Flexible deformation wing rib of variable camber wing trailing edge and driving device of flexible deformation wing rib
Through the combination of flexible structure and duplex lever, the complex driving system problems caused by multi-section rotating wing ribs in the prior art are solved, and the continuous changes in the wing trailing edge bending and the optimization of aerodynamic efficiency are achieved.
Patent Information
- Application Number
- CN202510586345.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-08
- Publication Date
- 2025-07-11
AI Technical Summary
The trailing edges of existing variable bending wings mostly use multi-section rotating ribs, which makes the drive system complex and it is difficult to achieve continuous changes in the trailing edge bending.
The deformed wing ribs and their driving devices with flexible structures, including flexible cells, connecting chains and duplex levers, are achieved by the cooperation of flexible cells and duplex levers.
The continuous changes in the wing trailing edge curvature are achieved, the aerodynamic efficiency is optimized, the structural weight is reduced, and the surface of the airfoil is smooth and the aerodynamic shape is maintained.
Smart Images
Figure CN120288231A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the field of variable aircraft structural design, and particularly relates to a flexible deformable wing rib for the trailing edge of a variable camber wing and its driving device. Background Art
[0002] A variable aircraft can change its aerodynamic shape during flight so as to obtain optimal aerodynamic performance when performing different tasks in different flight environments. A variable trailing edge camber wing can optimize the aerodynamic shape of the wing by changing the camber of the trailing edge, achieving the purpose of improving aerodynamic efficiency and reducing fuel consumption.
[0003] Currently, most variable camber wing trailing edges adopt multi-segment rotating wing ribs. The multi-segment rotating mechanism has a complex drive system and it is difficult to achieve continuous change of the trailing edge camber. Summary of the Invention
[0004] Aiming at the defects existing in the prior art, the present invention discloses a flexible deformable wing rib for the trailing edge of a variable camber wing and its driving device. The use of a flexible structure to achieve the change of the trailing edge camber of the wing can enable continuous change of the trailing edge camber, thereby optimizing the aerodynamic efficiency of the wing, and designing a driving device to control the change of the trailing edge camber and maintain the required aerodynamic shape.
[0005] The present invention is implemented as follows: A flexible deformable wing rib for the trailing edge of a variable camber wing and its driving device, wherein the flexible deformable wing rib comprises a set of serially connected flexible cells, a connecting chain and a trailing edge body; the driving device comprises a driving arm and a compound lever, and the driving device is installed behind the wing rear beam / rear wall; the flexible cell at the front end of the flexible deformable wing rib is connected to the wing rear beam / rear wall, and the flexible cell at the rear end of the flexible deformable wing rib is connected to the trailing edge body; the connecting chain passes through each flexible cell, one end of the connecting chain is connected to the wing rear beam / rear wall, and the other end of the connecting chain is connected to the trailing edge body; the driving arm is arranged between two flexible deformable wing ribs arranged along the wing span direction, the driving arm is supported on the wing rear beam / rear wall, and the compound lever drives the trailing edge body to move upward or downward, driving the trailing edge of the wing to deflect upward or downward.
[0006] Furthermore, the height of each flexible cell is the same as the airfoil height at its chordwise position, and the connecting chain keeps the length of the airfoil center line unchanged.
[0007] Furthermore, the flexible cell is composed of two adjacent flexible plates; the flexible plates are rectangular and are divided into the upper end, lower end, middle part, the middle between the upper and lower ends, and the two sides of the upper and lower ends; the upper and lower ends of the rectangular flexible plate are divided into the middle and the two sides as the middle bending plate and the side bending plates. The width of the middle bending plate is half of the width of the flexible plate, and the widths of the two side bending plates on both sides are each one-fourth of the width of the flexible plate; the side bending plates and the middle bending plate bend in different directions perpendicular to the plane of the flexible plate, while ensuring that the tangents at both ends of the bending plates are parallel to the middle part; after determining the initial position, the shape is fixed by stamping, and the side bending plates or the middle bending plates of adjacent flexible plate units are welded at the contact edges to form a flexible cell group; a square hole corresponding to the cross-sectional dimension of the connecting chain is opened at the center position of the middle part of the flexible plate, so that the connecting chain can pass through it; the height of the flexible cell is adapted to the height of the airfoil at the corresponding position.
[0008] Furthermore, the connecting chain is composed of rigid connecting pieces; the rigid connecting pieces are two-hole thin plates with rectangles at both ends and arcs, and the connecting chain is formed by alternately hinging single pieces and double pieces; the connecting pieces pass through the central holes of the flexible plate units of the flexible cell and are adhesively fixed to the flexible plates. Furthermore, the compound lever includes a lever and a b lever; the driving arm is a cantilever beam fixed on the rear beam / wall of the wing.
[0009] Furthermore, the driving arm leaves a space for the movement of the a lever and the b lever. There are two support seats above the cantilever beam as fulcrum A and fulcrum B; the fixed position of the cantilever beam is slightly lower than the airfoil midline, so that the fulcrums are in the chord plane of the airfoil; the a lever and the b lever move between the spaces at the center of the driving arm, and waist-shaped holes are opened on the levers, and the positions correspond to the positions of the fulcrums; the force of the driving motor / hydraulic actuator acts on the front end of the a lever, the rear end of the a lever is hinged to the front end of the b lever, and the rear end of the b lever is hinged to the trailing edge fairing.
[0010] Furthermore, when the camber of the trailing edge of the wing does not change, the a lever, the b lever and the fulcrums are on the same straight line; when changing the camber of the trailing edge of the wing, a downward driving force is applied to the front end of the a lever, and this driving force is transmitted to the b lever through the a lever, and the b lever transmits it to the trailing edge fairing, causing it to deflect downward; at this time, the opening distance between the upper ends of the flexible plate units becomes larger, and the opening distance between the lower ends becomes smaller; the connecting chain (6) undergoes a bending deformation as a whole at the trailing edge to ensure that the length of the midline remains unchanged.
[0011] The beneficial effects of the present invention compared with the prior art are as follows: The present invention uses a flexible structure to achieve the change of the camber of the trailing edge of the wing, which can make the camber change continuously, the airfoil surface is smooth, complex connections are avoided, the structural weight is reduced, and the aerodynamic efficiency of the wing is optimized.
[0012] The present invention can achieve a smooth change in the camber of the wing trailing edge, with a uniform change in the chordwise distance between adjacent flexible plates, providing uniform support for the flexible skin; when the camber of the wing trailing edge changes, the internal forces of the structure are uniform, the airfoil surface is smooth, and the aerodynamic shape is maintained. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 It is a schematic diagram of a flexible deformable wing rib and its driving device for the trailing edge of a variable-camber wing according to the present invention; Figure 2 It is a schematic diagram of the connection between the flexible cell and the rigid sheet of a flexible deformable wing rib and its driving device for the trailing edge of a variable-camber wing according to the present invention; Figure 3 It is a flexible deformable wing rib of a flexible deformable wing rib and its driving device for the trailing edge of a variable-camber wing according to the present invention; Figure 4 It is a driving device of a flexible deformable wing rib and its driving device for the trailing edge of a variable-camber wing according to the present invention; (a) driving device, (b) cross-section of the driving arm and the support, (c) schematic diagram of the lever connection; Wherein: 1 - flexible deformable wing rib, 2 - driving device, 3 - wing rear beam / rear wall, 4 - trailing edge fairing, 5 - flexible cell, 6 - connecting chain, 7 - driving arm, 8 - lever a, 9 - lever b. DETAILED DESCRIPTION OF THE EMBODIMENTS
[0014] To make the objectives, technical solutions and effects of the present invention clearer and more definite, the following examples are listed to further elaborate on the present invention in detail. It should be noted that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.
[0015] As Figure 1 shown, the flexible deformable wing rib 1 of the present invention includes a group of serially connected flexible cells 5, a connecting chain 6 and a trailing edge fairing 4. The driving device 2 includes a driving arm 7 and a compound lever, and is installed behind the wing rear beam / rear wall 3. The flexible cell 5 at the front end of the flexible deformable wing rib 1 is connected to the wing rear beam / rear wall 3, and the flexible cell 5 at the rear end is connected to the trailing edge fairing 4; the connecting chain 6 passes through each flexible cell 5, one end is connected to the wing rear beam / rear wall 3, and the other end is connected to the trailing edge fairing 4. The driving arm 7 is arranged in the middle of two flexible wing ribs arranged along the wing span direction, supported on the wing rear beam / rear wall 3, and the compound lever drives the trailing edge fairing 4 to move up or down, driving the wing trailing edge to deflect up or down. The height of each flexible cell 5 is the same as the airfoil height at the chordwise position where it is located, and the middle chain can keep the length of the airfoil center line unchanged.
[0016] The flexible cell 5 is composed of two adjacent flexible plates. The flexible plates are rectangular and are divided into upper ends, lower ends, middle parts, the middle of the upper and lower ends, and the two sides of the upper and lower ends. The middle of the upper and lower ends of the rectangular flexible plate is divided into the middle and the two sides as the middle bending plate and the side bending plates. The width of the middle bending plate is half of the width of the flexible plate, and the widths of the two side bending plates on both sides are each one-fourth of the width of the flexible plate. The side bending plates and the middle bending plate bend in different directions perpendicular to the plane of the flexible plate, and at the same time, ensure that the tangents at both ends of the bending plate are parallel to the middle part. After determining the initial position, the shape is fixed by stamping, and the side bending plates or the middle bending plates of adjacent flexible plate units are welded at the contact edges to form a flexible cell group. A square hole corresponding to the cross-sectional dimension of the connecting chain 6 is opened at the center position of the middle part of the flexible plate, so that the connecting chain 6 can pass through it. The height of the flexible cell 5 is adapted to the height of the airfoil at the corresponding position.
[0017] The described connecting chain 6 is composed of rigid connecting pieces. The rigid connecting pieces are two-hole thin sheets with rectangles at both ends and arcs, and the connecting chain 6 is formed by alternately hinging single sheets and double sheets. The connecting pieces pass through the central holes of the flexible plate units and are adhesively fixed to the flexible plates, as Figures 2 - 3 shown.
[0018] The driving device 2 of the present invention is a compound lever, including a driving support arm 7, a lever 8, and a lever 9. The driving support arm 7 is a cantilever beam fixed on the rear beam / wall 3 of the wing, as Figure 4 shown, where (a) the driving device, (b) the cross-section of the driving support arm and the support, and (c) the schematic diagram of the lever connection. The driving support arm 7 needs to leave a gap for the movement of the lever. There are two support seats above the cantilever beam as the fulcrums A and B. The fixed position of the cantilever beam is slightly lower than the center line of the airfoil, so that the fulcrums are in the chord plane of the airfoil. The lever 8 and the lever 9 move between the gaps at the center of the driving support arm 7. Waist-shaped holes are opened on the levers, and the positions correspond to the positions of the fulcrums. The force of the driving motor / hydraulic actuator acts on the front end of the lever 8. The rear end of the lever 8 is hinged to the front end of the lever 9, and the rear end of the lever 9 is hinged to the trailing edge fairing 4.
[0019] When the camber of the trailing edge of the wing does not change, the lever 8, the lever 9, and the fulcrums are on the same straight line; when changing the camber of the trailing edge of the wing, a downward driving force is applied to the front end of the lever 8. This driving force is transmitted through the lever 8 to the lever 9, and the lever 9 transmits it to the trailing edge fairing 4, causing it to deflect downward. At this time, the opening distance between the upper ends of the flexible plate units becomes larger, and the opening distance between the lower ends becomes smaller. The connecting chain 6 undergoes a bending deformation as a whole at the trailing edge to ensure that the length of the center line remains unchanged.
[0020] The following lists specific data to describe the present invention: In this example, the wing uses the NACA0018 airfoil, with a chord length of 1500 mm. The distance between the rear spar / rear wall of the wing and the leading edge of the wing is 900 mm, the height of the rear spar / rear wall is 200 mm, and the length of the trailing edge section of the wing is 600 mm. The flexible deformable wing rib is 400 mm long, with a terminal height of 78 mm. The trailing edge fairing is 200 mm long, and the spacing between adjacent deformable wing ribs is 800 mm. The driving device is installed in the middle of two deformable wing ribs, driving the trailing edge of the wing to deflect downward by 15°.
[0021] The deformable wing rib consists of 13 flexible cells. The width of a single flexible plate is 40 mm, the thickness is 2 mm, the initial bending shape spacing between the upper and lower ends is 30 mm, and the height is consistent with the airfoil height at this position. A square hole with a height of 15 mm is opened in the middle of the flexible plate. The width of the square hole corresponding to a single piece is 2.5 mm, and the width of the square hole corresponding to a double piece is 6.5 mm. The connecting chain is composed of 12 rigid connecting pieces, each with a height of 15 mm and a length of 30 mm. A single piece is a rigid thin sheet with a thickness of 2 mm, and a double piece is composed of two rigid thin sheets with a thickness of 2 mm arranged side by side, with a 2 mm gap left between the two thin sheets. The radius of the semi - circles at both ends of the rigid connecting piece is 7.5 mm, and a connecting hole with a diameter of 5 mm is opened at the center of the semi - circle.
[0022] The driving arm of the driving device is 230 mm long, 20 mm high, and 26 mm wide. Supports are set at positions 40 mm and 220 mm respectively from the rear spar / rear wall of the wing. The shape is a rectangle plus a semi - circle. The rectangle is 20 mm long and 20 mm high, and the radius of the semi - circle is 10 mm. A hole with a diameter of 6 mm is opened at the center of the semi - circle. Gaps of 16 mm are milled on the 0 - 20 mm and 60 - 210 mm sections of the driving arm as the lever movement space. The dimensions of the two sides of the driving arm are 20 mm high and 5 mm wide. Lever a is 200 mm long, lever b is 240 mm long. The main bodies of the two levers are 20 mm high and 5 mm thick, and the material is structural steel. The rear end of lever a has a single ear - piece 20 mm long and 5 mm thick. The front end of lever b has a double ear - piece 20 mm long, with an ear - piece thickness of 4 mm and a gap of 6 mm. The oblong hole on lever a is 32 mm long and 6 mm wide, and the distance from the center of the oblong hole to the center of the round hole at the rear end of lever a is 134 mm; the oblong hole on lever b is 28 mm long and 6 mm wide, and the distance from the center of the oblong hole to the center of the round hole at the front end of lever b is 50 mm. A joint for connecting to the output end of the driving motor / hydraulic actuator is set at the front end of lever a, and a joint for connecting to the trailing edge fairing is set at the rear end of lever b.
[0023] The drive motor / hydraulic actuator is installed on the rear wing beam / rear wall and is connected to the front end of a lever. When the wing deflects, the drive motor / hydraulic actuator drives the front end of the a lever to deflect downward. While deflecting, the a lever moves towards the trailing edge of the wing. During the deformation process, the connection point between the rear end of the a lever and the front end of the b lever deviates upward from the original airfoil center line by 24 mm, and the connection point between the rear end of the b lever and the trailing edge fairing deviates downward from the original airfoil center line by 105 mm. At this time, the trailing edge deflects downward by 15°. During the deformation process, the flexible cells produce flexible deformation, making the wing profile smooth.
[0024] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements can be made, and these improvements should also be regarded as the protection scope of the present invention.
Claims
1. A flexible deformable wing rib for the trailing edge of a variable camber wing and its driving device, characterized in that the flexible deformable wing rib (1) includes a set of serially connected flexible cells (5), a connecting chain (6) and a trailing edge fairing (4); the driving device (2) includes a driving arm (7) and a compound lever, and the driving device (2) is installed behind the wing rear beam / rear wall (3); the flexible cells at the front end of the flexible deformable wing rib (1) are connected to the wing rear beam / rear wall (3), and the flexible cells at the rear end of the flexible deformable wing rib (1) are connected to the trailing edge fairing (4); the connecting chain (6) passes through each flexible cell, one end of the connecting chain (6) is connected to the wing rear beam / rear wall, and the other end of the connecting chain (6) is connected to the trailing edge fairing (4); the driving arm (7) is arranged in the middle of two flexible deformable wing ribs (1) arranged along the wing span direction, the driving arm (7) is supported on the wing rear beam / rear wall (3), and the compound lever drives the trailing edge fairing (4) to move up or down, driving the wing trailing edge to deflect up or down.
2. The flexible deformation wing rib and its driving device for the trailing edge of a variable camber wing according to claim 1, characterized in that, The height of each flexible cell (5) is consistent with the airfoil height at the corresponding chordwise position, and the connecting chain (6) keeps the length of the airfoil center line unchanged.
3. The flexible deformation wing rib and its driving device of the variable camber wing trailing edge according to claim 1, characterized in that, The flexible cell (5) is composed of two adjacent flexible plates; the flexible plate is rectangular and is divided into the upper end, the lower end, the middle part, the middle between the upper and lower ends, and the two sides of the upper and lower ends; the middle and the two sides are divided at the upper and lower ends of the rectangular flexible plate as the middle bending plate and the side bending plates. The width of the middle bending plate is one-half of the width of the flexible plate, and the widths of the two side bending plates on both sides are each one-fourth of the width of the flexible plate; the side bending plates and the middle bending plate bend in different directions perpendicular to the flexible plate surface, and at the same time ensure that the tangents at both ends of the bending plate are parallel to the middle part; after determining the initial position, the shape is fixed by stamping, and the side bending plates or the middle bending plates of adjacent flexible plate units are welded at the contact edges to form a flexible cell group; a square hole corresponding to the cross-sectional size of the connecting chain is opened at the center position of the middle part of the flexible plate, so that the connecting chain (6) can pass through it; the height of the flexible cell (5) is adapted to the airfoil height at the corresponding position.
4. A flexible deformation wing rib and its driving device for a variable camber wing trailing edge according to claim 1, characterized in that, The connecting chain (6) is composed of rigid connecting pieces; the rigid connecting piece is a two-hole thin plate with a rectangle at both ends and arcs, and the connecting chain (6) is formed by alternately hinging single pieces and double pieces; the connecting piece passes through the central hole of the flexible plate unit of the flexible cell (5) and is adhesively fixed to the flexible plate.
5. The flexible deformation rib and its driving device of the trailing edge of a variable camber wing according to claim 1, characterized in that, The compound lever includes a lever a (8) and a lever b (9); the driving arm (7) is a cantilever beam fixed on the wing rear beam / rear wall (3).
6. The flexible deformation wing rib and its driving device for the trailing edge of a variable camber wing according to claim 1, characterized in that, The described driving support arm (7) leaves a gap for the movement of the a-lever (8) and the b-lever (9). There are two support seats above the cantilever beam as the fulcrum A and the fulcrum B; the fixed position of the cantilever beam is slightly lower than the airfoil center line, so that the fulcrums are in the chord plane of the airfoil; the a-lever (8) and the b-lever (9) move between the gaps at the center of the driving support arm (7), and waist-shaped holes are opened on the levers, and the positions correspond to the positions of the fulcrums; the acting force of the driving motor / hydraulic actuator acts on the front end of the a-lever (8), the rear end of the a-lever (8) is hinged to the front end of the b-lever (9), and the rear end of the b-lever (9) is hinged to the trailing edge fairing (4).
7. The flexible deformable wing rib and its driving device for the trailing edge of a variable camber wing according to claim 6, characterized in that, When the camber of the wing trailing edge remains unchanged, the a-lever (8) and the b-lever (9) are in the same straight line as the fulcrum; when changing the camber of the wing trailing edge, a downward driving force is applied to the front end of the a-lever (8), and this driving force is transmitted to the b-lever (9) through the a-lever (8), and the b-lever (9) transmits it to the trailing edge fairing, causing it to deflect downward; at this time, the opening distance at the upper end of the flexible plate unit becomes larger, and the opening distance at the lower end becomes smaller; the connecting chain (6) undergoes bending deformation as a whole at the trailing edge to ensure that the center line length remains unchanged.