A wing with a trailing edge capable of continuous deformation in the span-chord direction

Abstract

The present invention discloses a wing whose trailing edge has the ability to deform in the span-chord direction, and belongs to the field of structural design of deformable aircraft. The wing of the present invention is composed of a leading edge, a wing box, and a deformable trailing edge. The deformable trailing edge system is the core component of the deformable wing, and is composed of a deformable trailing edge compliance mechanism, a servo-connecting rod drive system, and a sensing system. The trailing edge compliance mechanism is filled with a superelastic body to form a flexible transition area, so that the wing has a large span-wise deformation capability. The drive system includes a servo, a servo rocker arm, a connecting rod, and a long axis to drive the deformation of the trailing edge to change the curvature of the wing, so that the wing has a large chord-wise deformation capability. The sensing system includes a Hall angle sensor and its base, a rubidium magnet and its support seat, so as to realize the measurement of the servo angle. The entire process of the trailing edge deformation of the technical solution of the present invention is continuous, the skin surface is smooth and seamless, has three-dimensional torsion capability, and has a certain load-bearing capacity.

Description

Technical Field

[0001] The present invention relates to a wing structure, in particular to a wing based on a compliant mechanism, the trailing edge of which has the spanwise and chordwise continuous deformation capability. Background Art

[0002] Morphing aircraft can actively change their overall or partial shapes to adapt to different flight missions and conditions, meeting diverse mission requirements with varying aerodynamic shapes and layouts. They also maintain optimal efficiency and performance under a variety of flight conditions, thereby improving performance across the entire flight envelope. Among existing morphing aircraft, cambered wings are a current research hotspot. Conventional wings achieve camber changes through the deflection of ailerons, flaps, and other components. However, the deflection of these rigid control surfaces creates gaps in both directions, leading to airflow separation and increased drag and noise.

[0003] Traditional variable-camber morphing wings can achieve wing camber changes through smooth and continuous flexible deformation of the airfoil along the chordwise direction to adapt to the aerodynamic requirements of the structural shape. Current industry research focuses on the two-dimensional continuous and smooth chordwise deformation of the trailing edge deformation mechanism. This type of design usually only targets one wing profile, demonstrating the deformation capability using a straight wing segment with consistent spanwise deflection, and does not have spanwise transition capability. In this case, the actual wing can only achieve segmented control by creating gaps between adjacent deforming trailing edges, and the scissor-shaped gap still exists, making it impossible to achieve continuous and smooth deformation of the entire wing. Summary of the Invention

[0004] To address the aforementioned issues in the existing technology, the present invention proposes a compliant mechanism-based morphing wing design with a trailing edge capable of smooth and continuous spanwise and chordwise deformation. This design achieves continuous trailing edge deformation, a smooth and seamless skin surface, three-dimensional torsion capability, and a certain load-bearing capacity.

[0005] The technical problem addressed by this invention is a wing design with a trailing edge capable of smooth and continuous deformation in both the spanwise and chordwise directions. In this invention, the wing achieves smooth chordwise deformation by a drive mechanism pulling a 3D-printed compliant structure into shape. Spanwise deformation is achieved by embedding a hyperelastic material within the compliant structure.

[0006] The purpose of the present invention is achieved through the following technical solutions:

[0007] The wing skin consists of three parts: a rigid leading edge, a rigid wing box, and a deformable trailing edge system. The leading edge serves as an aerodynamic shape maintainer and does not deform. The wing box is the primary structural support for the wing section and has high rigidity. The deformable trailing edge system is the primary deformation area, capable of spanwise and chordwise deformation.

[0008] Both the trailing and leading edges are fixed to the wing box. Sliders, mounted on the underside of the wing box, are mounted on rails and move along them. Baffles cover the outer edges of the rails to maintain smoothness and maintain aerodynamic shape. Stainless steel main beams are bolted to the wing box to enhance spanwise stiffness.

[0009] The morphing trailing edge system is the core component of the morphing wing section, which consists of a morphing trailing edge compliance mechanism, a servo-connecting rod drive system and a sensing system.

[0010] The main structure of the deformable trailing edge compliance mechanism is 3D-printed, with a hyperelastic material regularly filled within the elastic main structure. When adjacent trailing edges deform differentially under the action of a driving force, the large deformation properties of the hyperelastic material enable smooth span-wise deformation.

[0011] The servo drive system is installed in the wing box and is hinged to the long axis fixed in the deformable trailing edge structure through rocker arms and connecting rods. The trailing edge long axis sleeve drives the trailing edge ribs and skin compliance mechanism to achieve overall deformation.

[0012] The sensing system uses a non-contact Hall effect angle sensor to measure the servo's true rotation angle in real time. The sensor is coaxial with the servo's rocker arm. A rubidium magnet support is mounted on the servo's rocker arm, with a rubidium magnet embedded in the end. The Hall effect angle sensor is mounted on the wing box. A gap is left between the sensor and the rubidium magnet, and the servo's rotation angle is determined by capturing changes in the magnetic field.

[0013] The beneficial effects of the present invention are:

[0014] The present invention addresses the key challenges of wings with span-to-chordwise deformation capabilities at the trailing edge, namely, sufficient structural flexibility to permit large deformations, sufficient out-of-plane stiffness to withstand aerodynamic loads, and a relatively low driving force required for deformation. The wing proposed in the present invention, based on a compliant mechanism, can achieve smooth, continuous span-to-chordwise deformation without gaps, and has potential applications such as reducing aerodynamic noise, alleviating gust loads, improving aerodynamic performance, and reducing radar crosstalk. The wing of the present invention can achieve significant aerodynamic changes, thereby adapting to diverse flight conditions and meeting a variety of mission requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is an overall axonometric view of a wing having a trailing edge with span-chordwise continuous deformation capability according to an embodiment of the present invention.

[0016] Figure 2 yes Figure 1 Rear view of the illustrated embodiment.

[0017] Figure 3 It is a compliant mechanism-drive-sensor system for the deforming trailing edge of a wing model.

[0018] Figure 4 It is the supporting mold required for the injection molding process of the transition section.

[0019] Figure 5 It is a one-side drive-sensing system on the deformable trailing edge of the wing model.

[0020] Figure 6 Schematic diagram of the trailing edge deflection results when both sides of the embodiment are driven at 32.5, 60, -30 and -60 degrees.

[0021] Figure 7 2 is a schematic diagram of the trailing edge deflection results when the driving angles on both sides of the embodiment are -40 degrees and 40 degrees respectively. DETAILED DESCRIPTION

[0022] The technical solution of the present invention is further described below with reference to the accompanying drawings.

[0023] like Figure 1 、 Figure 2 、 Figure 3 The figure shows a wing 1 having a trailing edge with span-chordwise deformation capability according to an embodiment of the present invention, comprising a wing leading edge 2, a wing box 3, a stainless steel main beam 6, and a wing deformable trailing edge 4. The wing leading edge 2 is fixed to corresponding positions of the wing box 3 via two rows of leading edge threaded holes 11 located on the upper surface 30 and lower surface 31 of the wing box; the upper surface of the wing deformable trailing edge 4 is fixed to the wing box 3 via threaded holes 12 on the upper surface of the trailing edge; the lower surface of the wing deformable trailing edge 4 is connected to the slider 24 via threaded holes 14 on the lower surface of the trailing edge using fasteners. The seven sliders 24 and corresponding slide rails 7 respectively form sliding connection pairs. The slide rails 7 and the wing box 3 are fixed to corresponding positions of the wing box 3 via threaded hole rows 25 located on the slide rails using fasteners, thereby establishing a sliding connection between the lower surface 31 of the wing deformable trailing edge 4 and the wing box 3.

[0024] An array of mounting holes 10 is reserved on the upper surface of the wing box 3 to facilitate the assembly process of the slide rail 7 (to facilitate the passage of a screwdriver through the holes).

[0025] The outside of the slide rail 7 area is covered with a wing lower surface baffle 9 to keep the smoothness of the lower surface. The wing lower surface baffle 9 is connected to the wing box 3 through small holes 13 on the baffle. The stainless steel main beam 6 is fixed on the wing box 3.

[0026] Deformable trailing edge system Figure 3 As shown in FIG, it includes a wing deformation trailing edge 4, a drive system and a sensor system. In this example, a flexible transition region 5 is installed in the spanwise middle of the wing deformation trailing edge 4, and a drive system and a sensor system are installed on both sides of the wing 1 in the spanwise symmetry. The drive-sensor system on the right side is as shown in FIG. Figure 5 shown.

[0027] The main part of the wing deformation trailing edge 4 is made of elastic material. In one embodiment of the present invention, the elastic main structure of the deformation trailing edge compliance mechanism is made by 3D printing, and the elastic main structure is filled with super elastic material in a certain pattern to form a flexible transition area 5. In one embodiment of the present invention, the super elastic material filled in the flexible transition section 5 is injection molded using a process such as Figure 4 The outer mold 27 and inner mold 28 are shown. During production, a release agent, such as vaseline, is evenly applied to the surfaces of the outer mold 27 and the inner mold 28 to facilitate subsequent demolding. Then, the outer mold 27 and the inner mold 28 are combined with the wing deformation trailing edge 4. Next, the superelastic material is slowly and continuously injected into the groove formed by the main part of the wing deformation trailing edge 4 and the inner mold 28, so that it is evenly filled into the groove of the main part of the wing deformation trailing edge 4 and the gap between the outer mold 27 and the main part of the wing deformation trailing edge 4. After standing for a certain period of time, the superelastic material solidifies, and the solidified colloid is flexible and elastic. Finally, the excess superelastic colloid on the skin surface of the wing deformation trailing edge 4 is cut off, and the outer mold 27 and the inner mold 28 are removed.

[0028] In this embodiment, there are two drive systems, which are installed symmetrically. Figure 3 and Figure 5 Taking the right-side drive system shown as an example, the drive system includes a servo 15, a servo rocker arm 16, a connecting rod 19, and a long shaft 20. The servo 15 is fixed to the wing box 3 via its front and rear servo mounting threaded holes 26. The extended servo rocker arm 16 is coaxial with one end of the connecting rod 19 to pull the connecting rod 19 to move. The other end of the connecting rod 19 is hinged to the long shaft 20, which is installed in the trailing edge long shaft sleeve 22 of the wing's deformable trailing edge 4, thereby enabling the servo 15 to drive the wing's deformable trailing edge 4.

[0029] In this embodiment, there are two sensor systems, which are installed symmetrically. Figure 3 and Figure 5 Taking the right-side sensor system shown as an example, this system includes a Hall effect sensor 17, a Hall effect sensor base 8, a rubidium magnet 29, and a rubidium magnet support 18. The Hall effect sensor base 8 is secured to the wing box 3 via threaded sensor holes 23. The Hall effect sensor 17 and Hall effect sensor base 8 are also connected by fasteners. The rubidium magnet support 18 is securely attached to the servo rocker arm 16 and holds the rubidium magnet 29. The Hall effect sensor 17 and the rubidium magnet 29 are coaxial, with a certain gap between them. This allows them to capture magnetic field changes and achieve non-contact, real-time measurement of the servo's true rotation angle.

[0030] The driving process in this embodiment includes: when the servo rocker arm 16 rotates toward the wing leading edge 2, the connecting rod 19 is pulled toward the wing leading edge 2, and the wing deformed trailing edge 4 deflects downward, thereby increasing the wing curvature. When the servo rocker arm 16 moves in the opposite direction of the wing leading edge 2, the wing deformed trailing edge 4 deflects upward. For example, when the servos on both sides simultaneously input angles of 32.5, 60, -30, and -60 degrees, the wing deformed trailing edge 4 deforms as follows: Figure 6 As shown. Taking the input of 40 degrees and -40 degrees on both sides of the servo as an example, the deformation of the wing trailing edge 4 is as follows Figure 7 shown.

[0031] The above description is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements can be made without departing from the principles of the present invention. These improvements should also be regarded as the scope of protection of the present invention.

Claims

1. A wing (1) having a trailing edge with spanwise-chordwise deformation capability, characterized in that include: Leading edge (2), wing box (3), main beam (6), deformable trailing edge (4), drive system and sensor system, in: The leading edge (2) is fixed to the wing box (3) through the leading edge threaded holes (11) located on the upper surface (30) and the lower surface (31) of the wing box; The upper surface of the deformed trailing edge (4) is fixed to the wing box via a threaded hole (12) on the upper surface of the trailing edge; The lower surface of the deformed trailing edge is connected to a plurality of sliders (24) through threaded holes (14) on the lower surface of the trailing edge; A plurality of sliders (24) and a corresponding number of slide rails (7) respectively form a sliding connection pair; The slide rail (7) and the wing box (3) are fixed to each other through the threaded hole (25) on the slide rail, so that the lower surface (31) of the deformed trailing edge (4) and the wing box (3) are in a sliding connection relationship; The outer side of the slide rail (7) is covered with a wing lower surface baffle (9) to maintain the smoothness of the lower surface; The wing lower surface baffle (9) is connected to the wing box through a small hole (13) on the wing lower surface baffle (9); The main beam (6) is fixedly connected to the wing box; A flexible transition area (5) is installed in the spanwise middle of the deformed trailing edge (4). The flexible transition region (5) comprises an elastic main structure and a superelastic material filled in the elastic main structure. The driving system and the sensing system are respectively installed on both sides of the wing (1) in a spanwise symmetrical manner. The driving system comprises: a steering gear (15), a steering gear rocker arm (16) extending from the steering gear (15), a connecting rod (19), and a long shaft (20). The steering gear (15) is fixed on the wing box. The steering gear rocker arm (16) is coaxial with one end of the connecting rod (19) to pull the connecting rod (19) to move. The other end of the connecting rod (19) is hinged to the long shaft (20). The long shaft (20) is installed in the trailing edge long shaft sleeve (22) of the deformed trailing edge (4), thereby realizing the driving of the servo (15) on the deformed trailing edge (4). The sensing system comprises: a Hall angle sensor (17), a sensor base (8), a magnet (29) and a magnet support base (18), The sensor base (8) is fixed on the wing box (3). The Hall angle sensor (17) is connected to the sensor base (8) via fasteners. The magnet support seat (18) is fixedly connected to the steering gear rocker arm (16) and clamps the magnet (29). The Hall angle sensor (17) is coaxial with the magnet (29) and has a certain gap therebetween, thereby sensing the change of the magnetic field and realizing non-contact real-time measurement of the steering gear rotation angle.

2. The wing (1) with a trailing edge having spanwise-chordwise deformation capability according to claim 1, characterized in that: The superelastic material filled in the flexible transition region (5) is formed by an injection molding process using an outer mold (27) and an inner mold (28). The injection molding process includes: Apply release agent evenly to the surface of the outer mold (27) and the inner mold (28) to facilitate subsequent demoulding. Then, the outer mold (27) and the inner mold (28) are combined with the wing deformation trailing edge (4), Then, the superelastic material is slowly and continuously injected into the groove formed by the elastic main structure of the deformed rear edge (4) and the inner mold 28, so that the superelastic material is evenly filled into the groove of the deformed rear edge (4) and fills the gap between the outer mold (27) and the deformed rear edge (4). The deformed trailing edge (4) of the wing filled with the superelastic material is left to stand for a period of time to allow the superelastic material to solidify. Then, the outer mold (27) and the inner mold (28) are removed.

3. The wing (1) having a trailing edge with spanwise-chordwise deformation capability according to any one of claims 1-2, characterized in that The driving process for deforming the deformation trailing edge (4) includes: By rotating the steering gear rocker arm (16) toward the leading edge (2), the connecting rod (19) is pulled toward the leading edge, thereby causing the deformed trailing edge (4) to deflect downward, thereby increasing the wing curvature. By moving the steering gear rocker arm (16) in the opposite direction to the leading edge (2), the deformed trailing edge (4) is deflected upward.

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