Wing with fused wing body and manufacturing method

Abstract

The invention provides a fused wing body wing and a manufacturing method, the fused wing body wing comprises a main wing, an aileron and a steering engine fairing, the main wing is of a symmetrical structure integrally formed by a left wing and a right wing and comprises a left wing section, a connecting middle section and a right wing section which are sequentially connected, and the connecting middle section is matched with a fuselage in shape and used for being connected with the fuselage; the two ailerons are movably mounted at the rear edges of the left wing section and the right wing section and can swing within a certain range; steering engine fairings are mounted on the sides, close to the fuselage, of the two ailerons. The left and right wing integrated design forming structure is adopted, the wing structure is simple, the number of parts is small, and disassembly and assembly are easy.

Description

Technical Field

[0001] The present invention belongs to the technical field of wing design, and in particular relates to a wing-body blended wing and a manufacturing method thereof. Background Art

[0002] Conventional wing designs are usually divided into left and right wings, with bolts used to connect and fix the left and right wings to the fuselage. However, the docking joints between the wing and the fuselage are usually complex mechanical processing structures with a long processing flow, which is not conducive to cost control and shortening the production cycle of the entire product. In addition, the wing structure using conventional structural solutions is complex, the disassembly and assembly process is cumbersome, and a large operating space is required. There are a large number of parts and fasteners, a long processing flow, and a heavy structure. It cannot meet the current requirements for low-cost manufacturing, rapid replacement, and lightweight structure of the fuselage structure that are urgently needed in the fields of drones and the like.

[0003] The use of integrated molding technology plays an important role in reducing the number of composite component structures, reducing use and maintenance costs, saving costs, and improving efficiency. This technology has been widely used in small UAV light-load rudders, but it has not been widely used in large structural components with heavy loads, especially wing-body fusion left and right wing one-piece molding structures, due to molding quality and deformation control. Summary of the invention

[0004] The object of the present invention is to provide a wing-body fusion wing and a manufacturing method thereof, which adopts a left-right wing integrated design molding structure, has a simple wing structure, a small number of parts, and is easy to disassemble and assemble.

[0005] The technical solution adopted by the present invention to achieve the above-mentioned purpose is as follows:

[0006] The present invention provides a wing-body blended wing, comprising a main wing, an aileron and a servo fairing, wherein the main wing is a symmetrical structure in which left and right wings are integrally formed, comprising a left wing section, a connecting middle section and a right wing section connected in sequence, wherein the shape of the connecting middle section matches a fuselage and is used to be connected to the fuselage; two ailerons are movably mounted at the trailing edges of the left and right wing sections, and the ailerons swing within a certain range; and a servo fairing is mounted on one side of the two ailerons close to the fuselage.

[0007] Furthermore, the main wing includes a main wing frame, a skin, and a lightweight foam component; the main wing frame includes a beam component, a rib component, a wing-to-body joint, an aileron mounting seat and a servo fairing mounting seat; the beam component is arranged along the span direction of the main wing, and the rib component is perpendicular to the beam component and overlaps the beam component; the wing-to-body joint is connected to the beam component and is located inside the middle section of the main wing connection, and wing-to-body mounting through holes are provided on the wing-to-body joint and the beam component; the aileron mounting seat and the servo fairing mounting seat are connected to the beam component and face the rear of the main wing; the skin covers the main wing frame, and the lightweight foam component is filled between the skin and the main wing frame.

[0008] Furthermore, the aileron includes an aileron skin, an aileron lightweight foam, and an aileron mounting joint. The aileron skin is filled with an aileron lightweight foam, the thickness of the aileron skin gradually decreases from the wing root to the wing tip, and the aileron skin is provided with an aileron mounting joint at the wing root for connection with the main wing;

[0009] The steering gear fairing comprises an upper cover and a lower cover, the inner mechanical mounting points of the upper cover and the lower cover are filled with fillers to form a mounting platform, and the upper cover and the lower cover are connected and fixed to the steering gear fairing mounting seat by connecting bolts;

[0010] The wing-body fusion wing uses connecting bolts to be screwed into pre-embedded threaded bushings on the fuselage to achieve connection between the wing and the fuselage.

[0011] Further, the aileron mounting seat includes an inner aileron mounting seat and an outer aileron mounting seat, both of which are supports with holes;

[0012] The aileron mounting joint comprises an inner aileron mounting joint and an outer aileron mounting joint;

[0013] The inner aileron mounting joint comprises a slot and a positioning hole vertically penetrating the slot, and the aileron servo connecting rod passes through the inner aileron mounting seat and is inserted into the inner aileron mounting joint slot, and is fixedly connected to the inner aileron mounting joint positioning hole by a pin;

[0014] The outer aileron mounting joint comprises a rotating shaft, and the outer aileron mounting joint rotating shaft passes through an outer side aileron mounting seat.

[0015] Furthermore, the beam assembly includes a front beam and a rear beam, the cross-sections of the front beam and the rear beam are C-shaped, the openings of the two are arranged opposite to each other, and the upper and lower end surfaces of the front beam and the rear beam are attached to the inner side of the skin; the two groups of rib assemblies are symmetrically arranged on both sides of the main wing, including root ribs arranged at the root of the main wing, end ribs at the tip of the main wing, and reinforcing ribs at the turning point of the rear beam, and the root ribs include three sections, which are respectively located between the front and rear beams and on the outside of the front and rear beams.

[0016] The present invention also provides a method for manufacturing a wing-body fusion wing, comprising the following steps:

[0017] The main wing skin is divided into upper wing skin and lower wing skin, both of which are symmetrically laid on the left and right wing sections. Several layers of upper wing skin are laid on the lower mold, and several layers of lower wing skin are laid on the upper mold. A certain length of the intersection area is reserved at the leading edge of the upper wing skin or the lower wing skin.

[0018] Arrange the beam assembly, rib assembly, lightweight foam, wing-body joint, and steering gear fairing mounting seat on the upper wing skin according to the corresponding positions, and lay adhesive film between adjacent parts; use small holes of different diameters and shapes at the wing-body mounting holes for positioning;

[0019] The upper mold and the lower mold of the main wing are molded together for pre-pressing;

[0020] Demoulding, connecting the lower wing skin and the upper wing skin leading edge area by overlapping in layers in an alternating manner using the junction area, and controlling the temperature during the overlapping process to compact the layers;

[0021] The upper mold and the lower mold are closed again, the mold gap is controlled within the first threshold, the first heating rate is used for heating, the temperature is kept for a certain period of time, the mold gap is adjusted, and the temperature keeping process is repeated until the mold gap is reduced to within the second threshold, thereby completing the co-curing molding;

[0022] The ailerons are formed by co-curing through compression molding;

[0023] The servo fairing is formed by hot pressing and co-curing;

[0024] Fix the main wing on the assembly jig, expand the small holes at the wing-body mounting holes, and assemble the aileron mounting seat, aileron, and servo fairing.

[0025] Furthermore, the compression molding and co-curing of the aileron specifically includes the following steps:

[0026] The aileron skin is divided into an upper aileron skin and a lower aileron skin, which are laid in the lower mold and the upper mold of the aileron respectively. A certain length of the intersection area is reserved at the leading edge of the layup of the upper aileron skin and the lower aileron skin;

[0027] Arrange the lightweight foam and aileron mounting joints on the aileron upper skin according to the corresponding positions, and lay adhesive film between adjacent parts;

[0028] The upper mold of the aileron is molded together with the lower mold for pre-pressing;

[0029] The mold is removed, and the leading edge areas of the upper skin of the aileron and the lower skin of the aileron are overlapped alternately layer by layer using the junction area, and the mold is closed and co-cured to form;

[0030] The hot-pressing co-curing molding of the steering gear fairing is specifically as follows: the upper and lower covers are hot-pressed and cured after being laid on respective molds, and a filling material is arranged in the mechanical installation area.

[0031] Furthermore, the beam assembly and the rib assembly are composite material parts, which are laid on the mold and pre-compacted and shaped;

[0032] The lightweight foam, wing-body joint, servo fairing mounting seat, aileron mounting seat, and aileron mounting joint are machined;

[0033] The beam assembly, rib assembly, lightweight foam, wing-body joint, servo fairing mounting seat, and aileron mounting seat are arranged symmetrically on the left and right through a positioning structure.

[0034] Furthermore, during the laying process of the upper and lower wing skins, an isolation layer is laid between the upper wing skin or the lower wing skin layers, and an isolation layer is laid on the leading edge of the corresponding lower wing skin or the upper wing skin layers;

[0035] The number of layers of the main wing skin decreases from the wing root to the wing tip, and the length of the lost layer ranges from 10 to 20 mm;

[0036] The first threshold is 0.5 mm to 1 mm, and the second threshold is 0 to 0.2 mm;

[0037] The first temperature rise rate is 50% to 80% of the ply curing curve, and the main wing co-curing molding temperature rise rate and temperature drop rate are 50% to 80% of the ply curing curve.

[0038] Furthermore, the wing-body mounting holes include four holes arranged front and back. After expansion, one of the two mounting holes near the head of the fuselage is a precision hole matching the size of the bolts, and the other is an oblong hole extending along the span direction; the two holes near the tail of the fuselage are larger than the bolt diameter.

[0039] The beneficial effects of the present invention compared with the prior art are as follows:

[0040] The present invention provides a wing-body fusion wing, which adopts a left-right wing integrated design and molding structure, has a simple wing structure, a small number of parts, and is easy to assemble and disassemble.

[0041] According to the aerodynamic shape characteristics of the wing-body fusion and the characteristics of large load bearing, the present invention rationally arranges the load-bearing components such as skin, beams, ribs, designs the integrated molding structure of the left and right wings, and rationally controls the process parameters of the molding process to achieve integrated molding of larger structural components under large load conditions.

[0042] The present invention provides a method for manufacturing a wing-body fusion wing. The main wing and aileron of the wing load-bearing components are assembled together by integral molding and co-curing, which reduces the number of wing structure parts, improves the bearing performance of the wing structure, simplifies the production process, shortens the wing structure manufacturing cycle, and reduces costs.

[0043] The wing structure and manufacturing method of the present invention can effectively improve the structural bearing performance, solve the problems of the large number of parts, complex manufacturing process, long production cycle and high cost of traditional assembled wing structures, and is suitable for the design and manufacture of wings for aircraft such as drones. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] The included drawings are used to provide a further understanding of the embodiments of the present invention, which constitute a part of the specification, are used to illustrate the embodiments of the present invention, and together with the text description, explain the principles of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0045] Figure 1 A schematic diagram of the structure of a wing-body blended wing provided in a specific embodiment of the present invention;

[0046] Figure 2 A schematic diagram of the exploded structure of the main wing of a wing-body blended wing provided in a specific embodiment of the present invention;

[0047] Figure 3 A schematic diagram of the exploded structure of the aileron of a wing-body blended wing provided by a specific embodiment of the present invention;

[0048] Figure 4 A schematic diagram of the structure of a wing-body blended wing servo fairing provided in a specific embodiment of the present invention;

[0049] Figure 5 A partial cross-sectional view of the wing-fuselage installation of a wing-body blended wing provided in a specific embodiment of the present invention, wherein the above-mentioned figure includes the following figure numbers:

[0050] 10. Skin; 20. Beam assembly; 21. Front beam; 22. Rear beam; 30. Left rib assembly; 31. Left root rib; 32. Left reinforcing rib; 33. Left end rib; 40. Right rib assembly; 41. Right root rib; 42. Right reinforcing rib; 43. Right end rib; 50. Wing-body joint; 51. Left wing-body joint; 52. Right wing-body joint; 60. Servo fairing mounting seat; 61. Left servo fairing mounting seat; 62. Right servo fairing mounting seat; 70. Left aileron mounting seat; 71. Left inner aileron mounting seat; 72. Left outer aileron mounting seat; 80. Right aileron mounting seat; 81. Right inner aileron mounting seat; 82. Right outer aileron mounting seat; 90. Lightweight foam assembly; 100. Main wing; 110. Bolt; 120. Threaded bushing; 200. Aileron; 210. Left aileron; 211. Aileron skin; 212. Aileron lightweight foam; 213. Inboard aileron mounting joint; 214. Outboard aileron mounting joint; 215. Servo connecting rod; 216. Pin; 220. Right aileron; 300. Servo fairing; 310. Left servo fairing assembly; 311. Servo fairing upper cover; 312. Servo fairing lower cover; 320. Right servo fairing assembly; 1000. Wing; 2000. Fuselage. DETAILED DESCRIPTION

[0051] Specific embodiments of the present invention are described in detail below. In the following description, for the purpose of explanation and not limitation, specific details are set forth to help fully understand the present invention. However, it will be apparent to those skilled in the art that the present invention may also be practiced in other embodiments that depart from these specific details.

[0052] It should be noted that in order to avoid obscuring the present invention due to unnecessary details, only the device structure and / or processing steps closely related to the scheme of the present invention are shown in the drawings, while other details that are not closely related to the present invention are omitted.

[0053] The present invention provides a wing-body blended wing, such as Figure 1 As shown, the main structure includes: a main wing 100, an aileron 200 and a steering gear fairing 300. The main wing 100 is a symmetrical structure of left and right wings formed in one piece, including a left wing section, a connecting middle section, and a right wing section. The shape of the connecting middle section matches the fuselage and is used for connection with the fuselage; two ailerons 200 are installed at the trailing edges of the left and right wing sections, and the ailerons 200 can swing up and down around the hinge; the two ailerons 200 are installed near the side of the fuselage. The steering gear fairing 300. The present invention adopts a left and right wing integrated structure, the wing structure is simple, the number of parts is small, and it is easy to disassemble and assemble.

[0054] Furthermore, if Figure 2As shown, the main wing 100 includes a main wing frame, a skin 10, and a lightweight foam component 90. The main wing frame includes a beam component 20, a rib component 30 / 40, a wing-body joint 50, an aileron mounting seat 70 / 80, and a servo fairing mounting seat 60; the beam component 20 is arranged along the wingspan direction of the main wing 100, and the rib component 30 / 40 is perpendicular to the beam component 20 and overlaps with the beam component 20; the wing-body joint 50 is connected to the beam component 20 and is located inside the middle section of the main wing 100. The wing-body joint and the beam component are provided with a wing-body mounting through hole for connection with the fuselage; the aileron mounting seat 70 / 80 and the servo fairing mounting seat 60 are connected to the beam component 20 and face the rear of the main wing 100. The skin 10 covers the main wing frame, and the lightweight foam component 90 is filled between the skin 10 and the main wing frame. The aileron mounting seat 70 / 80 includes an inner aileron mounting seat 71 / 81 and an outer aileron mounting seat 72 / 82, both of which are supports with holes.

[0055] Furthermore, if Figure 3 As shown, the aileron 200 includes a left aileron 210 and a right aileron 220 that are symmetrically arranged on the left and right sides, including an aileron skin 211 , an aileron lightweight foam 212 , an inner aileron mounting joint 213 and an outer aileron mounting joint 214 . The aileron skin 211 is filled with aileron lightweight foam 212, and the thickness of the aileron skin 211 gradually decreases from the wing root to the wing tip. The inner aileron mounting joint 213 and the outer aileron mounting joint 214 are respectively arranged on the two sides of the wing root of the aileron skin 211 facing the wing root and the wing tip of the main wing. The inner aileron mounting joint 213 includes a slot parallel to the trailing edge of the main wing and a positioning hole vertically passing through the slot. The servo connecting rod 215 passes through the inner aileron mounting seat 71 / 81 and is inserted into the slot of the inner aileron mounting joint 213, and is fixedly connected to the positioning hole of the inner aileron mounting joint 213 by a pin 216. The outer aileron mounting joint 214 includes a rotating shaft parallel to the trailing edge of the main wing. The rotating shaft of the outer aileron mounting joint 214 passes through the outer aileron mounting seat 72 / 82 to connect the aileron 200 with the main wing 100.

[0056] Furthermore, if Figure 4 As shown, the servo fairing 310 includes a left servo fairing 310 and a right servo fairing 320 which are symmetrically arranged. The servo fairing includes an upper servo fairing cover and a lower servo fairing cover. The servo fairing body is a composite laminated structural member, and fillers are filled at the mechanical mounting points inside the cover to form a mounting platform. The connecting bolts are connected and fixed to the main wing through the upper servo fairing cover, the servo fairing mounting seat and the mechanical mounting holes of the lower servo fairing cover.

[0057] Preferably, the main wing 100 is an integrated design of a composite skin 10, a composite front beam 21, a composite rear beam 22, a composite rib assembly 30 / 40, a lightweight foam assembly 90, a metal wing-body joint 50 and a metal servo fairing mounting seat 60, and is manufactured by an overall co-curing molding process, and the metal aileron mounting seat 70 / 80 is mechanically connected to the aforementioned molded parts. The aileron 200 is an integral molded part of a composite aileron skin 211, aileron lightweight foam 212 and a metal aileron mounting joint 213 / 214. The aileron 200 is respectively installed into the inner aileron mounting seat 71 / 81 and the outer aileron mounting seat 72 / 82 through the servo connecting rod 215 and the outer aileron mounting joint 214. The servo connecting rod 215 is inserted into the slot of the inner aileron mounting joint 213 and fixed by the pin 216 to connect the aileron 200 to the main wing 100; the servo fairing 300 is installed and fixed by bolts passing through the servo fairing 300 and the servo fairing mounting seat 60.

[0058] Furthermore, if Figure 5 As shown, the wing 1000 is connected to the fuselage by connecting bolts 110 that pass through the wing-to-body joint 50 and are screwed into the pre-embedded threaded bushing 120 on the fuselage 2000 .

[0059] In order to ensure that the wing can be connected to the fuselage efficiently and accurately, the four mounting holes of the wing and the fuselage are of different diameters and shapes. The two mounting holes at the front end are designed as precision holes that precisely match the bolts, and the other is designed as an oblong hole to ensure heading accuracy (the length of the oblong hole is along the span direction). The two holes at the rear end are designed as large holes. In order to reduce the deformation effect after the wing surface is formed, the wing-body mounting holes on the wing surface are manufactured by step-by-step processing. During the co-curing process of the wing surface, the wing-body mounting holes are positioned by the above-mentioned small precision holes of different diameters and shapes (the theoretical four wing mounting holes can be proportionally reduced, and the use of small holes of different diameters and shapes can ensure the release of thermal stress during the curing process). After the wing surface is formed and demolded, it is fixed to the assembly jig through the positioning holes and the outer shape card plate. A special drilling jig for the wing-body docking hole is used. The wing-body docking mounting hole is made into a final hole by expanding the hole once and reaming the hole twice, thereby improving the docking quality of the wing and fuselage.

[0060] The present invention also provides a method for manufacturing a wing of a UAV with a wing-body fusion, comprising the following steps:

[0061] The main wing skin is divided into upper wing skin and lower wing skin, both of which are symmetrically laid on the left and right wing sections. Several layers of upper wing skin are laid on the lower mold, and several layers of lower wing skin are laid on the upper mold. A certain length of the intersection area is reserved at the leading edge of the upper wing skin or the lower wing skin.

[0062] Arrange the beam assembly, rib assembly, lightweight foam, wing-body joint, and steering gear fairing mounting seat on the upper wing skin according to the corresponding positions, and lay adhesive film between adjacent parts; use small holes of different diameters and shapes at the wing-body mounting holes for positioning;

[0063] The upper mold and the lower mold of the main wing are molded together for pre-pressing;

[0064] Demoulding, connecting the lower wing skin and the upper wing skin leading edge area by overlapping in layers in an alternating manner using the junction area, and controlling the temperature during the overlapping process to compact the layers;

[0065] The upper mold and the lower mold are closed again, the mold gap is controlled within the first threshold, the first heating rate is used for heating, the temperature is kept for a certain period of time, the mold gap is adjusted, and the temperature keeping process is repeated until the mold gap is reduced to within the second threshold, thereby completing the co-curing molding;

[0066] The ailerons are formed by co-curing through compression molding;

[0067] The servo fairing is formed by hot pressing and co-curing;

[0068] Fix the main wing on the assembly jig, expand the small holes at the wing-body mounting holes, and assemble the aileron mounting seat, aileron, and servo fairing.

[0069] The invention provides a method for manufacturing a wing-body fused wing for an unmanned aerial vehicle. The main wing and aileron of the wing load-bearing components are assembled together by integral molding and co-curing. This reduces the number of wing structure parts, improves the bearing performance of the wing structure, simplifies the production process, shortens the wing structure manufacturing cycle, and reduces costs.

[0070] Furthermore, the first temperature rise rate is 50% to 80% of the ply curing curve. ， The heating rate and cooling rate of the main wing co-curing molding are 50% to 80% of the ply curing curve 。 The first threshold is 0.5 mm to 1 mm, and the second threshold is 0 mm to 0.2 mm.

[0071] Furthermore, the specific manufacturing method of the aileron includes:

[0072] The aileron skin is divided into an upper aileron skin and a lower aileron skin, which are laid in the lower mold and the upper mold of the aileron respectively. A certain length of the intersection area is reserved at the leading edge of the layup of the upper aileron skin and the lower aileron skin;

[0073] Arrange the lightweight foam and aileron mounting joints on the aileron upper skin according to the corresponding positions, and lay adhesive film between adjacent parts;

[0074] The upper mold of the aileron is molded together with the lower mold for pre-pressing;

[0075] The mold is removed, and the leading edge areas of the aileron upper skin and the aileron lower skin are overlapped alternately layer by layer using the junction area, and the mold is closed and co-cured to form.

[0076] Furthermore, the specific manufacturing method of the steering gear fairing includes:

[0077] The upper and lower covers are formed by hot pressing and curing after being laid on their respective molds, and filling materials are arranged in the mechanical installation area.

[0078] Furthermore, the beam assembly and rib assembly are composite material parts, which are laid on the mold for pre-compaction and shaping; the lightweight foam, wing-body joint, servo fairing mounting seat, aileron mounting seat, and aileron mounting joint are machined; the beam assembly, rib assembly, lightweight foam, wing-body joint, servo fairing mounting seat, and aileron mounting seat are installed symmetrically on the left and right through a positioning structure.

[0079] Furthermore, during the laying process of the upper and lower wing skins, an isolation layer is affixed between the junction areas of the upper wing skin or the lower wing skin, and an isolation layer is affixed to the leading edge of the corresponding lower wing skin or the upper wing skin to facilitate the subsequent overlap of the two.

[0080] Furthermore, the wing-body mounting holes include four arranged front and rear. After expansion, one of the two mounting holes near the head of the fuselage is a precision hole matching the size of the bolts, and the other is an oblong hole extending along the span direction; the two holes near the tail of the fuselage are larger than the bolt diameter.

[0081] Furthermore, the number of main wing skin layers decreases from the wing root to the wing tip, reducing the structural weight while meeting the structural strength.

[0082] In the manufacturing method of the present invention, in order to ensure the molding quality and deformation control of the main wing during the co-curing molding process, the mold fixture must ensure sufficient rigidity while ensuring that the heat transfer efficiency of each part is basically consistent. According to the characteristics of the selected composite material resin system, the initial insulation time is appropriately extended during the heating process to reduce the heating rate. For the bolt pre-tightening molding process, the fastening bolts should be tightened several times during the heating process to ensure that the mold fixture fits well. The cooling rate should also be reduced during the cooling process to ensure the molding quality of the main wing structure and reduce its deformation. Specifically, the method for controlling the molding quality and deformation control of the main wing mainly includes:

[0083] In terms of design, 1) the wing structure adopts a symmetrical ply laying method for both left and right wings to reduce deformation caused by asymmetric ply design; 2) optimize the ply drop design, lengthen the ply drop length, reduce the local stiffness change rate of the parts, and reduce the structural deformation caused by large local stiffness changes. Preferably, the ply drop length is preferably 10 to 20 mm.

[0084] During the manufacturing process, 1) the laying and dropping of each part are carried out strictly in accordance with the designed laying and cutting method; 2) For composite parts such as beams and ribs, the pre-compacting method is used to expel the air between the layers as much as possible to make the layers fit tightly; 3) According to the characteristics of each part, such as the fitting plane, positioning holes, etc., the left-right symmetric positioning of the wing parts is ensured by positioning methods such as clamps and locating pins; 4) The upper and lower molds on the wing are closed, and the upper and lower molds are pre-pressed by tightening bolts to ensure that all parts fit tightly; 5) After pre-pressing, the upper mold is demolded, and the leading edge areas of the upper and lower skins are connected in an overlapping manner, and during the overlapping process, an electric iron is used to assist in laying at the required temperature (not exceeding the glass transition temperature) to compact the layers; 6) The upper and lower skins After the leading edge area is connected, the mold is re-closed, and the initial mold gap is controlled at 0.5mm~1mm, and the furnace is put into heating at a low heating rate (not exceeding the glass transition temperature), and kept warm for a certain period of time to ensure that the wing surface structure is evenly heated. The mold is tightened after entering the furnace to ensure that the mold gap is controlled within 0.2mm before curing. During the curing process, the heating and cooling time are appropriately extended according to the ply curing curve to ensure uniform temperature transfer and stress release after molding; 7) After the wing surface is demoulded, it is fixed to the assembly frame through the wing-fuselage mounting hole and the outer shape card plate. A special drilling jig for the wing-fuselage docking hole is used. The wing-fuselage docking mounting hole is made into a final hole through one hole expansion and two hole boring methods, which reduces the error caused by residual deformation due to curing and improves the quality of wing-fuselage docking.

[0085] According to a specific embodiment of the present invention, a UAV wing-body fusion wing and a manufacturing method are provided, such as Figure 1 As shown, the wing structure includes: a main wing 100, an aileron 200 and a servo fairing 300. The aileron 200 is respectively installed in the inner aileron mounting seat 71 / 81 and the outer aileron mounting seat 72 / 82 through a servo connecting rod 215 and an outer aileron mounting joint 214. The servo connecting rod 215 is inserted into the slot of the inner aileron mounting joint 213 and fixed by a pin 216, so that the aileron 200 is connected and fixed to the main wing 100; the servo fairing 300 is connected through bolts passing through the servo fairing 300 and the servo fairing mounting seat 60 to achieve connection and fixation with the main wing 100. The main wing 100 connection bolt 110 passes through the wing-body joint 50 and is screwed into the embedded threaded bushing 120 on the fuselage to achieve connection between the wing and the fuselage.

[0086] like Figure 2As shown, the main wing 100 includes a skin 10, a beam assembly 20, a rib assembly 30 / 40, a wing-body joint 50, a steering gear fairing mounting seat 60, an aileron mounting seat 70 / 80 and a lightweight foam assembly 90, wherein the skin 10, the beam assembly 20, and the rib assembly 30 / 40 are all composite materials structures, and they all need to be preformed separately before the overall compression molding; the wing-body joint 50, the steering gear fairing mounting seat 60, and the aileron mounting seat 70 / 80 are aluminum alloy structures, which are separately machined. The beam assembly 20, the rib assembly 30 / 40, the wing-body joint 50, the steering gear fairing mounting seat 60 and the lightweight foam assembly 90 are separately molded and then assembled to form the main wing skeleton, and the skin 10 covers the above-mentioned main wing skeleton and is integrally molded and co-cured. The number of layers of the skin 10 decreases from the wing root to the wing tip, which reduces the structural weight on the basis of meeting the structural strength. The beam assembly 20 includes a front beam 21 and a rear beam 22, and the beam cross section is "C" shaped. The front beam 21 and the rear beam 22 are arranged with openings in the cross section opposite to each other. The upper end face and the lower end face of the "C" shape are attached to the inner side of the skin 10, and the remaining faces are attached to the lightweight foam assembly 90 and the outer contour surface of the rib assembly. The left rib assembly 30 and the right rib assembly 40 are symmetrically arranged on both sides of the wing 1000, including root ribs 31 / 41, reinforcing ribs 32 / 42, and end ribs 33 / 43. The rib cross section is "C" shaped. The root rib 31 / 41 is arranged at the inner root of the wing and consists of three sections: front, middle, and rear. The middle section is used for force transmission, and the front and rear sections are used for skin shaping. The reinforcing ribs 32 / 42 are arranged at the turning point of the rear beam, and the end ribs 33 / 43 are arranged at the wing tip. The root ribs, reinforcing ribs, and end ribs connect the front beam and the rear beam, and the front beam, the rear beam, and the skin partition area are filled with full-height lightweight foam. The wing-body joint 50 includes a left wing-body joint 51 and a right wing-body joint 52, which are symmetrically arranged on both sides of the wing 1000. The wing-body joint 50 connects the front beam 21 and the rear beam 22, and is fitted with the inner surfaces of the front beam 21 and the rear beam 22. The remaining surfaces are respectively fitted with the inner side surface of the skin 10 and the outer contour surface of the lightweight foam (that is, the surfaces of the left wing-body joint and the right wing-body joint are fitted with the skin, the front beam, the rear beam and the lightweight foam). Between the above-mentioned contact surfaces, except for the contact surface between the beam assembly 20 and the skin 10, foam film needs to be pasted between the contact surfaces. The servo fairing mounting seat 60 includes a left servo fairing mounting seat 61 and a right servo fairing mounting seat 62, which are symmetrically arranged on both sides of the wing 1000, and the front end surface of the servo fairing mounting seat 60 is in contact with the outer side of the web of the rear beam 22, and the upper and lower surfaces are in contact with the inner side of the skin 10. The partition area formed by the above parts is filled with a lightweight foam component 90.The aileron mounting seat 70 / 80 includes an inner aileron mounting seat 71 / 81 and an outer aileron mounting seat 72 / 82. The inner aileron mounting seat 71 / 81 is arranged on the inner side of the trailing edge of the wing 1000 (the rear side of the web of the inner rear beam of the wing), and the outer aileron mounting seat 72 / 82 is arranged on the outer side of the trailing edge of the wing 1000 (the rear side of the web of the outer rear beam of the wing). The aileron mounting seat 70 / 80 is formed separately and connected with the aforementioned molded parts by mechanical mounting nails. Specifically, the aileron mounting seats 70 / 80 can all adopt a support with an opening, wherein the inner aileron mounting seat 71 / 81 can be connected to the rear beam 22 and the skin 10, and fixed by gluing or screws, so as to facilitate the assembly of the steering gear shaft; the outer aileron mounting seat 72 / 82 only supports the aileron and can be directly connected to the skin 10.

[0087] The aileron 200 includes a left aileron 210 and a right aileron 220. The left aileron 210 and the right aileron 220 are symmetrically arranged on both sides of the wing 1000. Figure 3 As shown, the aileron structure includes an aileron skin 211, an aileron light foam 212, an inner aileron mounting joint 213, an outer aileron mounting joint 214, a servo connecting rod 215 and a pin 216. The aileron light foam 212, the inner aileron mounting joint 213 and the outer aileron mounting joint 214 are formed separately and then assembled to form an aileron skeleton. The aileron skin 211 is a composite material structure, which is coated on the outer side of the aileron skeleton composed of the aileron light foam 212, the inner aileron mounting joint 213 and the outer aileron mounting joint 214. The adjacent contact surfaces of the aileron skin 211, the aileron light foam 212, the inner aileron mounting joint 213 and the outer aileron mounting joint 214 are all pasted with foam film, and the main structure of the aileron is formed by a molding process. The servo connecting rod 215 passes through the inner aileron mounting seat 71 / 81 and is inserted into the slot of the inner aileron mounting joint 213 and is connected and fixed by the pin 216.

[0088] The servo fairing 300 includes a left servo fairing assembly 310 and a right servo fairing assembly 320. The servo fairing assembly 310 and the right servo fairing assembly 320 are symmetrically arranged on both sides of the wing 1000. The servo fairing assembly 310 is composed of a servo fairing upper cover 311 and a servo fairing lower cover 312. Both the servo fairing upper cover 311 and the servo fairing lower cover 312 are composite laminated shell structures. Fillers are filled at the mechanical installation points on the inner side of the cover to form an installation platform, which serves as the mechanical installation docking surface of the servo fairing upper cover 311 and the servo fairing lower cover 312 and the installation contact surface between the servo fairing 300 and the servo fairing mounting seat 60. Specifically, the connecting bolts are connected and fixed to the main wing 100 through the mechanical installation holes of the servo fairing upper cover 311, the servo fairing mounting seat 60 and the servo fairing lower cover 312. Figure 4As shown, the side of the servo fairing 300 facing the main wing is cut to match the shape of the main wing, and the side of the servo fairing 300 facing the aileron is extended to match the shape of the aileron to form a complete wing surface. A groove is provided on the side of the servo fairing 300 facing the servo fairing mounting seat 60, and the height of the upper and lower surfaces of the groove is consistent with the thickness of the ear piece of the fairing mounting seat 60, which is used to match and connect with the fairing mounting seat 60.

[0089] like Figure 5 As shown, the wing 1000 is connected to the fuselage 2000 by means of a bolt 110 passing through the mounting hole of the wing-body joint 50 and then screwed into a pre-embedded threaded bushing 120 on the fuselage 2000 .

[0090] In addition, the wing structure can pre-embed electrical and control system channels on relevant paths according to the needs of the electrical and control systems.

[0091] It should be noted that the main wing and aileron adopt a full-thickness sandwich structure design, that is, for the thinner wing body, the aerodynamic shape is maintained by adding full-thickness lightweight foam. At the same time, the stiffness of the skin is supported, the strength of the wing is improved, and then the load-bearing capacity is improved.

[0092] According to another embodiment of the present invention, a method for manufacturing a wing-body fusion wing of an unmanned aerial vehicle is provided, comprising the following steps:

[0093] The manufacture of the main wing 100, first, lay each layer of the upper wing skin 10 on the lower mold, each layer reserves a certain length of the intersection area at the leading edge, in the above laying process, paste an isolation layer between the intersection areas of each layer, to prevent adhesion between the layers in the reserved intersection area during the compaction process. Lay each layer of the lower wing skin 10 on the upper mold, paste an isolation layer between each layer at the leading edge, the length of the isolation layer should be longer than the length of the additional reserved intersection area of ​​the upper wing, and other laying requirements are consistent with the laying requirements of the upper wing skin layer. Lay the front beam 21, the rear beam 22, the wing rib assembly 30 / 40 and other laminated parts on their respective molds for pre-pressing and shaping, and the lightweight foam 90 and the metal wing-body joint 50, the servo fairing mounting seat 60, and the aileron mounting seat 70 / 80 are machined separately. Secondly, the pre-pressed and shaped front beam 21, rear beam 22, rib assembly 30 / 40 and other laminated parts and machined parts lightweight foam 90, metal wing-body joint 50, and steering gear fairing mounting seat 60 are arranged on the upper wing skin according to the corresponding positions, and the adhesive film is laid between adjacent parts. Finally, the pre-compacted lower skin 10 is taken out from the upper mold, covered on the above-mentioned assembly, the isolation layer between the layers of the leading edge of the upper and lower wing skins 10 is removed, and the paving connection of the leading edge of the upper and lower wing skins 10 is completed alternately layer by layer (that is, the upper wing skin junction area is placed where the lower wing skin is pasted with the isolation layer), that is, the upper and lower wing skins 10 are connected as a whole. The upper mold and the lower mold are combined, and the co-curing molding of the wing-body fusion main wing 100 is completed in the furnace. After demoulding, the aileron mounting seat 70 / 80 is installed on the assembly jig. On the assembly jig, the wing-fuselage mounting hole expansion and the aileron mounting seat assembly are completed by means of drilling jigs, positioning jigs, etc.

[0094] The manufacture of the aileron 200, first, lay each layer of the aileron upper skin 211 on the lower mold, and reserve a certain length of the aileron junction area at the leading edge of each layer. During the laying process of the above layers, an isolation layer is pasted between the aileron junction areas of each layer to prevent adhesion between the layers in the aileron junction area during the compaction process. Lay each layer of the aileron lower skin 211 on the upper mold, and paste an isolation layer between each layer at the leading edge. The length of the isolation layer should be longer than the length of the aileron junction area reserved for the aileron upper skin. Other laying requirements are consistent with the laying requirements of the rudder surface skin 211. The lightweight foam 212, aileron mounting joints 213 / 214, servo connecting rods 215, pins 216 and other parts are machined separately. Secondly, the lightweight foam 212 and aileron mounting joints 213 / 214 are arranged on the aileron upper skin 211 according to the corresponding positions, and a film is laid between adjacent parts. Finally, the pre-compacted aileron lower skin 211 is taken out from the upper mold and covered on the above assembly, the isolation layer between the leading edge layers of the upper and lower skins 211 of the aileron is removed, and the leading edge of the upper and lower skins 211 are laid and connected alternately layer by layer (i.e., the aileron upper skin-ailer junction area is placed at the aileron lower skin pasting isolation layer), that is, the upper and lower wing skins 211 are connected as a whole. The upper mold is closed with the lower mold, and the wing-body fusion aileron 200 is put into the furnace to complete the co-curing molding and demoulding.

[0095] In the manufacture of the servo fairing 300, both the upper and lower covers are laminated structural parts, which are cured and formed after being laid on their respective molds, and filling materials are arranged in the mechanical installation area.

[0096] The assembly of the wing is to complete the positioning and fixing of the main wing 100 on the assembly jig, and the aileron 200 is connected and fixed to the aileron mounting seat 70 / 80 through the steering gear connecting rod 215 and the pin 216. The steering gear fairing 300 is connected and fixed to the steering gear fairing mounting seat 60 through bolts.

[0097] In summary, the present invention provides a wing-body fused wing of an unmanned aerial vehicle and a manufacturing method thereof. The main load-bearing structures, the main wing and the aileron, of the wing structure adopt a full-thickness sandwich structure design and are integrally molded and co-cured. The number of structural parts is small and the load-bearing level is high. At the same time, the structural compression molding method effectively reduces the number of wing structural parts, simplifies the production process, shortens the wing structure manufacturing cycle, and reduces costs.

[0098] Features described and / or illustrated above for one embodiment may be used in the same or similar manner in one or more other embodiments, and / or combined with or used in place of features in other embodiments.

[0099] It should be emphasized that the term "include / comprises" when used herein refers to the presence of features, integers, steps or components, but does not exclude the presence or addition of one or more other features, integers, steps, components or combinations thereof.

[0100] The many features and advantages of these embodiments are apparent from this detailed description, and thus the appended claims are intended to cover all such features and advantages of these embodiments that fall within their true spirit and scope. Furthermore, since numerous modifications and changes will readily occur to those skilled in the art, it is not intended that the embodiments of the invention be limited to the exact construction and operation illustrated and described, but rather all suitable modifications and equivalents falling within the scope thereof are intended to be covered.

[0101] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

[0102] Parts of the present invention that are not described in detail are well known to those skilled in the art.

Claims

1. A wing-body blended wing, characterized in that: It includes a main wing, ailerons and a servo fairing. The main wing is a symmetrical structure with left and right wings formed in one piece, including a left wing section, a connecting middle section and a right wing section connected in sequence. The shape of the connecting middle section matches the fuselage and is used to be connected to the fuselage. The two ailerons are movably installed at the trailing edges of the left and right wing sections, and the ailerons can swing within a certain range. The servo fairing is installed on the side of the two ailerons close to the fuselage.

2. The wing-body blended wing according to claim 1, characterized in that: The main wing includes a main wing frame, a skin, and a lightweight foam component; the main wing frame includes a beam component, a rib component, a wing-to-body joint, an aileron mounting seat and a servo fairing mounting seat; the beam component is arranged along the span direction of the main wing, and the rib component is perpendicular to the beam component and overlaps the beam component; the wing-to-body joint is connected to the beam component and is located inside the middle section of the main wing connection, and wing-to-body mounting through holes are provided on the wing-to-body joint and the beam component; the aileron mounting seat and the servo fairing mounting seat are connected to the beam component and face the rear of the main wing; the skin covers the main wing frame, and the lightweight foam component is filled between the skin and the main wing frame.

3. The wing-body blended wing according to claim 2, characterized in that: The aileron comprises an aileron skin, an aileron lightweight foam, and an aileron mounting joint. The aileron skin is filled with an aileron lightweight foam, the thickness of the aileron skin gradually decreases from the wing root to the wing tip, and the aileron mounting joint is arranged at the wing root of the aileron skin for connecting with the main wing; The steering gear fairing comprises an upper cover and a lower cover, the inner mechanical mounting points of the upper cover and the lower cover are filled with fillers to form a mounting platform, and the upper cover and the lower cover are connected and fixed to the steering gear fairing mounting seat by connecting bolts; The wing-body fusion wing uses connecting bolts to be screwed into pre-embedded threaded bushings on the fuselage to achieve connection between the wing and the fuselage.

4. The wing-body blended wing according to claim 3, characterized in that: The aileron mounting seat includes an inner aileron mounting seat and an outer aileron mounting seat, both of which are supports with holes; The aileron mounting joint comprises an inner aileron mounting joint and an outer aileron mounting joint; The inner aileron mounting joint comprises a slot and a positioning hole vertically penetrating the slot, and the aileron servo connecting rod passes through the inner aileron mounting seat and is inserted into the inner aileron mounting joint slot, and is fixedly connected to the inner aileron mounting joint positioning hole by a pin; The outer aileron mounting joint comprises a rotating shaft, and the outer aileron mounting joint rotating shaft passes through an outer side aileron mounting seat.

5. The wing-body blended wing according to claim 4, characterized in that: The beam assembly includes a front beam and a rear beam, the cross-sections of the front beam and the rear beam are C-shaped, the openings of the two are arranged opposite to each other, and the upper and lower end faces of the front beam and the rear beam are attached to the inner side of the skin; the two groups of rib assemblies are symmetrically arranged on both sides of the main wing, including root ribs arranged at the root of the main wing, end ribs at the tip of the main wing, and reinforcing ribs at the turning point of the rear beam, and the root ribs include three sections, which are respectively located between the front and rear beams and on the outside of the front and rear beams.

6. A method for manufacturing a wing-body blended wing, characterized in that: The following steps are included The main wing skin is divided into upper wing skin and lower wing skin, both of which are symmetrically laid on the left and right wing sections. Several layers of upper wing skin are laid on the lower mold, and several layers of lower wing skin are laid on the upper mold. A certain length of the intersection area is reserved at the leading edge of the upper wing skin or the lower wing skin. Arrange the beam assembly, rib assembly, lightweight foam, wing-body joint, and steering gear fairing mounting seat on the upper wing skin according to the corresponding positions, and lay adhesive film between adjacent parts; use small holes of different diameters and shapes at the wing-body mounting holes for positioning; The upper mold and the lower mold of the main wing are molded together for pre-pressing; Demoulding, connecting the lower wing skin and the upper wing skin leading edge area by overlapping in layers in an alternating manner using the junction area, and controlling the temperature during the overlapping process to compact the layers; The upper mold and the lower mold are closed again, the mold gap is controlled within the first threshold, the first heating rate is used for heating, the temperature is kept for a certain period of time, the mold gap is adjusted, and the temperature keeping process is repeated until the mold gap is reduced to within the second threshold, thereby completing the co-curing molding; The ailerons are formed by co-curing through compression molding; The servo fairing is formed by hot pressing and co-curing; Fix the main wing on the assembly jig, expand the small holes at the wing-body mounting holes, and assemble the aileron mounting seat, aileron, and servo fairing.

7. The method for manufacturing a wing-body blended wing according to claim 6, characterized in that: The aileron molding co-curing molding specifically includes the following steps The aileron skin is divided into an upper aileron skin and a lower aileron skin, which are laid in the lower mold and the upper mold of the aileron respectively. A certain length of the intersection area is reserved at the leading edge of the layup of the upper aileron skin and the lower aileron skin; Arrange the lightweight foam and aileron mounting joints on the aileron upper skin according to the corresponding positions, and lay adhesive film between adjacent parts; The upper mold of the aileron is molded together with the lower mold for pre-pressing; The mold is removed, and the leading edge areas of the upper skin of the aileron and the lower skin of the aileron are overlapped alternately layer by layer using the junction area, and the mold is closed and co-cured to form; The hot-pressing co-curing molding of the steering gear fairing is specifically as follows: the upper and lower covers are hot-pressed and cured after being laid on respective molds, and a filling material is arranged in the mechanical installation area.

8. The method for manufacturing a wing-body blended wing according to claim 6, characterized in that: The beam assembly and rib assembly are composite material parts, which are laid on the mold and pre-compacted and shaped; The lightweight foam, wing-body joint, servo fairing mounting seat, aileron mounting seat, and aileron mounting joint are machined; The beam assembly, rib assembly, lightweight foam, wing-body joint, servo fairing mounting seat, and aileron mounting seat are arranged symmetrically on the left and right through a positioning structure.

9. The method for manufacturing a wing-body blended wing according to claim 6, characterized in that: During the laying process of the upper and lower wing skins, an isolation layer is applied between the joint areas of the upper wing skin or the lower wing skin, and an isolation layer is applied to the leading edge of the corresponding lower wing skin or the upper wing skin; The number of layers of the main wing skin decreases from the wing root to the wing tip, and the length of the lost layer ranges from 10 to 20 mm; The first threshold is 0.5 mm to 1 mm, and the second threshold is 0 to 0.2 mm; The first temperature rise rate is 50% to 80% of the ply curing curve, and the main wing co-curing molding temperature rise rate and temperature drop rate are 50% to 80% of the ply curing curve.

10. The method for manufacturing a wing-body blended wing according to claim 6, characterized in that: The wing-body mounting holes include four holes arranged front and back. After expansion, one of the two mounting holes near the head of the fuselage is a precision hole matching the size of the bolts, and the other is an oblong hole extending along the span direction; the two holes near the tail of the fuselage are larger than the bolt diameter.

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