Double-tail-rod unmanned aerial vehicle empennage
By employing a dual-tail boom design and combined rudder control, the problem of insufficient tail balance in drones has been solved, improving maneuverability and safety.
Patent Information
- Application Number
- CN202520429245.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-12
- Publication Date
- 2026-01-16
- Estimated Expiration
- 2035-03-12
AI Technical Summary
Existing drone tail fin designs cannot effectively balance the drone, resulting in decreased maneuverability and insufficient safety.
It adopts a dual tail boom design, including a horizontal tail fin assembly and a vertical tail fin. The combination of elevator and rudder enhances balance control, and the structural stability is improved by snap-fit and hollowed-out reinforcement plates.
This improved the drone's maneuverability and structural stability, ensuring a balance between safety and control.
Smart Images
Figure CN223803838U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model belongs to the unmanned plane technical field, concretely is a double tail rod unmanned plane tail wing. BACKGROUND
[0002] The unmanned plane is not loaded unmanned plane controlled by radio remote control equipment and self-provided program control device.
[0003] The unmanned plane tail wing mainly plays the role of balancing, and the unmanned plane flies by relying on the wing to generate the lift force, but the gravity center of the lift force of the unmanned plane is often not coincided with the gravity center of the unmanned plane, therefore, the lift force of the wing will generate a moment on the gravity center, and further make the unmanned plane pitch up or pitch down, in order to balance the moment, the unmanned plane tail wing needs to generate an opposite moment to balance the unmanned plane.
[0004] At present, the unmanned plane develops rapidly, for the small and medium-sized unmanned plane, the tail wing size is small, if the tail wing scheme of the conventional plane is designed, the unmanned plane cannot be well balanced, leading to the decline of the unmanned plane control performance, and the safety cannot be guaranteed. CONTENT OF UTILITY MODEL
[0005] In order to overcome the defects that the unmanned plane tail wing in the prior art cannot well balance the unmanned plane, leading to the decline of the unmanned plane control performance, and the safety cannot be guaranteed, the utility model provides a double tail rod unmanned plane tail wing.
[0006] The utility model discloses a tail boom of double tail rod unmanned aerial vehicle tail wing, including horizontal tail wing subassembly, the left end of horizontal tail wing subassembly is connected with two symmetrical tail rods that set up, and the right end of horizontal tail wing subassembly is provided with elevators, and the front and back two ends of horizontal tail wing subassembly are equipped with vertical tail wing respectively, and the right side of vertical tail wing is installed with rudder, and horizontal tail wing subassembly includes tail wing board frame and horizontal tail wing rudder, and one transverse long rib plate is equipped in tail wing board frame, and two symmetrical vertical wide rib plates are equipped, and transverse short rib plate is equipped in vertical wide rib plate, and the corresponding transverse long rib plate of transverse short rib plate is equipped with through -hole, and the vertical narrow rib plate is equipped between two symmetrical vertical wide rib plates, and the right end of vertical narrow rib plate and the corner position of tail wing board frame right side in the junction are all equipped with hollow strong board, and horizontal tail wing rudder is installed on hollow strong board, and the elevator is equipped with rudder connecting seat, and the side of elevator is equipped with a plurality of hinge devices that connect horizontal tail wing subassembly, and rudder connecting seat is connected with horizontal tail wing rudder, and the inner side of vertical tail wing is equipped with carbon rod that connects fixed seat, and the inner side of vertical tail wing is equipped with vertical rudder, and rudder is rotatably connected in vertical tail wing, and the inner side of rudder is equipped with direction connecting seat, and direction connecting seat is connected vertical rudder through connecting rod.
[0007] As a further improvement of the utility model, a plurality of grooves are arranged on the tail rod, and a buckle is arranged on each groove.
[0008] As a further improvement of the utility model, a concave structure is arranged on the front surface of the buckle, and the back surface of the buckle is a plane structure.
[0009] As a further improvement of the utility model, the rudder is hingedly connected to the vertical tail wing.
[0010] As a further improvement of the utility model, a plurality of tail wing reinforcing blocks are arranged on the inner side of the tail wing board frame.
[0011] As a further improvement of the utility model, a plurality of rudder reinforcing blocks are arranged in the elevator.
[0012] As can be seen from the above technical solutions, the beneficial effects of the utility model are as follows: in the device, the left end of the horizontal tail wing subassembly is connected with two symmetrical tail rods, the right end of the horizontal tail wing subassembly is provided with elevators, the front and back two ends of the horizontal tail wing subassembly are respectively provided with vertical tail wings, and the right side of the vertical tail wing is installed with a rudder, so that the overall structure is stable, the arrangement is reasonable, the unmanned aerial vehicle can be well balanced, the control performance of the unmanned aerial vehicle is improved, and the horizontal tail wing subassembly guarantees the structural strength and the weight, and the structure is stable and compact. BRIEF DESCRIPTION OF DRAWINGS
[0013] In order to make the technical scheme of the utility model more clear, the following will briefly introduce the drawings needed to be used in the description, obviously, the drawings in the following description are only some embodiments of the utility model, and for the ordinary skilled in the art, other drawings can be obtained according to these drawings without creative labor.
[0014] Figure 1 It is a structural schematic view of the tail boom of the utility model.
[0015] Figure 2 It is a structural schematic view of the tail boom of the utility model.
[0016] Figure 3 It is a structural schematic view of the horizontal tail assembly of the utility model.
[0017] Figure 4 It is a structural schematic view of the elevator of the utility model.
[0018] Figure 5 It is a sectional view of the elevator of the utility model.
[0019] Figure 6 It is a structural schematic view of the vertical tail and rudder of the utility model.
[0020] In the drawing: 1, tail boom; 2, horizontal tail assembly; 3, elevator; 4, vertical tail; 5, rudder; 6, recess; 7, buckle; 8, concave structure; 9, plane structure; 10, tail plate frame; 11, transverse long rib plate; 12, vertical wide rib plate; 13, transverse short rib plate; 14, through hole; 15, vertical narrow rib plate; 16, fixing seat; 17, hollow strong plate; 18, horizontal tail rudder; 19, tail strong block; 20, rudder connecting seat; 21, hinge device; 22, rudder strong block; 23, carbon rod; 24, vertical rudder; 25, direction connecting seat; 26, connecting rod; 27, hinge. DETAILED DESCRIPTION
[0021] In order to make the technical scheme of the utility model more clear, the following will briefly introduce the drawings needed to be used in the description, obviously, the drawings in the following description are only some embodiments of the utility model, and for the ordinary skilled in the art, other drawings can be obtained according to these drawings without creative labor.
[0022] As Figure 1The utility model discloses a double tail rod unmanned aerial vehicle tail wing, including horizontal tail wing subassembly 2, the left end of horizontal tail wing subassembly 2 is connected with two symmetrical tail rod 1 that sets up, the right end of horizontal tail wing subassembly 2 is provided with elevators 3, the front and rear ends of horizontal tail wing subassembly 2 are equipped with vertical tail 4 respectively, the right side of vertical tail 4 is installed with rudder 5.
[0023] Referring to Figure 2 , be equipped with several recesses 6 on tail rod 1, the recess 6 all is installed with buckle 7. The number of tail rod 1 is two, two tail rod 1 symmetrical setting, the front end of tail rod 1 is inserted into the fuselage of unmanned aerial vehicle, tail rod 1 is provided with recess 6 and buckle 7, buckle 7 is installed on recess 6, and recess 6 is matched with buckle 7, the rear end of tail rod 1 is inserted into horizontal tail wing subassembly 2 through hole structure, and is fixed by two buckles 7 limit, make the fixed more firm. Can quickly disassemble and assemble, facilitate tail rod 1's disassembly and maintenance work.
[0024] Buckle 7 is divided into two sides, the front of buckle 7 is provided with concave structure, to accommodate cylindrical tail rod related structure, the back of buckle 7 is plane structure, two buckles 7 are clamped in recess 6, and cooperate with horizontal tail wing subassembly 2, can limit the axial movement of tail rod 1.
[0025] Referring to Figure 3 , horizontal tail wing subassembly 2 includes tail wing plate frame 10 and horizontal tail wing rudder 18, be equipped with one transverse long rib plate 11 in tail wing plate frame 10, and two symmetrical vertical wide rib plate 12 that sets up, be equipped with transverse short rib plate 13 in vertical wide rib plate 12, be equipped with through -hole 14 on the corresponding transverse long rib plate 11 of transverse short rib plate 13 and with transverse short rib plate 13, be equipped with vertical narrow rib plate 15 between two symmetrical vertical wide rib plate 12, the right end of vertical narrow rib plate 15 and the corner position of tail wing plate frame 10 right side at vertical narrow rib plate 15 and tail wing plate frame 10 junction are all equipped with hollow strong plate 17, horizontal tail wing rudder 18 is installed on hollow strong plate 17;The inside of tail wing plate frame 10 is installed with several tail wing strong blocks 19.
[0026] Transverse long rib plate 11 is provided with fixed seat 16 symmetrically, and fixed seat 16 is connected with vertical tail 4. The right end of vertical narrow rib plate 15 and the corner position of tail wing plate frame 10 right side at vertical narrow rib plate 15 and tail wing plate frame 10 junction are all equipped with hollow strong plate 17, and hollow strong plate 17 is used for installing horizontal tail wing rudder 18, in addition to installing horizontal tail wing rudder 18, hollow strong plate 17 also has the effect of increasing wing rib intensity. The inside of tail wing plate frame 10 is installed with several tail wing strong blocks 19, tail wing strong blocks 19 can increase the local intensity of tail wing plate frame 10,
[0027] Buckle 7 combines the internal rib plate of horizontal tail wing subassembly 2 to fix horizontal tail wing subassembly 2, above structure cooperation is carried out at the clearance of tail rod 1 and through -hole simultaneously and smears high viscosity colloid and reinforces.
[0028] Referring to Figure 4 and Figure 5 , the elevator 3 is provided with a rudder connecting seat 20, the side surface of the elevator 3 is provided with a plurality of hinge devices 21 connected with the horizontal tail wing assembly 2, the rudder connecting seat 20 is connected with the horizontal tail wing rudder 18, and a plurality of rudder reinforcing blocks 22 are installed in the elevator 3.
[0029] The rudder reinforcing block 22 is used in cooperation with the tail wing reinforcing block 19, the tail wing reinforcing block 19 and the inside of the rudder reinforcing block 22 are both provided with notches, the hinge device 21 is installed in the notches, and the rotation of the elevator 3 is realized. In addition, the rudder reinforcing block 22 is in a trapezoidal structure, which is more helpful for the construction of the aerodynamic shape of the elevator 3, so that the aerodynamic shape can reduce air resistance. The rudder connecting seat 20 connected with the horizontal tail wing rudder 18 is located on the surface of the aerodynamic shape of the elevator 3.
[0030] Referring to Figure 6 , the inner side surface of the vertical tail wing 4 is provided with a carbon rod 23 connected with the fixed seat 16, the inner side surface of the vertical tail wing 4 is provided with a vertical rudder 24, the rudder 5 is hinged to the vertical tail wing 4 through a hinge 27, the inner side of the rudder 5 is provided with a direction connecting seat 25, the direction connecting seat 25 is connected with the vertical rudder 24 through a connecting rod 26, the number of the vertical tail wing 4 is two, the structure is relatively simple, the material is a light material such as a KT plate, the vertical tail wing 4 is fixed relative to the horizontal tail wing assembly 2, and the two are relatively static during flight. The number of the rudder 5 is two, the structure is relatively simple, the weight is light, and the shape is a rectangular plate-shaped mechanism, the rudder 5 is provided with a rudder connecting seat and accepts control from the vertical rudder 24 on the vertical tail wing 4.
[0031] The above description of the disclosed embodiments enables a person skilled in the art to implement or use the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to these embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.
Claims
1. A twin-tail boomless drone tail wing, characterized by: The horizontal tail assembly (2) is connected with two symmetrically arranged tail rods (1) at the left end, is provided with an elevator (3) at the right end, and is respectively provided with vertical tail wings (4) at the front and rear ends, and the right side of the vertical tail wing (4) is mounted with a rudder (5), the horizontal tail assembly (2) comprises a tail wing plate frame (10) and a horizontal tail rudder (18), the tail wing plate frame (10) is provided with a transverse long rib plate (11) and two symmetrically arranged vertical wide rib plates (12) inside, the vertical wide rib plate (12) is provided with a transverse short rib plate (13) inside, the transverse short rib plate (13) and the corresponding transverse long rib plate (11) are provided with through holes (14), the two symmetrically arranged vertical wide rib plates (12) are provided with a vertical narrow rib plate (15) between them, the transverse long rib plate (11) is symmetrically provided with a fixing seat (16), the right end of the vertical narrow rib plate (15) connected with the tail wing plate frame (10) and the corner position of the right side of the tail wing plate frame (10) are both provided with a hollow reinforcing plate (17), and the horizontal tail rudder (18) is mounted on the hollow reinforcing plate (17); the elevator (3) is provided with a rudder connecting seat (20), the side surface of the elevator (3) is provided with a plurality of hinge devices (21) connected with the horizontal tail assembly (2), the rudder connecting seat (20) is connected with the horizontal tail rudder (18), the inner side surface of the vertical tail wing (4) is provided with a carbon rod (23) connected with the fixing seat (16), the inner side surface of the vertical tail wing (4) is provided with a vertical rudder (24), the rudder (5) is rotatably connected with the vertical tail wing (4), the inner side of the rudder (5) is provided with a direction connecting seat (25), and the direction connecting seat (25) is connected with the vertical rudder (24) through a connecting rod (26).
2. The twin-tail boomless drone tail wing of claim 1, wherein: A plurality of grooves (6) are arranged on the tail rod (1), and a buckle (7) is arranged on each groove (6).
3. The twin-tail boomless drone tail wing of claim 2, wherein: The front surface of the buckle (7) is provided with a concave structure, and the back surface of the buckle (7) is a plane structure.
4. The twin-tail boomless drone tail wing of claim 3, wherein: The rudder (5) is hingedly connected with the vertical tail wing (4) through a hinge (27).
5. The twin-tail boomless drone tail wing of claim 4, wherein: A plurality of tail wing reinforcing blocks (19) are mounted on the inner side of the tail wing plate frame (10).
6. The twin-tail boomless drone tail wing of claim 5, wherein: A plurality of rudder reinforcing blocks (22) are mounted in the elevator (3).