Structure of control surface of unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle control plane structure which comprises a rudder, a round rod is fixedly connected to an inner cavity of the rudder, one end of the round rod penetrates to the outer side of the rudder, a connecting structure is arranged in the inner cavity of the rudder, and the connecting structure comprises a fixing plate fixedly connected with the round rod. A mounting block is detachably connected to one side of the fixing plate, a positioning rod is detachably connected to one side of the mounting block, a connecting rod is arranged at one end of the positioning rod, first bolts are arranged at the two ends of the connecting rod in a penetrating mode, the surfaces of the first bolts are connected with the positioning rod, and the positioning rod is located in an inner cavity of the connecting rod. The control surface has the advantages of being simple in structure, convenient to form and easy to assemble, in the actual using process, the control surface is simple in structural design, easy to produce and assemble parts, convenient to disassemble and low in replacement cost, and the control surface body is of a foam sandwich structure from material selection.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a structure of a control surface of an UAV. Background Art

[0002] UAV, short for unmanned aerial vehicle, is an unmanned aircraft that is mainly controlled by radio remote control equipment and self-contained program control devices, or operated completely or intermittently autonomously by an onboard computer. With the booming development of the UAV market, the field is undergoing rapid changes in the survival of the fittest, which puts higher requirements on the overall performance of UAVs, especially in terms of economy and safety. UAVs, with their high energy utilization rate and strong carrying capacity, have demonstrated absolute advantages in engineering applications with long flight time, long range and large payload.

[0003] The control surface of a UAV, such as the rudder, elevator, flaps, ailerons, etc., is one of the important components of a UAV. The control surfaces of most existing UAVs are generally composed of skins, beams, ribs, joints and fasteners, and most of them adopt all-metal structures or composite materials. The control surface with a metal structure increases the overall structural weight of the controller, which is not conducive to improving the operational economy of the UAV. In order to reduce the structural weight, carbon fiber composite materials are widely used in the manufacture of UAV control surfaces. Although carbon fiber composite materials control the structural weight to a certain extent and overcome the shortcomings of metal structures to a certain extent, the cost of carbon fiber composite parts is relatively high, which increases the manufacturing cost of UAVs; secondly, the production cycle of carbon fiber composite materials is long, which will affect the production and delivery time of UAVs. Finally, carbon fiber composite materials are prone to electrochemical corrosion when in contact with metal parts, which not only affects the durability of the parts, but may also have an adverse effect on the overall performance of the UAV. Utility Model Content

[0004] The purpose of the present invention is to provide a structure of a control surface of a UAV, which has the advantages of simple structure, convenient molding and easy assembly, and solves the problems raised by the above-mentioned background technology.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solution: a structure of a control surface of an unmanned aerial vehicle, comprising a rudder, an inner cavity of the rudder being fixedly connected to a round rod, one end of the round rod passing through the outer side of the rudder, and the inner cavity of the rudder being provided with a connecting structure.

[0006] The connecting structure includes a fixing plate fixedly connected to the round rod, a mounting block is detachably connected to one side of the fixing plate, a positioning rod is detachably connected to one side of the mounting block, a connecting rod is provided at one end of the positioning rod, a bolt 1 is passed through both ends of the connecting rod, a surface of the bolt 1 is connected to the positioning rod, and the positioning rod is located in the inner cavity of the connecting rod.

[0007] A fixing frame is fixedly connected to one side of the inner cavity of the rudder, one side of the connecting rod passes through the outside of the fixing frame, and positioning joints are fixedly connected to both sides of the fixing frame. A control surface assembly is provided on one side of the fixing frame, and three connecting grooves are provided on one side of the control surface assembly. Carbon tubes compatible with the positioning joints are fixedly connected to the opposite sides of the inner cavities of the connecting grooves on both sides, and a connecting joint is detachably connected to the inner cavity of the middle connecting groove, and the surface of the connecting joint is connected to the connecting rod by a bolt.

[0008] The control surface assembly includes a foam core, and the surfaces of the foam core and the carbon tube are provided with skins.

[0009] Furthermore, as a preferred embodiment of the present invention, the surface of the connecting joint is threadedly connected to two bolts 2, and the surface of the bolts 2 is rotatably connected to the control surface assembly.

[0010] Furthermore, as a preferred embodiment of the present invention, a baffle is fixedly connected to one side of the inner cavity of the fixing frame, the connecting rod is located in the inner cavity of the baffle, and a placement groove adapted to the connecting rod is provided on one side of the fixing frame.

[0011] Furthermore, as a preferred embodiment of the present invention, a groove is provided on one side of the rudder, and the groove is adapted to the middle connecting groove.

[0012] Furthermore, as a preferred embodiment of the present invention, the material of the skin is a fabric prepreg cured by a medium-high temperature OOA process, the material of the foam core is a high-strength PMI foam, the material of the positioning joint and the connecting joint are both high-strength aluminum alloy 7075, and the material of the carbon tube is a carbon fiber composite material.

[0013] A method for manufacturing a structure of a control surface of an unmanned aerial vehicle, the method comprising the following steps:

[0014] Step 1: Lay the cut skin on the lower mold and compact it. Then, locate and place the foam core according to the positioning line on the mold. Use the positioning template on the mold to locate the position of the carbon tube. Then, flip the skin of the lower mold from the leading edge and lay it on the surface of the foam core. Finally, close the upper and lower molds and assemble the bag. The product is manufactured through the OOA process, solidified under medium and high temperature conditions, and formed into preliminary parts after cooling. After demoulding, the parts are cut to the net size line, and the connection grooves are made according to the surface marks.

[0015] Step 2: After installing the mounting block to the surface of the fixing plate, fix the positioning rod and the mounting block with screws, and then connect the connecting rod and the positioning rod with a bolt. The bolt is passed through the outside of the fixing frame to complete the assembly of the connection structure connecting the rudder and the control surface assembly.

[0016] Step 3: The user puts the carbon tube on the surface of the two positioning joints to preliminarily position the rudder and control surface assembly. After turning another bolt one and moving the other bolt one away from the surface of the connecting rod, the user moves the connecting joint to the inner cavity of the connecting rod. At this time, the user takes another bolt one again and connects the connecting joint to the connecting rod through the other bolt one, thereby completing the connection and installation of the rudder and control surface assembly.

[0017] Beneficial effects: The technical solution of the present application has the following technical effects: the utility model has the advantages of simple structure, easy molding and easy assembly. In actual use, the structural design of the control surface is simple, easy to produce and assemble parts, easy to disassemble, and low replacement cost. From the material selection, the control surface body adopts a foam sandwich structure. Compared with the common beams and rib parts in aircraft, the processing process of the foam sandwich structure is more direct and efficient. It can be easily molded mainly by mechanical processing, without the need for complicated molds and processes, thereby effectively reducing production costs. In addition, the structure of the control surface focuses on lightweight. By optimizing the internal structure, unnecessary fasteners are removed, which not only further reduces the weight of the structure, but also helps to reduce flight energy consumption and improve the overall performance of the UAV. At the same time, the design without fasteners also reduces potential risks in the installation process and improves the reliability and safety of the structure. Therefore, this technical solution achieves the goals of efficient production and low-cost maintenance by adopting foam sandwich materials and simplifying the internal structure, providing strong support for the widespread application of UAVs.

[0018] It should be appreciated that all combinations of the foregoing concepts, as well as additional concepts described in greater detail below, may be considered to be part of the inventive subject matter of this disclosure, provided such concepts are not mutually inconsistent. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0020] Figure 1 This is a schematic diagram of the structure of the utility model;

[0021] Figure 2 This is a schematic diagram of the structure of the utility model;

[0022] Figure 3 It is a three-dimensional schematic diagram of the local structure of the utility model;

[0023] Figure 4 This is a three-dimensional schematic diagram of the fixing frame and positioning joint of the utility model;

[0024] Figure 5 It is a three-dimensional schematic diagram of the connection structure of the utility model.

[0025] In the figure, the meanings of the various reference numerals are as follows: 1. rudder; 2. round rod; 3. connecting structure; 31. fixing plate; 32. mounting block; 33. positioning rod; 34. connecting rod; 35. bolt one; 4. fixing frame; 5. positioning joint; 6. control surface assembly; 61. foam core; 62. skin; 7. connecting groove; 8. carbon tube; 9. connecting joint; 10. bolt two; 11. baffle; 12. groove. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. In order to better understand the technical content of the present invention, specific embodiments are cited and explained in conjunction with the drawings as follows. In this disclosure, various aspects of the present invention are described with reference to the drawings, and many illustrative embodiments are shown in the drawings. It should be understood that the various concepts and embodiments introduced above, as well as those described in more detail below, can be implemented in any of many ways. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0027] As attached Figure 1 To the attached Figure 5 As shown: This embodiment provides a structure of a UAV control surface, including a rudder 1, the inner cavity of the rudder 1 is fixedly connected to a round rod 2, one end of the round rod 2 passes through the outer side of the rudder 1, and the inner cavity of the rudder 1 is provided with a connecting structure 3.

[0028] The connecting structure 3 includes a fixing plate 31 fixedly connected to the round rod 2, and a mounting block 32 is detachably connected to one side of the fixing plate 31, and a positioning rod 33 is detachably connected to one side of the mounting block 32. A connecting rod 34 is provided at one end of the positioning rod 33, and bolts 35 are provided at both ends of the connecting rod 34. The surface of the bolt 35 is connected to the positioning rod 33, and the positioning rod 33 is located in the inner cavity of the connecting rod 34.

[0029] One side of the inner cavity of the rudder 1 is fixedly connected to a fixing frame 4, one side of the connecting rod 34 passes through the outside of the fixing frame 4, and both sides of the fixing frame 4 are fixedly connected to positioning joints 5. A control surface assembly 6 is provided on one side of the fixing frame 4, and three connecting grooves 7 are provided on one side of the control surface assembly 6. The opposite sides of the inner cavities of the connecting grooves 7 on both sides are fixedly connected to carbon tubes 8 that are compatible with the positioning joints 5. The inner cavity of the middle connecting groove 7 is detachably connected to a connecting joint 9, and the surface of the connecting joint 9 is connected to the connecting rod 34 by a bolt 35.

[0030] The control surface assembly 6 includes a foam core 61 , and a skin 62 is provided on the surface of the foam core 61 and the carbon tube 8 .

[0031] Specifically, two bolts 10 are threadedly connected to the surface of the connection joint 9 , and the surfaces of the bolts 10 are rotatably connected to the control surface assembly 6 .

[0032] In this embodiment, the connection joint 9 can be connected to the control surface assembly 6 by setting the second bolt 10, thereby ensuring the stability of the connection between the connection joint 9 and the control surface assembly 6.

[0033] Specifically, the baffle 11 is fixedly connected to one side of the inner cavity of the fixing frame 4 , the connecting rod 34 is located in the inner cavity of the baffle 11 , and a placement groove adapted to the connecting rod 34 is opened on one side of the fixing frame 4 .

[0034] In this embodiment, the baffle 11 is provided to guide the connecting rod 34 , thereby ensuring the stability of the connecting rod 34 during movement.

[0035] Specifically, a groove 12 is formed on one side of the rudder 1 , and the groove 12 is adapted to the middle connecting groove 7 .

[0036] In this embodiment, the groove 12 provides space for the connection and movement of the connecting joint 9 and the connecting rod 34 .

[0037] Specifically, the material of the skin 62 is a fabric prepreg cured by a medium-high temperature OOA process, the material of the foam core 61 is a high-strength PMI foam, the material of the positioning joint 5 and the connecting joint 9 are both high-strength aluminum alloy 7075, and the material of the carbon tube 8 is a carbon fiber composite material.

[0038] In this embodiment: by setting the material of the skin 62 to a fabric prepreg cured by a medium-high temperature OOA process, the generation of bubbles and defects can be effectively reduced, and the quality and performance of composite parts can be improved; by setting the material of the foam core 61 to a high-strength PMI foam, it can withstand a large load and prevent the core from absorbing water; by setting the material of the positioning joint 5 and the connecting joint 9 to high-strength aluminum alloy 7075, it has good mechanical properties, including high strength, hardness and toughness as well as corrosion resistance, and can withstand large loads and harsh environmental conditions; by setting the material of the carbon tube 8 to a carbon fiber composite material, while maintaining structural strength, the weight can be greatly reduced.

[0039] A method for manufacturing a structure of a control surface of an unmanned aerial vehicle, the method comprising the following steps:

[0040] Step 1: Lay and compact the cut skin 62 on the lower mold, then locate and place the foam core 61 according to the positioning lines on the mold, locate the position of the carbon tube 8 by the positioning template on the mold, and then flip the skin 62 of the lower mold from the leading edge and lay it on the surface of the foam core 61. Finally, close the upper and lower molds and assemble the bag. The bag is manufactured through the OOA process, solidified under medium and high temperature conditions, and formed into preliminary parts after cooling. After demolding, the parts are cut to the net size line, and the connecting grooves 7 are made according to the surface marks.

[0041] Step 2: After mounting the mounting block 32 onto the surface of the fixing plate 31, the positioning rod 33 is fixed to the mounting block 32 with screws. Then, the connecting rod 34 is connected to the positioning rod 33 with a bolt 1 35, and the bolt 1 35 is passed through the outside of the fixing frame 4, thereby completing the assembly of the connecting structure 3 connecting the rudder 1 and the control surface assembly 6.

[0042] Step 3: The user places the carbon tube 8 on the surfaces of the two positioning joints 5 to preliminarily position the rudder 1 and the control surface assembly 6. After rotating another bolt 35 and moving the other bolt 35 away from the surface of the connecting rod 34, the user moves the connecting joint 9 into the inner cavity of the connecting rod 34. At this time, the user takes another bolt 35 again and connects the connecting joint 9 to the connecting rod 34 through another bolt 35, thereby completing the connection and installation of the rudder 1 and the control surface assembly 6.

[0043] It should be noted that, in this document, relational terms such as first and second, etc. are merely used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations.

[0044] While the present invention has been described above with reference to preferred embodiments, this is not intended to limit the present invention. Persons skilled in the art will readily appreciate that various modifications and variations may be made without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention shall be determined by the claims.

Claims

1. A structure of a control surface of an unmanned aerial vehicle, comprising a rudder (1), characterized in that: The inner cavity of the rudder (1) is fixedly connected to a round rod (2), one end of the round rod (2) penetrates to the outside of the rudder (1), and the inner cavity of the rudder (1) is provided with a connecting structure (3); The connecting structure (3) includes a fixing plate (31) fixedly connected to the round rod (2), a mounting block (32) is detachably connected to one side of the fixing plate (31), a positioning rod (33) is detachably connected to one side of the mounting block (32), a connecting rod (34) is provided at one end of the positioning rod (33), a bolt (35) is provided through both ends of the connecting rod (34), a surface of the bolt (35) is connected to the positioning rod (33), and the positioning rod (33) is located in the inner cavity of the connecting rod (34); A fixing frame (4) is fixedly connected to one side of the inner cavity of the rudder (1), one side of the connecting rod (34) extends through the outer side of the fixing frame (4), and positioning joints (5) are fixedly connected to both sides of the fixing frame (4). A control surface assembly (6) is provided on one side of the fixing frame (4), and three connecting grooves (7) are provided on one side of the control surface assembly (6). Carbon tubes (8) adapted to the positioning joints (5) are fixedly connected to the opposite sides of the inner cavities of the connecting grooves (7) on both sides, and a connecting joint (9) is detachably connected to the inner cavity of the middle connecting groove (7), and the surface of the connecting joint (9) is connected to the connecting rod (34) via a bolt (35). The control surface assembly (6) comprises a foam core (61), and the surfaces of the foam core (61) and the carbon tube (8) are provided with a skin (62).

2. The structure of the control surface of an unmanned aerial vehicle according to claim 1, characterized in that: The surface of the connecting joint (9) is threadedly connected to two bolts 2 (10), and the surface of the bolts 2 (10) is rotatably connected to the control surface assembly (6).

3. The structure of the control surface of an unmanned aerial vehicle according to claim 1, characterized in that: A baffle (11) is fixedly connected to one side of the inner cavity of the fixed frame (4), the connecting rod (34) is located in the inner cavity of the baffle (11), and a placement groove adapted to the connecting rod (34) is provided on one side of the fixed frame (4).

4. The structure of the control surface of an unmanned aerial vehicle according to claim 1, characterized in that: A groove (12) is provided on one side of the rudder (1), and the groove (12) is adapted to the middle connecting groove (7).

5. The structure of the control surface of an unmanned aerial vehicle according to claim 1, characterized in that: The material of the skin (62) is a fabric prepreg cured by a medium-high temperature OOA process, the material of the foam core (61) is a high-strength PMI foam, the material of the positioning joint (5) and the connecting joint (9) are both high-strength aluminum alloy 7075, and the material of the carbon tube (8) is a carbon fiber composite material.

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