Medium-sized unmanned aerial vehicle block type wing and dieless forming process thereof

Abstract

The invention discloses a partitioned wing of a medium-sized unmanned aerial vehicle and a dieless forming process of the partitioned wing, and belongs to the technical field of unmanned aerial vehicles. The wing comprises a wing framework and a partitioned skin covering the outer side of the wing framework; the die-free forming process comprises the following steps: precisely positioning and bonding wing ribs, a C-shaped beam web and an upper beam cap by adopting a framework positioning fixture formed by splicing wooden laminates to form a framework frame, and assembling a framework after bonding a lower beam cap; the framework is coated with an adhesive, partitioned skins are laid on the framework, the front edge skin and the middle section skin are fixed to the main beam in a riveting and bonding mixed mode, and the rear edge skin is fixed to the auxiliary beam in a pure bonding mode; and the assembly is placed between an upper airfoil skin pressure-maintaining fixture and a lower airfoil skin pressure-maintaining fixture which are also formed by splicing wooden laminates for mold closing, pressure maintaining and curing. According to the invention, through the segmented skin design and the dieless forming method, the forming process is simplified, the production and maintenance cost is reduced, and light-weight, high-strength and high-efficiency manufacturing of the wing is realized.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of medium-sized unmanned aerial vehicles, and particularly relates to a medium-sized unmanned aerial vehicle block type wing and a mold-free forming process thereof. BACKGROUND

[0002] With the continuous expansion of the application scenarios of fixed-wing unmanned aerial vehicles, the task requirements for the aerodynamic performance of the wings are increasingly high, resulting in increasingly complex aerodynamic shapes of the wings, which puts higher requirements on the manufacturing process of the wings, and for the composite skin, an integrated forming method is usually adopted, which greatly increases the manufacturing cost of the wing mold and the maintenance cost of the skin.

[0003] In the current wing manufacturing process, the skin forming is mostly carried out by using a mold, and then the skin is fixed to the wing skeleton by mechanical connection or glue bonding to form the wing and related movable surfaces.

[0004] Therefore, the present application provides a medium-sized unmanned aerial vehicle block type wing and a mold-free forming process thereof, which can improve the maintainability of the skin and the economy of the wing mold, and has a wide application prospect in the fields of wing manufacturing and skin maintenance. SUMMARY

[0005] In view of the above problems in the prior art, the present application aims to provide a medium-sized unmanned aerial vehicle block type wing and a mold-free forming process thereof, and aims to realize efficient manufacturing of the wing and produce a wing with light weight, high strength and strong maintainability.

[0006] The present application provides the following technical solution: a medium-sized unmanned aerial vehicle block type wing, comprising a wing skeleton and a block type skin wrapped outside the wing skeleton, wherein the wing skeleton comprises a wing main C-shaped beam arranged along the wing span, a wing auxiliary C-shaped beam located behind the wing main C-shaped beam, a group of wing ribs connecting the wing main and auxiliary C-shaped beams, and a carbon rod arranged on the group of wing ribs for enhancing the overall torsional strength of the wing; the wing main and auxiliary C-shaped beams each comprise an upper beam cap, a lower beam cap and a corresponding beam web.

[0007] A mold-free forming process for a medium-sized unmanned aerial vehicle block type wing, comprising the following steps: S1, preparing a skeleton positioning jig for wing assembly, an upper wing surface skin pressure maintaining jig and a lower wing surface skin pressure maintaining jig, and assembling them; S2, positioning and assembling a group of wing ribs, beam webs in the wing main C-shaped beam, upper beam caps, beam webs in the wing auxiliary C-shaped beam, upper beam caps and carbon rods on the skeleton positioning jig to form a skeleton frame, and taking the skeleton frame out of the skeleton positioning jig; S3, bonding the lower beam caps in the wing main and auxiliary C-shaped beams to the taken-out skeleton frame to form a complete wing skeleton; S4, applying adhesive to the preset region of the wing skeleton, and pasting the segmented skin to the corresponding position; S5, placing the wing with the pasted skin on the upper or lower skin pressure holding jig, and performing mold closing and pressure holding to make the skin and the wing skeleton solidify and form; S6, demolding and performing surface treatment on the formed wing.

[0008] Further, the skeleton positioning jig is made of wood laminates, which comprises a set of longitudinal strip ribs and a set of skeleton transverse plates adapted to the shape of the wing ribs, and the longitudinal strip ribs and the skeleton transverse plates are vertically arranged and connected to form an integral whole, and the plates at the wing beams (i.e. the main and auxiliary C-shaped beams of the wing) are provided with grooves for facilitating the installation and positioning of the wing beams.

[0009] Further, the upper and lower skin pressure holding jigs are made of wood laminates, each of which comprises a set of transverse plates and longitudinal plates arranged along the transverse and longitudinal directions and adapted to the aerodynamic shape of the wing, and the transverse plates and the longitudinal plates on the same skin pressure holding jig are vertically arranged and connected.

[0010] Further, the specific process of S2 is as follows: S2.1) Positioning and pressing the wing ribs onto the skeleton positioning jig; S2.2) Clamping the main C-shaped beam web and the auxiliary C-shaped beam web into the preset positioning grooves of the skeleton positioning jig, and bonding the carbon rods and the wing ribs by adhesive; S2.3) Bonding the main C-shaped beam web and the auxiliary C-shaped beam web, the wing ribs, the main C-shaped beam upper cap and the auxiliary C-shaped beam upper cap along the joint by adhesive to form a skeleton frame, and taking the skeleton frame out of the skeleton positioning jig.

[0011] Further, in S2.1), the wing ribs are pressed onto the transverse plates of the skeleton positioning jig along the edges of the transverse plates by dovetail clamps.

[0012] Further, the specific process of S4 is as follows: S4.1) Applying adhesive on the caps of the main and auxiliary C-shaped beams of the wing, and laying the segmented skins of the front, middle and rear edges between the wing ribs; wherein the segmented skins of the front edge and the middle section are fixed to the main beam by rivets and adhesive, the segmented skin of the rear edge is fixed to the auxiliary beam only by adhesive, and all the segmented skins are connected to the wing ribs by adhesive; S4.2) When the adhesive is not cured, placing the wing skeleton in the lower or upper skin pressure holding jig, and fixing the lower or upper skin pressure holding jig and the wing skeleton, and forming the wing after curing.

[0013] Further, the transverse plate and longitudinal plate of the upper and lower skin pressure-keeping jig are arranged at the periphery of the rivets for fixing on each sub-skin to assist the wing skin forming.

[0014] Further, the wing surface treatment in S6 is as follows: The adhesive is filled at the joint between the adjacent skins to form a smooth airfoil surface.

[0015] By using the above-mentioned technology, compared with the prior art, the beneficial effects of the present application are as follows: In the present application, the wing skin adopts a sub-block design method, which can improve the manufacturing efficiency of the wing skin; the sub-block skin and the C-shaped beam for manufacturing the wing do not need to use a mold pressing forming skin, which can save the mold cost; the type frame assisted positioning method only needs a skeleton positioning jig, a lower wing surface skin pressure-keeping jig and an upper wing surface skin pressure-keeping jig assembled by wood layer plates, which has low cost; the wing manufacturing process is efficient and simple; the finished product rate is high, and the surface quality is high. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of the sub-block wing of the present application; Figure 2 It is a structural schematic diagram of the skeleton positioning jig of the present application; Figure 3 It is a structural schematic diagram of the wing rib, C-shaped beam web plate and carbon rod of the present application; Figure 4 It is a structural schematic diagram of the upper beam cap of the C-shaped beam of the present application; Figure 5 It is a structural schematic diagram of the lower beam cap of the C-shaped beam of the present application; Figure 6 It is a structural schematic diagram of the lower wing surface skin pressure-keeping jig of the present application; Figure 7 It is a structural schematic diagram of the upper wing surface skin pressure-keeping jig of the present application; Figure 8 It is a structural schematic diagram of the sub-block skin, lower wing surface skin pressure-keeping jig and upper wing surface skin pressure-keeping jig of the present application; Figure 9 It is a three-dimensional structural schematic diagram of the sub-block wing structure of the present application. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical scheme and advantages of the present application more clear, the present application is further described in detail below in combination with the drawings and examples in the specification. It should be understood that the specific examples described herein are only used to explain the present application, and are not used to limit the present application.

[0018] On the contrary, the present application covers any alternatives, modifications, equivalent methods and solutions made within the spirit and scope of the present application defined by the claims. Further, in order to make the public better understand the present application, some specific details are described in the following detailed description of the present application. The present application can also be completely understood without the description of these details by those skilled in the art.

[0019] Please refer to Figures 1-9 A medium-sized unmanned aerial vehicle block type wing, comprising a wing skeleton and a block type skin wrapped outside the wing skeleton, the wing skeleton comprising a wing main C-shaped beam arranged along the wing span direction, a wing auxiliary C-shaped beam located behind the wing main C-shaped beam, a group of wing ribs connecting the wing main and auxiliary C-shaped beams, and carbon rods arranged on the group of wing ribs for enhancing the overall torsional strength of the wing.

[0020] The wing main C-shaped beam comprises a main C-shaped beam upper beam cap 2, a main C-shaped beam lower beam cap 10 and a main C-shaped beam web plate 11.

[0021] The wing auxiliary C-shaped beam comprises an auxiliary C-shaped beam upper beam cap 4, an auxiliary C-shaped beam lower beam cap 8 and an auxiliary C-shaped beam web plate 7.

[0022] The block type skin comprises a block skin one 1 at the wing leading edge, a block skin two 3 at the middle section of the wing upper surface, a block skin three 5 at the wing upper surface trailing edge, a block skin four 6 at the wing lower surface trailing edge, and a block skin five 9 at the middle section of the wing lower surface.

[0023] The block skin and the C-shaped beam cap adopt corresponding size of planar thin plates, both of which are made of carbon fiber composite material laminated plate and polymethacrylimide plate by epoxy resin structural adhesive; the curing conditions of the epoxy resin structural adhesive are: the holding pressure is 0.6 Mpa, the curing temperature is 80℃, and the holding time is 2 hours. The curing process of the epoxy resin structural adhesive is: curing in an oven by using conventional vacuum bag method, the air exhaust pressure is 0.6 Mpa; or curing by using hot press tank, the holding pressure is 0.6 Mpa; the above atmospheric pressure depends on the type or model of the light material used.

[0024] A mold-free forming process of a medium-sized unmanned aerial vehicle block type wing, realized based on a forming tool, the forming tool comprising a skeleton positioning jig, an upper surface skin holding jig and a lower surface skin holding jig.

[0025] Specifically, the skeleton positioning jig is made of wood laminated board, which is inserted by longitudinal strip ribs 13 and skeleton transverse plates 14 provided with positioning grooves, and is used for accurately positioning all wing ribs 16 and web plates; the shape of the skeleton transverse plate 14 is adapted to the shape of the wing rib.

[0026] The upper and lower wing skin pressure-keeping molds are also made of wood laminates, and their profiles are consistent with the theoretical aerodynamic profile of the wing, which are used to provide uniform pressure for the skin during the curing process; the transverse and longitudinal plates of the upper and lower skin pressure-keeping molds are arranged on the periphery of the rivets for fixing the skin of each sub-block, which assists the forming of the wing skin. The lower wing skin pressure-keeping mold includes lower transverse plates 17 and lower longitudinal plates 18 which are adapted to the aerodynamic profile of the wing, and the upper wing skin pressure-keeping mold includes upper longitudinal plates 19 and upper transverse plates 20 which are adapted to the aerodynamic profile of the wing. The vertical plates between the plurality of transverse plates and longitudinal plates are perpendicularly arranged and connected by insertion to form the corresponding wing skin pressure-keeping mold.

[0027] All mold working surfaces are treated with anti-sticking treatment: iron fluoride is laid or release agent is applied.

[0028] Specifically, the steps of the moldless forming process are as follows: S1, making a skeleton positioning mold for wing assembly, an upper wing skin pressure-keeping mold and a lower wing skin pressure-keeping mold, and assembling them.

[0029] S2, positioning and assembling a set of wing ribs, web plates of main C-beams in the wing main C-beams, upper beam caps, web plates of auxiliary C-beams in the wing auxiliary C-beams, upper beam caps and carbon rods on the skeleton positioning mold to form a skeleton frame, and taking the skeleton frame out of the skeleton positioning mold; specifically as follows: S2.1) press and paste the wing ribs 16 to the transverse plates of the skeleton positioning mold along the edges of the transverse plates through dovetail clamps; S 2.2) insert the main C-beam web plate 11 and the auxiliary C-beam web plate 7 into the pre-set positioning groove on the skeleton positioning mold, and bond the carbon rods 15 and the wing ribs 16 by adhesive; S 2.3) bond the main C-beam web plate 11, the auxiliary C-beam web plate 7, the wing ribs 16, the main C-beam upper beam cap 2 and the auxiliary C-beam upper beam cap 4 along the joint by adhesive to form a skeleton frame, and take the skeleton frame out of the skeleton positioning mold.

[0030] S3, bond the main C-beam lower beam cap 10 and the auxiliary C-beam lower beam cap 8 with the main C-beam web plate 11, the auxiliary C-beam web plate 7 and the wing ribs 16 by adhesive to form a complete wing skeleton.

[0031] S4, apply adhesive to the pre-set area of the wing skeleton, and paste the sub-block skin to the corresponding position; specifically as follows: S 4.1)In the front and back of the wing frame, the main C-beam lower beam cap 10, the auxiliary C-beam lower beam cap 8, the main C-beam upper beam cap 2 and the auxiliary C-beam upper beam cap 4 are coated with adhesive and the segmented skin is laid at the front, middle and rear edges of the wing between each wing rib 16. The segmented skin at the front and middle edges is fixed with rivets and adhesive to the main C-beam lower beam cap 10 and the main C-beam upper beam cap 2, and the segmented skin at the rear edge is fixed with adhesive to the auxiliary C-beam upper beam cap 4 and the auxiliary C-beam lower beam cap 8, and the segmented skin is adhered to the wing rib 16 with adhesive; S 4.2)When the adhesive is not cured, the wing is placed in the lower wing skin pressure holding jig or the upper wing skin pressure holding jig, and the lower wing skin pressure holding jig and the upper wing skin pressure holding jig are fixed with screws 21, and after curing, the wing is formed.

[0032] S5, the wing with the skin pasted is placed between the upper wing skin pressure holding jig and the lower wing skin pressure holding jig, and the mold is closed and pressure is held to make the skin and the wing frame cured and formed; S6, demolding and surface treatment of the formed wing: filling adhesive between the joints between adjacent segmented skins to form a smooth wing surface.

[0033] The above only describes the preferred embodiments of the present application and is not intended to limit the present application. Any modification, equivalent replacement and improvement within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A modular wing for a medium-sized unmanned aerial vehicle (UAV), characterized in that: The wing includes a wing frame and a segmented skin covering the outside of the wing frame. The wing frame includes a main C-shaped wing spars arranged along the wing span, a secondary C-shaped wing spars located behind the main C-shaped wing spars, a set of wing ribs connecting the main and secondary C-shaped wing spars, and carbon rods arranged on the set of wing ribs to enhance the overall torsional strength of the wing. The main and secondary C-shaped wing spars each include upper and lower spars caps and corresponding spars webs.

2. The moldless forming process for a segmented wing of a medium-sized unmanned aerial vehicle according to claim 1, characterized in that, Includes the following steps: S1. Fabricate the frame positioning frame, upper wing skin pressure holding frame, and lower wing skin pressure holding frame for wing assembly, and assemble them. S2. On the frame positioning frame, a set of wing ribs, the web of the main C-beam of the wing, the upper beam cap, the web of the secondary C-beam of the wing, the upper beam cap, and the carbon rod are positioned and assembled to form a frame frame, and the frame frame is removed from the frame positioning frame. S3. Attach the lower beam caps from the main and secondary C-shaped beams of the wing to the removed skeleton frame to form a complete wing skeleton; S4. Apply adhesive to the predetermined area of ​​the wing frame and attach the segmented skin to the corresponding positions; S5. Place the wing with the skin attached on the upper wing skin pressure mold or the lower wing skin pressure mold, and perform mold closing and pressure holding to solidify the skin and the wing frame. S6. Demold and perform surface treatment on the molded wing.

3. The moldless forming process for a segmented wing of a medium-sized unmanned aerial vehicle according to claim 1, characterized in that, The frame positioning frame is made of wooden plywood, which includes a set of longitudinal strip ribs and a set of frame transverse plates adapted to the shape of the wing ribs. The set of longitudinal strip ribs and the frame transverse plates are vertically arranged and interlocked to form a whole. The plates located at the main and secondary C-shaped beams of the wing are provided with grooves to facilitate the installation and positioning of the main and secondary C-shaped beams of the wing.

4. The moldless forming process for a segmented wing of a medium-sized unmanned aerial vehicle according to claim 3, characterized in that, The upper and lower wing skin pressure-holding frames are made of wooden plywood and each includes a set of transverse and longitudinal plates arranged along the horizontal and vertical directions to adapt to the aerodynamic shape of the wing. The transverse and longitudinal plates on the same wing skin pressure-holding frame are arranged vertically and interlocked.

5. The moldless forming process for a segmented wing of a medium-sized unmanned aerial vehicle according to claim 2, characterized in that, The specific process of S2 is as follows: S2.1) Position the wing rib (16) and press it onto the frame positioning bracket; S2.2) Insert the web plate (11) of the main C-beam and the web plate (7) of the secondary C-beam into the pre-set positioning groove on the frame positioning frame, and bond the carbon rod (15) and the wing rib (16) with adhesive. S2.3) The main C-beam web (11), the secondary C-beam web (7), the wing rib (16), the main C-beam cap (2) and the secondary C-beam cap (4) are bonded together along the joint with adhesive to form a skeleton frame. The skeleton frame is then removed from the skeleton positioning frame.

6. The moldless forming process for a segmented wing of a medium-sized unmanned aerial vehicle according to claim 5, characterized in that, In S2.1), the wing rib (16) is pressed onto the transverse plate of the frame positioning frame along the edge of the transverse plate by a dovetail clip.

7. The moldless forming process for a segmented wing of a medium-sized unmanned aerial vehicle according to claim 5, characterized in that, The specific process of S4 is as follows: S4.1) Apply adhesive to the spar caps of the main and secondary C-spars of the wing, and lay out the segmented skins of the leading, middle and trailing edges between the wing ribs; among them, the segmented skins of the leading edge and middle section are fixed to the main spar by rivets and adhesives, and the segmented skins of the trailing edge are fixed to the secondary spar only by adhesives. All segmented skins are connected to the wing ribs by adhesives. S4.2) Before the adhesive has cured, place the wing frame in the lower wing skin pressure mold or the upper wing skin pressure mold, and then fix the lower wing skin pressure mold and the upper wing skin pressure mold to the wing frame. After curing, the wing is formed.

8. The moldless forming process for a segmented wing of a medium-sized unmanned aerial vehicle according to claim 7, characterized in that, The transverse and longitudinal plates of the upper and lower skin pressure-holding frames are arranged around the rivets used to fix each segment of the skin, assisting in the forming of the wing skin.

9. The moldless forming process for a segmented wing of a medium-sized unmanned aerial vehicle according to claim 2, characterized in that, The wing surface treatment in S6 is as follows: Adhesive is filled at the seams between adjacent skins to form a smooth wing surface.

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