Variable thickness airfoil

Abstract

The present application discloses a variable thickness wing, including a wing body and a cam link mechanism, which divides the wing profile into six sections, gives the deformation degree of freedom, and designs the cam link mechanism to drive the movement of each part of the wing. The cam link mechanism is a common mechanical transmission device used to convert rotary motion into linear motion, which is composed of a cam, a connecting rod and a crankshaft. The rotation of the cam will drive the whole wing to reciprocate. The convex part of the cam head will push the connecting rod, so that the connecting rod presents different positions and angles to drive the deformation of the wing. The motor is connected with the center of the cam, which can realize the automatic operation of the wing deformation. The present application has the advantages of simple structure, convenient manufacturing and maintenance; through the design and control of the cam, accurate position control and motion trajectory can be realized; through the rotation of a single motor, the thickness and curvature of the whole wing can be changed, and the surface of the wing frame is smooth during the deformation process without obvious turning.

Description

Technical Field

[0001] This invention relates to the field of deformable wing technology, and in particular to a variable thickness wing. Background Technology

[0002] The wing is the main component of an aircraft that generates lift, and its size and shape have a significant impact on the aircraft's lift and control. Currently, the size and shape of the wings of existing aircraft remain essentially unchanged during flight, regardless of changes in speed, altitude, and load; they cannot be adjusted according to actual control and lift requirements. Summary of the Invention

[0003] The purpose of this invention is to provide a variable thickness wing to solve the problems existing in the prior art. The variable thickness wing can meet the optimal aerodynamic requirements of the aircraft by adjusting the thickness and camber of the wing airfoil. The cam linkage mechanism enables the wing to change its thickness and camber according to the actual situation, and the surface remains smooth during the deformation process, reducing aerodynamic interference caused by deformation.

[0004] To achieve the above objectives, the present invention provides the following solution: The present invention provides a variable thickness wing, comprising...

[0005] The wing body comprises four, three, two, one, six, and five wing segments connected sequentially end-to-end. The six-segment wing is fixed to the fuselage. The four and five wing segments, located at the wing's tip, are positioned on the upper and lower sides respectively. The arc-shaped one-segment wing is located at the wing's leading edge.

[0006] A cam-linkage mechanism includes a cam, a first link, a second link, and a third link. A motor drives the cam to rotate. One end of the first link is connected to a cam head on the working surface of the cam, and the other end of the first link is hinged to the second link. One end of the second link is hinged to the sixth segment of the wing, and the other end of the second link is connected to the second segment of the wing via a first connector. One end of the third link is fixedly connected to the sixth segment of the wing, and the other end of the third link is connected to the third segment of the wing via a second connector.

[0007] Preferably, the wing body comprises four wing segments, three wing segments, two wing segments, one wing segment, six wing segments, and five wing segments that are sequentially connected end to end by a pivot.

[0008] Preferably, the connecting rod three includes a main connecting rod and a secondary connecting rod. One end of the main connecting rod is connected to the connecting member two, and the other end of the main connecting rod is hinged to the secondary connecting rod. The bottom end of the secondary connecting rod is fixed to the sixth segment of the wing.

[0009] Preferably, a support rod one and a support rod two are connected to the central axis of the cam. The other end of the support rod one is fixed to the sixth segment of the wing, and the other end of the support rod two is connected to the hinge point of the main link and the secondary link of the connecting rod.

[0010] Preferably, the first connector is a Y-shaped connector, the top ends of the two branches of the Y-shaped connector are fixedly connected to the second section of the wing, and the bottom ends of the two branches of the Y-shaped connector are joined together and hinged to the second connecting rod.

[0011] Preferably, the connector is a two-dimensional Y-shaped connector, with the top ends of the two branches of the Y-shaped connector fixedly connected to the three sections of the wing, and the bottom ends of the two branches of the Y-shaped connector converging and hinged to the three phases of the connecting rod.

[0012] The present invention achieves the following beneficial technical effects compared to the prior art:

[0013] The variable-thickness wing of this invention includes a wing body and a cam-linkage mechanism. The wing profile is divided into six segments, granting them degrees of freedom for deformation. The cam-linkage mechanism drives the movement of each part of the wing. The cam-linkage mechanism is a common mechanical transmission device used to convert rotational motion into linear motion. It consists of a cam, a connecting rod, and a crankshaft. The rotation of the cam drives the entire wing to reciprocate. The protruding part of the cam head pushes the connecting rod, causing it to present different positions and angles, thus deforming the wing. Connecting a motor to the center of the cam enables automated wing deformation. This invention has a simple structure, facilitating manufacturing and maintenance. Precise position control and motion trajectory can be achieved through the design and control of the cam. The thickness and camber of the entire wing can be varied by controlling the rotation of a single motor, and the wing frame surface remains relatively smooth without significant bends during deformation. Attached Figure Description

[0014] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 This is a schematic diagram of the overall structure of a variable thickness wing;

[0016] Figure 2 This is a schematic diagram of the cam linkage mechanism;

[0017] Figure 3 This is a structural diagram of the back of the cam used to connect to the motor;

[0018] Figure 4A diagram showing the airfoil's position when the cam head is at its highest point;

[0019] Figure 5 This is a diagram showing the state of the airfoil when the cam head is at the far right.

[0020] Figure 6 This is a diagram showing the state of the airfoil when the cam head is at its lowest position.

[0021] Figure 7 This is a diagram showing the airfoil's position when the cam head is at its far left.

[0022] Among them, 1. Wing four sections; 2. Wing three sections; 3. Wing two sections; 4. Wing one section; 5. Wing six sections; 6. Wing five sections; 7. Cam; 8. Link one; 9. Link two; 10. Link three. Detailed Implementation

[0023] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0024] The purpose of this invention is to provide a variable-thickness wing to address the problems existing in the prior art. This wing can achieve a structure as simple as possible while maintaining good coordination and surface smoothness, provided that variations in wing thickness and camber are met. Furthermore, to achieve linkage between the motor and the wing, the rotational motion of the motor needs to be converted into linear motion of the wing components.

[0025] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0026] like Figures 1-7 As shown, the present invention provides a variable thickness wing, comprising:

[0027] The main body of the wing comprises four wing segments 1, 2, 3, 4, 5, and 6, which are sequentially and movably connected end-to-end. Wing segment 5 is fixed to the fuselage. Wing segments 1 and 6, located at the wingtips, are positioned on the upper and lower sides respectively. The curved wing segment 4 is located at the leading edge of the wing.

[0028] The cam 7 linkage mechanism includes a cam 7, a first linkage 8, a second linkage 9, and a third linkage 10. The motor drives the cam 7 to rotate. One end of the first linkage 8 is connected to the cam head provided on the working surface of the cam 7, and the other end of the first linkage is hinged to the second linkage 9. One end of the second linkage 9 is hinged to the sixth segment 5 of the wing, and the other end of the second linkage 9 is connected to the second segment 3 of the wing through a first connector. One end of the third linkage 10 is fixedly connected to the sixth segment 5 of the wing, and the other end of the third linkage is connected to the third segment 2 of the wing through a second connector.

[0029] In one embodiment, the wing body includes four wing segments 1, three wing segments 2, two wing segments 3, one wing segment 4, six wing segments 5, and five wing segments 6, which are sequentially connected end to end by a pivot.

[0030] In one embodiment, the connecting rod three includes a main connecting rod and a secondary connecting rod. One end of the main connecting rod is connected to the connecting member two, and the other end of the main connecting rod is hinged to the secondary connecting rod. The bottom end of the secondary connecting rod is fixed to the wing segment 5.

[0031] In one embodiment, a support rod 1 and a support rod 2 are connected to the central axis of the cam 7. The other end of the support rod 1 is fixed to the wing segment 5, and the other end of the support rod 2 is connected to the hinge point of the main link and the secondary link.

[0032] In one embodiment, the first connector is a Y-shaped connector. The top ends of the two branches of the Y-shaped connector are fixedly connected to the second section 3 of the wing, and the bottom ends of the two branches of the Y-shaped connector are joined together and hinged to the second connecting rod 9.

[0033] In one embodiment, the connector is a two-dimensional Y-shaped connector. The top ends of the two branches of the Y-shaped connector are fixedly connected to the three segments 2 of the wing, and the bottom ends of the two branches of the Y-shaped connector are joined together and hinged to the three connecting rods 10.

[0034] The entire wing section is divided into six segments. Assuming that wing segment 5 is a fixed segment, the cam 7 linkage mechanism is concentrated on wing segment 5, wing segment 2, and wing segment 3. There is a protruding cam head on the working surface of cam 7. The cam head is connected to link 8, and link 8 drives link 9 to rotate slightly.

[0035] Link 2 (9) connects to the fixed wing segment 5 at one end and to wing segment 3 at the other. Rotation of link 2 (9) causes wing segment 3 to move, resulting in a change in the distance between wing segment 3 and wing segment 5, thus changing the overall wing thickness. The positions of wing segment 3 and wing segment 5 determine the shape of wing segment 4. Link 3 (10) connects to the fixed wing segment 5 at one end and to wing segment 2 at the other. Therefore, the shape of wing segment 2 is determined by link 3 (10) between wing segment 3 and wing segment 5. Once the positions of wing segment 2 and the link are determined, the positions of wing segment 1 and wing segment 6 are also determined.

[0036] As the above analysis shows, the rotation of cam 7 drives the movement of wing section 3 via connecting rod 1 (8) and connecting rod 2 (9). Wing section 3 and wing section 6 (5) determine the position of wing section 4 at the leading edge of the wing, and the position of the rear half of the wing, namely wing section 2, wing section 4 (1), and wing section 5 (6), is determined via connecting rod 3 (10). Thus, the rotation of cam 7 controls the overall thickness and camber of the wing.

[0037] Specifically, the changes in wing shape caused by the movement of cam 7 are as follows: Figures 4-7 As shown, as the cam head rotates clockwise around the central axis from the top, we obtain schematic diagrams of the wing shape when the cam head is at the top, right, bottom, and left.

[0038] As shown in the diagram above, as cam 7 rotates clockwise, the wing shape changes from a smooth curve to an upward curve, then back to a smooth curve, and finally downward curve, thus revealing the change in wing camber. Measurements show the thickness changes to 92.6mm-91.2mm-92.6mm-90.4mm. Specifically, the thickness is 92.6mm when the cam head is at its highest point, decreases to 91.2mm when the cam head is at its rightmost position, returns to 92.6mm when the cam head is at its lowest point, and decreases again to 90.4mm when the cam head is at its leftmost position. Therefore, the wing camber and thickness change cyclically with the rotation of cam 7. The rotation of cam 7 can be controlled by connecting a motor.

[0039] It should be noted that, for those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and that the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention, and no reference numerals in the claims should be construed as limiting the scope of the claims.

[0040] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A variable thickness wing, characterized in that: include The wing body comprises four, three, two, one, six, and five wing segments connected sequentially end-to-end. The six-segment wing is fixed to the fuselage. The four and five wing segments, located at the wing's tip, are positioned on the upper and lower sides respectively. The arc-shaped one-segment wing is located at the wing's leading edge. A cam-linkage mechanism includes a cam, a first link, a second link, and a third link. A motor drives the cam to rotate. One end of the first link is connected to a cam head on the working surface of the cam, and the other end of the first link is hinged to the second link. One end of the second link is hinged to the sixth segment of the wing, and the other end of the second link is connected to the second segment of the wing via a connector. One end of the third link is fixedly connected to the sixth segment of the wing, and the other end of the third link is connected to the third segment of the wing via a connector. The third link includes a main link and a secondary link. One end of the main link is hinged to the connector, and the other end of the main link is hinged to the secondary link. The bottom end of the secondary link is fixed to the sixth segment of the wing.

2. The variable thickness wing according to claim 1, characterized in that: The main body of the wing includes four wing sections, three wing sections, two wing sections, one wing section, six wing sections, and five wing sections that are connected sequentially end to end by a pivot.

3. The variable thickness wing according to claim 1, characterized in that: The cam's central axis is connected to support rod one and support rod two. The other end of support rod one is fixed to the sixth section of the wing, and the other end of support rod two is connected to the hinge point of the main connecting rod and the secondary connecting rod.

4. The variable thickness wing according to claim 1, characterized in that: The first connector is a Y-shaped connector. The top ends of the two branches of the Y-shaped connector are fixedly connected to the second section of the wing, and the bottom ends of the two branches of the Y-shaped connector are joined together and hinged to the second connecting rod.

5. The variable thickness wing according to claim 1, characterized in that: The second connector is a Y-shaped connector. The top ends of the two branches of the Y-shaped connector are fixedly connected to the three sections of the wing, and the bottom ends of the two branches of the Y-shaped connector are joined together and hinged to the three phases of the connecting rod.

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