Control surface control mechanism of V-tail unmanned aerial vehicle

Abstract

The utility model discloses a control surface control mechanism of a V-tail unmanned aerial vehicle, which comprises a pair of control surface main bodies which are arranged in a V shape, and the included angle between the two control surface main bodies is 90 degrees; the main shaft is vertically arranged on the end faces of the ends, close to each other, of the control surface main bodies; and the control assembly is used for controlling the pair of main shafts to rotate synchronously. The utility model has the following advantages and effects: after being assembled, the control mechanism is completely hidden in the fuselage of the aircraft, so that the flight resistance is not additionally increased; differential motion and homodromous motion of the two control surface main bodies are respectively driven by the same motor, so that the deflection consistency of the control surface main bodies on the two sides can be ensured.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicles (UAVs), and in particular to a control surface mechanism for a V-tailed UAV. Background Technology

[0002] In the industrial-grade drone sector, agricultural and forestry plant protection, logistics and transportation, and geographic surveying and mapping are the three core application scenarios. Especially in the logistics and transportation sector, drones, with their speed and flexibility, demonstrate enormous potential in remote areas and emergency situations. Consumer-grade drones are primarily used for aerial photography and entertainment, satisfying people's demand for high-altitude perspectives and unique shooting effects. Furthermore, the global market for military drones continues to expand, and China's technological leadership in reconnaissance and strike drones and stealth drones has added new growth points to the drone market.

[0003] The V-tail drone, as a novel drone design, stands out in the drone market thanks to its unique V-shaped tail layout and efficient control surface mechanism. The V-tail design not only optimizes the drone's aerodynamic performance and reduces drag, but also improves its maneuverability and flight path accuracy. Simultaneously, the V-tail drone's control surface mechanism ensures consistent deflection of the main control surfaces on both sides through synchronous rotation control, which is particularly important for flight missions requiring precise control.

[0004] However, traditional UAVs have several drawbacks in terms of control surface mechanisms. Traditional UAV control surface mechanisms typically employ independent wireless links and hardware switching devices, making it impossible for the flight control computer to monitor communication status. Once a communication failure occurs, the UAV will lose control, posing a serious safety hazard. Furthermore, the short communication range of traditional remote controllers limits the UAV's flight range, requiring ground operators to constantly monitor whether the UAV has flown out of its safe zone. Simultaneously, the complex design of traditional control mechanisms increases system cost and complexity, and also raises maintenance difficulties.

[0005] For example, patent publication number CN119408697A, entitled "An Aircraft and Its Dual-Axis Rotary Control Surfaces," describes dual-axis rotary control surfaces comprising: a circular turntable rotatably mounted on the aircraft surface via a turntable axis; control surfaces rotatably mounted on the circular turntable via control surface axis perpendicular to the turntable axis, and flush with the aircraft surface when the control surfaces are retracted; a turntable power mechanism connected to the turntable axis for driving the circular turntable to rotate 360° around the turntable axis within the aircraft surface; a control surface power mechanism connected to the control surface axis for driving the control surfaces to rotate around the control surface axis; and a control device, with both the turntable power mechanism and the control surface power mechanism signal-connected to the control device. The disadvantages are: the traditional control mechanism design is complex, increasing system cost and complexity, and also increasing maintenance difficulty. Utility Model Content

[0006] To address the shortcomings of existing technologies, the purpose of this invention is to provide a control surface mechanism for a V-tailed unmanned aerial vehicle (UAV) that reduces flight drag and ensures consistent deflection of the servos on both sides.

[0007] The above-mentioned technical objective of this utility model is achieved through the following technical solution: a control surface mechanism for a V-tailed unmanned aerial vehicle, comprising:

[0008] A pair of control surface bodies are arranged in a V-shape, and the included angle between the two control surface bodies is 90 degrees;

[0009] The main shaft is vertically disposed on the end face of each of the main bodies of the control surface that is close to one end of each other;

[0010] A manipulation component for controlling the synchronous rotation of the pair of said spindles;

[0011] The control assembly includes a base, a support plate, a rotating shaft, a bevel gear set, and a controller. The base is horizontally positioned between a pair of control surface bodies, and the angle between the base and the two control surface bodies is 45 degrees. The support plate is vertically positioned at both ends of the base. The rotating shaft is horizontally rotatably connected to the upper end of the support plate. The bevel gear set includes two meshing gears. One gear of the bevel gear set is located on the main shaft, and the other gear of the bevel gear set is located at the outer end of the rotating shaft (33). The controller is used to control the pair of rotating shafts to rotate synchronously in the same direction or in opposite directions.

[0012] In a preferred embodiment, the present invention can be further configured as follows: the controller includes a gantry, a first motor, a driving gear, a driven gear, an external gear ring, an external gear, and a second motor. Both ends of the gantry are rotatably connected to the rotating shaft. The first motor is located inside the gantry and connected to the driving gear. The driving gear is located between the rotating shafts. The driven gear is rotatably connected to the inner end of the rotating shaft and meshes with the driving gear. The external gear ring is arranged around the outside of the gantry and forms a 90-degree angle with the two main control surfaces. The external gear meshes with the external gear ring. The second motor is located on the support plate and fixed to the external gear.

[0013] In a preferred embodiment, the present invention can be further configured such that the cross-section of the main body of the rudder surface is teardrop-shaped and gradually expands from top to bottom.

[0014] In a preferred embodiment, the present invention can be further configured such that the lower end face of the rudder surface body is arc-shaped from the inside to the outside and extends to the outer end position of the rudder surface body.

[0015] In a preferred embodiment, the present invention can be further configured such that: the main body of the rudder surface includes a panel and a crossbeam, the crossbeam is horizontally disposed on the upper end of the panel, and the main shaft is disposed on the crossbeam.

[0016] In a preferred embodiment, the present invention can be further configured such that the upper end of the panel is provided with a notch for the crossbeam to be embedded.

[0017] In a preferred embodiment, the present invention can be further configured such that the crossbeam is made of aluminum alloy and the panel is made of lightweight plastic.

[0018] In summary, this utility model has the following beneficial effects:

[0019] 1. After assembly, the control mechanism is completely hidden inside the aircraft fuselage and will not add any additional flight drag;

[0020] 2. The differential and co-directional movements of the two control surfaces are driven by the same motor, which ensures the consistency of the deflection of the two control surfaces.

[0021] 3. The control mechanism does not require wiring, making installation easier, reducing initial manufacturing costs, and facilitating later maintenance;

[0022] 4. Reduce the number of parts and design complexity of the main body of the control surface, and reduce the weight of the main body of the control surface. Attached Figure Description

[0023] Figure 1 This is a structural schematic diagram of an embodiment;

[0024] Figure 2 This is a schematic diagram of the structure of the manipulation component in the embodiment.

[0025] Reference numerals: 1. Control surface body; 11. Panel; 12. Crossbeam; 13. Notch; 2. Main shaft; 3. Control assembly; 31. Base; 32. Support plate; 33. Rotating shaft; 34. Bevel gear set; 4. Controller; 41. Gantry; 42. First motor; 43. Drive gear; 44. Driven gear; 45. External gear ring; 46. External gear; 47. Second motor. Detailed Implementation

[0026] The present invention will be further described in detail below with reference to the accompanying drawings.

[0027] like Figure 1 , Figure 2 As shown, a control surface mechanism for a V-tailed unmanned aerial vehicle includes a pair of control surface bodies 1, a pair of main shafts 2, and a control component 3.

[0028] like Figure 1 , Figure 2As shown, a pair of control surface bodies 1 are arranged in a V-shape, and the included angle between the two control surface bodies 1 is 90 degrees. The main shaft 2 is vertically arranged on the end face of each control surface body 1 that is close to one end of each other, and the control assembly 3 is used to control the synchronous rotation of the pair of main shafts 2.

[0029] like Figure 1 , Figure 2 As shown, the control assembly 3 includes a base 31, a support plate 32, a rotating shaft 33, a bevel gear set 34, and a controller 4. The base 31 is horizontally positioned between a pair of control surface bodies 1, and the angle between the base 31 and the two control surface bodies 1 is 45 degrees.

[0030] like Figure 1 , Figure 2 As shown, the support plate 32 is vertically disposed at both ends of the base 31, and the rotating shaft 33 is horizontally rotatably connected to the upper end of the support plate 32. The bevel gear set 34 includes two meshing gears. One of the gears of the bevel gear set 34 is disposed on the main shaft 2, and the other gear of the bevel gear set 34 is disposed at the outer end of the rotating shaft 33.

[0031] like Figure 1 , Figure 2 As shown, the controller 4 is used to control a pair of rotating shafts 33 to rotate synchronously in the same direction or in opposite directions. The controller 4 includes a gantry frame 41, a first motor 42, a driving gear 43, a driven gear 44, an external gear ring 45, an external gear 46, and a second motor 47.

[0032] like Figure 1 , Figure 2 As shown, the two ends of the gantry frame 41 are rotatably connected to the rotating shaft 33, the driving gear 43 is disposed between the rotating shaft 33, the driven gear 44 is rotatably connected to the inner end of the rotating shaft 33 and meshes with the driving gear 43, and the first motor 42 is disposed on the gantry frame 41 and connected to the driving gear 43.

[0033] like Figure 1 , Figure 2 As shown, the external gear ring 45 is arranged around the outside of the gantry frame 41, and the included angle between it and the two rudder surface bodies 1 is 90 degrees. The external gear 46 meshes with the external gear ring 45. The second motor 47 is arranged on the support plate 32 and is fixed to the external gear 46.

[0034] When it is necessary to control the two main control surfaces 1 to rotate in opposite directions, the first motor 42 rotates, which drives the drive gear 43 to rotate. The drive gear 43 drives a pair of driven gears 44 to rotate synchronously, and the rotation directions of the pair of driven gears 44 are opposite. At this time, the driven gears 44 drive the rotating shaft 33 to rotate, and the rotating shaft 33 drives the bevel gear set 34 to rotate synchronously, so as to realize the synchronous rotation control of the main shaft 2, and finally drive the two main control surfaces 1 to move in opposite directions.

[0035] When it is necessary to control the two main control surfaces 1 to rotate in the same direction, the first motor 42 remains stationary and fixes the drive gear 43. At this time, the second motor 47 is controlled to rotate, driving the external gear 46 to rotate. The external gear 46 then drives the external gear ring 45 to rotate, which in turn drives the gantry 41 to rotate. The gantry 41 then drives the first motor 42 and the drive gear 43 to rotate synchronously. Simultaneously, the drive gear 43 drives a pair of driven gears 44 to rotate synchronously, and the two driven gears 44 rotate in the same direction. The driven gears 44 then drive the rotating shaft 33 to rotate, which in turn drives the bevel gear set 34 to rotate synchronously, thereby achieving synchronous rotation control of the main shaft 2 and ultimately driving the two main control surfaces 1 to move in the same direction.

[0036] Meanwhile, after assembly, the control mechanism is completely hidden inside the aircraft fuselage, without adding extra flight drag. The differential and co-directional movements of the two control surface main bodies 1 are driven by the same motor, which can ensure the consistency of the deflection of the two control surface main bodies 1.

[0037] like Figure 1 , Figure 2 As shown, the cross-section of the control surface body 1 is teardrop-shaped and gradually expands from top to bottom to reduce wind resistance and ensure stable and high-speed flight of the UAV. The lower end face of the control surface body 1 is arc-shaped from the inside to the outside and extends to the outer end of the control surface body 1 to make all parts of the control surface body 1 streamlined, reduce wind resistance, and improve stability during flight.

[0038] like Figure 1 , Figure 2 As shown, the control surface body 1 includes a panel 11 and a crossbeam 12. The crossbeam 12 is made of aluminum alloy, and the panel 11 is made of lightweight plastic. This design ensures the structural strength of the control surface body 1 while reducing its weight, thus ensuring the stable flight of the UAV.

[0039] like Figure 1 , Figure 2 As shown, the crossbeam 12 is horizontally positioned on the upper end of the panel 11, and the main shaft 2 is positioned on the crossbeam 12. The upper end of the panel 11 is provided with a notch 13 for the crossbeam 12 to be inserted. The crossbeam 12 and the panel 11 are fixed by adhesive or screws to ensure quick assembly and stable fixation between the two.

[0040] The specific embodiments are merely explanations of this utility model and are not intended to limit it. After reading this specification, those skilled in the art can make modifications to these embodiments without contributing any inventive step, but such modifications are protected by patent law as long as they fall within the scope of the claims of this utility model.

Claims

1. A control surface mechanism for a V-tailed unmanned aerial vehicle, characterized in that: include: A pair of rudder surfaces (1) are arranged in a V-shape, and the included angle between the two rudder surfaces (1) is 90 degrees; The main shaft (2) is vertically disposed on the end face of each of the rudder surfaces (1) that is close to one end of each other; A control component (3) is used to control the synchronous rotation of the pair of spindles (2); The control assembly (3) includes a base (31), a support plate (32), a rotating shaft (33), a bevel gear set (34), and a controller (4). The base (31) is horizontally positioned between a pair of control surface bodies (1) and the angle between the base (31) and the two control surface bodies (1) is 45 degrees. The support plate (32) is vertically positioned at both ends of the base (31). The rotating shaft (33) is horizontally rotatably connected to the upper end of the support plate (32). The bevel gear set (34) includes two meshing gears. One of the gears of the bevel gear set (34) is located on the main shaft (2), and the other gear of the bevel gear set (34) is located at the outer end of the rotating shaft (33). The controller (4) is used to control the pair of rotating shafts (33) to rotate synchronously in the same direction or in opposite directions.

2. The control surface mechanism for a V-tailed unmanned aerial vehicle according to claim 1, characterized in that: The controller (4) includes a gantry (41), a first motor (42), a driving gear (43), a driven gear (44), an external gear ring (45), an external gear (46), and a second motor (47). Both ends of the gantry (41) are rotatably connected to the rotating shaft (33). The first motor (42) is located inside the gantry (41) and connected to the driving gear (43). The driving gear (43) is located on the rotating shaft (33). Between 33), the driven gear (44) is rotatably connected to the inner end of the rotating shaft (33) and meshes with the driving gear (43). The outer gear ring (45) is arranged around the outside of the gantry frame (41) and the included angle between it and the two rudder surface bodies (1) is 90 degrees. The outer gear (46) meshes with the outer gear ring (45). The second motor (47) is arranged on the support plate (32) and fixed with the outer gear (46).

3. The control surface mechanism for a V-tailed unmanned aerial vehicle according to claim 1, characterized in that: The cross-section of the main body of the rudder surface (1) is teardrop-shaped and gradually expands from top to bottom.

4. The control surface mechanism for a V-tailed unmanned aerial vehicle according to claim 3, characterized in that: The lower end face of the rudder body (1) is arranged in an arc shape from the inside to the outside, and extends to the outer end position of the rudder body (1).

5. The control surface mechanism for a V-tailed unmanned aerial vehicle according to claim 3, characterized in that: The main body of the rudder surface (1) includes a panel (11) and a crossbeam (12). The crossbeam (12) is horizontally arranged on the upper end of the panel (11), and the main shaft (2) is arranged on the crossbeam (12).

6. The control surface mechanism for a V-tailed unmanned aerial vehicle according to claim 5, characterized in that: The upper end of the panel (11) is provided with a notch (13) for the crossbeam (12) to be inserted.

7. The control surface mechanism for a V-tailed unmanned aerial vehicle according to claim 5, characterized in that: The crossbeam (12) is made of aluminum alloy, and the panel (11) is made of lightweight plastic.

Images