CN117602059A - A deformable skin structure that can achieve variable camber and thickness of the wing - Google Patents

Abstract

The invention discloses a deformable skin structure capable of changing the camber and thickness of an airfoil, including: a deformable skin, a chordwise support structure, a spanwise truss, and a locking device; the deformable skin serves as the outer surface of the wing. Wrap other structures in it. The chordwise support structure is laid in the chordwise direction. Multiple spanwise girders are arranged in the wing direction according to the spanwise length of the skin. The spanwise long trusses are set between the chordwise support structures and are fixedly connected to the skin. , the locking device is laid between the chordwise support structures and is fixedly connected to the deformed skin. The invention can realize the rapid deformation of the wing skin and the ability to flexibly adapt to different flight conditions, thereby improving the performance and application breadth of the deformed wing.

Description

A deformable skin structure that can achieve variable camber and thickness of the wing

Technical field

The present invention relates to the technical field of aircraft deformation wing structures, in particular to a deformation skin structure that can achieve variable curvature and thickness of the wing.

Background technique

With the continuous development of deformable wing technology, the requirements for skins have also further increased. Traditional skin structures and design methods can no longer meet the requirements of continuous, smooth large deformation and high load-bearing performance of morphing wings. In order to cope with this demand, domestic and foreign scholars have proposed two types of deformable skins based on special structures and based on special materials. Deformable skins based on special structures mainly use corrugated structures and honeycomb structures, but their main technical difficulties lie in their complex structures, limited load-bearing capacity, and difficulty in being widely used on a single wing. Deformable skins based on special materials mainly face technical problems such as small deformation stiffness, low economy, slow deformation response speed, and limited deformation stroke.

Contents of the invention

The technical problem to be solved by the present invention is to provide a deformable skin structure that can realize the changing curvature and thickness of the wing, and can realize the rapid deformation of the wing skin and the ability to flexibly adapt to different flight conditions, thereby improving the performance of the deformed wing. Performance and application breadth.

In order to solve the above technical problems, the present invention provides a deformable skin structure capable of changing the curvature and thickness of the wing, including: a deformable skin, a chordwise support structure, a spanwise truss, and a locking device; the deformable skin serves as an aircraft wing. The outer surface of the wing wraps other structures. The chordwise support structure is laid in the chordwise direction. Multiple spanwise girders are arranged in the wing direction according to the spanwise length of the skin. The spanwise long trusses are set between the chordwise support structures. Fixedly connected to the skin, the locking device is laid between the chordwise support structures and fixedly connected to the deformed skin.

Preferably, the deformed skin includes a leading edge skin, a middle skin and a trailing edge skin. The three parts overlap each other and leave a certain length; when the skin is deformed, relative sliding will occur between the skins.

Preferably, a spanwise truss is provided in the spanwise direction of the wing, which is connected to the chordwise support structure. The spanwise truss adopts a "Γ" cross-sectional shape.

Preferably, the chordwise support structure includes the connection point of the leading edge actuator, the overlapping mechanism between the leading edge skin and the middle skin, the connection point between the middle actuator, the overlapping mechanism between the middle skin and the trailing edge skin, and the flange; The upper and lower structures of the chordwise support structure are symmetrically arranged. From front to back, they are the connection between the leading edge actuator, the overlapping mechanism between the leading edge skin and the middle skin, the connection between the middle actuator, and the connection between the middle skin and the trailing edge skin. The skin lap joint mechanism is fixedly connected through the flange; the upper surface of the chordwise support structure is connected to the wing skin.

Preferably, the leading edge actuator connection and the mid-section actuator connection of the wing are connected to the driving device. By controlling the connection between the actuator connection and the driving device, the chordwise support structure is controlled to produce the same or different changes.

Preferably, the chordwise support structure includes four pull-out overlapping sliding mechanisms, which are arranged at the overlapping skins. The sliding guide rails and the fixed end of the first roller are respectively connected to the different overlapping skins, so that the overlapping skins can Displacement along the chute direction is generated, which in turn deforms the entire wing skin.

Preferably, the locking device includes a second roller, a chute and a support. The second roller is installed on one piece of skin through the support and is fixedly connected to the skin. The chute is fixedly installed on the other piece of skin; this kind of The design ensures that buckling will not occur when the skin deflects and deforms, allowing the skin to better maintain its streamlined shape.

Preferably, the first roller and the sliding guide rail are respectively fixed on different skins. Through their connection, the two adjacent skins are displaced along the direction of the sliding guide rails, thereby deforming the skin of the entire wing.

The beneficial effects of the present invention are: the wing deformation skin structure can realize the changing curvature and thickness of the skin of the wing. Through the control of different positions by the driving device, any shape can be theoretically realized, thereby effectively realizing the upper and lower wings of the wing. With complex changes in curvature and thickness, this design allows the wing to adaptively deform according to different flight stages or mission requirements, providing better flight control performance and aerodynamic efficiency; the wing deformation skin structure has a simple structural form. It has high reliability, strong load-bearing capacity and wide deformation range. It has high engineering applicability and can be used in various aviation fields that require wing deformation. The reliability and strength of this design ensure the wing's performance under various working conditions. Stability and safety, as well as large deformation ability and adaptability to different flight conditions and load requirements, make this wing deformable skin structure have broad application prospects in aeronautical engineering.

Description of drawings

Figure 1 is a three-dimensional schematic diagram of the deformable skin structure of the present invention.

Figure 2 is a three-dimensional schematic diagram of the hidden upper skin and spanwise trusses of the deformed skin structure of the present invention.

Figure 3 is a schematic diagram of the chordwise support structure of the deformed skin structure of the present invention.

Figure 4 is a schematic diagram of the pull-out overlap sliding mechanism of the deformed skin structure of the present invention.

Figure 5 is a schematic diagram of the lock of the deformable skin structure of the present invention.

Figure 6 is a schematic diagram of the leading edge skin of the deformed skin structure of the present invention.

Figure 7 is a schematic diagram of the middle section of the deformed skin structure of the present invention.

Figure 8 is a schematic diagram of the trailing edge skin of the deformed skin structure of the present invention.

Figure 9 is a schematic diagram of the deformed skin structure of the present invention after the skin becomes curved.

Figure 10 is a schematic diagram of the deformed skin structure of the present invention after the skin becomes thicker.

Among them, 1. Leading edge skin; 2. Middle section skin; 3. Trailing edge skin; 4. Span-direction truss; 5. Chordal support structure; 6. Locking device; 7. Leading-edge actuator connection 8. The overlapping mechanism between the leading edge skin and the middle skin; 9. The connection between the middle actuator; 10. The overlapping mechanism between the middle skin and the trailing edge skin; 11. Flange; 12. The first roller; 13. Sliding guide rail; 14. Fixed end of roller; 15. Chute; 16. Second roller; 17. Support.

Detailed ways

As shown in Figures 1, 2 and 3, a deformable skin structure that can achieve variable curvature and thickness of the wing includes: deformable skin, chordwise support structure 5, spanwise truss 4, and locking device 6 ; The deformed skin serves as the outer surface of the wing and wraps other structures in it. The chordwise support structure 5 is laid in the chordwise direction. Multiple spanwise trusses 4 are arranged in the wing direction according to the spanwise length of the skin. It is arranged between the chordwise support structures 5 and is fixedly connected to the skin. The locking device 6 is laid between the chordwise support structures 5 and is fixedly connected to the deformed skin.

As shown in Figures 6, 7, 8, 9 and 10, the deformed skin includes leading edge skin 1, middle skin 2 and trailing edge skin 3; on the upper and lower surfaces of the wing, the leading edge skin is As a whole, the middle skin and the trailing edge skin are divided into upper and lower parts. A total of five skins form the overall deformation skin of the wing; adjacent skins overlap each other through the chordwise support structure 5, as shown in the figure , four chordwise support structures 5 can be seen, but depending on the length of the wing, the number of support structures and the spacing between structures can be appropriately increased. In order to enhance the structural strength of the wing, a spanwise girder 4 is provided in the spanwise direction of the wing, which is connected to the chordwise support structure 5. The cross-sectional shape of the spanwise girder adopts a "Γ" shape. This shape makes the spanwise girder The long girders have better bending resistance and give the wing greater load-bearing capacity in the spanwise direction. The chordwise support structure 5 consists of the flange 16, the leading edge actuator connection 7, the middle wing connection 9 and the pull-out overlap sliding mechanisms 8 and 10. Flange 6 is the wide flange part in the figure, which is divided into three parts: the leading edge, the middle section and the trailing edge. They are fixedly connected to the leading edge skin 1, the middle section skin 2 and the trailing edge skin 3 respectively; through this wide The design of the strip flange can increase the contact area between the flange and the skin, thereby better transferring the aerodynamic load on the skin to the spars and wing ribs, and at the same time dispersing the driving force generated by deformation, making the deformation effect of the wing more effective. ideal. The leading edge actuator connection 7 and the mid-section actuator connection 9 of the wing are connected to the driving device. By controlling the connection between the actuator connection and the driving device, the chordwise support structure 5 can be controlled to produce the same or different changes. . The thickness and curvature of the upper and lower skin of the wing can be adjusted and changed in complex ways.

As shown in Figure 4, a pull-out overlap sliding mechanism is shown, which is shown in the position designated by 8 and 10 in the figure. Although the design dimensions of these two positions are different, the design structure of the mechanism and the effect achieved are the same. The leading edge skin 1 and the middle skin 2 are two overlapping skin sheets. These two skin pieces can refer to the leading edge skin and the middle skin or the middle skin and the trailing edge skin. The leading edge skin 1 is fixedly connected to the roller fixed end 12, and two sets of first rollers are installed on the roller fixed end 14. 12. The first roller 12 is constrained in the sliding guide rail 14 and can slide along the guide rail to constrain other directions; when the fixed end of the roller 14 and the first roller 12 slide relative to each other along the chute direction, the connected skin sheet will also be displaced. , thereby changing the shape of the wing skin.

As shown in Figure 5, the locking device 6 is installed at the overlap between the leading edge skin 1 and the middle skin 2, and at the overlap between the middle skin 2 and the trailing edge skin 3. In order to avoid buckling deformation of the overlapping skin when the wing deflects and deforms, a locking device 6 is designed to play a fixing role. The leading edge skin 1 and the middle skin 2 are two connected skins. The roller 14 is installed on the support 16, and the support 16 is fixedly connected to the leading edge skin 1. The chute 17 is fixedly connected to the middle skin 2, and the chute 15 and the middle skin 2 are provided with fractures to facilitate the sliding of the support. The rear end of the leading edge skin 1 is provided with a protruding rectangular area for covering the fracture, which is beneficial to the streamline shape of the entire skin and helps to reduce drag.

The present invention can realize relative displacement changes between the leading edge skin 1, the middle skin 2 and the trailing edge skin 3 through the design and application of the pull-out overlap mechanism, thereby changing the appearance of the skin and changing the shape of the wing. thickness and camber. The chordwise support structure 5 can better disperse the concentrated force of the drive device and maintain the shape of the wing, and the spanwise girder 4 can improve the bending resistance of the wing, and the locking device 6 can avoid the overlapping skin. buckling phenomenon.

Claims (8)

1. A morphing skin structure capable of achieving wing camber and thickness, comprising: the device comprises a deformation skin, a spanwise stringer (4), a chordwise supporting structure (5) and a locking device (6); the deformed skin is taken as the outer surface of the wing, other structures are wrapped in the deformed skin, the chord direction supporting structures (5) are paved in the chord direction, a plurality of deformed skin supporting structures are arranged in the wing direction according to the span length of the skin, the span stringers (4) are arranged between the chord direction supporting structures (5) and fixedly connected with the skin, and the locking device (6) is paved between the chord direction supporting structures (5) and fixedly connected with the deformed skin.

2. The deformed skin structure capable of realizing wing deflection and thickness according to claim 1, wherein the deformed skin comprises a front edge skin (1), a middle section skin (2) and a rear edge skin (3), and the three parts are mutually overlapped and have a certain length; when the skins deform, relative sliding occurs between the skins.

3. A deformable skin structure for achieving wing camber and thickness according to claim 1, wherein spanwise direction is provided with spanwise stringers (4) which are connected to the chord-wise support structure (5) and which exhibit a "Γ" cross-sectional shape.

4. The deformed skin structure capable of realizing wing deflection and thickness according to claim 1, wherein the chord-wise support structure (5) comprises a front edge actuator connection (7), a front edge skin and middle section skin overlapping mechanism (8), a middle section actuator connection (9), a middle section skin and rear edge skin overlapping mechanism (10) and a flange (11); the upper structure and the lower structure of the chord-wise supporting structure (5) are symmetrically arranged, and are sequentially provided with a front edge actuator connecting part (7), a front edge skin and middle section skin overlapping mechanism (8), a middle section actuator connecting part (9) and a middle section skin and rear edge skin overlapping mechanism (10) from front to back and are fixedly connected through a flange (11); the upper surface of the chord-wise supporting structure (5) is connected with the wing skin.

5. A deformable skin structure for achieving wing camber and thickness according to claim 4, wherein the leading edge actuator connection (7) and the midsection actuator connection (9) of the wing are connected to the drive means, and wherein the chord support structure (5) is controlled to produce the same or different changes by controlling the connection of the actuator connection to the drive means.

6. The deformed skin structure capable of realizing the bending degree and thickness of the wing according to claim 4, wherein the chord-wise supporting structure (5) comprises four pull-type lap sliding mechanisms which are arranged at the lap skin, and the fixed ends of the sliding guide rail (13) and the first roller (12) are respectively connected with different lap skins, so that the lap skin is displaced along the direction of the sliding groove, and the whole wing skin is deformed.

7. The deformable skin structure capable of achieving wing bending and thickness according to claim 1, wherein the locking device (6) comprises a second roller (16), a sliding groove (15) and a support (17), the second roller (16) is mounted on one skin through the support (17) and fixedly connected with the skin, and the sliding groove (15) is fixedly mounted on the other skin.

8. A deformable skin structure for achieving wing deflection and thickness according to claim 1, characterized in that the first roller (12) and the sliding rail (13) are respectively fixed to different skins, and by their connection, adjacent two skins are displaced in the direction of the sliding rail (13), so that the skin of the whole wing is deformed.