Angle-adjustable empennage structure of fixed-wing unmanned aerial vehicle

Abstract

The utility model discloses an angle-adjustable empennage structure of a fixed-wing unmanned aerial vehicle, and relates to the technical field of fixed-wing unmanned aerial vehicles, the angle-adjustable empennage structure of the fixed-wing unmanned aerial vehicle comprises a fuselage and an adjusting assembly, wings are arranged on two sides of the outer part of the fuselage, and the adjusting assembly is arranged at the rear end of the fuselage. The adjusting assembly comprises a movable rotating rod, a butt joint block, an empennage body, a threaded mounting rod, a limiting sliding groove, a movable sliding block, a pneumatic rod and a fixing block, the butt joint block is connected to the front end of the movable rotating rod, the empennage body is arranged outside the butt joint block, the threaded mounting rod is connected to the interior of the butt joint block, and the limiting sliding groove is formed in the middle end of the interior of the movable rotating rod. A movable sliding block is connected into the limiting sliding groove, a pneumatic rod is arranged at the upper end of the movable sliding block, and meanwhile a fixed block is installed at the bottom of the pneumatic rod. According to the angle-adjustable empennage structure of the fixed-wing unmanned aircraft, the use angle of the empennage of the aircraft can be adjusted according to different flight scenes, and the initiative of the fixed-wing unmanned aircraft in the use process is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of fixed-wing unmanned aircraft, in particular to a tail wing structure of a fixed-wing unmanned aircraft with adjustable angle. Background Art

[0002] Fixed-wing UAVs are a type of UAVs with fixed wings whose wing sweep angle can be adjusted automatically or manually with speed. Due to their excellent functions and modular integration, they are now widely used in surveying and mapping, geology, petroleum, agriculture and forestry, and have broad market application prospects. Fixed-wing UAVs include a fuselage and a tail wing set at the rear end of the fuselage. The speed can be changed by adjusting the tail wing angle, and they can adapt to different flight scenarios. In order to improve the efficiency of fixed-wing UAVs, a tail wing structure is needed, but the existing tail wing structure still has the following shortcomings:

[0003] For example, the utility model with application number 201920797763.1 discloses a fixed-wing UAV with a stable and reliable structure. The utility model can fix the vertical tail to the fuselage. After the second protrusion is positioned and installed in the second mounting hole and the second mounting groove, the vertical wing, the horizontal tail and the fuselage can be fixedly connected, and the second connecting member can fix the horizontal tail to the fuselage, thereby forming a multiple fixed connection structure to achieve a firm connection between the horizontal tail, the vertical tail and the fuselage. The overall connection method is relatively stable and reliable. However, similar to the comparative documents of the above-mentioned application, when the existing tail structure is used, since most tail structures are fixedly connected to the fuselage, it is difficult for the UAV to adjust its own structure in different flight scenarios, which affects the speed, resulting in reduced practicality and reduced efficiency of the fixed-wing UAV.

[0004] Therefore, in view of this, the existing structure and defects are studied and improved, and a tail structure of a fixed-wing unmanned aircraft with adjustable angle is proposed. Utility Model Content

[0005] The utility model aims to provide a tail structure of a fixed-wing unmanned aircraft with an adjustable angle, so as to solve the problems raised in the above-mentioned background technology.

[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a tail structure of a fixed-wing unmanned aircraft with adjustable angle, comprising a fuselage and an adjustment component, wings are arranged on both sides of the outside of the fuselage, an adjustment component is arranged at the rear end of the fuselage, and the adjustment component comprises a movable rotating rod, a docking block, a tail body, a threaded mounting rod, a limiting slide groove, a movable slider, a pneumatic rod and a fixed block, the front end of the movable rotating rod is connected to the docking block, the tail body is arranged outside the docking block, and the threaded mounting rod is connected inside the docking block, a limiting slide groove is provided at the middle end of the movable rotating rod, and a movable slider is connected inside the limiting slide groove, and a pneumatic rod is arranged at the upper end of the movable slider, and a fixed block is installed at the bottom of the pneumatic rod, and a warning component is arranged at the upper end of the wing.

[0007] Furthermore, the number of the wings is two, and the two wings are symmetrically arranged on both sides of the fuselage exterior with respect to the front center axis of the fuselage.

[0008] Furthermore, the docking block is embeddedly connected to the movable rotating rod, and the docking block is connected to the movable rotating rod through a threaded mounting rod.

[0009] Furthermore, the inner dimensions of the limiting slide groove match the outer dimensions of the movable slider, and the movable slider is slidably connected to the movable rotating rod via the limiting slide groove.

[0010] Furthermore, the pneumatic rod and the fixing block are vertically distributed, and the pneumatic rod and the fixing block are threadedly connected.

[0011] Furthermore, the warning component includes an installation frame, a solar panel, an LED warning light, a solar converter and a battery. The solar panel is arranged inside the installation frame, LED warning lights are additionally arranged on both sides of the outside of the wing, the solar converter is arranged inside the fuselage, and a battery is arranged at the front end of the solar converter.

[0012] Furthermore, the outer dimensions of the solar panel match the inner dimensions of the mounting frame, and the solar panel is connected to the wing via the mounting frame.

[0013] Furthermore, the LED warning lights are symmetrically arranged on both sides of the wing, and the LED warning lights are threadedly connected to the wing.

[0014] The utility model provides a tail structure of a fixed-wing unmanned aircraft with adjustable angle, which has the following beneficial effects:

[0015] 1. The utility model can, through the setting of the adjustment component, when the tail structure of the fixed-wing unmanned aircraft with adjustable angle is used, limit the movable rotating rod to the inner two sides of the rear end of the fuselage through the limit piece, and limit the docking block to the front end of the movable rotating rod in conjunction with the threaded mounting rod, so that the tail body is installed at the front end of the movable rotating rod, and the internal size of the limit slide groove opened inside the movable rotating rod matches the external size of the movable slider at the front end of the pneumatic rod, so that when the pneumatic rod is in operation, the movable slider is driven to move inside the limit slide groove, and the angle of the movable rotating rod is adjusted accordingly, so that the tail body can change the use angle during use, increase the flight efficiency of the unmanned aircraft in different flight scenarios, and improve the mobility of the fixed-wing unmanned aircraft during use.

[0016] 2. The utility model, through the setting of the warning component, can fix the installation frame on the upper end of the wing through fasteners when the tail structure of the fixed-wing unmanned aircraft with adjustable angle is used, and the solar panel is limited inside the installation frame with the help of the fasteners. The solar heat is absorbed by the solar panel, and the solar energy is converted into electrical energy by the solar converter, and stored in the battery to provide power for the LED warning lights set on both sides of the wing. Whether at night or during the day, the position of the unmanned aircraft can be clearly found through the tail body by the LED warning lights, thereby improving the use efficiency of the fixed-wing unmanned aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a three-dimensional structural schematic diagram of a tail structure of an angle-adjustable fixed-wing unmanned aircraft of the utility model;

[0018] Figure 2 The utility model is a tail structure of a fixed-wing unmanned aircraft with adjustable angle Figure 1 The enlarged structural diagram at A in the middle;

[0019] Figure 3 The utility model is a schematic diagram of the three-dimensional unfolding structure of the adjusting component of the tail structure of the fixed-wing unmanned aircraft with adjustable angle.

[0020] In the figure: 1. fuselage; 2. wing; 3. adjustment component; 301. movable rotating rod; 302. docking block; 303. tail body; 304. threaded mounting rod; 305. limiting slide groove; 306. movable slider; 307. pneumatic rod; 308. fixing block; 4. warning component; 401. mounting frame; 402. solar panel; 403. LED warning light; 404. solar converter; 405. battery. DETAILED DESCRIPTION

[0021] The following is a further detailed description of the implementation of the present invention in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but cannot be used to limit the scope of the present invention.

[0022] like Figures 1 to 3 As shown, a tail structure of an angle-adjustable fixed-wing unmanned aircraft includes a fuselage 1 and an adjustment component 3. Wings 2 are arranged on both sides of the fuselage 1. The adjustment component 3 is arranged at the rear end of the fuselage 1, and the adjustment component 3 includes a movable rotating rod 301, a docking block 302, a tail body 303, a threaded mounting rod 304, a limiting slide groove 305, a movable slider 306, a pneumatic rod 307 and a fixed block 308. The front end of the movable rotating rod 301 is connected to the docking block 302, and the tail body 303 is arranged outside the docking block 302, and the threaded mounting rod 304 is connected inside the docking block 302. The middle end of the movable rotating rod 301 is provided with a The limiting slide groove 305 is provided with a movable slider 306 connected thereto, and a pneumatic rod 307 is provided at the upper end of the movable slider 306, and a fixed block 308 is installed at the bottom of the pneumatic rod 307. The number of wings 2 is two, and the two wings 2 are symmetrically arranged on both sides of the outside of the fuselage 1 with the front center axis of the fuselage 1. The docking block 302 is embeddedly connected with the movable rotating rod 301, and the docking block 302 is connected with the movable rotating rod 301 through a threaded mounting rod 304. The internal size of the limiting slide groove 305 matches the external size of the movable slider 306, and the movable slider 306 is connected to the movable rotating rod 301 through the limiting slide groove 305. The rotating rod 301 is slidably connected, the pneumatic rod 307 and the fixed block 308 are vertically distributed, and the pneumatic rod 307 and the fixed block 308 are threadedly connected. The movable rotating rod 301 is limitedly installed on both sides of the inner rear end of the fuselage 1 through the limiter. At the same time, the docking block 302 is embedded with the movable rotating rod 301, and the docking block 302 is limitedly installed at the front end of the movable rotating rod 301 in conjunction with the threaded mounting rod 304, so that the tail body 303 is installed at the front end of the movable rotating rod 301, so that the tail body 303 is easy to quickly dock and install, and the convenience of subsequent disassembly and maintenance is improved. The fixed block 308 is fixedly installed with fasteners The pneumatic rod 307 is fixedly installed on the lower end of the fixed block 308 with fasteners on both sides of the outside of the movable rotating rod 301. At the same time, the internal dimensions of the limiting slide groove 305 opened inside the movable rotating rod 301 match the external dimensions of the movable slider 306 at the front end of the pneumatic rod 307. When the pneumatic rod 307 is operating, the movable slider 306 is driven to move inside the limiting slide groove 305, and the angle of the movable rotating rod 301 is adjusted accordingly, so that the tail wing body 303 can change the use angle during use, increase the flight efficiency of the unmanned aircraft in different flight scenarios, and enhance the mobility of the fixed-wing unmanned aircraft during use.

[0023] like Figure 1As shown, a warning component 4 is arranged at the upper end of the wing 2, and the warning component 4 includes a mounting frame 401, a solar panel 402, an LED warning light 403, a solar converter 404 and a battery 405. The solar panel 402 is arranged inside the mounting frame 401, and LED warning lights 403 are additionally arranged on both sides of the outside of the wing 2. A solar converter 404 is arranged inside the fuselage 1, and a battery 405 is arranged at the front end of the solar converter 404. The outer size of the solar panel 402 matches the inner size of the mounting frame 401, and the solar panel 402 is connected to the wing 2 through the mounting frame 401. The LED warning lights 403 are symmetrically arranged with the wing 2. 2, and the LED warning lights 403 are threadedly connected to the wing 2, the mounting frame 401 is fixedly mounted on the upper end of the wing 2 by fasteners, and the solar panel 402 is limited inside the mounting frame 401 with the fasteners, the solar panel 402 absorbs the heat of the sun, and the solar energy converter 404 is used to convert the solar energy into electric energy, which is stored by the battery 405 to provide power for the LED warning lights 403 arranged on the two sides of the wing 2. Whether at night or during the day, the LED warning lights 403 can clearly find the position of the UAV through the tail body 303, thereby improving the use efficiency of the fixed-wing UAV.

[0024] In summary, when the tail structure of the fixed-wing unmanned aircraft with adjustable angle is used, the wing 2 is first limitedly installed on the outer sides of the fuselage 1 by fasteners, the mounting frame 401 is fixedly installed on the upper end of the wing 2 by fasteners, and the solar panel 402 is limited inside the mounting frame 401 with the fasteners, and the solar panel 402 absorbs the heat of the sun, and at the same time, the solar energy converter 404 is used to convert the solar energy into electrical energy, and the electrical energy is stored by the battery 405, so as to provide power for the LED warning lights 403 arranged on the outer sides of the wing 2. Whether at night or during the day, the position of the unmanned aircraft can be clearly found through the tail body 303 by the LED warning lights 403, so as to improve the use efficiency of the fixed-wing unmanned aircraft. Then, the movable rotating rod 301 is limitedly installed on the inner sides of the rear end of the fuselage 1 by the limiting pieces, and at the same time, the docking block 302 is embeddedly connected with the movable rotating rod 301, and cooperates with the threaded mounting rod. The docking block 304 is limitedly installed at the front end of the movable rotating rod 301, so that the tail wing body 303 is installed at the front end of the movable rotating rod 301, so that the tail wing body 303 is convenient for quick docking and installation, and the convenience of subsequent disassembly and maintenance is improved. The fixing block 308 is fixedly installed on both sides of the outside of the movable rotating rod 301 by fasteners, and the pneumatic rod 307 is fixedly installed at the lower end of the fixing block 308 with the fasteners. At the same time, the internal size of the limiting slide groove 305 opened inside the movable rotating rod 301 matches the external size of the movable slider 306 at the front end of the pneumatic rod 307, so that when the pneumatic rod 307 is in operation, the movable slider 306 is driven to move inside the limiting slide groove 305, and the movable rotating rod 301 is adjusted in angle accordingly, so that the tail wing body 303 can change the use angle during use, increase the flight efficiency of the unmanned aircraft in different flight scenarios, and improve the mobility of the fixed-wing unmanned aircraft during use.

[0025] The embodiments of the present invention are provided for the purpose of illustration and description, and are not intended to be exhaustive or to limit the present invention to the disclosed forms. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments are selected and described to better illustrate the principles and practical applications of the present invention, and to enable those of ordinary skill in the art to understand the present invention and thereby design various embodiments with various modifications suitable for specific uses.

Claims

1. An angle-adjustable tail structure of a fixed-wing unmanned aircraft, comprising a fuselage (1) and an adjustment assembly (3), characterized in that: Wings (2) are arranged on both sides of the fuselage (1), and an adjustment assembly (3) is arranged at the rear end of the fuselage (1), and the adjustment assembly (3) comprises a movable rotating rod (301), a docking block (302), a tail wing body (303), a threaded mounting rod (304), a limiting sliding groove (305), a movable sliding block (306), a pneumatic rod (307) and a fixing block (308), and the front end of the movable rotating rod (301) is connected to the docking block (302), and the docking block (302) A tail body (303) is arranged on the outside, and a threaded mounting rod (304) is connected to the inside of the docking block (302), a limiting slide groove (305) is arranged at the middle end of the movable rotating rod (301), and a movable slider (306) is connected to the inside of the limiting slide groove (305), and a pneumatic rod (307) is arranged on the upper end of the movable slider (306), and a fixing block (308) is installed at the bottom of the pneumatic rod (307), and a warning component (4) is arranged on the upper end of the wing (2).

2. The tail structure of an angle-adjustable fixed-wing unmanned aircraft according to claim 1, characterized in that: The number of the wings (2) is two, and the two wings (2) are symmetrically arranged on both sides of the outside of the fuselage (1) with respect to the front center axis of the fuselage (1).

3. The tail structure of an angle-adjustable fixed-wing unmanned aircraft according to claim 1, characterized in that: The docking block (302) is embeddedly connected to the movable rotating rod (301), and the docking block (302) is connected to the movable rotating rod (301) via a threaded mounting rod (304).

4. The tail structure of an angle-adjustable fixed-wing unmanned aircraft according to claim 1, characterized in that: The inner dimensions of the limiting sliding groove (305) match the outer dimensions of the movable sliding block (306), and the movable sliding block (306) is slidably connected to the movable rotating rod (301) via the limiting sliding groove (305).

5. The tail structure of an angle-adjustable fixed-wing unmanned aircraft according to claim 1, characterized in that: The pneumatic rod (307) and the fixing block (308) are vertically distributed, and the pneumatic rod (307) and the fixing block (308) are threadedly connected.

6. The tail structure of an angle-adjustable fixed-wing unmanned aircraft according to claim 1, characterized in that: The warning component (4) comprises a mounting frame (401), a solar panel (402), an LED warning light (403), a solar energy converter (404) and a storage battery (405); the mounting frame (401) is provided with a solar panel (402), the wing (2) is provided with LED warning lights (403) on both sides of the outside, the fuselage (1) is provided with a solar energy converter (404), and the front end of the solar energy converter (404) is provided with a storage battery (405).

7. The tail structure of an angle-adjustable fixed-wing unmanned aircraft according to claim 6, characterized in that: The external dimensions of the solar panel (402) match the internal dimensions of the mounting frame (401), and the solar panel (402) is connected to the wing (2) via the mounting frame (401).

8. The tail structure of an angle-adjustable fixed-wing unmanned aircraft according to claim 6, characterized in that: The LED warning lights (403) are symmetrically arranged on both sides of the outside of the wing (2), and the LED warning lights (403) are threadedly connected to the wing (2).

Images