Unmanned aerial vehicle sub-wing structure

Abstract

The utility model discloses an unmanned aerial vehicle sub-wing structure which comprises a skin, a sub-wing body, an undercarriage and a fairing, the sub-wing body is arranged on one side of the undercarriage, the skin is arranged above the sub-wing body, and the fairing is arranged on one side of the skin; the sub-wing body comprises a front beam, a rear beam, a root rib, an end rib and a rotating shaft, one end of the front beam is arranged at one end of the end rib, and one end of the rear beam is arranged at the other end of the end rib; the root rib is arranged at the other ends of the front beam and the rear beam; a supporting rod connector is arranged on one side of the end rib, the supporting rod connector and the end rib are integrally manufactured, and a plurality of reinforcing ribs are arranged on one side of the end rib and one side of the root rib. By the adoption of the technical scheme, due to the fact that the supporting rod connector and the end rib are integrally manufactured, and the reinforcing ribs are arranged on one side of the end rib and one side of the root rib, the projection area in the course direction is reduced, a traditional fastener connecting mode is changed, stress generated by mounting holes is avoided, stress distribution of the end rib is optimized, and stress of the sub-wing structure is smoother.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a sub-wing structure of an unmanned aerial vehicle. Background Art

[0002] At present, my country's UAV industry is developing rapidly, and the demand for load capacity of large UAVs is increasing. The landing gear needs to have a larger load-bearing capacity. Due to the limitations of the theoretical shape of the UAV body and the requirements of the body structural strength and deformation capacity, the main landing gear of large UAVs needs to add a sub-wing structure to meet the requirement of reducing the strength of the fuselage connection structure.

[0003] The traditional sub-wing structure is composed of ribs, front and rear beams, and skins. The strut joint is connected to the rear beam. Since the strut load is large, the corresponding strut joint is large in size, and the connection between the strut joint and the rear beam must have sufficient strength. Considering that the shape of the sub-wing itself has a huge impact on the aerodynamic load, causing a significant increase in aircraft resistance, when designing the sub-wing, the projection area of ​​the sub-wing structure along the heading direction should be minimized. As a result, the traditional sub-wing structure is difficult to meet the strength requirements.

[0004] Based on this, this application is made. Utility Model Content

[0005] The technical problem to be solved by the utility model is to provide a UAV sub-wing structure which reduces the projection area along the heading direction, makes the sub-wing structure more smoothly stressed, avoids the stress generated by the mounting holes, and optimizes the stress distribution of the end ribs.

[0006] In order to solve the above technical problems, the technical solution of the utility model is:

[0007] A sub-wing structure of an unmanned aerial vehicle comprises a skin, a sub-wing body, a landing gear and a fairing, wherein the sub-wing body is arranged on one side of the landing gear, the skin is arranged above the sub-wing body, and the fairing is arranged on one side of the skin;

[0008] The sub-wing body includes a front beam, a rear beam, a root rib, an end rib and a rotating shaft, one end of the front beam is arranged at one end of the end rib, and one end of the rear beam is arranged at the other end of the end rib; the root rib is arranged at the other end of the front beam and the rear beam; one end of the rotating shaft is arranged on the root rib, and the other end thereof passes through the end rib and the support of the landing gear and is fixed to the landing gear by a limiting bolt.

[0009] Preferably, the rotating shaft is a rotary rotating shaft, and the diameter of the rotating shaft decreases from the end rib side to the root rib side.

[0010] Preferably, the skin and fairing adopt a composite material layup design and a unidirectional prepreg combination design, and the unidirectional prepreg layup direction is along the lateral laying direction; the inner and outer side surfaces are laid at 45 degrees, and the layup ratio of plain cloth and unidirectional prepreg is 1:1.

[0011] Preferably, a connection joint is provided on one side of the front beam and the rear beam respectively, and the connection joint is integrally machined with the front beam and the rear beam respectively using T7050 aluminum alloy material.

[0012] Preferably, the connection joint is of a double-ear type, which adopts a groove structure, and the edge of the connection joint is provided with a flange strip.

[0013] Preferably, the front beam and the rear beam adopt an I-beam structure, whose edge strips are connected to the skin, and whose webs are connected to the root ribs and the end ribs.

[0014] Preferably, a reinforcing rib is provided in the middle portion of the rear beam.

[0015] Preferably, a strut joint is provided on one side of the end rib, and the strut joint is made integrally with the end rib. A plurality of reinforcing ribs are provided on one side of the end rib and the root rib, and the reinforcing ribs are arranged to intersect.

[0016] Preferably, fasteners are provided between the strut joint and the end rib and the connecting joint, and the fasteners include bolts, bushings and nuts. The bolts pass through the strut joint or the connecting joint, and the nut is provided at one end of the bolt; the bushing is provided between the bolt and the strut joint or between the connecting joint and the bolt; and a gasket is also provided between the bushing and the bolt.

[0017] By adopting the above technical solution, since the strut joint is made integrally with the end rib, a plurality of reinforcing ribs are provided on one side of the end rib and the root rib, so that the projection area along the heading direction is reduced, the traditional fastener connection method is changed, the stress generated by the mounting hole is avoided, the stress distribution of the end rib is optimized, and the force of the sub-wing structure is smoother. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a structural schematic diagram of the utility model;

[0019] Figure 2 This is a schematic diagram of the structure of the utility model without the fairing;

[0020] Figure 3 It is a structural schematic diagram of the sub-wing body of the utility model;

[0021] Figure 4 It is an exploded schematic diagram of the fastener at the connection of the brace joint of the utility model;

[0022] Figure 5 It is an exploded schematic diagram of the fasteners at the connection of the sub-wing body of the utility model;

[0023] Figure 6 This is a schematic diagram of the connection structure between the support rod joint and the end rib of the utility model;

[0024] Figure 7 The utility model is a schematic diagram of the structure of the connection between the column and the rotating shaft of the landing gear.

[0025] Numbers in the figure: 1-skin, 2-wing body, 3-landing gear, 4-fairing, 5-limit bolt, 6-connecting joint, 7-edge strip, 8-fastener, 201-front beam, 202-rear beam, 203-root rib, 204-end rib, 205-rotating shaft, 206-reinforcement rib, 207-strut joint, 801-bolt, 802-bushing, 803-nut, 804-gasket. DETAILED DESCRIPTION

[0026] The specific implementation methods of the present invention are further described below in conjunction with the accompanying drawings. It should be noted that the description of these implementation methods is used to help understand the present invention, but does not constitute a limitation of the present invention. In addition, the technical features involved in each implementation method of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0027] like Figure 1-7 As shown, a sub-wing structure of an unmanned aerial vehicle includes a skin, a sub-wing body, a landing gear and a fairing, wherein the sub-wing body is arranged on one side of the landing gear, the skin is arranged above the sub-wing body, and the fairing is arranged on one side of the skin;

[0028] The sub-wing body includes a front beam, a rear beam, a root rib, an end rib and a rotating shaft. One end of the front beam is arranged at one end of the end rib, and one end of the rear beam is arranged at the other end of the end rib; the root rib is arranged at the other end of the front beam and the rear beam; one end of the rotating shaft is arranged on the root rib, and the other end thereof passes through the end rib and the support of the landing gear and is fixed to the landing gear by a limit bolt, so as to reduce the projected area along the heading, change the traditional fastener connection method, avoid the stress generated by the mounting hole, optimize the stress distribution of the end rib, and make the sub-wing structure more smooth in force.

[0029] In addition, the shaft is a rotary shaft, and the diameter of the shaft decreases from the end rib side to the root rib side, which reduces the weight of the shaft, makes the stress of the shaft as uniform as possible and bears the directional, lateral and vertical translational loads and directional and vertical moments from the main landing gear.

[0030] Furthermore, the skin and fairing adopt a composite layup design and a unidirectional prepreg combination design. The unidirectional prepreg layup direction is along the side; the inner and outer surfaces are laid at 45 degrees, and the layup ratio of plain cloth and unidirectional prepreg is 1:1.

[0031] In addition, a connecting joint is provided on one side of the front beam and the rear beam respectively, and the connecting joint is machined integrally with the front beam and the rear beam respectively using T7050 aluminum alloy material.

[0032] Furthermore, the connection joint adopts a double-ear type, which adopts a groove structure, and the edge of the connection joint is provided with a flange to improve the out-of-plane stiffness of the connection joint.

[0033] In addition, the front beam and the rear beam adopt an I-beam structure, which has good strength and is not easy to cut and process. It also has excellent impact resistance and wear resistance. Its edge strips are connected to the skin, and its webs are connected to the root ribs and the end ribs.

[0034] Furthermore, a reinforcing rib is provided in the middle of the rear beam to improve the stability of the web of the rear beam and reduce the thickness of the web.

[0035] In addition, a strut joint is provided on one side of the end rib, and the strut joint is made integrally with the end rib. A plurality of reinforcing ribs are provided on one side of the end rib and the root rib, and the reinforcing ribs are arranged to intersect. In this embodiment, there are no less than 2 reinforcing ribs to improve the strength and stability of the end rib and the root rib.

[0036] Furthermore, fasteners are provided between the strut joint and the end rib and the connecting joint, and the fasteners include bolts, bushings and nuts. The bolts pass through the strut joint or the connecting joint, and the nut is arranged at one end of the bolt; the bushing is arranged between the bolt and the strut joint or between the connecting joint and the bolt to prevent the ear piece from being worn; a gasket is also provided between the bushing and the bolt.

[0037] The above is a detailed description of the embodiments of the present invention in conjunction with the accompanying drawings, but the present invention is not limited to the described embodiments. For those skilled in the art, various changes, modifications, substitutions and variations of these embodiments are made without departing from the principles and spirit of the present invention, and still fall within the scope of protection of the present invention.

Claims

1. A drone wing structure, characterized in that: It comprises a skin, a wing body, a landing gear and a fairing, wherein the wing body is arranged on one side of the landing gear, the skin is arranged above the wing body, and the fairing is arranged on one side of the skin; The sub-wing body includes a front beam, a rear beam, a root rib, an end rib and a rotating shaft, one end of the front beam is arranged at one end of the end rib, and one end of the rear beam is arranged at the other end of the end rib; the root rib is arranged at the other end of the front beam and the rear beam; one end of the rotating shaft is arranged on the root rib, and the other end thereof passes through the end rib and the support of the landing gear and is fixed to the landing gear by a limiting bolt.

2. The drone sub-wing structure according to claim 1, characterized in that: The rotating shaft is a rotary rotating shaft, and the diameter of the rotating shaft decreases from the end rib side to the root rib side.

3. The drone sub-wing structure according to claim 1, characterized in that: The skin and fairing adopt a composite material layup design and a unidirectional prepreg combination design, and the unidirectional prepreg layup direction is along the side; the two side surfaces are laid at 45 degrees, and the layup ratio of plain cloth and unidirectional prepreg is 1:

1.

4. The drone sub-wing structure according to claim 1, characterized in that: A connection joint is provided on one side of the front beam and the rear beam respectively, and the connection joint is machined integrally with the front beam and the rear beam respectively using T7050 aluminum alloy material.

5. The drone sub-wing structure according to claim 4, characterized in that: The connecting joint is of double-ear type and has a groove structure, and edge strips are arranged on the edges of the connecting joint.

6. The drone sub-wing structure according to claim 4, characterized in that: The front beam and the rear beam adopt an I-beam structure, the flanges of which are connected to the skin, and the webs of which are connected to the root ribs and the end ribs.

7. The drone sub-wing structure according to claim 6, characterized in that: A reinforcing rib is arranged in the middle of the rear beam.

8. The drone sub-wing structure according to claim 2, characterized in that: A brace joint is provided on one side of the end rib, and the brace joint is made integrally with the end rib. A plurality of reinforcing ribs are provided on one side of the end rib and the root rib, and the reinforcing ribs are arranged to intersect.

9. The drone sub-wing structure according to claim 8, characterized in that: Fasteners are provided between the strut joint and the end rib and the connecting joint. The fasteners include bolts, bushings and nuts. The bolts pass through the strut joint or the connecting joint, and the nut is provided at one end of the bolt; the bushing is provided between the bolt and the strut joint or between the connecting joint and the bolt; and a gasket is also provided between the bushing and the bolt.

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