CN117682051A - Fishbone-like flexible trailing edge bending wing - Google Patents

Abstract

The invention provides a fishbone-imitated flexible trailing edge camber wing, which comprises a wing body, a middle wing box and a flexible trailing edge section which are connected in sequence; the tail ends of the multiple groups of rigid fishbone joints are hinged in series and then are hinged with the rear edge rigid wing tips to form a fishbone-like structure; the ends of adjacent rigid fishbone condyles are connected through a composite flexible corrugated plate, and the outermost layer of the fishbone-like flexible trailing edge camber wing is bonded with a micro-groove wing skin; the driving device comprises a double-shaft driving motor and a carbon steel aluminum-clad rope, wherein the double-shaft driving motor is fixed on one side of the middle wing box, which is close to the wing body, the carbon steel aluminum-clad rope is arranged in the rigid fishbone joints and the rear edge rigid wing tips in a penetrating mode, and two ends of the carbon steel aluminum-clad rope are respectively wound on two driving shafts of the double-shaft driving motor. The fishbone-like flexible trailing edge bending wing can reduce landing and approach noise caused by gaps, and can simplify the mechanical structure, thereby effectively improving the overall performance of an airplane.

Description

A kind of fishbone-like flexible trailing edge variable camber wing

Technical field

The invention relates to deformable wing technology, and in particular to a fishbone-like flexible trailing edge variable camber wing.

Background technique

Biomimicry is an approach that uses design principles from natural biological systems to solve engineering problems. The efficient swimming of fish in water has always been one of the inspirations for human engineering design. Fish bones are lightweight and strong, able to provide sufficient support. The fish bones are slender and flexible, and are highly similar to streamlined wings, thereby reducing drag and improving their movement performance. Herringbone wing designs simulate this structure by using lightweight yet strong materials, such as composites or advanced alloys, to build the wing's frame. This design not only ensures sufficient stiffness, but also reduces the overall weight and improves flight efficiency.

Lift-increasing devices on the trailing edge of traditional wings, such as flaps and slats, although providing certain performance advantages in flight, also have some disadvantages:

1. Noise generation: The expansion and contraction process of flaps and slats may generate noise, which is detrimental to the environmental impact of the aircraft and the comfort of the pilot. As restrictions on aircraft noise become increasingly tight, this is an issue that needs to be addressed.

2. Mechanical complexity: Traditional lifting devices usually require complex mechanical systems to implement, including numerous actuators and transmission systems. This increases the aircraft's maintenance costs and likelihood of failure.

Contents of the invention

The purpose of the present invention is to propose a fishbone-like flexible trailing edge variable camber wing in view of the above-mentioned problems of high noise and complex mechanical structure of traditional wings. It reduces landing and approach noise, and can simplify the mechanical structure, thereby effectively improving the overall performance of the aircraft.

In order to achieve the above object, the technical solution adopted by the present invention is: a fishbone-like flexible trailing edge variable camber wing, including a wing body, a middle wing box, a flexible trailing edge section and a biaxial drive motor. The wing body , the middle wing box and the flexible trailing edge section are connected in sequence;

The flexible trailing edge section includes a micro-groove wing skin, multiple sets of rigid fish bone joints, a trailing edge rigid wing tip and a composite flexible corrugated plate. The multiple groups of rigid fish bone joints are connected in series to articulate the rear tail end and the trailing edge. The rigid wingtips are hinged to form an imitation fishbone structure; the sizes of the rigid fishbone joints from the middle wing box to the rigid wingtips at the trailing edge gradually become smaller, making the entire wing form a smooth airfoil; the ends of adjacent rigid fishbone joints are passed through Composite flexible corrugated plates are connected, and the outermost layer of the herringbone-like flexible trailing edge variable camber wing is bonded with a micro-groove wing skin;

The drive device includes a biaxial drive motor and a carbon steel-clad aluminum rope. The biaxial drive motor is fixed on the side of the middle wing box close to the wing body. The carbon steel-clad aluminum rope is threaded through the rigid fishbone joints and the trailing edge. On the rigid wingtip, both ends of the carbon steel-clad aluminum rope are respectively wrapped around the two drive shafts of the dual-axis drive motor.

Further, the wing body is in the shape of a wing, and one end thereof is integrally bonded and fixed with the middle wing box to form an inner cavity of the wing.

Further, a plurality of reinforcing ribs are provided in the inner cavity of the wing of the wing body.

Furthermore, the wing body is made of glass fiber reinforced composite material. Variable stiffness can be achieved by adjusting the thickness of the ply, and its stiffness can be customized according to the requirements of specific applications. With layered materials, each layer contributes to the stiffness of the overall structure. The total stiffness of a structure can be viewed as the sum of the stiffnesses of each layer. When the thickness of a layer increases, the stiffness of this layer also increases accordingly. Since the overall stiffness is the sum of the stiffness of each layer, the stiffness of the overall structure also increases.

Furthermore, the structural shape of the middle wing box can be diversified in design according to the wing shape and coordination requirements with the flexible skin to meet different adaptability requirements. Preferably, the middle wing box is approximately E-shaped in cross-section and has the function of installing and fixing the two-axis drive motor.

Further, the upper and lower parts of the side of the middle wing box close to the flexible trailing edge section are respectively provided with elongated through holes for penetrating carbon steel-clad aluminum ropes.

Further, the two ends of the middle wing box close to the flexible trailing edge section are bonded to the trailing edge composite flexible corrugated plate.

Further, the rigid fish bone condyle is in 3-8 groups, preferably 4 groups.

Further, the rigid fish bone joint takes the plane where the center arc line of the wing is as the axis of symmetry, and includes an upper bone rib, a middle bone rib and a lower bone rib arranged integrally.

Further, the upper and lower ribs of the first rigid fish bone joint (the rigid fish bone joint near the middle wing box) are respectively inclined backward (to the side away from the middle wing box) by 45°-75°, preferably 60° , the angle between the upper bone rib and the lower bone rib is 90-150°, preferably 120°, and the upper and lower bone ribs of the remaining rigid fish bone joints are respectively tilted backward by 25°-40°, preferably 30° °, the angle between the upper rib and the lower rib is 50-80°, preferably 60°.

Furthermore, the head and tail of adjacent rigid fish bone joints are hinged through cylindrical pins, which increases the flexibility of deformation.

Furthermore, the rigid fish bone joints are made of glass fiber composite materials and manufactured through 3D printing technology, which reduces the difficulty of structural manufacturing and reduces the weight of the structure while ensuring strength, stiffness and stability.

Further, the rigid fish bone joints are symmetrically provided with openings in the middle of the upper and lower ribs for penetrating the carbon steel-clad aluminum rope.

Further, a rolling shaft is symmetrically provided at the opening of the middle wing box and a rolling bearing of the same size is installed. The rolling bearing is divided into two parts and bonded and fixed on the rolling bearing rolling shaft; the odd-numbered rigid fish bone joint opening is symmetrically provided with a rolling shaft. The rolling shaft is installed with a rolling bearing of the same size. The rolling bearing is divided into two parts and bonded to the rolling shaft. The odd-numbered rigid fish bone joints are: the first rigid fish bone joints, the third rigid fish bone joints...

Further, in order to meet the overall structural strength requirements, circular weight-reducing holes are provided on the rigid fish bone joints.

Furthermore, the composite flexible corrugated board combines high-performance fiber materials and lightweight and high-strength resin matrix, using composite manufacturing technology to form a unique corrugated structure, which increases the tensile and bending deformation capabilities. , the high specific strength and high specific stiffness of composite materials enable the corrugated plate to withstand complex mechanical loads inside the wing, achieve a shock-absorbing effect and ensure the stability of the structure. The composite flexible corrugated plate provides constraints for the rigid fishbone joints and can provide support for the micro-grooved wing skin without affecting the compliant deformation of the micro-grooved wing skin. Therefore, during the wing deformation process, the aircraft The wing can always maintain a good aerodynamic shape.

Furthermore, the micro-grooved wing skin is made of carbon fiber composite material, and the micro-grooves are removed by CNC laser cutting. The existence of micro-grooves can improve air flow and reduce the generation of turbulence, thereby reducing frictional resistance, which is beneficial to increasing aircraft speed and reducing fuel consumption.

Furthermore, a single wheel is installed in the rigid wing tip of the trailing edge. The size of the single wheel is larger than that of the rolling bearing to meet the tensile strength requirements, and the bonding method is the same as that of the rolling bearing. The single-wheel rotating shaft is parallel to the rolling axis of the rolling bearing.

Further, one end of the carbon steel-clad aluminum rope is wound around a drive shaft of the dual-axis drive motor, and the other end is passed through the opening of the rib on the rigid fish bone joint, wound around the wheel, and then passed through the rigid fish bone in turn. After opening the bone rib under the joint, it is wound around the other drive shaft of the dual-axis drive motor.

Further, a plurality of bolt holes are provided on the side of the middle wing box close to the wing body; the biaxial drive motor is fixed to the middle wing box through the bolts and bolt holes, and the bolt model is M10. The dual-axis drive motor is placed in the middle wing box. The two sets of drive shafts are wrapped with carbon steel-clad aluminum ropes. Positive and negative currents are input to the motors to control the drive shaft to rotate clockwise (counterclockwise) to retract and release the carbon steel-clad aluminum ropes. The rolling bearing is fixed on the rolling shaft of the rigid joint. The function of the rolling bearing is that during the deflection of the wing rib, the carbon steel-clad aluminum rope is always close to the groove of the rolling bearing and slides along the driving direction of the dual-axis drive motor. During operation, the rotational torque output by the dual-axis drive motor is transmitted to the trailing edge rigid wingtip through the carbon steel-clad aluminum rope. The drive system achieves symmetrical and precise deflection of the wing along the mid-arc line by adjusting the length of the carbon steel-clad aluminum rope.

Further, the dual-axis drive motor uses YB2-132S-4H model motor.

Furthermore, for the carbon steel-clad aluminum rope, carbon steel is a material with high strength and wear resistance, which makes this rope have better load bearing capacity and wear resistance. Aluminum is a relatively lightweight material, and cladding it over a carbon steel core reduces the overall rope weight. This is particularly important for the design of lightweight wing structures in air transportation.

The structure of the fishbone-like flexible trailing edge variable camber wing of the present invention is simple, reasonable and compact, and has the following advantages compared with the existing technology:

1) The present invention's fishbone-like flexible trailing edge variable camber wing trailing edge structure can simultaneously meet precise deformation and high aerodynamic load-bearing;

2) The present invention can realize seamless, smooth and continuous shape changes of the continuous trailing edge aerodynamic shape, can realize real-time optimization of the wing airfoil, reduce landing and approach noise caused by gaps, and can effectively improve the overall performance of the aircraft;

3) The present invention uses a dual-axis drive motor to drive, which is beneficial to realizing the drive of multi-ribbed three-dimensional wings;

4) The carbon steel-clad aluminum rope of the present invention reduces the complexity of the trailing edge mechanism of the variable camber wing and reduces the weight;

5) The overall structure of the present invention has a small number of connecting parts, easy module assembly, disassembly and maintenance, small relative errors, and high reliability.

In summary, the trailing edge structure design of the present invention aims to achieve changes in the curvature of the wing to simultaneously meet precise deformation requirements and high aerodynamic load-bearing performance. This design helps reduce landing and approach noise caused by gaps and simplifies the mechanical structure, thereby effectively improving the overall performance of the aircraft.

Description of the drawings

Figure 1 is a schematic structural diagram of the herringbone-like flexible trailing edge variable camber wing of the present invention;

Figure 2 is a schematic structural diagram of the middle wing box and flexible trailing edge section of the present invention;

Figure 3 is a schematic structural diagram of the rigid fish bone joint of the present invention;

Figure 4 is a schematic diagram of the hinge of the rigid fish bone joints of the present invention;

Figure 5 is a schematic structural diagram of the fishbone-like flexible corrugated plate of the present invention;

Figure 6 is a schematic diagram of the variable camber trailing edge driving device of the present invention;

Figure 7 is an exploded schematic diagram of the variable camber trailing edge driving device of the present invention;

Figure 8 is a schematic diagram of the trailing edge rigid wingtip structure of the present invention.

Reference signs: 1-wing body; 2-middle wing box; 3-flexible trailing edge section; 4-micro-groove wing skin; 5-first rigid fish bone joint; 6-second rigid fish bone joint ;7-The third rigid fish bone joint; 8-The fourth rigid fish bone joint; 9-Composite flexible corrugated plate; 10-Trailing edge rigid wing tip; 11-Pin; 12-Rolling bearing; 13-Rolling bearing rolling axis; 14 -Unique wheel; 15-uniwheel rolling shaft; 16-carbon steel clad aluminum rope; 17-dual-axis drive motor; 18-bolt; 19-bolt hole; 20-weight reduction hole.

Detailed ways

The present invention will be further described below in conjunction with the examples:

Example 1

This application discloses a fishbone-like flexible variable-bend wing trailing edge structure, as shown in Figure 1, including a wing body 1, a middle wing box 2, a flexible trailing edge section 3 and a dual-axis drive motor 17, specifically including the following Structure: micro-groove wing skin 4, first rigid fish bone joint 5; second rigid fish bone joint 6; third rigid fish bone joint 7; fourth rigid fish bone joint 8, composite flexible corrugated plate 9, Carbon steel clad aluminum rope 16, dual-axis drive motor 17 and other components. The flexible trailing edge section 3 includes four groups of rigid fish bone joints and flexible corrugated plates that are hinged in sequence to form a hinge mechanism, which together with the trailing edge rigid wingtip 7 form an approximate fishbone structure; from the middle wing box 2 to the rear Each segment of the edge-rigid wing tip 10 follows a pattern of successively smaller sizes, so that the entire wing forms a smooth airfoil.

Turbulence is a chaotic flow of air over the wing surface that causes increased drag. As shown in Figure 2, the wing skin 4 containing micro-grooves on the surface of the wing package is closely bonded with the internal structure of the skin. The micro-groove wing skin is made of carbon fiber composite material. Removal is performed by CNC laser cutting. The existence of micro-grooves can improve air flow and reduce the generation of turbulence, thereby reducing frictional resistance, which is beneficial to increasing aircraft speed and reducing fuel consumption.

The wing body 1 is in the shape of a wing, and its two ends are integrally bonded and fixed with the middle wing box 2 to form an inner cavity of the wing. A plurality of reinforcing ribs are provided in the inner cavity of the wing body 1 . In the embodiment of the present application, the wing body 1 is made of glass fiber reinforced composite material. Variable stiffness can be achieved by adjusting the thickness of the ply, and its stiffness can be customized according to the requirements of specific applications.

The right end of the wing body 1 is provided with an intermediate wing box 2. The structural shape of the intermediate wing box can be diversified according to the wing shape and coordination requirements with the flexible skin to meet different adaptability requirements. In this embodiment, it is preferred that the section of the middle wing box of the wing is approximately E-shaped, and has the function of installing and fixing the two-axis drive motor. There is a long opening on the right side of the wing box for penetrating carbon steel-clad aluminum ropes and bonding to the trailing edge composite flexible corrugated plate.

The flexible trailing edge section 3 mainly includes a first rigid fish bone joint 5; a second rigid fish bone joint 6; a third rigid fish bone joint 7; a fourth rigid fish bone joint 8 and a composite flexible corrugated plate 9. A multi-section hinged structure, each multi-section structure includes a plurality of rigid joints articulated in sequence, forming a fish-bone-like structure, and is bonded and formed with a composite flexible corrugated plate 9; the size of each rigid joint of the multi-section structure It decreases in sequence, and each rigid joint includes an upper bone rib, a middle bone rib, and a lower bone rib that are integrated together.

Specifically, as shown in Figure 3, a single rigid joint takes the plane of the center arc of the wing as the axis of symmetry. The upper and lower ribs of the first section are respectively tilted backward by 60°. The included angle is 120°. The upper and lower ribs of the remaining rigid joints are tilted backward by 30° respectively, and the angle between the upper and lower ribs is 60°. As shown in Figure 4, adjacent rigid joints are hinged through cylindrical pins 11, which increases the flexibility of deformation. The rigid joints 5-8 are made of glass fiber composite materials and manufactured through 3D printing technology, which reduces the difficulty of structural manufacturing and reduces the weight of the structure while ensuring strength, stiffness and stability. The rigid fish bone joints 5-8 are provided with openings at the middle positions of the upper and lower joints for penetrating the carbon steel-clad aluminum rope 13. At the opening of the middle wing box, rolling shafts are symmetrically provided at the openings of the first rigid fish bone joint 5 and the third rigid fish bone joint 7, and rolling bearings of the same size are installed. The rolling bearing 12 is divided into two parts and bonded and fixed in The rolling bearing is on the rolling shaft 13. In addition, in order to meet the overall structural strength requirements, a circular weight-reducing hole 20 is provided on each rigid fish bone joint.

Specifically, as shown in Figure 5, the composite flexible corrugated plate 9 combines high-performance fiber materials and lightweight and high-strength resin matrix, and uses composite manufacturing technology to form a unique corrugated structure. This structure increases the tensile strength And bending deformation ability, the high specific strength and high specific stiffness of composite materials enable the corrugated plate to withstand complex mechanical loads inside the wing, exert a shock absorption effect, and ensure the stability of the structure. The composite flexible corrugated plate 9 provides constraints and can provide support for the micro-grooved wing skin 4 without affecting the compliant deformation of the micro-grooved wing skin 4. Therefore, during the deformation process of the wing, the wing is always Able to maintain better aerodynamic shape.

As shown in Figures 6 and 7, in order to enable the variable camber wing structure of the present invention to continuously deform, a driving system is provided in the middle wing box 2. As shown in Figures 6 and 7, the drive system includes a carbon steel-clad aluminum rope 16 and a dual-axis drive motor 17. The details are as follows: there are multiple bolt holes 19 in the front of the middle wing box 2; specifically, 8 bolts 18 are used to fix the dual-axis drive motor 17, and the bolt model is M10. The dual-axis drive motor 17 is placed in the middle wing box 2. The two sets of drive shafts are wrapped with carbon steel-clad aluminum ropes 16. Positive and negative currents are input to the motors to control the drive shaft to rotate clockwise (counterclockwise) in order to retract and unfold the carbon steel-clad aluminum ropes 16. . The rolling bearing 12 is fixed on the rolling shaft 13 of the rigid joint. The function of the rolling bearing 12 is that during the deflection of the wing rib, the carbon steel-clad aluminum rope 16 is always close to the rolling bearing groove and slides along the driving direction of the dual-axis drive motor. During operation, the rotational torque output by the dual-axis drive motor 17 is transmitted to the trailing edge rigid wingtip 10 as shown in Figure 8 through the carbon steel-clad aluminum rope 16, in which a single wheel 14 is installed in the trailing edge rigid wingtip 10, and the size of the single wheel is Larger than rolling bearings to meet tensile strength requirements, and the bonding method is the same as rolling bearings. The drive system achieves symmetrical and precise deflection of the wing along the central arc line by adjusting the length of the rope. In this embodiment, the motor is YB2-132S-4H model motor. Specifically, carbon steel-clad aluminum rope 16, carbon steel is a high-strength, wear-resistant material, which makes this rope have better load bearing capacity and wear resistance. Aluminum is a relatively lightweight material, and cladding it over a carbon steel core reduces the overall rope weight. This is particularly important for the design of lightweight wing structures in air transportation.

The herringbone-like flexible trailing edge variable camber wing provided by the embodiment of the present invention divides the wing into a wing body 1, a middle wing box 2, a flexible trailing edge section 3, and a multi-section flexible trailing edge section 3 along the chord direction. The structure is mainly composed of multiple rigid joints in a hinged form, forming a structure similar to fish bone joints. According to different flight conditions, during operation, the rotational torque output by the dual-axis drive motor 17 is transmitted to the trailing edge rigid wingtip 10 through the carbon steel-clad aluminum rope 16. By adjusting the length of the rope, the wing is symmetrically and accurately deflected along the center arc line, achieving the seamless, smooth and continuous shape change requirements of the continuous trailing edge aerodynamic shape. This invention actively adjusts the curvature of the trailing edge of the wing to optimize the aerodynamic performance of the aircraft, thereby achieving the goals of increasing lift and reducing drag. The wing surface adopts a design containing micro-grooves, namely micro-groove wing skin 4, to enhance the drag-reducing effect of the wing. In addition, the leading edge rigid section adopts a hollow structure with reinforced ribs, which can not only withstand the effects of aerodynamic forces, but also effectively reduce the weight of the wing, achieving energy saving and emission reduction.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention, but not to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: The technical solutions described in the foregoing embodiments can still be modified, or some or all of the technical features can be equivalently replaced; and these modifications or substitutions do not deviate from the essence of the corresponding technical solutions from the technical solutions of the embodiments of the present invention. scope.

Claims (10)

1. The fishbone-like flexible trailing edge camber wing is characterized by comprising a wing body (1), a middle wing box (2), a flexible trailing edge section (3) and a double-shaft driving motor (17), wherein the wing body (1), the middle wing box (2) and the flexible trailing edge section (3) are sequentially connected;

the flexible trailing edge section (3) comprises a micro-groove wing skin (4), a plurality of groups of rigid fishbone sections, a trailing edge rigid wing tip (10) and a composite flexible corrugated plate (9), wherein the tail ends of the groups of rigid fishbone sections are hinged in series and then are hinged with the trailing edge rigid wing tip (7) to form a fishbone-like structure; the sizes of the rigid fishbone condyles from the middle wing box (2) to the rear edge rigid wing tip (10) become smaller in sequence; the ends of adjacent rigid fishbone condyles are connected through a composite flexible corrugated plate (9), and the outermost layer of the fishbone-like flexible trailing edge camber wing is bonded with a micro-groove wing skin (4);

the driving device comprises a double-shaft driving motor (17) and a carbon steel aluminum-clad rope (16), wherein the double-shaft driving motor (17) is fixed on one side, close to the wing body (1), of the middle wing box (2), the carbon steel aluminum-clad rope (16) is arranged in the rigid fishbone condyle and the rear edge rigid wing tip (10) in a penetrating mode, and two ends of the carbon steel aluminum-clad rope (16) are respectively wound on two driving shafts of the double-shaft driving motor (17).

2. The fishbone simulated flexible trailing edge camber wing according to claim 1, wherein a plurality of stiffeners are provided in the wing inner cavity of the wing body (1).

3. The fishbone flexible trailing edge camber airfoil of claim 1 wherein the intermediate wing box (2) is approximately E-shaped in cross section.

4. The fishbone simulated flexible trailing edge camber wing according to claim 1, wherein the upper and lower parts of the side of the intermediate wing box (2) adjacent to the flexible trailing edge section (3) are provided with elongated through holes respectively.

5. The fish bone-like flexible trailing edge camber airfoil of claim 1 wherein the upper and lower rib sections of the first section of rigid fish bone condyle are each inclined rearwardly 45 ° -75 ° with an included angle between the upper and lower rib sections of 90-150 °; the upper rib and the lower rib of the rest rigid fish bone condyle are respectively inclined backwards by 25-40 degrees, and the included angle between the upper rib and the lower rib is 50-80 degrees.

6. The fishbone-like flexible trailing edge camber airfoil of claim 1 wherein adjacent rigid fishbone segments are hinged at their head and tail by cylindrical pins (11).

7. The simulated fish bone flexible trailing edge camber wing of claim 1 wherein said rigid fish bone condyle is symmetrically provided with openings in the upper and lower bone ribs.

8. The fishbone-imitated flexible trailing edge camber wing according to claim 1, wherein the middle wing box (2) is symmetrically provided with rolling shafts at the openings and is provided with rolling bearings with the same size, and the rolling bearings (12) are divided into two parts and are adhered and fixed on the rolling bearing rolling shafts (13); the odd rigid fishbone condyle is symmetrically provided with rolling shafts at the holes, and rolling bearings with the same size are installed, and the rolling bearings (12) are divided into two parts and are adhered and fixed on the rolling bearing rolling shafts (13).

9. The fishbone flexible trailing edge camber airfoil of claim 1 wherein a single wheel (14) is disposed within the trailing edge rigid wing tip (10), the single wheel (14) axis of rotation being parallel to the rolling bearing axis of rotation (13).

10. The fishbone-like flexible trailing edge camber wing according to claim 1, wherein the carbon steel aluminum clad rope (16) is wound on one driving shaft of the double-shaft driving motor (17) at one end, and is wound on the single wheel (14) after sequentially passing through the holes of the upper rib of the rigid fishbone segment and then sequentially passing through the holes of the lower rib of the rigid fishbone segment, and is wound on the other driving shaft of the double-shaft driving motor (17).