Control surface connection structure, single-bubble airfoil, and unmanned aerial vehicle

Abstract

This utility model discloses a control surface connection structure, a single-bulge wing, and an unmanned aerial vehicle, relating to the field of high-speed unmanned aerial vehicle technology. The control surface connection structure includes a control surface and a servo motor. The control surface is connected to the servo motor's drive rod via a first connector. The first connector is located on the side of the control surface and includes a first hinge plate and a rocker arm. The control surface is fixedly connected to the first hinge plate, which is rotatably connected to the side of the wing surface. The rocker arm is integrally connected to the first hinge plate, and extends away from the rotation axis of the first hinge plate. The servo motor's drive rod is rotatably connected to the end of the rocker arm away from the first hinge plate, thereby driving the first hinge plate to rotate relative to the wing surface. By adopting an integrated rocker arm and first hinge plate, the support and driving functions are integrated into the first connector, reducing the number of wing surface connection nodes, reducing structural redundancy, and decreasing the number of parts, thus lowering costs and improving production consistency.

Description

Technical Field

[0001] This utility model relates to the field of high-speed unmanned aerial vehicle (UAV) technology, and in particular to a control surface connection structure, a single-bulge wing, and an unmanned aerial vehicle. Background Technology

[0002] In existing high-speed UAV designs, control surfaces are typically mounted on the wings to achieve precise control of flight attitude, and servos drive the deflection of these surfaces. To improve the ease of servo installation and increase structural reliability, designers often use bulges on the wings to accommodate the servos and the telescopic rods connecting the control surfaces. However, this design method has significant drawbacks in terms of structural connections, especially related to the connection structure of the telescopic rods.

[0003] Specifically, in traditional designs, a hinge support needs to be installed at the wing root area to connect to the wing body, while a special connector needs to be installed in the center of the control surface to accommodate the servo telescopic rod. This not only increases the number of parts and makes the connection structure on the wing more complex, but also places higher demands on the machining and installation accuracy of the connectors, increasing the overall weight and production cost. Utility Model Content

[0004] The main purpose of this invention is to propose a control surface connection structure, a single-bulge wing, and an unmanned aerial vehicle, aiming to improve the utilization rate of parts, reduce costs, and reduce the weight of the aircraft.

[0005] To achieve the above objectives, the present invention proposes an operating surface connection structure, comprising:

[0006] The control surface and the servo motor are connected by a first connector to the drive rod of the servo motor.

[0007] The first connector is located on the side of the control surface. The first connector includes a first hinge plate and a rocker arm. The control surface is fixedly connected to the first hinge plate, and the first hinge plate is rotatably connected to the side of the wing surface. The rocker arm is integrally connected to the first hinge plate, and the rocker arm extends away from the rotation axis of the first hinge plate. The drive rod of the servo is rotatably connected to the end of the rocker arm away from the first hinge plate, so as to drive the first hinge plate to rotate relative to the wing surface.

[0008] In one embodiment, the first hinge plate has a recessed first clamping groove to clamp and fix the rudder surface.

[0009] In one embodiment, the end of the servo motor away from the first connector is rotatably connected to the wing surface via a mounting bracket;

[0010] The mounting bracket includes a first clamping piece and a second clamping piece, which are located on both sides of the single-sided skin of the wing surface to clamp the skin. The first clamping piece extends outward and is provided with a lug to rotatably connect to the servo motor.

[0011] In one embodiment, the control surface includes flaps and ailerons, and the number of servos is two, which control the rotation of the flaps and the ailerons respectively;

[0012] The mounting bracket is provided with two lugs for rotatably connecting the two servo motors.

[0013] In one embodiment, there are two first connectors, which are fixedly connected to the flap and the aileron, respectively, and the rocker arms of the two first connectors are located on the side close to the other first connector.

[0014] This invention also proposes a single-bulge wing, including the aforementioned control surface connection structure.

[0015] In one embodiment, the center of the wing surface of the single-bulge wing is recessed to form a mounting cavity, and both servos are located within the mounting cavity.

[0016] In one embodiment, a fairing is also included to cover the mounting cavity, and the two servos share one fairing.

[0017] In one embodiment, the fairing includes a front fairing and a rear fairing, the front fairing being fixedly connected to the wing surface, and the rear fairing having two parts, which are respectively fixedly connected to the flap and the aileron;

[0018] The front cover has a rotating interface on the side away from the nose of the fuselage. The rear cover extends into the front cover from the rotating interface. The control surface rotates relative to the wing surface. The volume of the rear cover extending into the front cover changes, and the cross-sectional size of the rear cover located at the rotating interface is adapted to the cross-sectional size of the rotating interface.

[0019] This utility model also proposes an unmanned aerial vehicle, including the aforementioned single-bulge wing.

[0020] The technical solution of this utility model integrates the supporting and driving functions into the first connector by adopting an integrated rocker arm and the first hinge plate, reducing the number of connection nodes on the wing surface, reducing structural redundancy, reducing the number of parts, reducing costs, and also reducing the overall weight to a certain extent; the integrated first hinge plate and the rocker arm serve as pre-assembled units, avoiding the position matching problem when multiple joints are installed independently, reducing sensitivity to processing and assembly accuracy, and improving production consistency. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0022] Figure 1 A schematic diagram of an embodiment of the control surface connection structure provided by this utility model;

[0023] Figure 2 for Figure 1 A magnified view of a section at point A in the middle;

[0024] Figure 3 This is a structural schematic diagram of the first connector and the mounting bracket;

[0025] Figure 4 An assembly diagram of the control surface connection structure provided by this utility model;

[0026] Figure 5 A schematic diagram of a single-bulge wing embodiment provided by this utility model;

[0027] Figure 6 for Figure 5 A magnified view of a section at point B in the middle;

[0028] Figure 7 A schematic diagram of another embodiment of the control surface connection structure provided by this utility model.

[0029] Explanation of icon numbers:

[0030] 100. Control surface connection structure; 1. Control surface; 11. Flaps; 12. Ailerons; 2. Servo; 21. Drive stick; 3. First connector; 31. First hinge plate; 32. First clamping slot; 33. Rocker arm; 4. Mounting bracket; 41. First clamping piece; 42. Second clamping piece; 43. Lug; 5. Wing surface; 51. Mounting cavity; 6. Fairing; 61. Front fairing; 611. Rotating interface; 62. Rear fairing; 7. Rotating connector; 8. Second connector.

[0031] The realization of the purpose, functional features and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0032] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present utility model.

[0033] It should be noted that if the embodiments of this utility model involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indicators will also change accordingly.

[0034] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the use of "and / or" or "and / or" throughout the text includes three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.

[0035] In existing high-speed UAV designs, control surfaces are typically mounted on the wings to achieve precise control of flight attitude, and servos drive the deflection of these surfaces. To improve the ease of servo installation and increase structural reliability, designers often use bulges on the wings to accommodate the servos and the telescopic rods connecting the control surfaces. However, this design method has significant drawbacks in terms of structural connections, especially related to the connection structure of the telescopic rods.

[0036] Specifically, in traditional designs, a hinge support needs to be installed at the wing root area to connect to the wing body, while a special connector needs to be installed in the center of the control surface to accommodate the servo telescopic rod. This not only increases the number of parts and makes the connection structure on the wing more complex, but also places higher demands on the machining and installation accuracy of the connectors, increasing the overall weight and production cost.

[0037] This utility model proposes a control surface connection structure 100.

[0038] Please see Figures 1 to 7 In one embodiment of this utility model, the operating surface connection structure 100 includes:

[0039] The control surface 1 and the servo motor 2 are connected by a first connector 3 and a drive rod 21 of the servo motor 2.

[0040] The first connecting member 3 is located on the side of the control surface 1. The first connecting member 3 includes a first hinge plate 31 and a rocker arm 33. The control surface 1 is fixedly connected to the first hinge plate 31, and the first hinge plate 31 is rotatably connected to the side of the wing surface 5. The rocker arm 33 is integrally connected to the first hinge plate 31, and the rocker arm 33 extends away from the rotation axis of the first hinge plate 31. The drive rod 21 of the servo motor 2 is rotatably connected to the end of the rocker arm 33 away from the first hinge plate 31, so as to drive the first hinge plate 31 to rotate relative to the wing surface 5.

[0041] It should be noted that the first connecting member 3 and the second connecting member are provided on both sides of the control surface 1. The second connecting member includes a second hinge plate. The control surface 1 is rotatably connected to the wing surface 5 through the first connecting member 3 and the second connecting member.

[0042] like Figure 2 and Figure 3 As shown, the servo motor 2 can drive the control surface 1 to rotate through the rocker arm 33 provided by the first connecting member 3. The drive rod 21 of the servo motor 2 is rotatably connected to the rocker arm 33. When the drive rod 21 moves, the drive rod 21 will drive the control surface 1 to rotate around its rotation axis, that is, rotate relative to the wing surface 5, so as to achieve control.

[0043] Optionally, the first hinge plate 31 and the second hinge plate are fixed to the rudder surface 1 by fasteners, the fasteners passing through the first hinge plate 31 and the second hinge plate to fix them to the rudder surface 1;

[0044] Both the first hinge plate 31 and the second hinge plate are provided with rotatable connection holes to rotatably connect the wing surface 5. In some embodiments, a rotatable connector 7 is sandwiched inside the skin of the wing surface 5. The rotatable connector 7 is provided with a rotatable connecting rod, which is connected to the rotatable connection hole so that the first hinge plate 31 and the second hinge plate can rotate relative to the wing surface 5.

[0045] In some embodiments, the line segment formed from the rotational connection of the first connector 3 and the wing surface 5 to the rotational connection of the first connector 3 and the drive rod 21 is defined as the first line segment. The first line segment is located on the side of the normal of the first hinge plate 31 closer to the servo motor 2. This arrangement can further reduce the required installation space and enable the servo motor 2 to generate a larger driving torque under the same output force, thereby improving the dynamic response speed of the control surface 1.

[0046] The technical solution of this utility model integrates the supporting and driving functions into the first connecting member 3 by adopting the integrated rocker arm 33 and the first hinge plate 31, reducing the number of connection nodes of the wing surface 5, reducing structural redundancy, reducing the number of parts, reducing costs, and also reducing the overall weight to a certain extent; the integrated first hinge plate 31 and the rocker arm 33 serve as pre-assembled units, avoiding the position matching problem when multiple joints are installed independently, reducing sensitivity to processing and assembly accuracy, and improving production consistency.

[0047] Optionally, the first hinge plate 31 is recessed to form a first clamping groove 32 to clamp and fix the rudder surface 1.

[0048] It is understood that the first clamping groove 32 can embed the control surface 1 into the first hinge plate 31 without the need to add a connecting boss on the surface of the control surface 1, thus fully preserving the curvature continuity of the airfoil surface, eliminating the risk of local airflow separation caused by the head of traditional fasteners, and improving assembly efficiency.

[0049] It should be noted that the rudder surface 1 has mounting grooves on both sides to fit the first hinge plate 31. The cross-section of the hinge plate and the rudder surface 1 is U-shaped, and the cross-section of the rudder surface 1 and the hinge plate is U-shaped. The two are fitted and inserted. When the rudder surface 1 is inserted into the first clamping groove 32, the first hinge plate 31 is embedded in the mounting groove. The surfaces of the two are uniformly and continuously connected to ensure the continuity of curvature.

[0050] Furthermore, the surface of the first clamping groove 32 is provided with a plurality of countersunk holes, and the connector is inserted into the countersunk holes to connect and fix the rudder surface 1 and the first hinge plate 31 to each other. Through the countersunk holes, the connector can not protrude from the surface of the first clamping groove 32, thus ensuring the continuity of curvature.

[0051] Optionally, six countersunk holes are provided on one side of the first clamping groove 32 to ensure the reliability of the assembly of the first hinge plate 31 and the rudder surface 1. It is understood that the number of countersunk holes is not limited to six, and this embodiment does not impose a specific limitation on this.

[0052] Optionally, the end of the servo motor 2 away from the first connector 3 is rotatably connected to the wing surface 5 via a mounting bracket 4;

[0053] The mounting bracket 4 includes a first clamping piece 41 and a second clamping piece 42, which are located on both sides of the single-sided skin of the wing surface 5 to clamp the skin. The first clamping piece 41 extends outward and is provided with an ear piece 43 to rotatably connect to the servo motor 2.

[0054] like Figure 3 As shown, it can be understood that the first clamping piece 41 and the second clamping piece 42 can effectively clamp the skin of the wing surface 5 with the mounting bracket 4, and the lug 43 can rotatably connect the servo motor 2 to ensure that the servo motor 2 is rotatably connected to the wing surface 5.

[0055] Furthermore, the first clamping piece 41 and the second clamping piece 42 of the mounting bracket 4 have a certain degree of flexibility, which can adapt to the wing skin 5 of different thicknesses and materials, enhancing the adaptability of the structure and making it easier to install the servo 2 on different types of wings, thus improving versatility.

[0056] It should be noted that the drive rod 21 of the servo motor 2 is rotatably connected to the rocker arm 33. When the drive rod 21 drives the control surface 1 to rotate, the body of the servo motor 2 will also rotate relative to the wing surface 5 to ensure control of the control surface 1.

[0057] In some embodiments, the first clamping piece 41 and the second clamping piece 42 are respectively located on both sides of the single-sided skin of the wing surface 5, and are connected by connectors so that the first clamping piece 41 and the second clamping piece 42 tightly clamp the single-sided skin of the wing surface 5. Optionally, the first clamping piece 41 and the second clamping piece 42 are connected and fixed by six spaced connectors. This embodiment does not impose a specific limit on the number of connectors.

[0058] Optionally, the control surface 1 includes flaps 11 and ailerons 12, and the number of servo motors 2 is two, which respectively control the rotation of the flaps 11 and the ailerons 12;

[0059] The mounting bracket 4 is provided with two lugs 43 for rotatably connecting the two servo motors 2.

[0060] It should be noted that in the design of high-speed unmanned aerial vehicles (UAVs), the precise control of the flaps 11 and the ailerons 12 is crucial for achieving stable flight attitude and excellent flight performance. Therefore, optimizing the connection structure of the flaps 11 and the ailerons 12, improving the drive efficiency of the servo motor 2, and reducing the complexity and weight of the structure have become important issues.

[0061] like Figure 3 and Figure 4 As shown, it can be understood that the two lugs 43 can rotatably connect the two servo motors 2, and the two servo motors 2 can be installed simultaneously through one mounting bracket 4, saving the number of parts, reducing weight and production costs. Furthermore, the two servo motors 2 can be installed in one place, which can further reduce the required installation space.

[0062] Furthermore, if any of the aforementioned servo motors 2 or servo surfaces 1 malfunction, they can be replaced or repaired individually without disassembling the entire system, which facilitates maintenance.

[0063] Optionally, there are two first connectors 3, which are fixedly connected to the flap 11 and the aileron 12 respectively, and the rocker arms 33 of the two first connectors 3 are located on the side closer to the other first connector 3.

[0064] It should be understood that, in order to control the flap 11 and the aileron 12 separately, two first connectors 3 are required, wherein both first connectors 3 are provided on the side close to each other of the flap 11 and the aileron 12;

[0065] It should be noted that the rocker arm 33 requires a certain amount of space. Therefore, by setting the two first connectors 3 close to each other and having the rocker arms 33 of the two first connectors 3 located on the side closer to the other first connector 3, the required space can be further reduced, the integrity of the airfoil can be maintained to the maximum extent, and airflow disturbance can be reduced.

[0066] By placing the two servo motors 2 together, the position of the servo motor 2 will be changed from the neutral position of the control surface 1 to one end closer to the center of the wing surface 5. In this way, the connection structure connected to the drive rod 21 and the connection structure connected to the control surface 1 can be combined into one, a single part. With almost no increase in weight, a new function is added, which significantly improves the efficiency of the part.

[0067] This utility model also proposes a single-bulge wing, which includes a control surface connection structure 100. The specific structure of the control surface connection structure 100 is as described in the above embodiments. Since this single-bulge wing adopts all the technical solutions of all the above embodiments, it has at least all the beneficial effects brought about by the technical solutions of the above embodiments, which will not be described in detail here.

[0068] It should be noted that in the current design field of high-speed UAVs, thin airfoils have become the mainstream choice, widely favored for their lower drag and higher aerodynamic efficiency. However, to improve the ease of installation and structural reliability of the servo 2, the traditional approach is to create bulges on the wing surface 5. These bulges are designed to ensure that the servo 2 and its connected telescopic rod remain stably within the structure of the wing surface 5 throughout its entire stroke, avoiding interference from the external environment. Since a wing typically has two control surfaces 1 (such as flaps 11 and ailerons 12), two corresponding bulges are needed on the wing surface 5.

[0069] However, the presence of bulges significantly compromises the integrity of the airfoil, leading to a decrease in the wing's aerodynamic performance. During high-speed flight, even minor changes to the airfoil can increase drag and reduce lift; therefore, changes to the airfoil shape should be minimized.

[0070] Optionally, the center of the wing surface 5 of the single-bulge wing is recessed to form a mounting cavity 51, and both of the servo motors 2 are located within the mounting cavity 51.

[0071] like Figure 1 and Figure 5 As shown, it can be understood that by forming the mounting cavity 51 in the center of the wing surface 5, both of the servo motors 2 are placed therein, thus avoiding the need to create multiple bulges on the wing surface 5, thereby maximizing the integrity of the airfoil and improving the aerodynamic performance of the wing.

[0072] Furthermore, a single bulge can effectively reduce the number of required parts, thereby lowering the cost of production and manufacturing.

[0073] It should be noted that when the servo motor 2 controls the control surface 1, it will rotate relative to the wing surface 5. Therefore, there is a certain gap between the servo motor 2 and the mounting cavity 51 so that the rudder can rotate within the mounting cavity 51.

[0074] Optionally, the fairing 6 is used to cover the mounting cavity 51, and the two servos 2 share one fairing 6.

[0075] It should be noted that the presence of bulges significantly disrupts the integrity of the airfoil, leading to a decrease in the wing's aerodynamic performance. Therefore, a fairing 6 is used. The shape of the fairing 6 for the servo 2 is typically determined by its travel, making its shape relatively complex. When multiple bulges need to be created on the wing surface 5, more complex fairing 6 shapes need to be designed and manufactured, undoubtedly increasing the difficulty and cost of component processing. More bulges mean more expensive components are required, causing the manufacturing cost of the drone to soar.

[0076] Therefore, the mounting cavity 51 can accommodate two servo motors 2 simultaneously, and the mounting cavity 51 can be covered by a single fairing 6, significantly reducing the number of parts and simplifying the wing's structural form. This not only reduces processing difficulty but also reduces material usage, thereby effectively lowering manufacturing costs.

[0077] Optionally, the fairing 6 includes a front fairing 61 and a rear fairing 62. The front fairing 61 is fixedly connected to the wing surface 5, and there are two rear fairings 62, which are respectively fixedly connected to the flap 11 and the aileron 12.

[0078] The front cover 61 has a rotating interface 611 on the side away from the nose. The rear cover 62 extends into the front cover 61 from the rotating interface 611. The control surface 1 rotates relative to the wing surface 5. The volume of the rear cover 62 extending into the front cover 61 changes, and the cross-sectional size of the rear cover 62 located at the rotating interface 611 is adapted to the cross-sectional size of the rotating interface 611.

[0079] like Figure 6 and Figure 7 As shown, it should be noted that the front cover 61 and the rear cover 62 of the fairing 6, as well as the rotating interface 611 between the rear cover 62 and the front cover 61, allow the fairing 6 to flexibly adjust its shape and position as the flaps 11 and the ailerons 12 rotate. This design not only maintains the streamlined shape of the wing and reduces airflow disturbance, but also improves the aerodynamic performance and adaptability of the UAV under different flight conditions.

[0080] Furthermore, the rear cover 62 extends into the overlapping structure of the front cover 61 to form an airtight interface. Combined with the cross-sectional adaptation characteristics of the rotating interface 611, it effectively blocks high-speed airflow from entering the mounting cavity 51, reducing the risk of aerodynamic impact and contaminant intrusion into the servo motor 2 system.

[0081] This utility model also proposes an unmanned aerial vehicle (UAV) including a single bulging wing. The specific structure of the single bulging wing is as described in the above embodiments. Since this UAV adopts all the technical solutions of all the above embodiments, it has at least all the beneficial effects brought about by the technical solutions of the above embodiments, which will not be described in detail here.

[0082] The above description is merely an exemplary embodiment of the present utility model and does not limit the patent scope of the present utility model. Any equivalent structural transformations made based on the technical concept of the present utility model and the contents of the present utility model specification and drawings, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present utility model.

Claims

1. A control surface connection structure, characterized in that, include: The control surface and the servo motor are connected by a first connector to the drive rod of the servo motor. The first connector is located on the side of the control surface. The first connector includes a first hinge plate and a rocker arm. The control surface is fixedly connected to the first hinge plate, and the first hinge plate is rotatably connected to the side of the wing surface. The rocker arm is integrally connected to the first hinge plate, and the rocker arm extends away from the rotation axis of the first hinge plate. The drive rod of the servo is rotatably connected to the end of the rocker arm away from the first hinge plate, so as to drive the first hinge plate to rotate relative to the wing surface.

2. The control surface connection structure as described in claim 1, characterized in that, The first hinge plate has a recessed first clamping groove to clamp and fix the rudder surface.

3. The control surface connection structure as described in claim 1, characterized in that, The end of the servo motor away from the first connector is rotatably connected to the wing surface via a mounting bracket; The mounting bracket includes a first clamping piece and a second clamping piece, which are located on both sides of the single-sided skin of the wing surface to clamp the skin. The first clamping piece extends outward and is provided with a lug to rotatably connect to the servo motor.

4. The control surface connection structure as described in claim 3, characterized in that, The control surface includes flaps and ailerons, and there are two servo motors, which control the rotation of the flaps and ailerons respectively. The mounting bracket is provided with two lugs for rotatably connecting the two servo motors.

5. The control surface connection structure as described in claim 4, characterized in that, There are two first connectors, which are fixedly connected to the flap and the aileron respectively, and the rocker arms of the two first connectors are located on the side closer to the other first connector.

6. A single-bulge wing, characterized in that, Includes the control surface connection structure as described in claim 5.

7. The single-bulge wing as described in claim 6, characterized in that, The single-bulge wing has a recessed mounting cavity at the center of its wing surface, and both servos are located within the mounting cavity.

8. The single-bulge wing as described in claim 7, characterized in that, It also includes a fairing used to cover the mounting cavity, and the two servos share one fairing.

9. The single-bulge wing as described in claim 8, characterized in that, The fairing includes a front fairing and a rear fairing. The front fairing is fixedly connected to the wing surface, and there are two rear fairings, which are fixedly connected to the flaps and the ailerons, respectively. The front cover has a rotating interface on the side away from the nose of the fuselage. The rear cover extends into the front cover from the rotating interface. The control surface rotates relative to the wing surface. The volume of the rear cover extending into the front cover changes, and the cross-sectional size of the rear cover located at the rotating interface is adapted to the cross-sectional size of the rotating interface.

10. An unmanned aerial vehicle, characterized in that, Includes the single-bulge wing as described in any one of claims 6 to 9.

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