Steering engine and piezoelectric patch hybrid driven variable camber wing

Abstract

The invention relates to a steering engine and piezoelectric patch hybrid driven variable camber wing, belongs to the technical field of aerospace, and solves the problems of poor wing surface deformation continuity and poor transmission effect in the prior art. The plurality of flexible trailing edge deflection modules are arranged in the straight wing main body; the skin structure is arranged on the outer surfaces of the straight wing main body and the flexible trailing edge deflection module; the module connecting structure is connected with the plurality of flexible trailing edge deflection modules; wherein the straight wing main body comprises a front edge D-shaped structure wing box, a plurality of wing ribs arranged on the rear side of the front edge D-shaped structure wing box, and a bearing rear wall arranged on the rear sides of the wing ribs; each flexible trailing edge deflection module comprises a driving rib assembly fixed to the bearing rear wall, driven rib assemblies arranged on the two sides of the driving rib assembly, carbon rods sequentially connected with the driving rib assembly and the driven rib assemblies, an inhaul cable driving mechanism and a piezoelectric driving mechanism, and the driving rib assembly and the driven rib assemblies are sequentially arranged in the longitudinal direction of the variable-camber wing.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and particularly to a variable camber wing driven by a hybrid of a servo and piezoelectric wafers. Background Art

[0002] Traditional fixed-wing aircraft can only achieve high aerodynamic performance under fixed flight missions and limited flight conditions through the deflection of structures such as flaps and ailerons, and it is difficult to meet the requirements for aerodynamic performance and flight quality under different flight conditions. By actively deforming the wing, the wing can maintain the optimal aerodynamic shape in different flight environments. In order to improve the aerodynamic efficiency of the aircraft, expand the flight envelope, and achieve multiple functions with one aircraft, researchers have conducted in-depth research on wing active deformation technology.

[0003] The variable camber wing in the variable wing can not only achieve the functions of traditional flaps and ailerons by changing the camber of the airfoil; but also play roles such as improving the lift-drag characteristics of the aircraft and delaying the airflow separation. Combing the development context of the variable camber wing, the main development trend is that the drive control system of the wing is more refined and complex, the structure is simplified, and flexibility is increased.

[0004] However, the existing variable camber wings have problems such as poor continuity of wing surface deformation; poor transmission effect; single support structure; and poor continuity of deformation.

[0005] Therefore, there is a need in the art for an improved variable camber wing to provide a wing deformation method that can achieve continuous deformation, better transmission effect, and high-precision control. Summary of the Invention

[0006] In view of the above problems, the present invention provides a variable camber wing driven by a hybrid of a servo and piezoelectric wafers, which solves the problems of low deformation accuracy, inability to achieve large-angle bending deformation of the wing trailing edge, poor transmission effect, and easy collapse and deformation of the structure in the prior art.

[0007] According to an embodiment of the present invention, there is provided a variable camber wing driven by a hybrid of a servo and piezoelectric wafers, characterized in that it comprises:

[0008] A straight wing body;

[0009] A plurality of flexible trailing edge deflection modules disposed within the straight wing body;

[0010] A skin structure disposed on the outer surfaces of the straight wing body and the flexible trailing edge deflection modules;

[0011] A module connection structure connecting the plurality of flexible trailing edge deflection modules;

[0012] Among them, the straight wing body includes: a leading-edge D-shaped structural wing box, a plurality of wing ribs arranged behind the leading-edge D-shaped structural wing box, and a load-bearing rear wall arranged behind the wing ribs;

[0013] Each flexible trailing-edge deflection module includes: an active rib assembly fixed to the load-bearing rear wall, driven rib assemblies arranged on both sides of the active rib assembly, carbon rods sequentially connecting the active rib assembly and the driven rib assemblies, a cable drive mechanism, and a piezoelectric drive mechanism. The active rib assembly and the driven rib assemblies are arranged sequentially along the longitudinal direction of the variable-camber wing;

[0014] The cable drive mechanism includes a servo and a rigid cable. The cable connects the output of the servo to the active rib assembly to drive the deflection of the active rib assembly;

[0015] The active rib assembly includes an active rib support plate, rib plates, a plurality of U-shaped cable support plates, a honeycomb structure support plate, and an active rib wedge-shaped tail end.

[0016] Optionally, the leading-edge D-shaped structural wing box includes:

[0017] A leading-edge balsa wood mask, which constitutes the outer contour of the leading-edge D-shaped wing box to maintain the wing surface shape;

[0018] A leading-edge positioning beam, which connects the front ends of each wing rib to form a D-shaped structure;

[0019] A load-bearing main beam, which passes through the upper and lower parts of each wing rib to provide stable support.

[0020] Optionally, the plurality of wing ribs are arranged sequentially along the longitudinal direction of the variable-camber wing. The extending direction of the wing ribs is perpendicular to the longitudinal direction of the variable-camber wing, and the plurality of wing ribs are arranged parallel to each other;

[0021] The plurality of wing ribs include:

[0022] A root complete wing rib, located at the wing root of the variable-camber wing;

[0023] A tip complete wing rib, located at the wing tip of the variable-camber wing; and

[0024] A plurality of intermediate wing ribs, between the root complete wing rib and the tip wing rib. The intermediate wing ribs include assembly wing ribs and structural wing ribs. The assembly wing ribs are arranged to cooperate with the installation of the servo.

[0025] Optionally, round holes and rectangular holes are opened in the assembly wing ribs. The rectangular holes are used for installing the servo, and the round holes are used for routing wires; a plurality of triangular lightening holes are opened in the structural wing ribs, and the corners of the triangular lightening holes are rounded.

[0026] Optionally, in the active rib assembly:

[0027] The active rib support plate is vertically arranged and fixed to the load-bearing rear wall, and has an installation groove in the vertical middle part;

[0028] The rib plate is horizontally arranged and inserted into the installation groove of the active rib support plate and fixed, extending from the load-bearing rear wall to the rear side of the variable-camber wing;

[0029] A plurality of U-shaped cable support plates are sequentially installed along the extension direction of the rib plate and fixedly connected to the rib plate;

[0030] The active rib wedge-shaped tail end has a wedge-shaped structure, is fixed at the end of the rib plate, and is arranged with the wedge-shaped tip facing outward;

[0031] A plurality of honeycomb structure support plates have a honeycomb structure, are installed on the rib plate, and are arranged between adjacent U-shaped cable support plates, and between the U-shaped cable support plates and the active rib wedge-shaped tail end.

[0032] Optionally, the active rib assembly includes:

[0033] Two groups of U-shaped cable support plates and honeycomb structure support plates, and the two groups of U-shaped cable support plates and honeycomb structure support plates are arranged parallel to each other.

[0034] Optionally, each driven rib assembly includes:

[0035] The driven rib support plate is vertically arranged and fixed to the load-bearing rear wall;

[0036] A plurality of fishbone-shaped support plates have an I-shaped structure,

[0037] The driven rib wedge-shaped tail end has a wedge-shaped structure and has the wedge-shaped tip facing outward;

[0038] A plurality of quasi-honeycomb structures are arranged between adjacent fishbone-shaped support plates, between the driven rib support plate and the fishbone-shaped support plates, and between the fishbone-shaped support plates and the driven rib wedge-shaped tail end.

[0039] Optionally, the module connection structure includes a trailing edge round-section carbon rod and a silica gel film; wherein

[0040] The trailing edge round-section carbon rod sequentially connects the active rib wedge-shaped tail ends and the driven rib wedge-shaped tail ends of a plurality of flexible trailing edge deflection modules along the longitudinal direction of the variable-camber wing;

[0041] The silica gel film covers the joints between adjacent flexible trailing edge deflection modules, the joints between the root complete rib and adjacent flexible trailing edge deflection modules, and the joints between the tip rib and adjacent flexible trailing edge deflection modules.

[0042] Optionally, the skin structure includes a heat-shrinkable film and a trailing edge flexible skin, wherein,

[0043] The heat-shrinkable film is tightly stretched and covered on the surface of the leading edge balsa wood mask to keep the surface of the leading edge balsa wood mask smooth;

[0044] The trailing-edge flexible skin tightly adheres to the surface of the flexible trailing-edge deflection module to achieve continuous deformation.

[0045] Optionally, the cable drive mechanism further includes a servo traction disc, where:

[0046] The servo traction disc is connected to the output end of the servo;

[0047] One end of the cable is wound around the servo traction disc, and the other end sequentially passes through the load-bearing rear wall, the active rib support plate, each U-shaped cable support plate and is connected to the wedge-shaped tail end of the active rib.

[0048] Compared with the prior art, a variable camber wing driven by a servo and piezoelectric patches according to an embodiment of the present invention has at least the following advantages.

[0049] 1) The servo drive realizes large-angle bending deformation, and the addition of piezoelectric drive makes up for the defect of servo drive in high-frequency drive, realizing a faster and more accurate deformation response. At the same time, the function of the piezoelectric patch to convert mechanical energy into electrical energy can play a role in gust mitigation and reducing wing flutter.

[0050] 2) The use of flexible materials reduces the weight of the variable structure and truly realizes continuous deformation. The flexible trailing-edge structure all adopts the optimized bionic fishbone structure, combining the deformation characteristics of the honeycomb structure, ensuring the continuity and reliability of the flexible trailing-edge deformation.

[0051] 3) Multiple carbon rods are designed between the active rib and the driven rib for transmission and shaping. This not only ensures the efficient force transmission between the active rib and the driven rib in each drive unit, but also ensures that the flexible skin between the active rib and the driven rib has good shaping, and can still maintain the wing surface shape well at high speeds.

[0052] 4) Each flexible trailing-edge deflection module uses an independent integral flexible skin, and at the same time, the flexible skins are connected by a silicone film between different modules, ensuring the wing surface continuity of the transition section between different flexible trailing-edge deflection modules and having good airtightness.

[0053] 5) Through the force transmission of the active rib, the transmission of the flexible skin and the carbon rod, and the edge-locking connection with the silicone film, it is ensured that the trailing edge is continuously closed during the flexible deformation process. At the same time, combining the advantages of servo and piezoelectric drive in driving, it realizes the variable camber control of the wing with a wide frequency band and high precision.

[0054] 6) Different from the traditional rigid control surface, the variable trailing-edge wing based on the flexible material and the fishbone trailing-edge structure makes the wing surface deformation more continuous, and the control surface is seamlessly connected to the main body part, truly realizing the maximization of flight efficiency and aerodynamic efficiency at different flight stages by changing the airfoil.

[0055] 7) A honeycomb support structure is provided in the active rib assembly and the driven rib assembly to provide enhanced structural strength and ensure continuous deformation while maintaining a light weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0056] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required 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 construed as any limitation to the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0057] Figure 1 FIG. 10 is a schematic diagram of the overall structure of the right half wing of a variable camber wing driven by a servo and a piezoelectric sheet according to an embodiment of the present invention.

[0058] Figure 2 FIG. 14 is a schematic diagram of the overall structure of a single flexible trailing edge deflection module in a variable camber wing driven by a servo and a piezoelectric sheet according to an embodiment of the present invention.

[0059] Figure 3 FIG. 18 is an assembly diagram of the active rib assembly, the cable drive mechanism, and the piezoelectric drive mechanism of a single flexible trailing edge deflection module in a variable camber wing driven by a servo and a piezoelectric sheet according to an embodiment of the present invention.

[0060] Figure 4 FIG. 22 is a schematic diagram of a fishbone driven rib assembly in a variable camber wing driven by a servo and a piezoelectric sheet according to an embodiment of the present invention.

[0061] Figure 5 FIG. 26 is a schematic diagram of the installation of a piezoelectric sheet in a variable camber wing driven by a servo and a piezoelectric sheet according to an embodiment of the present invention.

[0062] Reference Numerals:

[0063] 11, wing rib;

[0064] 12, load-bearing main beam;

[0065] 13, leading edge positioning beam;

[0066] 14, rear wall;

[0067] 15, leading edge balsa wood mask;

[0068] 111, wing root complete wing rib;

[0069] 112, wing tip wing rib;

[0070] 113, assembled wing rib;

[0071] 114. Structural rib

[0072] 121. Upper web

[0073] 122. Lower web

[0074] 21. Active rib assembly

[0075] 211. Active rib support plate

[0076] 212. Rib plate

[0077] 213. U-shaped cable support plate

[0078] 214. Honeycomb structure support plate

[0079] 215. Active rib wedge-shaped tail end

[0080] 22. Driven rib assembly

[0081] 221. Driven rib support plate

[0082] 222. Fishbone-shaped support plate

[0083] 223. Quasi-honeycomb structure

[0084] 224. Driven rib wedge-shaped tail end

[0085] 231. Actuator

[0086] 232. Actuator traction disc

[0087] 233. Cable

[0088] 33. Trailing edge flexible skin

[0089] 24. Piezoelectric sheet

[0090] 25. Carbon rod

[0091] 41. Trailing edge round-section carbon rod

[0092] 42. Square-section carbon tube

[0093] 43. Silicone membrane Detailed implementation manners

[0094] In order to more clearly understand the above objects, features and advantages of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and specific implementation manners. It should be noted that, without conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

[0095] In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. However, the present invention may be implemented in other ways different from those described herein. Therefore, the scope of protection of the present invention is not limited by the specific embodiments disclosed below.

[0096] The following provides a detailed description of a variable-camber wing with a hybrid drive of a servo and piezoelectric wafers according to an embodiment of the present invention with reference to the accompanying drawings. A variable-camber wing with a hybrid drive of a servo and piezoelectric wafers according to an embodiment of the present invention utilizes a biomimetic fishbone structure and piezoelectric wafers to design a flexible trailing edge. By cleverly connecting a plurality of flexible deflection units, a piezoelectric fishbone variable-camber wing that combines a fishbone variable-camber wing and a piezoelectric variable-camber wing is proposed.

[0097] As Figures 1 to 4 shown, a variable-camber wing with a hybrid drive of a servo and piezoelectric wafers according to an embodiment of the present invention includes: a straight wing main body; a plurality of flexible trailing edge deflection modules accommodated in the straight wing main body; a skin structure; and a module connection structure. The straight wing main body occupies the main part of the leading edge and the middle section of the wing; the flexible trailing edge deflection modules are installed on the rear wall of the straight wing main body and occupy the trailing edge of the wing; the skin structure is installed on the outer surfaces of the straight wing main body and the flexible trailing edge deflection modules; and the module connection mechanism is installed between the plurality of flexible trailing edge deflection modules to connect the plurality of flexible trailing edge deflection modules. The variable-camber wing with a hybrid drive of a servo and piezoelectric wafers in this embodiment includes three flexible trailing edge deflection modules. Optionally, in other embodiments, more or fewer flexible trailing edge deflection modules may be provided as needed.

[0098] The straight wing main body may include: a leading edge D-shaped structural wing box; a plurality of wing ribs arranged in parallel along the longitudinal direction of the wing behind the leading edge D-shaped structural wing box; a load-bearing main beam and a load-bearing rear wall. In a schematic example, the dimensions of the straight wing main body are a semi-span of 752 mm, a chord length of 240 mm, the chord length ratio of the flexible trailing edge is 45%, and the span ratio is 100%. Here, the longitudinal direction of the wing is the direction in which the wing extends from the wing root to the wing tip; the front is the direction in which the wing faces the front of the aircraft and is consistent with the aircraft nose when installed on the fuselage; and the rear is the direction in which the wing faces the rear of the aircraft and is consistent with the aircraft tail when installed on the fuselage.

[0099] The flexible trailing edge deflection module may include: an active rib assembly; driven rib assemblies arranged on both sides of the active rib assembly; a cable drive mechanism; a piezoelectric drive mechanism; and a connecting carbon rod.

[0100] Each flexible trailing edge deflection module may include an active rib assembly and two passive rib assemblies disposed on both sides of the active rib assembly. The active rib assembly is used to drive the flexible trailing edge deflection module to bend. The front end of the active rib assembly is connected to the wing rib through the rear wall, and the servo is installed on the wing rib. A winch and two non-stretchable and non-deformable thin wires pass through the rear wall and multiple U-shaped cable support plates and are connected to the connection holes at the wedge-shaped tail end of the active rib to form a transmission structure. The active rib plate is made of spring steel, and piezoelectric sheets can be attached to its upper side to achieve high-frequency deformation and more precise micro-deformation. The passive rib assembly is designed with a bionic fish bone structure for transmission and shaping. The bionic fish bone structure may include a support plate, three fish bone-shaped support plates, a honeycomb structure connecting the support plates, and a wedge-shaped tail end of the passive rib. Within a flexible trailing edge deflection module, the passive ribs are located on both sides of the active rib. The active rib assembly and the passive ribs are connected by multiple carbon rods for transmission and shaping the middle wing surface area between the active rib assembly and the passive ribs.

[0101] The skin structure may include a balsa wood layer, a heat shrinkable film, and a trailing edge flexible skin. The thickness of the balsa wood layer is 1 mm, and it covers the part between the wing main beam and the load-bearing rear wall of the leading edge D-shaped wing box. The heat shrinkable film is tightly stretched and covered on the surface of the balsa wood layer. The trailing edge flexible skin is stretched and covered on the surface of the flexible trailing edge deflection module to achieve continuous deformation. Each independent flexible trailing edge deflection module can be covered by an independent flexible skin, and the skins covered by each flexible trailing edge deflection module are connected through a module connection structure.

[0102] The module connection structure may include carbon rods and a silicone film. The carbon rods have a diameter of 1 mm and are placed at the very end of the wedge-shaped tail ends of the active ribs and the passive ribs to connect the active rib assemblies and the passive ribs of all flexible trailing edge deflection modules. In addition, carbon tubes can be provided inside each module for providing transmission between the active ribs and the passive ribs. The silicone film is attached to the transition of the flexible skin structures of two flexible trailing edge deflection modules to ensure the wing surface continuity of the transition section between multiple flexible trailing edge deflection modules. Additionally, the silicone film can also be used to connect the wing root and the flexible trailing edge deflection module near the wing root to ensure the continuity of the spanwise deformation of the flexible trailing edge and good airtightness inside the flexible trailing edge.

[0103] The straight wing body can adopt a wooden structure. Specifically, 2mm paulownia wood can be used as the main material for the wing ribs to provide the stiffness of the leading-edge D-shaped box; 2mm plywood can be used as the main material for the main beam and the rear wall to ensure its good load-bearing performance; at the connection between the root of the main beam and the wing body, there is a square-section carbon tube with a size of 8mm x 8mm to ensure good load-bearing performance at the wing-body connection, and at the same time, the square structure can provide a certain torsional resistance for the wing; a square-section carbon tube with a size of 4mm x 4mm can be arranged inside the rear wall to enhance the torsional resistance of the rear wall, and the square structure can fit more closely with the rear wall. The fishbone follower ribs and the active rib assembly can be made by 3D printing, and the material can be polyethylene plastic PLA. The rib plate of the active rib can be selected from spring steel. The trailing-edge flexible skin can adopt PET flexible material.

[0104] See Figures 1 to 4 , in order to better understand the technical solutions provided by the embodiments according to the present invention, the following will give a detailed description of an embodiment of a variable-camber wing driven by a servo and a piezoelectric sheet according to the embodiments provided by the present invention.

[0105] In this embodiment, the variable-camber wing driven by a servo and a piezoelectric sheet is a piezoelectric fishbone variable-camber wing, which includes a straight wing body, three flexible trailing-edge deflection modules, a skin structure, and a module connection structure. The straight wing body occupies the main part of the leading edge and the middle section of the wing; the flexible trailing-edge deflection modules are installed on the rear wall of the straight wing body and occupy the trailing edge of the wing; the skin structure is installed on the outer surfaces of the straight wing body and the flexible trailing-edge deflection modules; the module connection mechanism is installed between multiple flexible trailing-edge deflection modules to connect multiple flexible trailing-edge deflection modules. Optionally, in other embodiments, more or fewer flexible trailing-edge deflection modules can be set according to needs.

[0106] As Figure 1 shown, the straight wing body includes: a leading-edge D-shaped structural wing box; a plurality of wing ribs 11 arranged behind the leading-edge D-shaped structural wing box; a load-bearing rear wall 14 arranged behind the wing ribs 11. The plurality of wing ribs 11 are arranged parallel to each other and are arranged in sequence along the longitudinal direction of the wing. The extending direction of the wing ribs 11 is substantially perpendicular to the longitudinal direction of the wing and extends from the front side to the rear side. The rear side of the leading-edge D-shaped structural wing box refers to the side corresponding to the tail of the aircraft when the variable-camber wing is installed on the aircraft; correspondingly, the front side is the side corresponding to the nose of the aircraft. The plurality of wing ribs 11 have the same contour shape. The contour of the wing ribs 11 is consistent with the cross-sectional contour of the straight wing body.

[0107] The leading-edge D-shaped structural wing box may include: a leading-edge balsa wood mask 15, a leading-edge positioning beam 13, and a load-bearing main beam 12. The leading-edge positioning beam 13 connects the front ends of each wing rib 11 to form a D-shaped structure. The leading-edge positioning beam 13 may be a long strip member, for example, it may be a smooth sanded long wooden strip, and may have structural forms such as a square cross-section, a circular cross-section, etc. The load-bearing main beam 12 passes through the upper and lower sides of each wing rib 11 respectively to provide stable support. Optionally, the load-bearing main beam 12 may include an upper web 121, a lower web 122, and a carbon tube 42 at the wing root. The upper web 121 and the lower web 122 pass through each wing rib 11 from above and below respectively. The carbon tube 42 may have a square cross-section, which is a square with a side length of 8 mm, passes through the mounting holes reserved on three intermediate wing ribs near the wing root complete wing rib 111, separates the upper web 121 and the lower web 122, and the other end is suspended outside the wing root complete wing rib 111 to connect to the fuselage part structure. The extending direction of the square cross-section carbon tube 42 is along the longitudinal direction of the variable camber wing and is perpendicular to the plane of the wing rib. Through the square cross-section carbon tube 42, the torque received by the wing along the chord direction during flight can be effectively borne. The leading-edge surface of the wing rib 11 is covered by the leading-edge balsa wood mask 15, forming the outer shape body of the leading-edge D-shaped structural wing box. The leading edge of the wing rib 11 is located inside the D-shaped structural wing box and serves to support the leading-edge balsa wood mask 15. The leading-edge balsa wood mask 15 has a thickness of 1 mm and forms the outer contour of the leading-edge D-shaped wing box, which is used to maintain the wing surface shape of the variable camber wing.

[0108] The multiple wing ribs 11 may include a wing root complete wing rib 111 located at the wing root of the variable camber wing; a wing tip complete wing rib 112 located at the wing tip; and a plurality of intermediate wing ribs between the wing root complete wing rib 111 and the wing tip wing rib 112. All the wing ribs are wing ribs without trailing edges. Each wing rib may be provided with lightening holes, and the shapes of the lightening holes may be set to be different according to the functions of each wing rib. The intermediate wing ribs may include an assembly wing rib 113 and a structural wing rib 114. The assembly wing rib is used to install the servo for driving the active rib structure, and the rest of the wing ribs are structural wing ribs 114. For example, one structural wing rib 114 may be provided on each side of the assembly wing rib 113. Round holes and rectangular holes are opened in the assembly wing rib 113, where the rectangular hole can be used to install the servo in it; the round hole can be used for wiring. A plurality of triangular lightening holes are opened in the structural wing rib 114 to increase the hollow area, so as to reduce the weight while meeting the strength requirements. The corners of the triangular lightening holes may be rounded. As Figure 1 shown, four triangular lightening holes may be opened in the structural wing rib 114, combined into a trapezoidal shape, matching the outer shape of the structural wing rib 114, providing a better structural lightening effect. The upper web 121 and the lower web 122 are two upper and lower blocks, vertically inserted into each wing rib 11 but not cutting the wing rib 11 into two parts.

[0109] The load-bearing rear wall 14 can be inserted into the holes in the root rib 111 and the tip rib 112 of the wing along the spanwise direction (i.e., the longitudinal direction of the wing) through the mortise and tenon structure, and is inserted by the assembled rib 113 and the structural rib 114 along the chordwise direction, so as to be fixed on the rib.

[0110] As Figure 2 and Figure 3 shown, in this embodiment, three flexible trailing edge deflection modules are arranged side by side along the longitudinal direction of the wing and connected to the rear wall 14 at the rear side thereof. The flexible trailing edge deflection module may include: an active rib assembly; driven rib assemblies arranged on both sides of the active rib assembly; a cable drive mechanism; a piezoelectric drive mechanism; and a connecting carbon rod. Each flexible trailing edge deflection module includes an active rib assembly 21, two driven rib assemblies 22 arranged on both sides of the active rib assembly 21, and a carbon rod 25 connecting the active rib assembly 21 and the driven rib assemblies 22 in sequence along the longitudinal direction, so as to connect the rib assemblies into a whole to enhance its transmission performance. The installation position of the active rib assembly 21 corresponds to the position of the assembled rib 113, so that the cable drive mechanism installed on the assembled rib 113 can drive the active rib assembly 21.

[0111] The active rib assembly 21 may include: an active rib support plate 211, a rib plate 212, a U-shaped cable support plate 213, a honeycomb structure support plate 214, and an active rib wedge-shaped tail end 215.

[0112] In this embodiment, the active rib support plate 211 is vertically arranged and fixed on the rear wall 14 by bolts, and has an installation groove in the vertical middle part. The rib plate 212 is horizontally arranged and inserted into the installation groove of the active rib support plate 211 and fixed with glue or screws. The rib plate 212 extends from the load-bearing rear wall 14 to the rear side of the variable camber wing. The U-shaped cable support plates 213 are sequentially arranged on the rib plate 212 and fixedly bonded to the rib plate 212. The three U-shaped cable support plates 213 gradually decrease in height from the rear wall to the rear side direction of the variable camber wing, but the width remains unchanged. Each U-shaped cable support plate 213 has a U-shaped structure, including an upper support piece, a lower support piece, and a vertical connecting part connecting the upper and lower support pieces. Optionally, the upper support piece and the lower support piece at both ends may have a certain slope to be consistent with the surface contour shape of the airfoil of the straight wing body (i.e., the variable camber wing). The active rib wedge-shaped tail end 215 has a wedge-shaped structure, is fixed at the end of the rib plate 212, and is arranged with the wedge-shaped tip facing outward to support the rear end contour of the straight wing body.

[0113] As Figure 3As shown, the honeycomb structure support plate 214 is disposed between adjacent U-shaped cable support plates 213, and between the U-shaped cable support plate 213 and the active rib wedge-shaped end 215 to connect the three U-shaped cable support plates 213 and the active rib wedge-shaped end 215. The honeycomb structure support plate 214 is formed with an installation groove in the middle to allow the rib plate 212 to pass through for assembly and fixation. The honeycomb structure support plate 214 has a honeycomb structure. The honeycomb structure support plate 214 may include an intermediate parallel bending section and triangular connection sections at both ends thereof. Optionally, the parallel bending section is a flat plate structure, and the honeycomb structure support plate 214 may include two upper and lower parallel bending sections, and triangular connection sections are provided at both ends of the two parallel bending sections. Among them, the triangular connection section (the long side of the triangle) is connected to the U-shaped cable support plate 213 or the active rib wedge-shaped end 215 to ensure the strength of the connection and provide reliable support. The parallel bending section extends in the same direction as the rib plate 212 and is generally parallel or slightly inclined, and bends and deforms together with the rib plate 212. One corner of the triangular connection section (i.e., the corner opposite to the above-mentioned long side) faces the parallel bending section, and at both sides of the corner close to the corner vertex, it is fixed or integrally formed with the parallel bending section, and the corner vertex is located between the two parallel bending sections. The honeycomb structure support plate 214 enhances the stability of the connection between adjacent U-shaped cable support plates 213, and between the U-shaped cable support plate 213 and the active rib wedge-shaped end 215 through the triangular connection section, and ensures a certain deformation and bending ability; through the parallel bending section, it bends together with the rib plate 212 to achieve a variable camber at the trailing edge. The honeycomb structure support plate 214 can be appropriately changed according to the installation position and size, for example, the height gradually decreases from the front side to the rear side to be consistent with the variable camber wing profile.

[0114] The three parts of the U-shaped cable support plate 213, the honeycomb structure support plate 214, and the active rib wedge-shaped end 215 can be integrally formed by 3D printing. Installation grooves can be provided in the U-shaped cable support plate 213, the honeycomb structure support plate 214, and the active rib wedge-shaped end 215 for the rib plate 212 to be inserted and fixed.

[0115] When installing the active rib assembly 21, the rib plate 212 is successively passed through the installation grooves of the active rib support plate 211, the installation grooves of each U-shaped cable support plate 213 and the honeycomb structure support plate 214 from front to back, and finally inserted into the installation groove of the active rib wedge-shaped end 215 and fixed. By including the above-mentioned active rib assembly 21, the variable camber wing can have a light weight for flight, have improved support strength and maintain the profile of the straight wing body in various flight modes, and also have good and flexible variable camber adjustment ability.

[0116] As Figure 3As shown, in this embodiment, the active rib assembly includes: two sets of U-shaped cable support plates and a honeycomb structure support plate, which are arranged parallel to each other along the longitudinal direction (i.e., spanwise direction) of the variable camber wing to provide enhanced support and deflection force. In this embodiment, multiple U-shaped cable support plates 213 increase the contact area with the trailing edge flexible skin 33, and the trailing edge flexible skin 33 deflects according to a predetermined law with good continuity.

[0117] In this embodiment, the honeycomb structure support plate 214 is arranged between two adjacent U-shaped cable support plates 213 to transfer the shear force and bending moment received by the U-shaped cable support plate 213 during the deflection process, thereby increasing the structural stability and the buffering ability against gust loads. In this embodiment, the active rib wedge-shaped tail end 215 is connected to the honeycomb structure support plate 214 at the outermost end, and the wedge tip faces outward. The above-mentioned vertical setting means setting in the vertical direction perpendicular to the horizontal direction. The above-mentioned horizontal setting means setting in the direction of extending substantially horizontally.

[0118] As Figure 2 and Figure 4 shown, the passive rib assemblies 22 are symmetrically arranged on both sides of the active rib assembly 21. Each passive rib assembly 22 includes a passive rib support plate 221, multiple fishbone-shaped support plates 222, a passive rib wedge-shaped tail end 224, and multiple honeycomb-like structures 223. Each fishbone-shaped support plate 222 has an I-shaped structure, and the heights of multiple fishbone-shaped support plates 222 gradually decrease from the passive rib support plate 221 to the passive rib wedge-shaped tail end 224. The shape of the passive rib assembly 22 is similar to that of the active rib assembly 21. The passive rib support plate 211 is vertically arranged and fixed to the load-bearing rear wall 14 by bolts. The fishbone-shaped support plate 222 has an I-shaped structure to play a role in supporting the skin. In this embodiment, 3 fishbone-shaped support plates 222 are provided. Optionally, according to needs, 2-5 fishbone-shaped support plates 222 can be provided. Optionally, the upper plane part and the lower plane part of the I-shaped structure of the fishbone-shaped support plate 222 can have a certain slope to be consistent with the slope of the surface profile of the straight wing main body (i.e., the variable camber wing).

[0119] As Figure 4As shown, the driven rib assembly 22 includes a plurality of honeycomb-like structures 223 disposed between adjacent fishbone-shaped support plates 222, between the driven rib support plate 221 and the fishbone-shaped support plates 222, and between the fishbone-shaped support plates 222 and the driven rib wedge-shaped tail end 224. The honeycomb-like structure 223 may include two parallel curved segments in the middle and triangular connection segments at both ends thereof. Among them, the triangular connection segment (the long side of the triangle) is connected to the driven rib support plate 221, the fishbone-shaped support plate 222, or the driven rib wedge-shaped tail end 224 to ensure the strength at the connection and provide reliable support. One corner of the triangular connection segment (i.e., the corner opposite to the above-mentioned long side) faces the parallel curved segment, and at both sides of this corner near the corner vertex, it is fixed or integrally formed with the parallel curved segment, and the corner vertex is located between the two parallel curved segments. The parallel curved segment may be a flat plate structure, and its extending direction is generally consistent with that of the rib plate 212 and bends and deforms together with the rib plate 212. The honeycomb-like structure 223 enhances the connection stability between adjacent fishbone-shaped support plates 222, between the driven rib support plate 221 and the fishbone-shaped support plates 222, and between the fishbone-shaped support plates 222 and the driven rib wedge-shaped tail end 224 through the triangular connection segment, and ensures a certain deformation and bending ability; through the parallel curved segment, it bends together with the rib plate 212 to achieve a variable camber at the trailing edge. The honeycomb-like structure 223 can be appropriately changed according to the installation position and size, for example, the height gradually decreases from the front side to the rear side to be consistent with the variable camber wing profile. One end of the honeycomb-like structure 223 close to the load-bearing rear wall 14 abuts and is installed on the driven rib support plate 221, and the other end abuts the front side of the fishbone-shaped support plate 222. Two honeycomb-like structures 223 are respectively disposed between adjacent fishbone-shaped support plates 222, and both ends respectively abut the sides of the fishbone-shaped support plates 222, playing a role in increasing the structural stability to enhance the buffering of gust loads. At the same time, the honeycomb-like structure has good deformation continuity, enabling the skin to maintain a good wing surface shape. One end of the honeycomb-like structure 223 farthest from the driven rib support plate 221 abuts the fishbone-shaped support plate 222, and the other end is connected to the front side of the driven rib wedge-shaped tail end 224, and the wedge tip of the driven rib wedge-shaped tail end 224 faces outward (i.e., towards the rear side of the wing).

[0120] As Figure 1 and Figure 2 shown, a plurality of through holes are respectively formed in the U-shaped cable support plate 213 in the active rib assembly and the fishbone-shaped support plates 222 of the two driven ribs at corresponding positions. A plurality of carbon rods 25 sequentially pass through the through holes of the U-shaped cable support plate 213 and the fishbone-shaped support plates 222 along the longitudinal direction of the variable camber wing to connect them into a whole, so as to enhance their transmission performance and realize the deflection of the flexible trailing edge along the spanwise direction according to the preset equal deflection angle law. As Figure 2As shown, in this embodiment, the through holes of the U-shaped cable support plate 213 and the fishbone-shaped support plate 222 are arranged at the structural bending points and are respectively close to the upper and lower edges. The carbon rods 25 passing through the through holes also play a role in supporting the trailing-edge flexible skin 33 covered on the upper and lower surfaces, avoiding its internal collapse.

[0121] As Figure 4 shown, the cable drive mechanism includes a servo motor 231, a servo traction disc 232, and a rigid cable 233. A rectangular hole is opened on the assembled wing rib 113, and its size and shape match those of the servo motor 231. The servo motor 231 is fixedly installed in the rectangular hole of the assembled wing rib 113, and the main body of the servo motor 231 can be arranged on the side of the assembled wing rib 113 close to the wing root. A single-sided wing can be provided with multiple cable drive mechanisms. For example, three cable drive mechanisms can be provided, and each cable drive mechanism drives a corresponding active rib assembly. That is, a single-sided wing can be provided with three servo motors, respectively driving three independent flexible trailing-edge deflection modules. The servo traction disc 232 is connected to the output end of the servo motor 231 and is located on the side of the assembled wing rib 113 opposite to the servo motor 231 to avoid interfering with the cable operation and maintaining the balance on both sides of the assembled wing rib 113. One end of the cable 233 is wound around the servo traction disc 232, and the other end sequentially passes through the load-bearing rear wall 14, the active rib support plate 211, and each U-shaped cable support plate 213 from front to back and is connected to the wedge-shaped tail end 215 of the active rib. When the servo motor 231 works, it drives the servo traction disc 232 to rotate, and then drives the cable 233 to pull a plurality of force transmission components on the active rib assembly 21, realizing the continuous deflection of the force transmission components. Then, the active rib assembly 21 drives the driven rib assembly 22 to rotate through the carbon rod 25 and the skin 33, thereby realizing the continuous deformation and rotation of the entire flexible module.

[0122] As Figure 3 and Figure 5 shown, the piezoelectric drive mechanism may include a piezoelectric sheet 24, and the piezoelectric sheet 24 is arranged on the upper surface of the rib plate 212 of the active rib assembly. For example, the piezoelectric sheet 24 can be bonded to the rib plate 212 through epoxy resin. By changing the drive voltage and frequency provided to the piezoelectric sheet 24 from the outside, the deflection amplitude of the piezoelectric sheet 24 can be changed, and then the rib plate 212 is driven by the piezoelectric sheet 24 to deflect, realizing piezoelectric control.

[0123] See Figure 1, the skin structure may include a heat shrinkable film and a trailing edge flexible skin 33. The heat shrinkable film is tightly stretched and covered on the surface of the leading edge balsa wood mask 15, making the surface of the leading edge balsa wood mask 15 smoother, and thus making the wing surface smoother. The trailing edge flexible skin 33 is tensioned and then covered on the surface of the flexible trailing edge deflection module to achieve continuous deformation. Each independent flexible trailing edge deflection module can be covered by an independent flexible skin respectively, and the trailing edge flexible skins 33 covered by each flexible trailing edge deflection module are connected by a module connection structure. Optionally, each trailing edge flexible skin 33 is tensioned and covered on the upper surface and the lower surface to cover a corresponding set of wing ribs 11, a corresponding section of the load-bearing rear wall 14, and a set of active rib components 21 and passive rib components 22. Optionally, each trailing edge flexible skin 33 can cover the part of a corresponding set of wing ribs 11 that is not covered by the leading edge balsa wood mask 15. As Figure 1 shown, the module connection structure may include a trailing edge round-section carbon rod 41 and a silica gel film 43. In this embodiment, the cross-sectional diameter of the trailing edge round-section carbon rod 41 is set to 1 mm, and it is sequentially connected in the round holes at the wedge-shaped tails 215 of the active ribs and the wedge-shaped tails 224 of the passive ribs of the three flexible trailing edge deflection modules along the longitudinal direction of the variable camber wing. On the one hand, it is used to transmit the rudder surface deflection driving force on the active rear rib component, and on the other hand, it is used to maintain the shape of the trailing edge flexible skin and prevent internal collapse. The silica gel film 43 covers the surfaces at the joints of adjacent flexible trailing edge deflection modules, the joints of the root complete wing rib 111 and adjacent flexible trailing edge deflection modules, and the joints of the tip wing rib 112 and adjacent flexible trailing edge deflection modules. The silica gel film 43 can be arranged at the adjacent surfaces of the independent trailing edge flexible skins 33 covering each flexible trailing edge deflection module. By setting the silica gel film 43, on the one hand, it plays a transitional role to ensure the continuity of the transition section when different flexible trailing edge deflection modules have different deflection directions and angles, and realizes the continuous deformation in the spanwise direction of the trailing edge. On the other hand, it can avoid the air leakage problem and ensure the airtightness inside the flexible trailing edge structure.

[0124] All the above optional technical solutions can be combined arbitrarily to form the optional embodiments of the present application, which will not be elaborated one by one here.

[0125] It should be understood that the magnitudes of the sequence numbers of the steps in the above embodiments do not mean the order of execution. The execution order of each process should be determined according to its function and internal logic, and should not constitute any limitation to the implementation process of the embodiments of the present invention.

[0126] The above is only the preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A variable-camber wing driven by a servo and a piezoelectric sheet, characterized in that: include: Straight wing body; A plurality of flexible trailing edge deflection modules are arranged in the straight wing body; A skin structure, arranged on the outer surface of the straight wing body and the flexible trailing edge deflection module; A module connection structure, connecting a plurality of flexible trailing edge deflection modules; The straight wing body includes: a leading edge D-shaped structural wing box, a plurality of wing ribs arranged at the rear side of the leading edge D-shaped structural wing box, and a load-bearing rear wall arranged at the rear side of the wing ribs; Each flexible trailing edge deflection module comprises: an active rib assembly fixed to a load-bearing rear wall, a driven rib assembly arranged on both sides of the active rib assembly, a carbon rod sequentially connecting the active rib assembly and the driven rib assembly, a cable drive mechanism, and a piezoelectric drive mechanism, wherein the active rib assembly and the driven rib assembly are sequentially arranged along the longitudinal direction of the variable camber wing; The cable drive mechanism includes a steering gear and a rigid cable, wherein the cable connects the output of the steering gear to the active rib assembly to drive the deflection of the active rib assembly; The active rib assembly comprises an active rib support plate, a rib plate, a plurality of U-shaped cable support plates, a honeycomb structure support plate and an active rib wedge-shaped tail end.

2. The variable camber wing driven by a combination of a steering gear and a piezoelectric sheet according to claim 1, characterized in that: The leading edge D-shaped structural wing box includes: The leading edge balsa wood mask forms the outer contour of the leading edge D-shaped wing box to maintain the wing shape; Leading edge positioning beam, connecting the front ends of each wing rib to form a D-shaped structure; The load-bearing main beam passes through the upper and lower parts of each wing rib to provide stable support.

3. The variable camber wing driven by a combination of a steering gear and a piezoelectric sheet according to claim 1, characterized in that: The plurality of wing ribs are sequentially arranged along the longitudinal direction of the variable camber wing, the extending direction of the wing ribs is perpendicular to the longitudinal direction of the variable camber wing, and the plurality of wing ribs are arranged parallel to each other; The plurality of ribs include: A full wing root rib, located at the root of the variable camber wing; A wingtip integral rib located at the wingtip of the variable camber wing; and A plurality of intermediate ribs are provided between the complete ribs at the wing root and the ribs at the wing tip. The intermediate ribs include assembly ribs and structural ribs. The assembly ribs are configured to be mounted in cooperation with the steering gear.

4. The variable camber wing driven by a combination of a steering gear and a piezoelectric sheet according to claim 3, characterized in that: A circular hole and a rectangular hole are opened in the assembly rib, wherein the rectangular hole is used to install the servo, and the circular hole is used to route the wires; A plurality of triangular lightening holes are opened in the structural rib, and the corners of the triangular lightening holes are rounded.

5. The variable camber wing driven by a combination of a steering gear and a piezoelectric sheet according to claim 1, characterized in that: In the active rib assembly: The active rib support plate is vertically arranged and fixed to the load-bearing rear wall, and has a mounting groove in the vertical middle; The rib plate is horizontally arranged and inserted into and fixed in the mounting slot of the active rib support plate, extending from the load-bearing rear wall to the rear side of the variable camber wing; A plurality of U-shaped cable support plates are sequentially installed on the rib plates along the extension direction of the rib plates and are fixedly connected to the rib plates; The active rib wedge-shaped tail end has a wedge-shaped structure, is fixed to the end of the rib plate, and is arranged with the tip of the wedge facing outwards; A plurality of honeycomb structure support plates have a honeycomb structure, are mounted to the rib plate, and are disposed between adjacent U-shaped cable support plates and between the U-shaped cable support plates and the wedge-shaped tail end of the active rib.

6. The variable camber wing driven by a combination of a steering gear and a piezoelectric sheet according to claim 5, characterized in that: The active rib assembly comprises: Two groups of U-shaped cable support plates and honeycomb structure support plates are provided, and the two groups of U-shaped cable support plates and honeycomb structure support plates are arranged parallel to each other.

7. The variable camber wing driven by a combination of a steering gear and a piezoelectric sheet according to claim 5, characterized in that: Each follower rib assembly includes: A driven rib support plate, vertically arranged and fixed to the load-bearing rear wall; Multiple fishbone support plates with I-shaped structure, The wedge-shaped tail end of the follower rib has a wedge-shaped structure with the tip of the wedge pointing outward; A plurality of honeycomb-like structures are arranged between adjacent fishbone-shaped support plates, between the driven rib support plate and the fishbone-shaped support plate, and between the fishbone-shaped support plate and the wedge-shaped tail end of the driven rib.

8. The variable camber wing driven by a combination of a steering gear and a piezoelectric sheet according to claim 7, characterized in that: The module connection structure includes a trailing edge circular cross-section carbon rod and a silicone membrane; in A trailing edge circular cross-section carbon rod sequentially connects active rib wedge-shaped tail ends and driven rib wedge-shaped tail ends of a plurality of flexible trailing edge deflection modules along the longitudinal direction of the variable-camber wing; The silicone membrane covers the connection between adjacent flexible trailing edge deflector modules, the connection between the complete rib at the wing root and the adjacent flexible trailing edge deflector module, and the connection between the rib at the wing tip and the adjacent flexible trailing edge deflector module.

9. The variable camber wing driven by a combination of a steering gear and a piezoelectric sheet according to claim 1, characterized in that: The skin structure includes a heat shrinkable film and a trailing edge flexible skin, wherein: The heat shrink film is stretched and tightly covered on the surface of the front edge balsa wood mask to keep the surface of the front edge balsa wood mask smooth; The trailing edge flexible skin is stretched tightly against the surface of the flexible trailing edge deflection module to achieve continuous deformation.

10. The variable camber wing driven by a combination of a steering gear and a piezoelectric sheet according to claim 1, characterized in that: The cable drive mechanism also includes a steering gear traction plate, wherein: The steering gear traction plate is connected to the output end of the steering gear; One end of the cable is wound around the steering gear traction disc, and the other end passes through the load-bearing rear wall, the active rib support plate, each U-shaped cable support plate in sequence and is connected to the wedge-shaped tail end of the active rib.

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