to claim 1, characterized in that, The first layer inside the flexible skin (4) is laid using a concave tube (5) to adapt the angle, and the first layer of the cross beam (7) is laid using a concave tube (5).

8. The intelligent airfoil according to claim 1, characterized in that, Both the I-beam (1) and the concave beam (3) are rigid structures, and all edges are chamfered.

9. A helicopter rotor, characterized in that, The helicopter rotor is implemented using the smart airfoil as described in any one of claims 1 to 8.

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