Intelligent airfoil profile and rotor wing

Abstract

The invention provides an intelligent airfoil profile and a rotor wing, the intelligent airfoil profile comprises an I-shaped pipe 6, a U-shaped pipe 5, a cross beam 7, a flexible skin 4 and a fuel oil medium 9, the cross beam 7 is located in the middle of the whole airfoil profile, and the center of the cross beam 7 is matched with the gravity center of the whole airfoil profile; the flexible skin 4 is arranged on the outer contour of the whole intelligent airfoil; the wing-shaped space inside the flexible skin 4 and the first-layer concave pipe 5 on the flexible skin 4 and outside the cross-shaped beam 7 and the first-layer concave pipe 5 on the cross-shaped beam 7 is filled with the I-shaped pipe 6 in a combined mode, and the gap space outside the I-shaped pipe 6 is filled with the fuel oil medium 9; the I-shaped pipe 6 comprises an I-shaped beam 1 and two flexible half pipes 2; the N I-shaped pipes form three combination types, namely a crisscross uniform distribution combination 8, a longitudinal arrangement combination 10 and a transverse arrangement combination 11; the concave pipe 5 comprises a concave beam 3 and a flexible half pipe 2; the flexible half pipes of the I-shaped pipe and the U-shaped pipe are filled with fuel oil media. The flexible half pipe 2 comprises an arc-shaped edge and a right-angle edge.

Description

Technical Field

[0001] The invention patent belongs to the field of aviation, and specifically relates to an intelligent airfoil and rotor. Background Art

[0002] The airfoil refers to the cross-sectional shape of the wing or tail. Changes in the airfoil of an aircraft wing or helicopter rotor can affect the lift coefficient and drag coefficient to varying degrees. By studying and applying the exact laws of the influence of airfoil changes on the lift coefficient and drag coefficient, we can change the lift or drag of the aircraft as we expect when necessary, improve the stall characteristics, and always maintain the best flight state according to changes in the environment and mission. For example, flaps extending backward and downward can increase lift, and spoilers flipping up can increase drag.

[0003] At present, there are three main methods for changing the airfoil: 1. Changing the airfoil through the action of a rigid separation structure, such as the setting of ailerons and flaps, which is widely used on various aircraft; 2. Changing the airfoil through a pre-set adjustment mechanism, such as the trailing edge adjustment plate of a helicopter blade; 3. Setting an action mechanism inside the wing, which pushes the flexible skin to change the airfoil, which is currently mostly used in the experimental stage or on light aircraft models. The first and second technologies are very mature, but can only change the airfoil in a single direction and are limited to a relatively single flight mode. The third method of only setting an action mechanism inside the wing has two major shortcomings: one is that it can only change the curvature of the airfoil, but not the area of ​​the airfoil; the other is that there is a "cavity" inside the wing, that is, the space vacated for the movement of the actuator will become an area with reduced stiffness. Under the action of aerodynamic force, it will affect the smoothness of the skin and thus affect the aerodynamic characteristics. Summary of the invention

[0004] The present application provides an intelligent wing and rotor, which can change the lift or drag of the aircraft according to pre-conceived ideas when needed, and can also improve the stall characteristics, so as to always maintain the best flight state according to changes in the environment and tasks.

[0005] In a first aspect, the present application provides an intelligent airfoil, which includes: an I-shaped tube 6, a concave tube 5, a cross beam 7, a flexible skin 4, and a fuel medium 9, wherein:

[0006] 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 intelligent airfoil; the airfoil space within the flexible skin 4 and the first layer of concave tubes 5 thereon, and outside the cross beam 7 and the first layer of concave tubes 5 thereon, is filled with an I-tube 6 for combination filling, and the gap space outside the I-tube 6 is filled with a fuel medium 9; the I-tube 6 includes an I-beam 1 and two flexible half-tubes 2; N I-tubes 6 constitute three types of combinations, namely, a combination 8 uniformly distributed in the longitudinal and transverse directions, a combination 10 arranged in longitudinal rows, and a combination 11 arranged in transverse rows; the concave tube 5 includes a concave beam 3 and a flexible half-tube 2; the inside of the I-tube 6 and the flexible half-tube 2 of the concave tube 5 are both filled with the fuel medium 9; the flexible half-tube 2 includes an arc edge and a right-angle edge;

[0007] A pressure mechanism is used to fill the fuel medium 9 inside the flexible half-tube 2. 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 achieved.

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

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

[0010] Furthermore, the longitudinal and transverse cross-distribution combination 8 is a combination of 3*3 I-tubes 6 arranged longitudinally and transversely, the longitudinal arrangement combination 10 is a combination of 2*3 I-tubes 6 arranged longitudinally, and the transverse arrangement combination 11 is a combination of 2*3 I-tubes 6 arranged transversely.

[0011] Furthermore, when the fuel medium 9 in the flexible half-tube 2 is pressurized and expanded, the flexible half-tube 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 thickness of the airfoil, the length of the cross beam 7 is nine-tenths of the chord length of the airfoil, and the thickness of the cross beam 7 is one-tenth of the thickness of the airfoil.

[0013] Furthermore, the first layer in the flexible skin 4 is paved with the concave tube 5 at an adaptive angle, and the first layer of the cross beam 7 is paved with the concave tube 5 .

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

[0015] In a second aspect, the present application provides 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.

[0016] In summary, the technical effects of the intelligent airfoil and rotor provided by the present application are as follows:

[0017] 1. The present invention mainly uses a combination of two key components, the I-shaped tube 6 and the concave-shaped tube 5, to achieve intelligent changes in the airfoil, with ingenious design, simple logic and easy control.

[0018] 2. The present invention only uses the I-shaped tube 6, the concave tube 5, the flexible skin 4 and the cross beam 7, which are simple in size design and easy to manufacture. Fuel is used as the filling medium, which is easy to obtain and can also be used as the fuel of the aircraft when necessary.

[0019] 3. Through a large number of computer simulations and experiments, the desired airfoil can be obtained, and rapid changes between various airfoils can be achieved. The present invention has great potential for airfoil design. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 An airfoil cross-sectional view of an intelligent airfoil provided in the present application;

[0021] Figure 2 A schematic diagram of an I-shaped tube and a concave-shaped tube of a smart airfoil provided in this application;

[0022] Among them, 1-I-beam, 2-flexible half-tube, 3-concave beam, 4-flexible skin, 5-concave tube, 6-I-tube, 7-cross beam, 8-vertical and horizontal cross-distribution combination, 9-fuel medium, 10-vertical arrangement combination, 11-horizontal arrangement combination. DETAILED DESCRIPTION

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

[0024] like Figure 1 As shown, the present application provides a smart airfoil including: an I-shaped tube 6, a concave tube 5, a cross beam 7, a flexible skin 4, and a fuel medium 9, wherein:

[0025] 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 intelligent airfoil; the airfoil space within the flexible skin 4 and the first layer of concave tubes 5 thereon and outside the cross beam 7 and the first layer of concave tubes 5 thereon is filled with an I-tube 6 for combination filling, and the gap space outside the I-tube 6 is filled with a fuel medium 9; the I-tube 6 includes an I-beam 1 and two flexible half-tubes 2; N I-tubes 6 constitute three types of combinations, namely, a combination 8 of uniformly distributed vertically and horizontally, and a combination 10 of uniformly distributed vertically and horizontally, and a combination 10 of uniformly distributed vertically and horizontally. , a combination of horizontal arrangement 11; the concave tube 5 includes a concave 3 and a flexible half-tube 2; the inside of the flexible half-tube 2 of the I-tube 6 and the concave tube 5 are filled with fuel medium 9; a pressure mechanism is used to fill the inside of the flexible half-tube 2 with fuel medium 9, and different amounts of fuel medium 9 are filled into the flexible half-tube 2 in different areas of the airfoil by controlling the combination valve, so that the flexible half-tube 2 in different areas of the airfoil undergoes expansion deformation to different degrees and in different directions; by controlling the expansion 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 achieved.

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

[0027] Specifically, Figure 2 As shown, the concave beam 3 is 6mm high, 10mm wide, and 1mm thick. The right-angled edge of the flexible half tube 2 is bonded to the inner side of the concave beam 3. The diameter of the arc edge 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-shaped tube 6 is generally arranged longitudinally or transversely inside the airfoil. The concave tube 5 can be arranged at any angle and laid on the attachment inside the airfoil, and generally the long side bottom of the concave tube 5 is used as the laying surface.

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

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

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

[0032] It can be understood that the present invention utilizes this characteristic of the structure to achieve directional changes in the airfoil.

[0033] Specifically, the height, length and thickness of the cross beam 7 are determined according to the size of the entire airfoil.

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

[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 in the flexible skin 4 is paved with the concave tube 5 at an adaptive angle, mainly to better maintain the outer contour of the airfoil.

[0037] Specifically, the first layer of the cross beam 7 is paved with the concave tube 5, mainly to better protect the I-tube 6 in the middle of the airfoil to have a good deformation environment.

[0038] Specifically, the longitudinal and transverse uniformly distributed combination 8 is a combination of 3*3 I-shaped tubes 6 arranged in a longitudinal and transverse manner. This combination is mainly arranged in places where the longitudinal and transverse deformation amounts in the airfoil are not significantly different, such as the area close to the coordinate origin of the cross beam 7.

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

[0040] Specifically, the transverse arrangement combination 11 is a combination of 2*3 I-shaped tubes 6 arranged in transverse rows. This combination is mainly arranged in places where the transverse deformation requirement is large in the airfoil, such as the left and right end sides of the airfoil.

[0041] Key points of a smart airfoil provided in this application:

[0042] 1. I-beam 1 is 10mm high, 10mm wide, 1mm thick, 14mm in diameter in the unexpanded state, and 0.5mm in wall thickness. Concave beam 3 is 6mm high, 10mm wide, and 1mm thick. The right-angled side of flexible half-tube 2 is bonded to the inner side of concave beam 3. The diameter of the arc side in the unexpanded state is 14mm, and the wall thickness in the unexpanded state is 0.5mm.

[0043] 2. The I-beam 1 and the concave beam 3 are both rigid structures, and all edges are chamfered to prevent the flexible structure of the half-tube from being scratched. When the fuel medium 9 in the flexible half-tube 2 is pressurized and expanded, the flexible half-tube 2 can only expand in the direction of the arc edge. The present invention utilizes this structural characteristic to achieve directional changes in the airfoil.

[0044] 3. There are three main types of combinations of I-tubes 6: longitudinal and transverse cross-distribution combination 8, longitudinal arrangement combination 10 and transverse arrangement combination 11, which are respectively suitable for places in the airfoil where the longitudinal and transverse deformations are not significantly different (such as the area close to the coordinate origin of the cross beam 7), places in the airfoil where the longitudinal deformation is required to be large (such as the upper and lower ends of the airfoil), and places in the airfoil where the transverse deformation is required to be large (such as the left and right ends of the airfoil).

[0045] 4. Principle of intelligent change of airfoil: Use a pressure mechanism to fill the fuel medium 9 inside the flexible half-tube 2, and control the combination valve to fill different amounts of fuel medium 9 in the flexible half-tube 2 in different areas of the airfoil, so that the flexible half-tube 2 in different areas of the airfoil can be expanded and deformed to different degrees and in different directions. Mainly control the longitudinal and lateral expansion deformation of different areas in the airfoil, and under certain logical control, the intelligent change of the airfoil can be achieved. Through a large number of computer simulations and experiments, the desired airfoil can be obtained, and rapid changes between various airfoils can be achieved.

[0046] The technical effect of the intelligent airfoil provided by this application is as follows:

[0047] 1. The present invention mainly uses a combination of two key components, the I-shaped tube 6 and the concave-shaped tube 5, to achieve intelligent changes in the airfoil, with ingenious design, simple logic and easy control.

[0048] 2. The present invention only uses the I-shaped tube 6, the concave tube 5, the flexible skin 4 and the cross beam 7, which are simple in size design and easy to manufacture. Fuel is used as the filling medium, which is easy to obtain and can also be used as the fuel of the aircraft when necessary.

[0049] 3. The desired airfoil can be obtained through a large number of computer simulations and experiments, and rapid changes between various airfoils can be achieved. The present invention has great potential for airfoil design.

Claims

1. A smart airfoil, characterized in that: The smart airfoil comprises: an I-shaped tube (6), a concave tube (5), a cross beam (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 intelligent airfoil; the airfoil space inside the flexible skin (4) and the first layer of concave tube (5) thereon and outside the cross beam (7) and the first layer of concave tube (5) thereon is filled with an I-tube (6) for combination filling, and the gap space outside the I-tube (6) is filled with a fuel medium (9); the I-tube (6) includes an I-beam (1) and two flexible half-tubes (2); N I-tubes (6) form three types of combinations, namely, a combination of uniformly distributed vertically and horizontally, a combination of longitudinally arranged combinations (8), a combination of longitudinally arranged combinations (10), and a combination of transversely arranged combinations (11); the concave tube (5) includes a concave sub-beam (3) and a flexible half-tube (2); the inside of the flexible half-tubes (2) of the I-tube (6) and the concave tube (5) are filled with a fuel medium (9); the flexible half-tube (2) includes an arc edge and a right-angle edge; A fuel medium (9) is filled into the flexible half-tube (2) by using a pressure mechanism, and different amounts of the fuel medium (9) are filled into the flexible half-tube (2) in different areas of the airfoil by controlling a combination valve, so that the flexible half-tube (2) in different areas of the airfoil expands and deforms to different degrees and in different directions; and the expansion and deformation of the I-shaped tube (6) and the concave-shaped tube (5) in different areas of the intelligent airfoil are controlled, thereby realizing intelligent changes in the airfoil.

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

3. The smart airfoil according to claim 1, characterized in that: The right-angled side of the flexible half pipe (2) is bonded to the inner side of the concave beam (3), the diameter of the arc-shaped side in the unexpanded state is 14 mm, and the wall thickness in the unexpanded state is 0.5 mm.

4. The smart airfoil according to claim 1, characterized in that: The vertical and horizontal cross-distribution combination (8) is a combination of 3*3 I-shaped tubes (6) arranged vertically and horizontally. The longitudinal arrangement combination (10) is a combination of 2*3 I-shaped tubes (6) arranged in longitudinal rows, and the transverse arrangement combination (11) is a combination of 2*3 I-shaped tubes (6) arranged in transverse rows.

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

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

7. The smart airfoil according to claim 1, characterized in that: The first layer in the flexible skin (4) is paved with a concave tube (5) at an adaptive angle, and the first layer of the cross beam (7) is paved with a concave tube (5).

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

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

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