Unmanned aerial vehicle wingtip structure for antenna connection and assembly method of unmanned aerial vehicle wingtip structure

Abstract

The invention provides an unmanned aerial vehicle composite wingtip structure with an antenna mounting function and an assembly method thereof. The unmanned aerial vehicle composite wingtip structure comprises a left interlayer skin 1 and a right interlayer skin 2, wherein each of the left interlayer skin 1 and the right interlayer skin 2 comprises an outer skin 18, a foam core 19 and an inner skin 20; the foam core 19 is positioned at the rear part of the wingtip; the outer skin 18 and the inner skin 20 are completely and symmetrically laid to form a pure laminate structure; the front beam supporting piece 3 and the rear beam supporting piece 4 are of a pure laminate box-shaped structure formed by completely and symmetrically laying fabric prepreg and are of a wingtip bearing structure. The lower portion of the front beam supporting piece 3 and the lower portion of the rear beam supporting piece 4 are each provided with a sunken area, and the sunken areas are installed on the front beam tail section 13 and the rear beam tail section 15 in an embedded mode. The antenna supporting piece 5 is of a pure laminate box-shaped structure formed by completely and symmetrically laying fabric prepreg, and is embedded in the front beam supporting piece 3 and the rear beam supporting piece 4; the antenna switching support 6 is a plate-shaped structural member and is in threaded connection with the antenna supporting member 5; and the skin folding strip 7 is laid outside the left interlayer skin 1 and the right interlayer skin 2.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of fixed-wing unmanned aerial vehicle structure design, in particular to a unmanned aerial vehicle composite wing tip structure with antenna mounting function and an assembling method thereof. BACKGROUND

[0002] Unmanned aerial vehicles are a hot topic in the development of aircraft in the world today, and have important significance in enhancing national security capabilities, promoting the process of military modernization, promoting industrial upgrading and economic development, and improving social governance capabilities. Lightweight, low cost, adaptation to multi-task scenarios, and convenient operation are the eternal pursuit.

[0003] Unmanned aerial vehicles are often used for multiple purposes. In order to adapt to multi-task scenarios, the functional equipment will be frequently replaced. The body structure connected with the functional equipment needs to realize compatible installation of multiple functional equipment, and also needs to consider the convenience of operation.

[0004] The wing tip is installed at the tip of the wing and has the functions of maintaining the aerodynamic shape and improving the aerodynamic performance. The space region where it is located is open, and the installation of functional equipment on the wing tip has the convenience of equipment replacement and maintenance.

[0005] The unmanned aerial vehicle wing tip structure has the characteristics of small size and small internal space, and is usually a non-load-bearing structure. In order to realize low cost and lightweight, full-height foam sandwich composite material structure is usually used in the design and manufacturing process. Although the full-height foam sandwich structure is a lightweight structure, it lacks strong skeletal support inside the structure, and the overall structural strength is weak, making it difficult to install functional equipment. The diversity of wing tip types and the demand for improving aerodynamic efficiency require that the aerodynamic shape of the unmanned aerial vehicle wing tip may be a complex curvature envelope. When the wing tip shape has complex curvature, the relative thickness of some regions is small, which will cause two problems: first, it will make it difficult to install functional equipment on the wing tip; second, it will make it difficult to process foam core and skin parts, resulting in large manufacturing errors and making it difficult for components to fit the shape during assembly.

[0006] The existing technology has the following problems: first, although the unmanned aerial vehicle wing tip region is open and has the convenience of equipment replacement and maintenance, the overall strength of the traditional foam sandwich structure of the unmanned aerial vehicle wing tip is weak, making it difficult to connect different functional equipment. Second, the complex shape design of the wing tip makes it difficult to process parts and assemble components, increases the manufacturing and assembly errors of parts, and reduces the manufacturing feasibility of the wing tip structure. SUMMARY

[0007] The purpose of the present application is to provide a unmanned aerial vehicle wing tip structure for antenna connection and an assembling method thereof. The purpose is to solve the problem that the unmanned aerial vehicle wing tip structure is difficult to install different types of antennas, quickly and accurately form, and be lightweight when the shape curvature is complex.

[0008] Technical solution: In a first aspect, the application provides a UAV composite wing tip structure with antenna installation function, comprising a left sandwich skin 1, a right sandwich skin 2, a front beam support 3, a rear beam support 4, an antenna support 5, an antenna adapter support 6, and a skin butt strap 7, wherein: The left sandwich skin 1 and the right sandwich skin 2 are composite foam core conformal symmetric members; the left sandwich skin 1 and the right sandwich skin 2 each comprise an outer skin 18, a foam core 19, and an inner skin 20; the foam core 19 is located at the rear of the wing tip; the outer skin 18 and the inner skin 20 are completely symmetrically laid pure laminate structures; the front beam support 3 and the rear beam support 4 are pure laminate box-shaped structures of completely symmetrically laid fabric prepregs, which are wing tip load-bearing structures; the front beam support 3 and the rear beam support 4 each have a sunken area at the lower part, which is embeddedly installed in the front beam tail section 13 and the rear beam tail section 15; the antenna support 5 is a pure laminate box-shaped structure of completely symmetrically laid fabric prepregs, which is embeddedly installed in the front beam support 3 and the rear beam support 4; the antenna adapter support 6 is a plate-shaped structural member, which is screwed to the antenna support 5; the skin butt strap 7 is laid on the left sandwich skin 1 and the right sandwich skin 2, and is a closed wing tip structure; an antenna installation slot 17 is designed at the top of the UAV wing tip structure, which is used for installing an antenna 11.

[0009] Specifically, the antenna support 5 has a sunken area at both ends, is provided with N antenna support bolt through holes 21 and antenna support electric connector through holes 22, and is fixed with N bracket nuts 23 at the antenna support bolt through holes 21.

[0010] Specifically, the antenna adapter support 6 is an aluminum alloy machined plate-shaped structural member, which is a detachable structure; the antenna adapter support 6 is provided with at least four hexagonal head bolt through holes 24, N countersunk bolt through holes 25, and antenna adapter support electric connector through holes 26, and the lower part of both sides is provided with a rectangular boss 27. Specifically, the skin butt strap 7 is a strip-shaped conformal structure of alkali-free glass fiber cloth.

[0011] Specifically, the outer skin 18, the inner skin 20, and the foam core 19 are integrally cured and formed by a heat press tank.

[0012] In a second aspect, the application provides an assembly method of a UAV composite wing tip structure with antenna installation function, which comprises the following steps: Step 1: install the front beam support 3 to the front beam tail section 13 and the rear beam support 4 to the rear beam tail section 15; Step 2: install the antenna support 5; Step 3: install the left sandwich skin 1 and the right sandwich skin 2; Step 4: install the skin butt strap 7; after the left sandwich skin 1 and the right sandwich skin 2 are butted, the wet bonding of the epoxy adhesive is adopted on the left sandwich skin 1 and the right sandwich skin 2; Step 5: install the antenna adapter support 6; Step 6: install the antenna 11; the antenna 11 is screwed on the antenna adapter support 6, the head of the hexagonal head bolt 8 is located at the rectangular boss 27 of the antenna adapter support 6, the rectangular boss 27 of the antenna adapter support 6 limits the rotation of the head of the hexagonal head bolt 8 during installation, and only the self-locking nut 9 needs to be tightened, which has an open construction space.

[0013] Specifically, step 1 includes: The lower sinking areas of the front beam support 3 and the rear beam support 4 are respectively overlapped on the front beam tail section 13 and the rear beam tail section 15; the contact area of the front beam support 3 and the edge strip of the front beam tail section 13 is fixed by room temperature glue, and the contact area of the web is mechanically connected by bolts; the contact area of the rear beam support 4 and the edge strip of the rear beam tail section 15 is fixed by room temperature glue, and the contact area of the web is mechanically connected by bolts.

[0014] Specifically, step 2 includes: The lower sinking area of the antenna support is overlapped on the front beam support 3 and the rear beam support 4, and the contact area of the edge strip of the front beam support 3 and the rear beam support 4 is fixed by room temperature glue, and the contact area of the web is respectively mechanically connected by rivets.

[0015] Specifically, step 3 includes: The left sandwich skin 1 and the right sandwich skin 2 are fixed by room temperature glue on the contact surface of the front edge end partition plate 12, the wing box end rib 14, the rear edge end partition plate 16, the front beam tail section 13, the rear beam tail section 15, the front beam support 3, the rear beam support 4 and the antenna support 5.

[0016] Specifically, step 5 includes: The antenna adapter support 6 is connected to the antenna support 5 by two countersunk head bolts 10; during assembly, only the two end plate nuts 23 are connected, and the remaining plate nuts 23 are redundant, and when a connection failure occurs, other plate nuts 23 are connected, which has the advantage of quickly and conveniently processing faults.

[0017] In summary, the unmanned aerial vehicle composite wing tip structure with an antenna installation function and the assembly method thereof provided by the present application have the following advantages: (1) The parts of the wing tip structure are made of composite materials and light aluminum alloys, which can realize lightweight.

[0018] (2) The wing tip structure is designed with a support connected to the main beam, so that the wing tip structure has the strength and stiffness required for connecting antenna equipment.

[0019] (3) The skin structure is divided into two parts and each part is formed, which can avoid the problems of complex curvature, difficult manufacturing of opening shrinkage parts, assembly and large error, and can realize rapid and accurate forming and assembly.

[0020] (4) The antenna adapter support with a lower boss design realizes reverse bolt installation, which can effectively solve the problems of interference with the wing tip structure during bolt installation and narrow construction space.

[0021] (5) The wing tip is provided with a universal interface and a detachable and replaceable antenna adapter support, which can meet the requirements of installing different types of antennas on a thin wing tip; BRIEF DESCRIPTION OF DRAWINGS Figure 1 An overall structure schematic diagram of a UAV composite wing tip structure with an antenna installation function is provided.

[0022] Figure 2 An internal structure schematic diagram of a UAV composite wing tip structure with an antenna installation function is provided.

[0023] Figure 3 A theoretical shape schematic diagram of a UAV composite wing tip structure with an antenna installation function is provided.

[0024] Figure 4 A sandwich skin structure schematic diagram is provided.

[0025] Figure 5 A front beam support structure schematic diagram and a rear beam support structure schematic diagram are provided.

[0026] Figure 6 An antenna support structure schematic diagram is provided.

[0027] Figure 7 An antenna adapter support structure schematic diagram is provided.

[0028] Numbering in the figure: 1 left sandwich skin, 2 right sandwich skin, 3 front beam support, 4 rear beam support, 5 antenna support, 6 antenna adapter support, 7 skin butt strap, 8 hexagonal head bolt, 9 self-locking low nut, 10 countersunk bolt, 11 antenna, 12 front edge end partition, 13 front beam tail section, 14 wing box end rib, 15 rear beam tail section, 16 rear edge end partition, 17 antenna installation slot, 18 outer skin, 19 foam sandwich, 20 inner skin, 21 antenna support bolt through hole, 22 antenna support electrical connector through hole, 23 support plate nut, 24 hexagonal head bolt through hole, 25 countersunk bolt through hole, 26 antenna adapter support electrical connector through hole, 27 rectangular boss. DETAILED DESCRIPTION

[0029] This invention relates to a wingtip structure for antenna connection in a UAV and its assembly method. To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to specific embodiments and the accompanying drawings.

[0030] Example 1 like Figures 1-3 As shown, this invention application discloses a wingtip structure for antenna connection in a UAV. The wingtip structure is mounted on the wingtip and includes a left interlayer skin 1, a right interlayer skin 2, a front beam support 3, a rear beam support 4, an antenna support 5, an antenna adapter 6, and skin mating strips 7, wherein: The left and right sandwich panels 1 and 2 are conformal symmetrical composite foam core components; both include an outer skin 18, a foam core 19, and an inner skin 20; the foam core 19 is located at the rear of the wingtip; the outer skin 18 and inner skin 20 are a completely symmetrically laid pure layered board structure; the front beam support 3 and rear beam support 4 are completely symmetrically laid pure layered board box-shaped structures made of prepreg fabric, serving as the wingtip load-bearing structures; both the front beam support 3 and rear beam support 4 have a lower part... There is a recessed area, which is embedded in the front beam tail section 13 and the rear beam tail section 15; the antenna support 5 is a pure layered box structure with completely symmetrically laid prepreg fabric, which is embedded in the front beam support 3 and the rear beam support 4; the antenna adapter 6 is a plate-shaped structure that is screwed to the antenna support 5; the skin mating strip 7 is laid on the outside of the left interlayer skin 1 and the right interlayer skin 2, which is a closed wingtip structure; an antenna mounting slot 17 is designed on the top of the UAV wingtip structure for mounting the antenna 11.

[0031] Specifically, the outer skin 18, inner skin 20, and foam core 19 are integrally cured and molded in a hot autoclave.

[0032] It should be noted that the skin structure is divided into two parts: the left interlayer skin 1 and the right interlayer skin 2, each integrally molded, which can ensure the process feasibility and shape accuracy of the closing parts; the foam core 19 is used to enhance local rigidity, and its size can be designed according to the rigidity requirements of the wingtip.

[0033] Specifically, such as Figure 5 As shown, the antenna support 5 has recessed areas at both ends, and has N antenna support bolt through holes 21 and antenna support electrical connector through holes 22. N support plate nuts 23 are fixed at the antenna support bolt through holes 21. Among them, the bracket nut 23 is a universal connection interface for the antenna adapter bracket 6; Specifically, the antenna adapter bracket 6 is a machined aluminum alloy plate-shaped structure, which is detachable; such as Figure 7As shown, the antenna adapter support 6 is provided with four hexagonal head bolt through holes 24, N countersunk bolt through holes 25, and an antenna adapter support electrical connector through hole 26, and the lower two sides are respectively provided with rectangular bosses 27; Optionally, the boss height of the rectangular boss 27 is determined according to the head height of the hexagonal head bolt 8 connecting the antenna; Optionally, the antenna adapter support 6 is designed according to the base shape of the antenna 11, that is, one type of antenna needs to be designed with one antenna adapter support 6, so as to be compatible with the installation of different types of antennas.

[0034] Specifically, the skin joint strip 7 is a non-alkali glass fiber cloth strip-shaped conformal structure.

[0035] Among them, N is greater than or equal to 4.

[0036] As Figure 3 As shown, the wing tip theoretical shape is A-A, and the A-A cross section is C-shaped opening. Along the B-B, C-C, D-D, and E-E cross sections, the two sides are flat and closed, and the local relative thickness is small.

[0037] Optionally, the groove depth, width, and length of the antenna mounting groove 17 need to be comprehensively designed according to the size and installation requirements of the base of each type of antenna.

[0038] Example two The application provides a manufacturing method of each component of a UAV composite wing tip structure with an antenna installation function, comprising: 1) The left sandwich skin 1 and the right sandwich skin 2 are composed of an outer skin 18, a foam core 19, and an inner skin 20. The outer skin 18 and the inner skin 20 are both 0 / 90°, ±45° fabric prepreg completely symmetrically laid pure laminate structures, which are then integrally cured and formed by a heat press tank together with the foam core; 2) The front beam support 3, the rear beam support 4, and the antenna support 5 are 0 / 90°, ±45° fabric prepreg completely symmetrically laid pure laminate structures which are cured and formed by a heat press tank; 3) The antenna adapter support 6 is a machined part; 4) The skin joint strip 7 is manually cut, laid, and wet formed.

[0039] Example three The application provides an assembly method of a UAV composite wing tip structure with an antenna installation function, comprising: Step 1: Install the front beam support 3 to the front beam tail section 13, and install the rear beam support 4 to the rear beam tail section 15; Specifically including: the front beam support 3, the rear beam support 4 lower area respectively lap in the front beam tail section 13, the rear beam tail section 15;The front beam support 3 and the front beam tail section 13 edge strip contact area uses room temperature glue fixed, web contact area bolt mechanical connection;The rear beam support 4 and the rear beam tail section 15 edge strip contact area uses room temperature glue fixed, web contact area uses bolt mechanical connection.

[0040] Step 2: install antenna support 5; Specifically including: the antenna support lower area lap in the front beam support 3, the rear beam support 4, and the front beam support 3, the rear beam support 4 edge strip contact area uses room temperature glue fixed, web contact area respectively uses rivet mechanical connection.

[0041] Step 3: install left sandwich skin 1, right sandwich skin 2; Specifically including: left sandwich skin 1, right sandwich skin 2 in the contact surface with front edge end partition 12, wing box end rib 14, rear edge end partition 16, front beam tail section 13, rear beam tail section 15, front beam support 3, rear beam support 4, antenna support 5 uses room temperature glue fixed.

[0042] Step 4: install skin butt strap 7; Specifically including: after the left sandwich skin 1, right sandwich skin 2 butt, uses epoxy adhesive wet bonding on the left sandwich skin 1 and right sandwich skin 2.

[0043] Step 5: install antenna adapter support 6; Specifically including: antenna adapter support 6 is connected to antenna support 5 through two countersunk head bolts 10;When assembling, only the two end plate nuts 23 are connected, and the remaining plate nuts 23 are redundant, which can be connected to other plate nuts 23 when there is a connection failure, having the advantage of quickly and conveniently processing failure.

[0044] Step 6: install antenna 11; Specifically including: antenna 11 is screwed on antenna adapter support 6, hexagonal head bolt 8 head is located at rectangular boss 27 of antenna adapter support 6, rectangular boss 27 of antenna adapter support 6 limits the rotation of hexagonal head bolt 8 head during installation, only need to tighten self-locking nut 9, has open construction space, can effectively solve the problem of interference with wing tip structure during bolt installation and narrow construction space.

Claims

1. An unmanned aerial vehicle composite wing tip structure with antenna mounting functionality, characterized by, It comprises left sandwich skin (1), right sandwich skin (2), front beam support (3), rear beam support (4), antenna support (5), antenna adapter support (6), skin butt strap (7), wherein: The left sandwich skin (1) and the right sandwich skin (2) are composite foam sandwich conformal symmetric members; The left sandwich skin (1) and the right sandwich skin (2) each comprise an outer skin (18), a foam core (19) and an inner skin (20); The foam core (19) is located at the rear of the wing tip; The outer skin (18) and the inner skin (20) are completely symmetrically laid pure laminate structures; The front beam support (3) and the rear beam support (4) are pure laminate box-shaped structures of completely symmetrically laid fabric prepreg, which are wing tip bearing structures; The front beam support (3) and the rear beam support (4) are each provided with a sunken area at the lower part and are embeddedly installed in the front beam tail section (13) and the rear beam tail section (15); The antenna support (5) is a pure laminate box-shaped structure of completely symmetrically laid fabric prepreg, which is embeddedly installed in the front beam support (3) and the rear beam support (4); The antenna adapter support (6) is a plate-shaped structural member and is screwed to the antenna support (5); The skin butt strap (7) is laid on the left sandwich skin (1) and the right sandwich skin (2) and is a closed wing tip structure; An antenna installation slot (17) is designed at the top of the unmanned aerial vehicle wing tip structure for installing an antenna (11).

2. The UAV composite wing tip structure of claim 1, wherein, The antenna support (5) has a sunken area at both ends, is provided with N antenna support bolt through holes (21) and antenna support electric connector through holes (22), and is fixed with N supporting plate nuts (23) at the antenna support bolt through holes (21).

3. The UAV composite wing tip structure of claim 1, wherein, The antenna adapter support (6) is an aluminum alloy machined plate-shaped structural member and is a detachable structure; The antenna adapter support (6) is provided with at least four hexagonal head bolt through holes (24), N countersunk bolt through holes (25) and antenna adapter support electric connector through holes (26), and the lower two sides are respectively provided with rectangular bosses (27).

4. The UAV composite wing tip structure of claim 1, wherein, The skin butt strap (7) is a strip-shaped conformal structure of alkali-free glass fiber cloth.

5. The UAV composite wing tip structure of Claim 1, wherein, The outer skin (18), the inner skin (20) and the foam core (19) are integrally cured and formed by a heat press tank.

6. An assembly method for a composite wingtip structure of an unmanned aerial vehicle (UAV) with antenna mounting function, characterized in that the method... It comprises: Step 1: install the front beam support (3) to the front beam tail section (13) and the rear beam support (4) to the rear beam tail section (15); Step 2: install the antenna support (5); Step 3: install the left sandwich skin (1) and the right sandwich skin (2); Step 4: install the skin butt strap (7); After the butt joint of the left sandwich skin (1) and the right sandwich skin (2) is completed, the skin butt strap (7) is wetly bonded on the left sandwich skin (1) and the right sandwich skin (2) by using epoxy adhesive; Step 5: install the antenna adapter support (6); Step 6: install the antenna (11); The antenna (11) is screwed to the antenna adapter support (6), the head of the hexagonal head bolt (8) is located at the rectangular boss (27) of the antenna adapter support (6), the rectangular boss (27) of the antenna adapter support (6) limits the rotation of the head of the hexagonal head bolt (8) during installation, and only the self-locking nut (9) needs to be tightened, which has an open construction space.

7. The method of claim 6, wherein, Step 1 comprises: The front beam support (3) and the rear beam support (4) are respectively overlapped on the front beam tail section (13) and the rear beam tail section (15); the front beam support (3) is fixed by normal temperature glue at the edge strip contact area of the front beam tail section (13), and is mechanically connected by a bolt at the web contact area; the rear beam support (4) is fixed by normal temperature glue at the edge strip contact area of the rear beam tail section (15), and is mechanically connected by a bolt at the web contact area.

8. The method of claim 6, wherein, Step 2 comprises: The antenna support is overlapped on the front beam support (3) and the rear beam support (4), and is fixed by normal temperature glue at the edge strip contact area of the front beam support (3) and the rear beam support (4), and is mechanically connected by a rivet at the web contact area.

9. The method of claim 6, wherein, Step 3 comprises: The left sandwich skin (1) and the right sandwich skin (2) are fixed by normal temperature glue at the contact surface of the front edge end partition (12), the wing box end rib (14), the rear edge end partition (16), the front beam tail section (13), the rear beam tail section (15), the front beam support (3), the rear beam support (4) and the antenna support (5).

10. The method of claim 6, wherein, Step 5 comprises: The antenna adapter support (6) is connected to the antenna support (5) by two countersunk bolts (10); during assembly, only the two end plate nuts (23) are connected, and the remaining plate nuts (23) are redundant; when a connection failure occurs, other plate nuts (23) are connected, which has the advantage of quickly and conveniently processing the failure.

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