Unmanned aerial vehicle wing surface structure and unmanned aerial vehicle

Abstract

The utility model discloses an unmanned plane wing rudder surface structure and unmanned plane relates to unmanned plane technical field, the utility model discloses the technical scheme of adopting multiple rudder surface structures that are arranged at the same side of wing interval, when the low -speed operation of unmanned plane, multiple drive parts synchronous operation, to make multiple rudder surface structures synchronous rotation, to this for the steering of unmanned plane provides the required torque, when the high -speed operation of unmanned plane, because the wind speed is too fast, control is away from the rudder surface structure of unmanned plane fuselage rotation, can provide the required torque for the steering action of unmanned plane when high -speed flight, and when the super -high -speed operation of unmanned plane, because the flight speed is too fast, the rudder surface structure rotation of unmanned plane away from unmanned plane fuselage can increase the deformation degree of wing, and through the drive unmanned plane structure rotation close to unmanned plane fuselage, to this through the control to multiple or single drive part, to facilitate the rotation of multiple rudder surface structures or single rudder surface structure control.

Description

Technical Field

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

[0002] As a military aircraft used in military exercises to simulate enemy missiles or aircraft, unmanned aerial vehicles (UAVs) need to possess low-speed, high-speed, and ultra-high-speed flight capabilities. For ease of control, their control surfaces need to be designed. Control surfaces are the operable surfaces on the wings of an aircraft. During flight, the aircraft's attitude and direction can be changed by manipulating these surfaces. Control surfaces are generally divided into three types, corresponding to controlling the aircraft's takeoff and landing, turning, and roll, respectively. Elevators are mounted on the horizontal stabilizer and are used to control the aircraft's climb and descent; rudders are mounted on the vertical stabilizer and are used to control the aircraft's turn; ailerons are mounted on the wings and are used to control the aircraft's roll.

[0003] The aerodynamic characteristics of drones are closely related to the control surfaces on their wings. Drones have a wide range of flight speeds, so there are certain requirements for the control surfaces and the control surfaces themselves.

[0004] In related technologies, most UAVs use a single control surface. However, a single control surface has low adaptability and requires high control algorithms. It is difficult to meet the speed control requirements of UAVs at low speeds, high speeds, and ultra-high speeds, which reduces the control accuracy of UAVs and affects their normal use. Utility Model Content

[0005] The main purpose of this invention is to propose a wing control surface structure for a drone and a drone in general, which aims to overcome the maneuverability of drones in different speed ranges, reduce the difficulty of control, and improve the flexibility of drones.

[0006] To achieve the above objectives, the UAV wing control surface structure proposed in this utility model includes:

[0007] The wing has multiple rotating slots spaced apart on its side.

[0008] Multiple control surface structures, one of the control surface structures is rotatably disposed in one of the rotating slots, and the multiple control surface structures are disposed along the edge of the wing;

[0009] Multiple drive units are provided, with one drive unit disposed on one side of each control surface structure. The drive unit is connected to the control surface structure to enable the control surface structure to rotate relative to the wing.

[0010] In one embodiment, the control surface structure includes a control surface shaft and a control surface wing, one end of the control surface shaft is connected to the side of the control surface wing, and the other end of the control surface shaft is rotatably connected to the side wall of the rotating slot.

[0011] In one embodiment, the control surface extends along the tilt direction of the wing surface.

[0012] In one embodiment, a transmission cavity is provided on the side of the rudder wing near the rudder axis, and a transmission cylinder is provided in the transmission cavity, and the drive unit is connected to the transmission cylinder;

[0013] The transmission cylinder is coaxial with the rudder surface shaft.

[0014] In one embodiment, the transmission cylinder includes a cylindrical body and a plug-in portion. The side wall of the transmission cavity is provided with a plug-in groove. The plug-in portion is connected to the side of the cylindrical body and is inserted into the plug-in groove. The connecting portion passes through the rudder wing and is connected to the plug-in portion.

[0015] In one embodiment, the insertion portion is restricted to rotation within the insertion slot.

[0016] In one embodiment, the surface of the rudder wing through which the connecting portion passes is provided with a groove.

[0017] In one embodiment, the drive unit includes a power assembly and a moving rod, the power assembly being connected to the moving rod to drive the moving rod to translate.

[0018] The cylindrical body has a spirally arranged transmission groove on its surface, and one end of the moving rod is inserted into the transmission groove.

[0019] In one embodiment, the power assembly includes a power component and a drive shaft. The power component is poweredly connected to the drive shaft. The drive shaft has a threaded surface and passes through the movable rod, with the movable rod threadedly engaged with the drive shaft.

[0020] This utility model also proposes an unmanned aerial vehicle (UAV), including the UAV wing control surface structure.

[0021] The technical solution of this utility model employs multiple control surface structures spaced apart on the same side of the wing. When the UAV is running at low speed, multiple drive units operate synchronously, causing the multiple control surface structures to rotate synchronously, thereby providing the necessary torque for the UAV's steering. When the UAV is running at high speed, due to the high wind speed, controlling the rotation of the control surface structures far from the UAV fuselage can provide the necessary torque for the UAV's steering action during high-speed flight. When the UAV is running at ultra-high speed, due to the high flight speed, the rotation of the UAV structures far from the UAV fuselage will increase the degree of wing deformation. By driving the UAV structures close to the UAV fuselage to rotate, and by controlling multiple or a single drive unit, it is possible to control the rotation of multiple or a single control surface structure. Thus, according to the UAV's operating speed, the UAV can fly stably and flexibly at different speeds, thereby improving the control surface manipulation efficiency and reducing the difficulty of slotting. Attached Figure Description

[0022] 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.

[0023] Figure 1 A schematic diagram of the first embodiment of the UAV wing control surface structure provided by this utility model;

[0024] Figure 2 A schematic diagram of the second embodiment of the UAV wing control surface structure provided by this utility model;

[0025] Figure 3 A schematic diagram of the third embodiment of the UAV wing control surface structure provided by this utility model;

[0026] Figure 4 A schematic diagram of the fourth embodiment of the UAV wing control surface structure provided by this utility model;

[0027] Figure 5 A schematic diagram of the fifth embodiment of the UAV wing control surface structure provided by this utility model;

[0028] Figure 6 This is a schematic diagram of the sixth embodiment of the UAV wing control surface structure provided by this utility model.

[0029] Explanation of icon numbers:

[0030] 1000. UAV wing and control surface structure; 10. Wing; 11. Drive cavity; 12. Rotating groove; 13. Receiving groove; 20. Control surface structure; 21. Control surface shaft; 22. Control surface wing; 23. Transmission cylinder; 231. Insertion part; 232. Connection hole; 233. Cylinder body; 24. Transmission cavity; 25. Transmission groove; 26. Insertion groove; 27. Through hole; 30. Drive unit; 31. Transmission shaft; 32. Power component; 33. Moving rod; 34. Linkage part; 35. Transmission sleeve; 36. Power sleeve.

[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] This utility model proposes a control surface structure for a drone wing.

[0036] Please see Figure 1 In one embodiment of this utility model, the wing control surface structure of the UAV includes:

[0037] Wing 10, wherein a plurality of rotating slots 12 are provided at intervals on the side of the wing 10;

[0038] Multiple control surface structures 20, one of the control surface structures 20 is rotatably disposed in one of the rotating slots 12, and the multiple control surface structures 20 are disposed along the edge of the wing 10;

[0039] Multiple drive units 30, one of which is provided on one side of the control surface structure 20. The drive unit 30 is connected to the control surface structure 20 so that the control surface structure 20 can rotate relative to the wing 10.

[0040] like Figure 2 As shown, the multiple rotating slots 12 provided on the side of the wing 10 are spaced apart so that the control surface structure 20 is provided in each rotating slot 12.

[0041] It is understood that by setting multiple control surface structures 20, and the multiple control surface structures 20 are arranged along the edge of the wing 10, a control surface that can be controlled separately is formed, so as to adapt to the control surface to stably provide the torque required for the UAV to turn in low-speed, high-speed and ultra-high-speed environments.

[0042] It should be noted that each of the control surface structures 20 is provided with a drive unit 30 on one side. In order to enable multiple control surface structures 20 to move simultaneously or individually, the multiple drive units 30 can be linked or controlled independently.

[0043] It is understandable that, in order to facilitate the control of the power output of the drive unit 30, a control module for controlling the operation of the drive unit 30 is installed inside the UAV.

[0044] Preferably, there are two control surface structures 20, and the two control surface structures 20 are spaced apart on the same side of the wing 10.

[0045] It is understood that the wing 10 is provided with a drive cavity 11, a plurality of drive units 30 are disposed in the drive cavity 11, and the drive cavity 11 is connected to a plurality of rotating slots 12.

[0046] The technical solution of this utility model employs multiple control surface structures 20 spaced apart on the same side of the wing 10. When the UAV is running at low speed, the multiple drive units 30 operate synchronously to make the multiple control surface structures 20 rotate synchronously, thereby providing the necessary torque for the UAV's steering. When the UAV is running at high speed, due to the high wind speed, controlling the rotation of the control surface structures 20 away from the UAV fuselage can provide the necessary torque for the UAV's steering action during high-speed flight. When the UAV is running at ultra-high speed, due to the high flight speed, the rotation of the UAV structures away from the UAV fuselage will increase the deformation of the wing 10. By driving the UAV structures close to the UAV fuselage to rotate, the rotation of multiple or a single control surface structure 20 can be controlled by multiple or a single drive unit 30. Thus, according to the UAV's operating speed, the UAV can fly stably and flexibly at different speeds, thereby improving the control surface's manipulation efficiency and reducing the difficulty of slotting.

[0047] In one embodiment, the control surface structure 20 includes a control surface pivot 21 and a control surface wing 22. One end of the control surface pivot 21 is connected to the side of the control surface wing 22, and the other end of the control surface pivot 21 is rotatably connected to the side wall of the rotating groove 12.

[0048] like Figures 4 to 5 As shown, the control surface wing 22 is provided with the control surface rotation shaft 21 on its side. In order to ensure the stability of the rotation of the control surface wing 22, the control surface rotation shaft 21 is provided on the opposite side of the control surface wing 22, and the rotation centers of the two control surface rotation shafts 21 are on the same straight line.

[0049] It is understood that each of the opposite sidewalls of the rotating groove 12 is provided with a receiving groove 13 for accommodating the control surface shaft 21, and the two receiving grooves 13 are arranged opposite to each other. When the control surface wing 22 is installed, the two control surface shafts 21 are respectively inserted into the two receiving grooves 13, so as to facilitate the stability of the control surface wing 22 when it rotates.

[0050] like Figure 2 As shown, in order to ensure the rotation of the control surface wing 22, the rotation groove 12 extends vertically through the wing, thereby providing rotation space for the rotation of the control surface wing 22.

[0051] In one embodiment, the surface of the control surface 22 extends along the tilt direction of the surface of the wing 10.

[0052] In order not to affect the normal operation of the wing 10, the surface of the control surface 22 is extended along the inclined direction of the surface of the wing 10.

[0053] It is understandable that by setting the surface of the wing 10 flush with the surface of the control wing 22, the normal operation of the UAV is ensured.

[0054] In one embodiment, the control surface wing 22 is provided with a transmission cavity 24 on the side near the control surface pivot 21, and a transmission cylinder 23 is provided in the transmission cavity 24. The drive unit 30 is connected to the transmission cylinder 23.

[0055] The transmission cylinder 23 is coaxial with the rudder surface shaft 21.

[0056] like Figure 4 As shown, a transmission cavity 24 is provided in the control surface wing 22 to provide a connection space for the connection between the transmission cylinder 23 and the drive unit 30. In this way, when the drive unit 30 outputs power, the transmission cylinder 23 can be used to ensure that the control surface wing 22 can rotate relative to the wing 10.

[0057] It is understood that by making the transmission cylinder 23 coaxial with the rotation center of the control surface shaft 21, when the drive unit 30 drives the control surface shaft 21 to rotate, the transmission cylinder 23 can rotate synchronously with the control surface shaft 21 and have the same rotation center, thereby ensuring the control efficiency of the control surface wing 22 rotation.

[0058] In one embodiment, the transmission cylinder 23 includes a cylindrical body 233 and a plug-in portion 231. The side wall of the transmission cavity 24 is provided with a plug-in groove 26. The plug-in portion 231 is connected to the side of the cylindrical body 233 and is plugged into the plug-in groove 26. The connecting portion passes through the rudder wing 22 and is connected to the plug-in portion 231.

[0059] like Figure 5 As shown, the insertion grooves 26 are provided on the opposite sidewalls of the transmission cavity 24, and the insertion grooves 26 are adapted to the insertion portions 231 provided on the sidewalls of the cylindrical body 233.

[0060] It is understood that the insertion part 231 is inserted into the insertion slot 26, and the side of the insertion part 231 contacts the side wall of the insertion slot 26, thereby fixing the transmission cylinder 23 and the control surface wing 22 relative to each other to ensure the stability of the transmission.

[0061] It should be noted that, in order to prevent the rudder wing 22 from rotating relative to the cylindrical body 233 during the rotation of the cylindrical body 233, both the cross-section of the insertion part 231 and the cross-section of the insertion groove 26 have side edges, so as to prevent the insertion part 231 from rotating in the insertion groove 26 after the insertion part 231 is inserted and engaged with the insertion groove 26.

[0062] In one embodiment, the cross-section of the insertion portion 231 and the cross-section of the insertion slot 26 are both polygonal.

[0063] To ensure the stability of the connection between the plug-in part 231 and the control surface wing 22, a through hole 27 is provided on the control surface wing 22, and a connecting hole 232 is provided on the plug-in part 231. When the plug-in part 231 is plugged into the control surface wing 22, the through hole 27 communicates with the connecting hole 232, so that the connecting part passes through the through hole 27 and is connected to the connecting hole 232.

[0064] It is understood that the connecting hole 232 is a threaded hole and the connecting part is a bolt.

[0065] In one embodiment, the insertion portion 231 is restricted to rotating within the insertion slot 26.

[0066] In one embodiment, the surface of the rudder wing 22 through which the connecting portion passes is provided with a groove.

[0067] It should be noted that when the connecting part is connected to the control surface wing 22, the top of the connecting part will be exposed on the surface of the control surface wing 22. This exposure of the connecting part can easily affect the normal flight of the wing 10.

[0068] It is understandable that the groove is designed so that after the connecting part passes through the control surface wing 22, one end of the connecting part is located in the groove, thereby preventing the connecting part from being exposed. By setting a cover, the cover can fill the groove, thereby preventing the groove from being exposed and affecting the operation of the wing.

[0069] In one embodiment, the drive unit 30 includes a power component and a moving rod 33, the power component being connected to the moving rod 33 to drive the moving rod 33 to translate.

[0070] The cylindrical body 233 has a spirally arranged transmission groove 25 on its surface, and one end of the moving rod 33 is inserted into the transmission groove 25.

[0071] like Figure 4 As shown, the power component is a power output component, and the moving rod 33 is a transmission part. When the power component outputs power, the moving rod 33 moves in translation, thereby facilitating the rotation of the cylindrical body 233.

[0072] like Figure 6As shown, the transmission groove 25 is spirally arranged, and one end of the moving rod 33 is inserted into the transmission groove 25. When the moving rod 33 moves horizontally with the output of the power component, the moving rod 33 can move within the transmission groove 25, thereby driving the cylindrical body 233 to rotate, thereby realizing the rotation control of the control surface wing 22.

[0073] To ensure the movement of the movable rod 33 within the transmission groove 25, a rolling part is connected to one end of the movable rod 33 inserted into the transmission groove 25. This prevents the rolling part from restricting the movement of the movable rod 33 when it moves within the transmission groove 25, thereby ensuring the stability of the rotation control of the control surface wing 22.

[0074] In one embodiment, the transmission groove 25 is a spiral line that circles the cylindrical body 233 by 180 degrees, thereby driving the moving rod 33 to translate back and forth to realize the rotation of the cylindrical body 233.

[0075] It is understandable that by inserting the movable rod 33 into the transmission groove 25, the rotation of the cylindrical body 233 is achieved by translating the movable rod 33, and the rotation of the cylindrical body 233 is restricted by inserting the movable rod 33 into the transmission groove 25. That is, when the control surface resists the thrust brought by the incoming flow, it can also prevent the control surface from deflecting back and ensure that the deflection angle remains unchanged.

[0076] In one embodiment, the power assembly includes a power component 32 and a drive shaft 31. The power component 32 is poweredly connected to the drive shaft 31. The drive shaft 31 has a thread on its surface. The drive shaft 31 passes through the moving rod 33, and the moving rod 33 is threadedly engaged with the drive shaft 31.

[0077] It is understood that the power output of the power component 32 drives the transmission shaft 31 to rotate, while one end of the moving rod 33 is restricted by the transmission groove 25 to rotate around the transmission shaft 31, thereby facilitating the control of the moving rod 33 to move along the transmission shaft 31. Furthermore, due to the restriction of the transmission groove 25, it is convenient to drive the transmission cylinder 23 and the control surface wing 22 to rotate.

[0078] It should be noted that the power component 32 is an electric motor.

[0079] To facilitate the connection between the drive shaft 31 and the moving rod 33, a coupling structure is used between the drive shaft 31 and the moving rod 33.

[0080] It is understandable that, such as Figure 3As shown, the coupling structure includes a power sleeve 36, a transmission sleeve 35, and a linkage part 34. The power sleeve 36 is sleeved on the output end of the power component 32, and the transmission sleeve 35 is sleeved on one end of the transmission shaft 31. The power sleeve 36 and the transmission sleeve 35 are connected by the linkage part 34, thereby facilitating the power transmission between the power component 32 and the transmission shaft 31.

[0081] To ensure the stability of the connection between the coupling structure, the output end of the power component 32, and the transmission shaft 31, multiple clamping bolts are provided on both the power sleeve 36 and the transmission sleeve 35. The clamping bolts abut against the transmission shaft 31 and the output end of the power component 32.

[0082] It is understandable that the tightness can be adjusted by relying on the clamping bolt, thereby improving the connection stability between the drive shaft 31 and the drive sleeve 35, and improving the connection stability between the output end of the power component 32 and the power sleeve.

[0083] Furthermore, both the transmission sleeve 35 and the power sleeve 36 are provided with a plurality of clamping bolts, which are arranged around and spaced apart on the transmission sleeve 35 and the power sleeve 36. By rotating the plurality of clamping bolts, the central axis alignment between the transmission sleeve 35 and the transmission shaft 31 is adjusted, and the central axis alignment between the output end of the power component and the power sleeve 36 is adjusted, thereby facilitating the alignment of the output end of the power component 32 with the central axis of the transmission shaft 31, and ensuring the efficiency and quality of transmission.

[0084] In one embodiment, a disc is provided at one end of the transmission sleeve 35, one end of the power sleeve 36, and both ends of the linkage part 34. The discs are connected in pairs, and two discs are connected by connecting bolts.

[0085] This utility model also proposes an unmanned aerial vehicle (UAV) including the aforementioned UAV wing control surface structure. The specific structure of the UAV wing control surface structure 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 elaborated here.

[0086] 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 structure for a UAV wing, characterized in that, include: The wing has multiple rotating slots spaced apart on its side. Multiple control surface structures, one of the control surface structures is rotatably disposed in one of the rotating slots, and the multiple control surface structures are disposed along the edge of the wing; Multiple drive units are provided, with one drive unit disposed on one side of each control surface structure. The drive unit is connected to the control surface structure to enable the control surface structure to rotate relative to the wing.

2. The UAV wing control surface structure as described in claim 1, characterized in that, The control surface structure includes a control surface shaft and a control surface wing. One end of the control surface shaft is connected to the side of the control surface wing, and the other end of the control surface shaft is rotatably connected to the side wall of the rotating slot.

3. The UAV wing control surface structure as described in claim 2, characterized in that, The control surface extends along the tilt direction of the wing surface.

4. The UAV wing control surface structure as described in claim 2, characterized in that, The control surface wing has a transmission cavity on the side near the control surface pivot, and a transmission cylinder is provided in the transmission cavity. The drive unit is connected to the transmission cylinder. The transmission cylinder is coaxial with the rudder surface shaft.

5. The UAV wing control surface structure as described in claim 4, characterized in that, The transmission cylinder includes a cylindrical body and a plug-in part. The side wall of the transmission cavity is provided with a plug-in groove. The plug-in part is connected to the side of the cylindrical body and is inserted into the plug-in groove. The connecting part passes through the rudder wing and is connected to the plug-in part.

6. The UAV wing control surface structure as described in claim 5, characterized in that, The insertion part is restricted to rotation within the insertion slot.

7. The UAV wing control surface structure as described in claim 5, characterized in that, The surface of the rudder wing through which the connecting part passes is provided with a groove.

8. The UAV wing control surface structure as described in claim 5, characterized in that, The drive unit includes a power component and a moving rod, the power component being connected to the moving rod to drive the moving rod to translate; The cylindrical body has a spirally arranged transmission groove on its surface, and one end of the moving rod is inserted into the transmission groove.

9. The UAV wing control surface structure as described in claim 8, characterized in that, The power assembly includes a power component and a drive shaft. The power component is poweredly connected to the drive shaft. The drive shaft has a thread on its surface. The drive shaft passes through the moving rod, and the moving rod is threadedly engaged with the drive shaft.

10. A drone, characterized in that, Includes the wing control surface structure of the UAV as described in any one of claims 1 to 9.

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