Integrated V-tail mechanism and unmanned aerial vehicle
By designing an integrated V-tail mechanism, the problems of large space occupation and easy breakage at the connection points of the UAV V-tail structure were solved, achieving convenient transportation and improved structural strength.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SHANGHAI FUKUN AVIATION TECH CO LTD
- Filing Date
- 2023-12-22
- Publication Date
- 2026-05-01
AI Technical Summary
The V-tail structure in existing drones takes up a lot of space and is inconvenient to transport. At the same time, making the V-tail a detachable connection will cause excessive stress at the connection between the tail fin and the fuselage, making it prone to breakage.
An integrated V-tail mechanism was designed, including a base, tail fin body, support assembly, and rotating assembly. It can be stored separately during transportation through a detachable connection. During flight, the support assembly supports the base to enhance structural strength, and the tail fin can be independently controlled through servo motors and linkage assemblies.
This enables convenient transportation of drones and improves the structural strength of the V-tail mechanism, reducing the risk of damage to the tail fin and base under high aerodynamic forces.
Smart Images
Figure CN224184539U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicles (UAVs), and in particular to an integrated V-tail mechanism. Background Technology
[0002] Unmanned aerial vehicles (UAVs), also known as drones, are unmanned aircraft controlled by radio remote control equipment and their own program control devices. They have no cockpit but are equipped with autopilots, program control devices, signal acquisition devices, and other equipment. Ground-based, shipboard, or mother-aircraft remote control stations track, locate, remotely control, telemetry, and transmit digital data to them using radar and other equipment. They can take off like ordinary aircraft under radio remote control or be launched into the air using booster rockets, or be carried into the air and released by a mother aircraft.
[0003] In the current drone industry, some drone products have adopted V-tail structures to replace the traditional horizontal and vertical tail structures. However, in current drones, V-tails take up a lot of space, making the drones inconvenient to transport. On the other hand, setting the V-tail to be detachably connected to the fuselage would cause excessive stress at the connection between the tail fin and the fuselage, making it prone to breakage. Utility Model Content
[0004] This invention aims to solve at least one of the technical problems existing in the prior art. To this end, this invention proposes an integrated V-tail mechanism, which facilitates transportation while improving the structural strength of the V-tail mechanism.
[0005] The integrated V-tail mechanism of this utility model includes: a base having a first mounting part for detachable connection with the fuselage; two tail fin bodies disposed on the upper side of the base, the two tail fin bodies being distributed in a V-shape; and a support assembly disposed on the lower side of the base, the support assembly including a truss structure composed of multiple trusses, the truss structure being used to support the support assembly.
[0006] According to some embodiments of the present invention, the integrated V-tail mechanism further includes: a first rotating shaft rotatably mounted on a base; a second rotating shaft rotatably mounted on the base; two tail fin bodies respectively mounted on the first rotating shaft and the second rotating shaft; and a moving component for driving the first rotating shaft and / or the second rotating shaft to rotate.
[0007] According to some embodiments of the present invention, the rotating assembly includes: a first servo motor, mounted on a base; a first linkage assembly, wherein the first servo motor drives a first rotating shaft to rotate via the first linkage assembly; a second servo motor, mounted on the base; and a second linkage assembly, wherein the second servo motor drives a second rotating shaft to rotate via the second linkage assembly.
[0008] According to some embodiments of the present invention, both the first servo motor and the second servo motor are mounted on a truss structure, and trusses are distributed on both the front and rear sides of the first servo motor and the second servo motor.
[0009] According to some embodiments of the present invention, both the base and the truss structure are provided with bearing assemblies for supporting the first rotating shaft.
[0010] According to some embodiments of this utility model, the tail fin body and the first rotating shaft are detachably connected.
[0011] According to some embodiments of the present invention, a first mounting part is fixedly connected to a first rotating shaft, and the first mounting part can be inserted into the tail wing body and fixed to the tail wing body.
[0012] According to some embodiments of the present invention, a locking button is provided on the first mounting part. When the first mounting part is inserted into the tail wing body, the locking button can pop out and be fixed to the tail wing body.
[0013] According to some embodiments of the present invention, the first fixing part includes a plurality of first fixing holes formed on the base, and the plurality of first fixing holes are distributed on the front and rear sides of the base.
[0014] This utility model also provides a drone, including: a fuselage, with a second mounting part provided at the tail of the fuselage; the aforementioned integrated V-tail mechanism, wherein the first mounting part and the second mounting part are detachably connected.
[0015] By applying the aforementioned integrated V-tail mechanism, during the transportation of the UAV, the first fixing part of the base can be detached from the fuselage, and the entire integrated V-tail mechanism can be stored separately. After the UAV is transported to the designated location, the first mounting part can be installed on the fuselage, which facilitates transportation. During the flight of the UAV, the support components, including the truss structure, can support the base from the underside, effectively reducing the possibility of damage to the tail fin and the base when subjected to high aerodynamic forces, and improving the structural strength of the V-tail mechanism.
[0016] Additional aspects and advantages of this invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description
[0017] The above and / or additional aspects and advantages of this utility model will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which:
[0018] Figure 1 This is a schematic diagram of the integrated V-tail mechanism in an embodiment of the utility model;
[0019] Figure 2 for Figure 1 Enlarged view of point A in the middle;
[0020] Figure 3 for Figure 1 Enlarged view of point B in the middle;
[0021] Figure 4 This is a top view of the tail section of the drone in an embodiment of the present utility model;
[0022] Figure 5 for Figure 4 Enlarged view of point C in the middle;
[0023] The above figures include the following reference numerals.
[0024] Detailed Implementation
[0025] The embodiments of this utility model are described in detail below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this utility model, and should not be construed as limiting this utility model.
[0026] In the description of this utility model, it should be understood that the directional descriptions, such as up, down, front, back, left, right, etc., indicate the directional or positional relationship based on the directional or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.
[0027] In the description of this utility model, "several" means one or more, "multiple" means two or more, "greater than," "less than," and "exceeding" are understood to exclude the stated number, while "above," "below," and "within" are understood to include the stated number. If the terms "first" and "second" are used, they are only for distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features or the order of the indicated technical features.
[0028] In the description of this utility model, unless otherwise explicitly defined, terms such as "setting," "installation," and "connection" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this utility model in conjunction with the specific content of the technical solution.
[0029] Reference Figures 1 to 5 The integrated V-tail mechanism of this embodiment includes: a base 210 having a first fixing part 211 for detachable connection with the fuselage 300; two tail fin bodies 100 disposed on the upper side of the base 210, the two tail fin bodies 100 being distributed in a V-shape; and a support assembly 212 disposed on the lower side of the base 210, the support assembly 212 including a truss structure composed of multiple trusses, the truss structure being used to support the support assembly 212.
[0030] By applying the aforementioned integrated V-tail mechanism, during the transportation of the UAV, the first fixing part 211 of the base 210 can be detached from the fuselage 300, and the entire integrated V-tail mechanism can be stored separately. After the UAV is transported to the designated location, the first mounting part 218 can be installed on the fuselage 300, which facilitates transportation. During the flight of the UAV, the support assembly 212, including the truss structure, can support the base 210 from the underside of the base 210, effectively reducing the possibility of damage to the tail fin body 100 and the base 210 when subjected to high aerodynamic forces, and improving the structural strength of the V-tail mechanism.
[0031] It is understood that the V-tail referred to in this embodiment is short for V-shaped tail fin; V-shaped tail fin is a type of aircraft tail fin, consisting of two wing surfaces, such as a horizontal tail with a large dihedral angle fixed to the rear of the fuselage.
[0032] The V-tail combines the functions of a vertical stabilizer and a horizontal stabilizer. The wing surface can be divided into fixed stabilizing surfaces and articulated control surfaces, or it can be made into an all-moving configuration. The two V-shaped tail surfaces have a certain projected area in both top-down and side-down views, thus simultaneously providing longitudinal pitch and directional stability. When both control surfaces deflect in the same direction, they function as elevators; when they deflect differentially in different directions, they function as rudders. Therefore, compared to the traditional horizontal stabilizer plus vertical stabilizer structure, the V-tail can achieve pitch and yaw control with only two control surfaces. Depending on the requirements, the V-tail can be installed on either the upper or lower side of the fuselage.
[0033] In this embodiment, the descriptions of the front-back, left-right, and up-down directions refer to the common orientation description methods used for aircraft, that is, the aircraft's heading is considered front, the left side of a person standing behind the aircraft looking forward is considered left, and the upward direction when the aircraft's roll angle is 0 degrees is considered up.
[0034] It is understandable that the first fixing part 211 can be detachably connected to the body 300 in various ways, such as by screws, clips, etc.
[0035] When the V-tail mechanism is fixed to the fuselage 300, the aerodynamic force on the two tail fin bodies 100 is transmitted to the fuselage 300 through the base 210. The support assembly 212 supports the base 210 on the lower side of the base 210, effectively reducing the deformation of the base 210 due to excessive aerodynamic force.
[0036] like Figures 1 to 4As shown, it also includes: a first rotating shaft 215, rotatably mounted on a base 210; a second rotating shaft, rotatably mounted on a base 210; two tail fin bodies 100 respectively mounted on the first rotating shaft 215 and the second rotating shaft; and a rotating assembly for driving the first rotating shaft 215 and / or the second rotating shaft to rotate. That is, in this embodiment, the V-tail assembly is a fully movable design, with the entire wing surface being a control surface and no stabilizing surface. Compared with the traditional design with a stabilizing surface, the fully movable V-tail can greatly improve aerodynamic efficiency with a fixed tail fin area.
[0037] like Figure 2 As shown, the rotating assembly includes: a first servo motor 213, mounted on the base 210; a first linkage assembly 214, through which the first servo motor 213 drives the first rotating shaft 215 to rotate; a second servo motor 216, mounted on the base 210; and a second linkage assembly 217, through which the second servo motor 216 drives the second rotating shaft to rotate; wherein, the two tail fin bodies 100 are independently controlled by two servo motors, thereby realizing the pitch and yaw control of the fuselage 300.
[0038] Specifically, such as Figure 2 As shown, both the first servo motor 213 and the second servo motor 216 are mounted on the truss structure, and trusses are distributed on both the front and rear sides of the first servo motor 213 and the second servo motor 216. That is, the outer shells of the first servo motor 213 and the second servo motor 216 serve as trusses. As part of the entire truss structure, they together with other trusses play the role of supporting the base 210. This not only saves the space for installing the two servos, but also enhances the support for the base 210, enabling the base 210 to better transmit the aerodynamic forces from the two tail fin bodies 100.
[0039] like Figure 2 As shown, both the base 210 and the truss structure are provided with bearing assemblies for supporting the first rotating shaft 215; specifically, both the base 210 and the truss structure are also provided with bearing assemblies for supporting the second rotating shaft; that is, both the first rotating shaft 215 and the second rotating shaft are supported by the base 210 and the support assembly 212 at the same time, which can better ensure the stability of the rotation of the two rotating shafts, thereby ensuring the stability of the rotation of the tail fin body 100.
[0040] like Figure 3As shown, the tail fin body 100 and the first pivot 215 are detachably connected. Specifically, the first pivot 215 is fixedly connected to a first mounting part 218, which can be inserted into and fixed to the tail fin body 100. When the tail fin body 100 is damaged, the damaged tail fin body 100 can be removed from the first mounting part 218 without disassembling the entire V-tail mechanism, making it easy to replace and repair. In addition, the tail fin body 100 can also be detachably connected to the first pivot 215 in other ways, such as by fixing with screws or clips.
[0041] It is understandable that a second fixing part 330 is also provided on the second rotating shaft for detachably connecting another tail fin body 100, and its structure is similar to that of the first rotating shaft 215 and the first mounting part 218.
[0042] like Figure 3 As shown, a locking button 219 is provided on the first mounting part 218. When the first mounting part 218 is inserted into the tail wing body 100, the locking button 219 can pop out and fix it to the tail wing body 100. When the tail wing body 100 is inserted into the first mounting part 218 and installed in place, the locking button 219 can automatically pop out and lock the tail wing body 100, so that the tail wing body 100 is firmly fixed to the first mounting part 218. When it is necessary to remove the tail wing body 100, simply press the locking button 219 to disengage the locking button 219 from the tail wing body 100, and the tail wing body 100 can be pulled out.
[0043] like Figures 1 to 5 As shown, the first fixing part 211 includes a plurality of first fixing holes opened on the base 210, and the plurality of first fixing holes are distributed on the front and rear sides of the base 210; wherein, a plurality of second fixing holes are correspondingly opened on the rear side of the body 300, and the first fixing holes and the second fixing holes correspond one to one; during installation, the plurality of first fixing holes and the plurality of second fixing holes are fixed by fasteners, so that the base 210 is firmly installed on the body 300.
[0044] This embodiment also provides a drone, including: a fuselage 300, and a second fixing part 330 provided at the tail of the fuselage 300; the first fixing part 211 and the second fixing part 330 of the aforementioned integrated V-tail mechanism are detachably connected.
[0045] Among them, such as Figure 4 , Figure 5 As shown, the tail of the fuselage 300 adopts a frameless design, and the aerodynamic force is directly transmitted from the surface of the fuselage 300. At this time, carbon fiber or composite materials can be used to make the skin of the fuselage 300 to ensure that the skin of the rear of the fuselage 300 will not be torn by the aerodynamic force of the tail fin body 100.
[0046] Specifically, such as Figure 5As shown, a receiving portion is provided on the rear surface of the fuselage 300 to accommodate the entire support assembly 212. At this time, the base 210 is equivalent to a cover, covering the opening of the receiving portion, which compensates for the reduction in structural strength caused by the opening on the surface of the fuselage 300. The frameless design of the tail of the fuselage 300 can also fully avoid the mounting positions of the support assembly 212 and the two servos, avoiding interference between the support assembly 212 and the frame of the fuselage 300. During flight, the aerodynamic force generated by the two tail rotor bodies 100 is directly transmitted to other parts of the fuselage 300 through the surface of the fuselage 300. A drive motor 310 is installed at the rear of the fuselage 300. The drive motor 310 is used to drive the tail rotor assembly 320 on the rear side, providing flight power to the fuselage 300.
[0047] The embodiments of the present utility model have been described in detail above with reference to the accompanying drawings. However, the present utility model is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present utility model.
Claims
1. An integrated V-tail mechanism characterized by, include: The base (210) has a first fixing part (211) for detachably connecting to the fuselage (300); Two tail fin bodies (100) are disposed on the upper side of the base (210), and the two tail fin bodies (100) are arranged in a V-shape; A support assembly (212) is disposed on the underside of the base (210). The support assembly (212) includes a truss structure composed of multiple trusses for supporting the support assembly (212).
2. The integrated V-tail mechanism of claim 1, wherein, Also includes: The first rotating shaft (215) is rotatably mounted on the base (210); The second rotating shaft is rotatably mounted on the base (210); The two tail fin bodies (100) are respectively mounted on the first pivot (215) and the second pivot; A rotating assembly for driving the first rotating shaft (215) and / or the second rotating shaft to rotate.
3. The integrated V-tail mechanism according to claim 2, characterized in that, The rotating assembly includes: The first servo motor (213) is mounted on the base (210); The first linkage assembly (214) is used to drive the first rotating shaft (215) to rotate. The first servo motor (213) drives the first rotating shaft (215) to rotate through the first linkage assembly (214). The second servo motor (216) is mounted on the base (210); The second linkage assembly (217) is used to drive the second shaft to rotate via the second servo motor (216).
4. The integrated V-tail mechanism according to claim 3, characterized in that, The first servo motor (213) and the second servo motor (216) are both mounted on the truss structure, and the truss is distributed on both the front and rear sides of the first servo motor (213) and the second servo motor (216).
5. The integrated V-tail mechanism according to claim 4, characterized in that, Both the base (210) and the truss structure are provided with bearing assemblies for supporting the first rotating shaft (215).
6. The integrated V-tail mechanism according to claim 2, characterized in that, The tail fin body (100) and the first pivot (215) are detachably connected.
7. The integrated V-tail mechanism according to claim 6, characterized in that, The first pivot (215) is fixedly connected to the first mounting part (218), which can be inserted into the tail fin body (100) and fixed to the tail fin body (100).
8. The integrated V-tail mechanism according to claim 7, characterized in that, The first mounting part (218) is provided with a locking button (219). When the first mounting part (218) is inserted into the tail wing body (100), the locking button (219) can pop out and be fixed to the tail wing body (100).
9. The integrated V-tail mechanism according to claim 1, characterized in that, The first fixing part (211) includes a plurality of first fixing holes opened on the base (210), and the plurality of first fixing holes are distributed on the front and rear sides of the base (210).
10. A drone, characterized in that, include: The fuselage (300) has a second fixing part (330) at its rear. The integrated V-tail mechanism of claim 7, wherein the first mounting part (218) and the second fixing part (330) are detachably connected.