Composite wing unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and discloses a composite wing unmanned aerial vehicle which comprises a fixing mechanism, a connecting mechanism and a main body mechanism, the connecting mechanism is arranged at the bottom end of the fixing mechanism, the main body mechanism is arranged at the left end of the connecting mechanism, and the fixing mechanism is arranged on the right side of the main body mechanism; the fixing mechanism comprises a connecting block, a sliding rail is arranged at the top of the connecting block, a fixing block is slidably connected into the sliding rail, a sliding handle is fixedly connected to the top of the fixing block, and a sliding block is fixedly connected to the top end of the fixing block. According to the unmanned aerial vehicle, internal sliding rails are arranged through the connecting blocks, so that the positions of internal sliding blocks and fixing blocks can be conveniently moved, and internal connecting and fixing threaded rods are arranged through the fixing blocks, so that the unmanned aerial vehicle body is fixed and connected; and due to the large size, disassembly and split charging are not convenient for storage in a storage box, and convenience is brought to use of workers.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a composite wing unmanned aerial vehicle. Background Art

[0002] Unmanned aerial vehicle, also known as "drone", is an unmanned aircraft controlled by radio remote control equipment and self-contained program control devices, or operated completely or intermittently autonomously by an on-board computer.

[0003] Compare authorization numbers 202210643346.8 201620090835.5 A composite-wing UAV, the vertical power unit comprising a propeller, a motor for driving the propeller to rotate, and an electronic speed regulator for controlling the motor speed, the vertical power unit being arranged around the center of gravity of the aircraft, the propeller shafts of the vertical power unit being installed at an angle so that the pulling force generated by the propeller has a vertical component and a horizontal component, the lines connecting the axis of each propeller and the center of gravity of the aircraft have an angle with the direction of the horizontal component of force generated by the propeller, and the angle is greater than zero or less than zero, the vertical component of force is the component of force parallel to the propeller axis decomposed from the pulling force generated by the corresponding propeller, and the component of force is used to overcome the gravity of the UAV during flight, and the horizontal component of force is the component of force perpendicular to the propeller axis decomposed from the pulling force generated by the corresponding propeller, and is used to achieve the yaw of the aircraft. Since the UAV can only fly level when the line connecting the axis of each propeller and the center of gravity of the aircraft is consistent with the direction of the horizontal component force generated by the propeller, in this technical solution, by limiting the inclination direction of the propeller axis, the above horizontal component force will inevitably produce a yaw moment for controlling the flight state of the UAV, which can effectively solve the problem of insufficient yaw control of the composite wing aircraft at low speed.

[0004] This composite wing UAV is configured in this way to limit the inclination direction of the propeller axis so that the above horizontal component force will inevitably generate a yaw moment for controlling the flight state of the UAV, which can effectively solve the problem of insufficient yaw control of the composite wing aircraft at low speed. However, when the aircraft body stops working, it is not convenient for users to carry, receive and store it due to its large size. Utility Model Content

[0005] In order to solve the above technical problems, the utility model provides a composite wing UAV.

[0006] The utility model is implemented by the following technical scheme: a composite wing UAV, comprising a fixing mechanism, a connecting mechanism and a main body mechanism, wherein the bottom end of the fixing mechanism is provided with a connecting mechanism, the left end of the connecting mechanism is provided with a main body mechanism, and the right side of the main body mechanism is provided with a fixing mechanism;

[0007] The fixing mechanism includes a connecting block, a sliding rail is provided on the top of the connecting block, a fixing block is slidably connected inside the sliding rail, a sliding handle is fixedly connected to the top of the fixing block, a sliding block is fixedly connected to the top of the fixing block, and a connecting and fixing threaded rod is threadedly connected inside the fixing block.

[0008] As a further improvement of the above solution, the sliding block is located inside the sliding rail, the connecting and fixing threaded rod is located at the top of the connecting block, and the connecting and fixing threaded rod passes through the fixing block and extends to the inside of the connecting block.

[0009] Through the above technical solution, the number of connecting blocks is set to two, which makes it convenient for workers to connect and fix the wings and the fuselage of the drone.

[0010] As a further improvement of the above scheme, the connecting mechanism includes a wing, a connecting rod is fixedly connected to the front of the wing, a driving motor is fixedly connected to the top of the connecting rod, a rotating shaft is fixedly connected to the top of the driving motor, a propeller is fixedly connected to the surface of the rotating shaft, and a mounting block is fixedly connected to the left end of the wing.

[0011] As a further improvement of the above solution, the wing is located at the bottom end of the connecting block, and the connecting rods are symmetrically distributed with the wing as the center.

[0012] Through the above technical solution, the number of driving motors and propellers is set to four, and the driving motor drives the propellers on the surface to rotate through the rotating shaft.

[0013] As a further improvement of the above scheme, the main body structure includes a drone body and wings, the rear end surface of the drone body is fixedly connected to a tail wing, the right side of the drone body is provided with a mounting groove, and the right end of the drone body is provided with a connecting threaded hole.

[0014] As a further improvement of the above solution, the mounting grooves are symmetrically distributed with the drone body as the center, the wings are symmetrically distributed with the drone body as the center, and the connecting blocks are symmetrically distributed with the drone body as the center.

[0015] Through the above technical solution, the number of the mounting grooves and the connecting threaded holes is set to two.

[0016] Compared with the prior art, the beneficial effects of the present invention are:

[0017] The utility model provides an internal slide rail through the connecting block to facilitate the movement of the internal slider and the fixed block, and fixes and connects the drone body through the internal connecting and fixing threaded rods of the fixed block, which increases the convenience for staff to use when the equipment needs to be stored as a whole and is not convenient for disassembly and subpackaging for storage in the storage box due to its large size.

[0018] The utility model increases the connection stability between the wing and the driving motor by arranging a connecting rod, and provides a mounting groove on the UAV fuselage for convenience of workers in installing and connecting the mounting block at the left end of the wing and the connecting threaded hole at the left end of the connecting block, thereby increasing the stability of the equipment when in use. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0020] Figure 2 This is a schematic diagram of the split structure of the fixed block of the utility model;

[0021] Figure 3 This is a schematic diagram of the wing structure of the utility model;

[0022] Figure 4 It is a schematic diagram of the wing split structure of the utility model.

[0023] Description of main symbols:

[0024] 1. Fixing mechanism; 101. Connecting block; 102. Sliding handle; 103. Fixing block; 104. Sliding block; 105. Slide rail; 106. Connecting and fixing threaded rod; 2. Connecting mechanism; 201. Wing; 202. Connecting rod; 203. Driving motor; 204. Rotating shaft; 205. Propeller; 206. Mounting block; 3. Main body; 301. UAV fuselage; 302. Tail; 303. Mounting slot; 304. Connecting threaded hole. DETAILED DESCRIPTION

[0025] The present invention is further described below in conjunction with the accompanying drawings and specific implementation methods. It should be noted that, under the premise of no conflict, the various embodiments or technical features described below can be arbitrarily combined to form a new embodiment.

[0026] Example:

[0027] Please combine Figure 1-4 A composite wing UAV of this embodiment includes a fixing mechanism 1, a connecting mechanism 2 and a main body mechanism 3, wherein the bottom end of the fixing mechanism 1 is provided with the connecting mechanism 2, the left end of the connecting mechanism 2 is provided with the main body mechanism 3, and the right side of the main body mechanism 3 is provided with the fixing mechanism 1;

[0028] The fixing mechanism 1 includes a connecting block 101, a slide rail 105 is provided on the top of the connecting block 101, a fixing block 103 is slidably connected inside the slide rail 105, a sliding handle 102 is fixedly connected to the top of the fixing block 103, a slider 104 is fixedly connected to the top of the fixing block 103, and a connecting and fixing threaded rod 106 is connected to the internal thread of the fixing block 103. The internal slide rail 105 is set by the connecting block 101 to facilitate the movement of the internal slider 104 and the fixing block 103, and the internal connecting and fixing threaded rod 106 is set by the fixing block 103 to fix and connect the drone fuselage 301, which increases the convenience for the staff to use when the equipment needs to be stored as a whole and is large in size and not convenient to be disassembled and repacked for storage in a storage box.

[0029] The slider 104 is located inside the slide rail 105 , the connecting and fixing threaded rod 106 is located at the top of the connecting block 101 , and the connecting and fixing threaded rod 106 penetrates the fixing block 103 and extends to the inside of the connecting block 101 .

[0030] The number of the connecting blocks 101 is set to two, so that the staff can easily connect and fix the wing 201 and the drone body 301.

[0031] The connecting mechanism 2 includes a wing 201, a connecting rod 202 is fixedly connected to the front of the wing 201, a driving motor 203 is fixedly connected to the top of the connecting rod 202, a rotating shaft 204 is fixedly connected to the top of the driving motor 203, a propeller 205 is fixedly connected to the surface of the rotating shaft 204, and a mounting block 206 is fixedly connected to the left end of the wing 201. The connection rod 202 is arranged on the wing 201 to increase the connection stability between the wing 201 and the driving motor 203.

[0032] The wing 201 is located at the bottom end of the connecting block 101 , and the connecting rods 202 are symmetrically distributed around the wing 201 .

[0033] The number of the driving motors 203 and the propellers 205 is set to four, and the driving motor 203 drives the propellers 205 on the surface to rotate through the rotating shaft 204.

[0034] The main body 3 includes a UAV body 301 and a wing 201. The rear end surface of the UAV body 301 is fixedly connected to a tail wing 302. A mounting groove 303 is provided on the right side of the UAV body 301. A connecting threaded hole 304 is provided on the right end of the UAV body 301. The mounting groove 303 is provided on the UAV body 301 to facilitate the staff to install and connect the mounting block 206 at the left end of the wing 201 and the connecting threaded hole 304 at the left end of the connecting block 101, thereby increasing the stability of the equipment during use.

[0035] The mounting grooves 303 are symmetrically distributed with the drone body 301 as the center, the wings 201 are symmetrically distributed with the drone body 301 as the center, and the connecting blocks 101 are symmetrically distributed with the drone body 301 as the center.

[0036] The number of the mounting grooves 303 and the connecting threaded holes 304 is set to two.

[0037] The implementation principle of a composite wing UAV in the embodiment of the present application is as follows: the device is placed in a suitable position, an internal slide rail 105 is set through the connecting block 101 to facilitate the movement of the internal slider 104 and the fixed block 103, and the internal connecting and fixing threaded rod 106 is set through the fixed block 103 to fix and connect the UAV fuselage 301, which increases the convenience of the staff when the device needs to be stored as a whole, as it is large in size and not convenient to disassemble and repack for storage in a storage box. The connection stability between the wing 201 and the driving motor 203 is increased by setting a connecting rod 202, and the installation groove 303 is set through the UAV fuselage 301, which is convenient for the staff to install and connect the installation block 206 at the left end of the wing 201 and the connecting threaded hole 304 at the left end of the connecting block 101, thereby increasing the stability of the device when in use.

[0038] The above-mentioned implementation modes are only preferred implementation modes of the present invention, and cannot be used to limit the protection scope of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. A composite wing UAV, characterized in that: It comprises a fixing mechanism (1), a connecting mechanism (2) and a main body mechanism (3), wherein the bottom end of the fixing mechanism (1) is provided with the connecting mechanism (2), the left end of the connecting mechanism (2) is provided with the main body mechanism (3), and the right side of the main body mechanism (3) is provided with the fixing mechanism (1); The fixing mechanism (1) comprises a connecting block (101), a slide rail (105) is provided on the top of the connecting block (101), a fixing block (103) is slidably connected inside the slide rail (105), a sliding handle (102) is fixedly connected to the top of the fixing block (103), a sliding block (104) is fixedly connected to the top of the fixing block (103), and a connecting and fixing threaded rod (106) is threadedly connected inside the fixing block (103).

2. A composite wing UAV as claimed in claim 1, characterized in that: The sliding block (104) is located inside the sliding rail (105), the connecting and fixing threaded rod (106) is located at the top of the connecting block (101), and the connecting and fixing threaded rod (106) penetrates the fixing block (103) and extends to the inside of the connecting block (101).

3. A composite wing UAV as claimed in claim 1, characterized in that: The connection mechanism (2) comprises a wing (201), the front side of the wing (201) is fixedly connected to a connection rod (202), the top of the connection rod (202) is fixedly connected to a drive motor (203), the top of the drive motor (203) is fixedly connected to a rotating shaft (204), the surface of the rotating shaft (204) is fixedly connected to a propeller (205), and the left end of the wing (201) is fixedly connected to a mounting block (206).

4. A composite wing UAV as claimed in claim 3, characterized in that: The wing (201) is located at the bottom end of the connecting block (101), and the connecting rods (202) are symmetrically distributed with the wing (201) as the center.

5. The composite wing UAV according to claim 1, characterized in that: The main body structure (3) comprises a drone body (301) and wings (201); a tail wing (302) is fixedly connected to the rear end surface of the drone body (301); a mounting groove (303) is provided on the right side of the drone body (301); and a connecting threaded hole (304) is provided at the right end of the drone body (301).

6. A composite wing UAV as claimed in claim 5, characterized in that: The mounting grooves (303) are symmetrically distributed with the drone body (301) as the center, the wings (201) are symmetrically distributed with the drone body (301) as the center, and the connection blocks (101) are symmetrically distributed with the drone body (301) as the center.

Images