Multi-degree-of-freedom deformable wingtip

Abstract

The invention relates to a multi-degree-of-freedom deformable wingtip, belongs to the technical field of aircraft design and aeroelasticity design, and solves the problem that a deformable wingtip in single-degree-of-freedom design in the prior art cannot maintain high aerodynamic efficiency in a wider flight envelope, the multi-degree-of-freedom deformable wingtip comprises: a root wing section (100) connected to a wing main body; the middle wing section (200) is rotatably connected to the outer end of the root wing section (100); the winglet (300) is connected to the outer end of the middle wing section (200) in a twisting manner; and the power assembly comprises a bending servo motor (400) for driving the middle wing section (200) to rotate and a torsion servo motor (500) for driving the winglet (300) to twist.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft design and aeroelastic design, and in particular to a multi-degree-of-freedom deformable wingtip. Background Art

[0002] The high-aspect-ratio wings of new large passenger aircraft typically utilize winglets. These winglets are either upward-curved or bifurcated, effectively reducing wingtip vortices and redistributing lift for optimal aerodynamics. To further increase range and improve fuel economy, aircraft will require a larger aspect ratio and wingspan, making winglet design particularly crucial.

[0003] Existing winglets are typically fixed structures that only improve flight performance during cruise conditions, but struggle to meet aerodynamic efficiency requirements in other flight conditions. Existing publicly available deformable winglet designs all utilize a single degree of freedom, making them incapable of maintaining high aerodynamic efficiency across a wide flight envelope.

[0004] Winglets are mainly used in large civil aircraft and large military aircraft. The winglet design used in large aircraft design mainly improves aircraft performance by reducing lift-induced drag. Existing winglets are simple in form with a vertical or slightly tilted wing tip. The winglets block the airflow from the lower surface to the upper surface, reducing the intensity of the wingtip vortex and reducing fuel consumption. Existing blended winglets smoothly connect the winglet to the wing to reduce the adverse effects of airflow and further reduce drag. At the same time, the outward-tilted winglets can increase lift, but will increase the wing root bending moment, which will have an adverse effect on the wing structure.

[0005] With the development of aircraft design technology and structural material technology, there is a demand for multifunctional, multi-degree-of-freedom deformable winglets to improve the overall performance of the aircraft. Summary of the Invention

[0006] In view of the above problems, the present invention provides a multi-degree-of-freedom deformable wingtip, which solves the problem in the prior art that the aerodynamic efficiency and performance of fixed winglets cannot meet the requirements under complex flight conditions.

[0007] The present application provides a controllable deformable winglet with two deflection degrees of freedom, capable of achieving bending and deflection about the axis of the chord direction of the wing and twisting of the winglet about the focal axis. This not only maintains a high aerodynamic efficiency of the winglet in a wider flight envelope, but also provides additional control torque to improve the control efficiency of the aircraft. The use of a flexible skin in the deformed area of ​​the winglet can maintain the continuous flow of airflow during the winglet deflection process, reduce the increase in drag caused by the winglet deflection, and improve the aerodynamic performance of the wing. At the same time, when encountering a gust of wind in the air, the deflection freedom of the winglet about the axis of the chord direction of the wing and the twisting of the winglet focal axis are controlled to achieve active control of gust mitigation.

[0008] According to an embodiment of the present invention, a multi-degree-of-freedom deformable wingtip is provided, comprising:

[0009] The root wing section is fixedly connected to the main wing body;

[0010] a mid-wing section rotatably connected to the outer end of the root wing section;

[0011] Winglets twistably connected to the outer ends of the center wing sections; and

[0012] A power assembly, including a bending servo motor that drives the rotation of the middle wing section and a torsion servo motor that drives the torsion of the winglets;

[0013] The multi-degree-of-freedom deformable wingtip switches between the following three working states:

[0014] In cruise flight, the propulsion system is not activated, the center wing section is in an unrotated, deployed position, and the winglets are in an untwisted, deployed position;

[0015] In the adaptive cruise speed change state, only the bending servo motor is activated to drive the bending and deflection movement of the middle wing section relative to the root wing section;

[0016] Adapting to the flight state, the bending servo motor and the twisting servo motor are started to drive the middle wing section to perform bending and deflecting movement relative to the root wing section, and to drive the winglet to perform bending and twisting movement relative to the middle wing section.

[0017] Optionally, in the adaptive cruise speed change state and the adaptive flight state, the bending deflection angle range of the middle wing section relative to the root wing section is -90° to +90°; in the adaptive flight state, the twisting angle range of the winglet relative to the middle wing section is -10° to +10°.

[0018] Optionally, the root wing section includes a root rib, a root spar and a root fixed skin covering the surface; the root rib includes a plurality of root longitudinal support ribs extending along the chord direction of the wing; the root spar includes two root transverse support beams extending along the span direction of the wing; and the bending servo motor is mounted and fixed on the root rib.

[0019] Optionally, the root ribs extending in the chord direction and the root spars extending in the span direction are intertwined to form a mesh structure; the root spars have a root spar protrusion extending beyond the outermost root ribs, and the root spar protrusion is formed with a mounting opening for assembly with the middle wing section and connection with the output of the bending servo motor.

[0020] Optionally, the middle wing section includes a middle wing rib, a middle wing spar, a middle fixed skin and a middle flexible skin; the middle wing rib includes two middle longitudinal support ribs extending along the chord direction of the wing; the middle wing spar includes two middle transverse support beams extending along the span direction of the wing; and the torsional servo motor is mounted and fixed on the middle wing rib.

[0021] Optionally, the middle flexible skin covers the portion of the middle wing segment close to the root spar; the middle fixed skin covers the portion of the middle wing segment close to the wingtip winglet; wherein the width ratio of the middle flexible skin and the middle fixed skin (230) along the span direction is 2:1; wherein, in the adaptive cruise speed change state and the adaptive flight state, the middle flexible skin deforms.

[0022] Optionally, the middle ribs extending in the chord direction and the middle spar extending in the span direction are intertwined to form a mesh structure; the middle spar has a middle spar protrusion extending beyond the innermost middle rib, and the middle spar protrusion is formed with a mounting opening for assembly with the root wing section.

[0023] Optionally, the wingtip winglet includes a winglet rib, a winglet main beam, a winglet fixed skin and a winglet flexible skin; the winglet rib includes a plurality of longitudinal support ribs extending along the chord direction; the inner end of the winglet main beam is connected to the output shaft of the torsion servo motor, and the outer end is fixed to the winglet rib.

[0024] Optionally, the winglet flexible skin covers the part of the wingtip winglet close to the middle wing section; the winglet fixed skin covers the outer part of the wingtip winglet; wherein, the width ratio of the winglet flexible skin and the winglet fixed skin along the span direction is 1:6; wherein, in the adaptive flight state, the winglet flexible skin deforms.

[0025] Compared with the prior art, the multi-degree-of-freedom deformable wingtip provided by the present invention has at least the following beneficial effects.

[0026] 1) It has two deflection modes, bending and twisting, which improves the applicable flight conditions of the winglet and has two deflection degrees of freedom.

[0027] 2) The winglet's twisting and bending deflections are controlled by two sets of motion mechanisms. The twisting direction is controlled by a servo motor output shaft connected to the outer end of the winglet, which can rotate the outer section of the winglet by ±10° around the output shaft. The output shaft is located near the aerodynamic focus of the outer section of the winglet, thereby reducing the torque required by the servo motor to control the twisting process of the winglet.

[0028] 3) The outer section of the winglet is made of lightweight composite materials with low weight and high stiffness.

[0029] 4) When encountering a gust of wind in the air, the wingtip winglet can control the bending deflection of the axis of the chord direction of the wing and the deflection freedom of the torsion about the rigid axis of the wing to achieve active control of gust mitigation.

[0030] 5) By providing a flexible skin, the additional drag caused by winglet deflection is reduced, thereby improving aerodynamic performance. Using a flexible skin on the winglet deformation area can maintain continuous airflow during the winglet deflection process, reducing the drag caused by winglet deflection and improving the wing's aerodynamic performance.

[0031] 6) By setting up dampers in parallel, the stability of the deflection mechanism system is improved to prevent the winglets from vibrating due to the influence of airflow and other unstable phenomena.

[0032] 7) It has both bending and torsion deflection modes, which improves the applicable flight envelope of the multi-degree-of-freedom deformable wingtip. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. By referring to the drawings, the features and advantages of the present invention can be more clearly understood. The drawings are schematic and should not be understood as limiting the present invention in any way. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0034] Figure 1 A schematic diagram of a multi-degree-of-freedom deformable wingtip provided according to an embodiment of the present invention, showing the overall structure and skin partitioning.

[0035] Figure 2 Schematic diagram of a driving power assembly of a multi-degree-of-freedom deformable wingtip provided according to an embodiment of the present invention.

[0036] Figure 3 Schematic diagram of a multi-degree-of-freedom deformable wingtip in an undeflected and untwisted extended state according to an embodiment of the present invention.

[0037] Figure 4 It is a schematic diagram of a middle wing section of a multi-degree-of-freedom deformable wingtip provided in accordance with an embodiment of the present invention in a deflected state.

[0038] Figure 5 A rear view of a middle wing section of a multi-degree-of-freedom deformable wingtip provided according to an embodiment of the present invention is in a deflected state.

[0039] Figure 6 It is a schematic diagram of a winglet of a multi-degree-of-freedom deformable wingtip provided in accordance with an embodiment of the present invention in a twisted state.

[0040] Reference numerals:

[0041] 100-root wing section;

[0042] 110- root rib;

[0043] 120-root spar;

[0044] 122-Root spar convex part;

[0045] 130-root fixed skin;

[0046] 200-middle wing section;

[0047] 210-center rib;

[0048] 220-middle spar;

[0049] 222-Middle spar convex part;

[0050] 230-central fixed skin;

[0051] 240-middle flexible skin;

[0052] 300-winglets;

[0053] 310-winglet rib;

[0054] 312-shaft hole;

[0055] 320-winglet main beam;

[0056] 330-winglet fixed skin;

[0057] 340-winglet flexible skin;

[0058] 400-bending servo motor;

[0059] 410-connector;

[0060] 420-bent rocker arm;

[0061] 430-damping link;

[0062] 440-Bending and rotating rod;

[0063] 500-torsion servo motor;

[0064] A-deflection axis;

[0065] B-focal axis. DETAILED DESCRIPTION

[0066] In order to more clearly understand the above-mentioned objects, features and advantages of the present invention, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that the embodiments of the present invention and the features therein can be combined with each other without conflict.

[0067] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Therefore, the scope of protection of the present invention is not limited to the specific embodiments disclosed below.

[0068] The following describes in detail a multi-degree-of-freedom deformable wingtip according to an embodiment of the present invention with reference to the accompanying drawings. The multi-degree-of-freedom deformable wingtip provided according to an embodiment of the present invention is installed at the end of an aircraft wing to form the wingtip. It can be used on large aircraft as well as small unmanned aerial vehicles (UAVs). It provides both torsion and bending deformation structures for the aircraft's wings, maintaining high aerodynamic efficiency across a wide flight envelope. It can also provide additional control torque, improving the aircraft's control efficiency.

[0069] like Figures 1 to 5 As shown, a multi-degree-of-freedom deformable wingtip provided according to an embodiment of the present invention includes: a root wing section 100 fixedly connected to the wing body; a mid-wing section 200 rotatably connected to the outer end of the root wing section 100; a winglet 300 torsionally connected to the outer end of the mid-wing section 200; and a power assembly that drives the rotation of the mid-wing section 200 and the torsion of the winglet 300. The power assembly may include a bending servo motor 400 and a torsion servo motor 500. The bending servo motor 400 is used to drive the up and down deflection of the mid-wing section 200 relative to the root wing section 100, and the torsion servo motor 500 is used to drive the torsion of the winglet 300 about the focal axis. The root wing section 100 can also be the outer section of the wing body.

[0070] The root wing section 100 supports and secures the mid-wing section 200, winglet 300, and bending servo motor 400. It comprises a root rib 110, a root spar 120, and a covering root fixed skin 130, all made of carbon fiber composite material. Epoxy resin can be used to secure these components.

[0071] See also Figure 1 and Figure 2 The root wing section 100 includes a root rib 110 and a root spar 120, which serve as the main support structure of the root wing section 100. In this embodiment, the root rib 110 extending along the chord direction and the root spar 120 extending along the span direction are interlaced to form a mesh structure to provide stable support. Figure 1As shown, specifically, the root rib 110 may include a plurality of root longitudinal support ribs extending along the chordwise direction of the wing, and the root spar 120 may include two root transverse support beams extending along the spanwise direction of the wing. It should be understood that the number of support ribs and beams included in the root rib 110 and the root spar 120, respectively, may be set according to the specific aircraft size and requirements. The root spar 120 includes a root spar protrusion 122 that extends beyond the outermost root rib 110; the root spar protrusion 122 protrudes outward from the outermost root rib 110 adjacent to the mid-wing section 200 and is used to mount the mid-wing section 200. Suitable mounting openings may be formed in the root spar protrusion 122 of the root spar 120.

[0072] The bending servo motor 400 of the power assembly can be mounted and fixed on the root rib 110. Specifically, the bending servo motor 400 is mounted to the root rib 110 via a connector 410. The bending servo motor 400 also has a matching transmission assembly, including a bending rocker arm 420, a damping link 430, and a bending rotating rod 440.

[0073] The middle wing section 200 is rotatably connected to the outer end of the root wing section 100, and includes a middle rib 210, a middle spar 220, a middle fixed skin 230, and a middle flexible skin 240. The middle spar 210, the middle rib 220, and the middle fixed skin 230 are made of carbon fiber composite materials, and the middle flexible skin 240 is made of a flexible material. The structural components can be fixed by epoxy resin bonding. The middle flexible skin 240 covers the portion of the middle wing section 200 close to the root spar 120, and the middle fixed skin 230 covers the portion of the middle wing section 200 close to the winglet 300; the middle flexible skin 240 and the middle fixed skin 230 together cover the surface of the middle wing section 200. The width ratio of the middle flexible skin 240 and the middle fixed skin 230 along the span direction can be set to 2:1 to form a continuous smooth surface when the middle wing section 200 deflects relative to the root wing section 100, providing good flexibility and a continuous aerodynamic shape.

[0074] See also Figure 1 and Figure 2The middle wing section 200 includes a middle rib 210 and a middle spar 220, which serve as the main support structure of the middle wing section 200. The middle ribs 210 extending along the chord direction and the middle spar 220 extending along the span direction are interlaced to form a mesh structure to provide stable support. Specifically, the middle rib 210 may include two middle longitudinal support ribs extending along the chord direction of the wing, and the middle spar 220 may include two middle transverse support beams extending along the span direction of the wing. It should be understood that the number of support ribs and support beams included in the middle rib 210 and the middle spar 220, respectively, can be set according to the specific aircraft size and requirements. The center spar 220 has a center spar protrusion 222 that extends beyond the innermost center rib 210. The center spar protrusion 222 protrudes inward from the innermost center rib 210, closest to the root wing section 100, and is used to pivotally mount the center wing section 200 to the root wing section 100. The center spar protrusion 222 and the root spar protrusion 122 are positioned to correspond to each other. Suitable mounting holes can be formed in the center spar protrusion 222 of the center spar 220, and can align and match the holes in the root spar protrusion 122. A through-hole 212 is formed in the center of the outermost center rib 210 of the center wing section 200 for mounting the winglet main spar 320 to torsionally mount the winglet 300. The torsion servo motor 500 of the power assembly can be mounted and fixed to the center rib 210.

[0075] like Figure 2 、 Figure 4 and Figure 5 As shown, the root wing section 100 and the mid-wing section 200 are connected by inserting a curved rotating rod 440 through the openings of the root spar protrusion 122 and the openings of the mid-wing spar protrusion 222, allowing the root spar protrusion 122 and the mid-wing spar protrusion 222 to rotate relative to each other, thereby driving the mid-wing section 200 to rotate relative to the root wing section 100. Specifically, the ends of the curved rotating rod 440 are inserted through the openings of the mid-wing spar protrusion 222 to be fixed thereto. Then, the ends of the curved rotating rod 440 are respectively extended outward through the openings of the root spar protrusion 122 and rotatably assembled therein. The curved rotating rod 440 extends along the chordwise direction, generally aligning with the extension direction of the root rib 110. By driving the curved rotating rod 440 to rotate, the mid-wing spar 220 and the mid-wing rib 210 are driven to rotate together, thereby achieving deflection and rotation of the mid-wing section 200 relative to the root wing section 100.

[0076] like Figure 4 and Figure 5As shown, the bending servo motor 400 is used to drive the bending rotating rod 440. The output shaft of the bending servo motor 400 is connected to the bending rocker arm 420, which can rotate around an axis extending along the chord direction. The movable end of the bending rocker arm 420 can be connected to the bending rotating rod 440 via a damping link 430. After the bending servo motor 400 is started, it drives the bending rocker arm 420 to rotate, and then drives the bending rotating rod 440 and the middle wing section 200 fixedly connected thereto to rotate through the damping link 430, thereby causing the middle flexible skin 240 covering the middle wing section 200 to undergo continuous deformation, thereby achieving the up and down bending of the middle wing section 200 and the winglet 300 around the deflection axis A in the chord direction of the wing, ensuring the continuity of the aerodynamic shape. In this embodiment, the bending direction is controlled by a bending servo motor 400 via a bending rocker arm 420 and a damping link 430, driving the center wing section 200 and winglet 300 to deflect vertically about a deflection axis A perpendicular to the span direction. The deflection angle range is ±90°, i.e., -90° to +90°. In this embodiment, the deflection axis A extends along the direction of the driving bending rotation rod 440, i.e., along the chordwise direction.

[0077] The winglet 300, which is torsionally connected to the outer end of the middle wing section, includes a winglet rib 310, a winglet main spar 320, a winglet fixed skin 330, and a winglet flexible skin 340. The winglet main spar 320, the winglet rib 310, and the winglet fixed skin 330 are made of carbon fiber composite materials, while the winglet flexible skin 340 is made of a flexible material. The structural components can be fixed by epoxy resin bonding. The structure of the winglet 300 is made of lightweight composite materials, with low weight and good rigidity. The winglet flexible skin 340 covers the portion of the winglet 300 near the middle wing section 200; the winglet fixed skin 330 covers the outer portion of the winglet 300; the winglet flexible skin 340 and the winglet fixed skin 330 together cover the surface of the winglet 300. The width ratio of the winglet flexible skin 340 and the winglet fixed skin 330 along the span direction can be set to 1:6 to provide sufficient support and form a continuous smooth surface when the winglet 300 is twisted relative to the middle wing section 200, providing good flexibility and a continuous aerodynamic shape.

[0078] like Figure 1 and Figure 2As shown, the winglet rib 310 includes a plurality of longitudinal support ribs extending in the chordwise direction. In this embodiment, the winglet rib 310 may include four longitudinal support ribs arranged in parallel. The inner end of the winglet main spar 320 is connected to the output shaft of the torsion servo motor 500, and the outer end is fixed to the winglet rib 310. Specifically, the inner end of the winglet main spar 320 is connected to the output shaft of the torsion servo motor 500, extends through the shaft hole 212 on the outermost middle rib 210 of the middle wing section 200, and is rotatable therein. It also passes through and is fixed to at least one winglet rib 310, for example, three winglet ribs 310. The winglet main spar 320 extends in the spanwise direction. The torsion servo motor 500 drives the winglet main spar 320 to rotate, causing the winglet rib 310 to twist along the focal axis B, thereby achieving fore-aft twisting of the wingtip 300 relative to the middle wing section 200.

[0079] like Figure 2 、 Figure 3 and Figure 6 As shown, the torsion servo motor 500 is used to drive the winglet main beam 320 and is fixedly mounted on the middle rib 210 of the middle wing section 200. The output shaft of the torsion servo motor 500 is connected to the winglet main beam 320. Figure 6 When the torsion servo motor 500 is started, it drives the winglet main beam 320 to rotate in the shaft hole 212 formed on the middle rib 210 of the middle wing section 200, and then drives the winglet rib 310 fixedly connected to the winglet main beam 320 to twist around the focal axis B along the span direction, so that the winglet flexible skin 340 covering the wingtip winglet 300 is continuously deformed, realizing the twisting of the wingtip winglet 300 on the focal axis B, and ensuring the continuity of the aerodynamic shape.

[0080] In this embodiment, the twisting direction is controlled by a torsion servo motor 500, which drives the winglet main spar 320 to rotate, thereby causing the winglet 300 to rotate about the focal axis B within a rotation angle range of ±10°, i.e., -10° to +10°. By positioning the winglet main spar 320 so that the focal axis B is located near the aerodynamic focus of the winglet outer section, the servo motor torque required to control the winglet twisting process can be reduced. In this embodiment, the focal axis B extends along the winglet main spar 320, i.e., along the wingspan.

[0081] The skin structure covering the root wing section 100 , the middle wing section 200 and the wingtip winglet 300 constitutes a skin assembly, including a fixed skin and a deformable flexible skin. The deformable flexible skin can be deformed together with the middle wing section 200 and the wingtip winglet 300 .

[0082] The skin assembly includes a root fixed skin 130, a mid-section flexible skin 240, a mid-section fixed skin 230, a winglet flexible skin 340, and a winglet fixed skin 330, arranged sequentially from the wing root to the tip. The root fixed skin 130, mid-section fixed skin 230, and winglet fixed skin 330 are fixed skins and can be made of a sandwich material consisting of carbon fiber and rigid foam. The mid-section flexible skin 240 and winglet flexible skin 340 are flexible skins made of flexible materials, ensuring that the aerodynamic surface remains continuous during bending and torsional deformation of the flexible skin, thereby reducing aerodynamic drag. The root fixed skin 130 covers the root wing section 100; the mid-section flexible skin 240 and mid-section fixed skin 230 cover the mid-section wing section 200; and the winglet flexible skin 340 and winglet fixed skin 330 cover the wingtip winglet 300. In this embodiment, the width ratio of the middle flexible skin 240, the middle fixed skin 230, the winglet flexible skin 340 and the winglet fixed skin 330 along the span direction can be set to 2:1:1:6, so that when the multi-degree-of-freedom deformable wingtip is in the deflection and torsion state, the skin components together form a continuous and smooth surface, provide the effect of maintaining a continuous aerodynamic surface and reducing aerodynamic drag, and achieve better flight performance.

[0083] like Figure 3 、 Figure 4 and Figure 5 As shown, the multi-degree-of-freedom deformable wingtip of this embodiment can be converted between the following three working states: the driving power assembly is not started, and the multi-degree-of-freedom deformable wingtip is in a cruising flight state; the bending servo motor 400 in the driving power assembly is started to drive the middle wing section 200 to deflect up and down relative to the root wing section 100 along the deflection axis A in the chord direction of the wing, and the multi-degree-of-freedom deformable wingtip is in an adaptive cruising speed change state; the bending servo motor 400 and the torsion servo motor 500 in the driving power assembly are started at the same time to drive the middle wing section 200 to bend up and down relative to the root wing section 100 along the deflection axis A in the chord direction of the wing, and to drive the winglet 300 to twist back and forth relative to the middle wing section 200 about the focal axis B, and the multi-degree-of-freedom deformable wingtip is in an adaptive flight state.

[0084] When encountering gusts in the air, an aircraft equipped with a multi-degree-of-freedom deformable wingtip of this embodiment can control the deflection degrees of freedom in two directions and achieve active gust mitigation according to the control law. The multi-degree-of-freedom deformable wingtip of this embodiment can achieve bending deflection along the deflection axis A in the chord direction of the wing and twisting about the focal axis B of the winglet. It can not only maintain the high aerodynamic efficiency of the winglet in a wider flight envelope, but also provide additional control torque to improve the control efficiency of the aircraft. The focal axis B of the winglet 300 is the projection axis of the aerodynamic focus of the winglet on the symmetry plane. The use of a flexible skin in the deforming part of the multi-degree-of-freedom deformable wingtip can maintain the continuous flow of airflow during the deflection process of the multi-degree-of-freedom deformable wingtip, reduce the increase in drag caused by the deflection of the multi-degree-of-freedom deformable wingtip, and improve the aerodynamic performance of the wing. At the same time, when encountering a gust in the air, the bending of the middle wing section 200 and the wingtip winglet 300 relative to the root wing section 100 about the deflection axis A along the chord direction of the wing, as well as the deflection freedom of the wingtip winglet 300 about the focal axis B along the span direction are controlled to achieve active control of gust mitigation.

[0085] The multi-degree-of-freedom deformable wingtip utilizes two separate drive mechanisms for torsion and bending. To ensure the stability of the deflection mechanism, dampers can be installed in parallel at the outputs of the torsion and bending servo motors to prevent the wingtip from being affected by airflow and causing instabilities such as flutter.

[0086] All of the above optional technical solutions can be combined in any way to form optional embodiments of the present application, and will not be described in detail here.

[0087] It should be understood that the size of the serial numbers of the steps in the above embodiments does not mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present invention.

[0088] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with this technical field within the technical scope disclosed by the present invention should be covered by the scope of protection of the present invention.

Claims

1. A multi-degree-of-freedom deformable wingtip, characterized in that: include: A root wing section (100) fixedly connected to the wing body; A middle wing section (200) rotatably connected to the outer end of the root wing section (100); a winglet (300) twistably connected to the outer end of the middle wing section (200); and A power assembly comprising a bending servo motor (400) for driving the middle wing section (200) to rotate and a torsion servo motor (500) for driving the winglet (300) to twist; The multi-degree-of-freedom deformable wingtip switches between the following three working states: In a cruising flight state, the driving power assembly is not started, the middle wing section (200) is in a non-rotated deployed state, and the winglets (300) are in a non-twisted deployed state; In an adaptive cruise speed change state, only the bending servo motor (400) is activated to drive the middle wing section (200) to perform bending and deflection motion relative to the root wing section (100); Adapting to the flight state, the bending servo motor (400) and the twisting servo motor (500) are started to drive the middle wing section (200) to perform bending and deflecting motion relative to the root wing section (100), and to drive the winglet (300) to perform bending and twisting motion relative to the middle wing section (200).

2. The multi-degree-of-freedom deformable wingtip according to claim 1, characterized in that: In the adaptive cruise speed change state and the adaptive flight state, the bending deflection angle of the middle wing section (200) relative to the root wing section (100) ranges from -90° to +90°; In the adaptive flight state, the winglet (300) is twisted relative to the middle wing section (200) at an angle ranging from -10° to +10°.

3. The multi-degree-of-freedom deformable wingtip according to claim 1, characterized in that: The root wing section (100) includes a root rib (110), a root spar (120) and a root fixed skin (130) covering the surface; The root rib (110) includes a plurality of root longitudinal supporting ribs extending along the chord direction of the wing; The root spar (120) includes two root transverse support beams extending along the span direction of the wing; The bending servo motor (400) is installed and fixed on the root rib (110).

4. The multi-degree-of-freedom deformable wingtip according to claim 3, characterized in that: The root ribs (110) extending in the chord direction and the root spars (120) extending in the span direction are interlaced to form a mesh structure; The root spar (120) has a root spar protrusion (122) extending beyond the outermost root rib (110), and the root spar protrusion (122) is formed with a mounting opening for assembly with the middle wing section (200) and connection with the output of the bending servo motor (400).

5. The multi-degree-of-freedom deformable wingtip according to claim 1, characterized in that: The middle wing section (200) includes a middle rib (210), a middle spar (220), a middle fixed skin (230) and a middle flexible skin (240); The middle wing rib (210) includes two middle longitudinal supporting ribs extending along the chord direction of the wing; The middle wing spar (220) includes two middle transverse support beams extending along the span direction of the wing; The torsion servo motor (500) is mounted and fixed on the middle wing rib (210).

6. The multi-degree-of-freedom deformable wingtip according to claim 5, characterized in that: A middle flexible skin (240) covers a portion of the middle wing section (200) close to the root spar (120); The middle fixed skin (230) covers the portion of the middle wing section (200) close to the winglet (300); The width ratio of the middle flexible skin (240) to the middle fixed skin (230) along the span direction is 2:1; In the adaptive cruise speed change state and the adaptive flight state, the middle flexible skin (240) is deformed.

7. The multi-degree-of-freedom deformable wingtip according to claim 5, characterized in that: The middle wing ribs (210) extending in the chord direction and the middle wing beams (220) extending in the span direction are interlaced to form a mesh structure; The middle spar (220) has a middle spar protrusion (222) extending beyond the innermost middle rib (210), and the middle spar protrusion (222) is formed with a mounting opening for assembly with the root wing section (100).

8. The multi-degree-of-freedom deformable wingtip according to claim 1, characterized in that: The winglet (300) comprises a winglet rib (310), a winglet main beam (320), a winglet fixed skin (330) and a winglet flexible skin (340); The winglet rib (310) includes a plurality of longitudinal support ribs extending along the chord direction; The inner end of the winglet main beam (320) is connected to the output shaft of the torsion servo motor (500), and the outer end is fixed to the winglet rib (310).

9. The multi-degree-of-freedom deformable wingtip according to claim 8, characterized in that: The winglet flexible skin (340) covers the portion of the winglet (300) close to the middle wing section (200); The winglet fixed skin (330) covers the outer portion of the winglet (300); The width ratio of the winglet flexible skin (340) to the winglet fixed skin (330) along the wingspan direction is 1:6; In the adaptive flight state, the winglet flexible skin (340) is deformed.

Images