Unmanned eVTOL capable of being quickly mounted, dismounted and transported

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned eVTOL capable of being quickly mounted, dismounted and transported, which comprises a fuselage main body structure, a wing structure is arranged at the top of the fuselage main body structure, motor support arms are detachably connected to two sides of the bottom of the wing structure, and an empennage structure is arranged on the rear side of the fuselage main body structure. The fuselage main body structure comprises a framework, a skin is fixedly connected to the surface of the framework, cabin doors are detachably connected to the front side, the right side and the top of the fuselage main body structure, and the surfaces of the cabin doors are detachably connected with the skin. The wing has the advantages of being fast to disassemble, assemble and transport, according to the scheme, the whole wing is split in a three-section mode, the central wing and the fuselage main body are integrated and disassembled disorderly, the left outer wing and the right outer wing can be disassembled in the transportation process, space is saved, and transportation is convenient; separation of the outer wing and the central wing may be restricted by a latch.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to an unmanned eVTOL (eVTOL) that can be quickly assembled, disassembled, and transported. Background Art

[0002] A drone is an unmanned aerial vehicle capable of performing flight missions, consisting of a fuselage, a central wing, outer wings, landing gear, motor arms, and tail (horizontal tail and vertical tail) sections installed on the fuselage. It is controlled by its own program control device and radio remote control equipment. When a drone flies in the air, it is mainly affected by lift, gravity, thrust and drag. Lift is mainly generated by the shape and inclination of the wings, thrust is usually generated by propellers or jet engines, and drag affects the speed and distance of the drone.

[0003] Existing composite-wing drones, due to their long left and right wings and tail, take up a large amount of space during storage and transportation, making them inconvenient to carry and transport. Although most current drones use quick-disassembly solutions that allow for quick disassembly of various sections, actual operation requires a large amount of disassembly and installation work. Before transportation, users need to spend a lot of time and effort to disassemble the various sections of the drone to ensure that they can be stored and transported compactly. Upon arrival at the destination, users need to perform tedious installation work again to restore the drone to its complete form and prepare for takeoff. This extensive disassembly and installation work not only increases the user's operational burden but may also lead to errors during the disassembly and assembly process, affecting the drone's flight performance. In addition, for drones that need to be transported frequently, excessive disassembly and assembly work can also damage the connection points of the sections. During frequent disassembly and assembly, the connection points between the various sections of the drone are easily worn and damaged. This damage not only reduces the structural strength of the drone but also may affect its stability and safety during flight. In severe cases, the damaged sections may need to be re-purchased and replaced, which undoubtedly increases the maintenance and operating costs of the drone. Utility Model Content

[0004] The purpose of the present invention is to provide an unmanned eVTOL that can be quickly installed, disassembled and transported, which has the advantages of quick disassembly, installation and transportation and solves the problems raised by the above-mentioned background technology.

[0005] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: an unmanned eVTOL that can be quickly installed, disassembled and transported, comprising a fuselage main structure, a wing structure is provided on the top of the fuselage main structure, motor arms are detachably connected on both sides of the bottom of the wing structure, and a tail structure is provided on the rear side of the fuselage main structure.

[0006] The main fuselage structure includes a skeleton, the surface of the skeleton is fixedly connected to a skin, the front side, right side and top of the main fuselage structure are detachably connected to cabin doors, and the surface of the cabin doors is detachably connected to the skin.

[0007] The wing structure includes a central wing located on the top of the fuselage main structure, outer wings are provided on both sides of the central wing, one side of the outer wing is fixedly connected to two plug-in mounting rods 1, one end of the plug-in mounting rod 1 passes through the inner cavity of the central wing, mounting holes compatible with the plug-in mounting rod 1 are opened on both sides of the central wing, and locking blocks are fixedly connected to both sides of the central wing.

[0008] The tail structure includes a tail rear beam that is arranged through the main structure of the fuselage, and both sides of the surface of the tail rear beam are fixedly connected with fused wing surfaces, and the opposite sides of the two fused wing surfaces are in contact with the skin. One side of the inner cavity of the fused wing surface is fixedly connected with a motor support, and the motor support is fixedly connected to the tail rear beam through bolts. The rear side of the inner cavity of the skeleton is fixedly connected with a connecting seat, and the top of the connecting seat passes through the top of the skin. The inner cavity of the connecting seat is embedded with an inserted mounting rod 2, and the surface of the inserted mounting rod 2 is fixedly connected with a vertical tail. The surface of the skin is fixedly connected with two symmetrically arranged fixing blocks, and both sides of the surface of the vertical tail are fixedly connected with blocking blocks that are adapted to the fixing blocks.

[0009] Furthermore, as a preferred embodiment of the present invention, the top of the frame is fixedly connected to a fixing frame, and the inner cavity of the fixing frame is fixedly connected to the central wing.

[0010] Furthermore, as a preferred embodiment of the present invention, a mounting block is fixedly connected to one side of the bottom of the outer wing, and the mounting block is adapted to the locking block.

[0011] Furthermore, as a preferred embodiment of the present invention, positioning plates are fixedly connected to both sides of the connecting seat, the positioning plates are located in the inner cavity of the frame, the surfaces of the positioning plates are fixedly connected to the frame, and the opposite sides of the two positioning plates are in contact with the rear beam of the tail wing.

[0012] Furthermore, as a preferred embodiment of the present invention, two symmetrically arranged through holes are opened on one side of the rear beam of the tail wing, and the through holes and the motor support are located on the same horizontal line.

[0013] Furthermore, as a preferred embodiment of the present invention, leaf spring landing gears are fixedly connected to four sides of the skeleton by bolts, and the surface of the leaf spring landing gears penetrates to the outside of the skin.

[0014] Furthermore, as a preferred embodiment of the present invention, the bottoms of the two outer wings are fixedly connected to support blocks, and the inner cavity of the support blocks is adapted to the motor support arms.

[0015] Beneficial effects: The technical solution of the present application has the following technical effects: the present invention has the advantages of quick disassembly, installation and transportation. The present solution splits the entire wing into three sections, wherein the central wing is integrated with the fuselage body and can be disassembled in an unordered manner. The left and right outer wings can be disassembled during transportation, which saves space and is convenient for transportation. After the three-section wing is spliced ​​through the pipeline channel, the separation of the outer wing and the central wing can be restricted by the lock. The power support arm is designed within the outer wing separation surface and does not need to be disassembled during transportation, and the space occupied by transportation is also reduced. During transportation, the vertical tail and landing gear can be disassembled and the transportation space is reduced, which is convenient for transportation. The horizontal tail adopts the fusion form of the motor support and the wing, and at the same time provides a good heat dissipation channel for the motor, reduces the disassembly and assembly sections, reduces the disassembly and assembly workload and reduces the risk of parts damage. Specifically, the vertical tail can be quickly removed from the tail section, and the outer wings can be quickly removed from the wing section. The tail and central wing are similar in length, so only the vertical tail and outer wings need to be disassembled before transportation, which reduces the disassembly steps and saves transportation space. Among them: the main fuselage includes a frame and skin, and the front, upper, and middle parts of the fuselage have quick-opening doors, which are convenient for loading cargo and installing battery packs; the outer wings adopt an inserted quick-release installation structure and have added a quick locking device; the motor support arm is on the inner side of the two set separation surfaces of the wing, so there is no need to disassemble the motor support arm when the aircraft is transported; the tail is composed of a horizontal tail and a vertical tail. The tail adopts a fusion wing form, which integrates the motor support and the tail into one. The motor support is connected to the rear beam of the tail with bolts and has a large through hole for travel heat dissipation channel, providing heat dissipation airflow for the tail thruster motor and reducing the operating temperature of the motor; the vertical tail adopts similar features to the outer wing of the aircraft, can be quickly disassembled and assembled, and contains a quick locking device; it can be quickly disassembled during transportation to reduce transportation space.

[0016] It should be appreciated that all combinations of the foregoing concepts, as well as additional concepts described in greater detail below, may be considered to be part of the inventive subject matter of this disclosure, provided such concepts are not mutually inconsistent. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0018] Figure 1 This is a schematic diagram of the structure of the utility model;

[0019] Figure 2This is a bottom-up perspective diagram of the structure of the utility model;

[0020] Figure 3 This is a three-dimensional schematic diagram of the main body structure of the utility model;

[0021] Figure 4 This is a partially disassembled three-dimensional schematic diagram of the wing structure of the utility model;

[0022] Figure 5 This is a partial bottom view of the wing structure of the present invention;

[0023] Figure 6 This is a schematic sectional perspective diagram of the main structure of the fuselage of the present invention;

[0024] Figure 7 This is a three-dimensional schematic diagram of the tail wing structure of the utility model;

[0025] Figure 8 This is a schematic diagram of the split three-dimensional structure of the tail wing of the utility model;

[0026] Figure 9 It is a disassembled three-dimensional schematic diagram of the fixing block and the clamping block of the utility model.

[0027] In the figure, the meanings of the various reference numerals are as follows: 1. main fuselage structure; 101. skeleton; 102. skin; 103. door; 104. fixing frame; 2. wing structure; 201. central wing; 202. outer wing; 203. plug-in mounting rod 1; 204. locking block; 205. mounting block; 3. motor support arm; 4. tail structure; 401. tail rear beam; 402. fused wing surface; 403. motor support; 404. connecting seat; 405. plug-in mounting rod 2; 406. vertical tail; 407. positioning plate; 408. through hole; 409. fixing block; 410. clamping block; 5. leaf spring landing gear; 6. support block. DETAILED DESCRIPTION

[0028] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. In order to better understand the technical content of the present invention, specific embodiments are cited and explained in conjunction with the drawings as follows. In this disclosure, various aspects of the present invention are described with reference to the drawings, and many illustrative embodiments are shown in the drawings. It should be understood that the various concepts and embodiments introduced above, as well as those described in more detail below, can be implemented in any of many ways. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0029] As attached Figure 1 To the attached Figure 8As shown: This embodiment provides an unmanned eVTOL that can be quickly installed, disassembled and transported, including a fuselage main structure 1, a wing structure 2 is provided on the top of the fuselage main structure 1, motor arms 3 are detachably connected to both sides of the bottom of the wing structure 2, and a tail structure 4 is provided on the rear side of the fuselage main structure 1.

[0030] The main fuselage structure 1 includes a skeleton 101 , the surface of the skeleton 101 is fixedly connected to a skin 102 , the front side, right side and top of the main fuselage structure 1 are detachably connected to a door 103 , and the surface of the door 103 is detachably connected to the skin 102 .

[0031] The wing structure 2 includes a central wing 201 located on top of the main fuselage structure 1. Outer wings 202 are provided on both sides of the central wing 201. Two plug-in mounting rods 203 are fixedly connected to one side of the outer wing 202. One end of the plug-in mounting rod 203 extends through the inner cavity of the central wing 201. Mounting holes compatible with the plug-in mounting rods 203 are provided on both sides of the central wing 201. Locking blocks 204 are fixedly connected to both sides of the central wing 201. A mounting block 205 is fixedly connected to one side of the bottom of the outer wing 202, and the mounting block 205 is compatible with the locking block 204.

[0032] The tail structure 4 includes a tail rear beam 401 that is set through the fuselage main structure 1. Both sides of the surface of the tail rear beam 401 are fixedly connected with fusion airfoils 402. The opposite sides of the two fusion airfoils 402 are in contact with the skin 102. One side of the inner cavity of the fusion airfoil 402 is fixedly connected with a motor support 403. One side of the tail rear beam 401 is provided with two symmetrically arranged through holes 408. The through holes 408 and the motor support 403 are located on the same horizontal line. The motor support 403 is connected to the motor support 403. It is fixedly connected to the rear beam 401 of the tail wing by bolts, and a connecting seat 404 is fixedly connected to the rear side of the inner cavity of the skeleton 101. The top of the connecting seat 404 passes through the top of the skin 102. An inserted mounting rod 2 405 is embedded in the inner cavity of the connecting seat 404. The surface of the inserted mounting rod 2 405 is fixedly connected to the vertical tail 406. The surface of the skin 102 is fixedly connected to two symmetrically arranged fixing blocks 409, and both sides of the surface of the vertical tail 406 are fixedly connected to blocks 410 that are compatible with the fixing blocks 409.

[0033] Specifically, the top of the skeleton 101 is fixedly connected to the fixing frame 104 , and the inner cavity of the fixing frame 104 is fixedly connected to the central wing 201 .

[0034] In this embodiment, the fixing frame 104 is provided to provide a component for connecting the central wing 201 with the main fuselage structure 1 , thereby ensuring the stability of the connection between the central wing 201 and the main fuselage structure 1 .

[0035] Specifically, positioning plates 407 are fixedly connected to both sides of the connecting seat 404. The positioning plates 407 are located in the inner cavity of the skeleton 101. The surfaces of the positioning plates 407 are fixedly connected to the skeleton 101. The opposite sides of the two positioning plates 407 are in contact with the rear beam 401 of the tail wing.

[0036] In this embodiment, the positioning plate 407 is provided to position the rear beam 401 of the empennage, thereby ensuring the accuracy of the position of the rear beam 401 during installation.

[0037] Specifically, the four sides of the skeleton 101 are fixedly connected with the leaf spring landing gear 5 by bolts, and the surface of the leaf spring landing gear 5 penetrates to the outside of the skin 102.

[0038] In this embodiment, the leaf spring landing gear 5 provides support when the fuselage main structure 1 contacts the ground.

[0039] Specifically, the bottoms of the two outer wings 202 are fixedly connected with support blocks 6 , and the inner cavity of the support blocks 6 is adapted to the motor support arm 3 .

[0040] In this embodiment, the support block 6 is provided to provide a component for connecting the motor arm 3 and the outer wing 202 , thereby ensuring the stability of the connection between the outer wing 202 and the motor arm 3 .

[0041] The working principle and usage process of the present invention are as follows: Since the main fuselage structure 1 is composed of a skeleton 101, a skin 102 and a hatch 103, it is convenient for users to load cargo and install battery packs through the hatch 103. When transportation is required, users only need to disassemble the wing structure 2 and the tail structure 4 separately. When disassembling the wing structure 2, the user pulls the two outer wings 202 to move away from each other. The outer wings 202 drive the inserted mounting rod 203 away from the inner cavity of the central wing 201, while driving the locking block 204 away from the inner cavity of the mounting block 205, so that the central wing 201 and the two outer wings 202 are separated. Since the motor support arm 3 is located within the separation surface of the outer wings 202, there is no need to disassemble between the motor support arm 3 and the outer wings 202 during transportation. When disassembling the tail structure 4, the user needs to move the card block 410 out of the fixing block After the inner cavity of 409 is formed, the second plug-in mounting rod 405 is pulled upward to move out of the inner cavity of the connecting seat 404, so that the vertical tail 406 is away from the connecting seat 404. Since the connecting seat 404 is fixedly connected to the skeleton 101, the vertical tail 406 is separated from the main fuselage structure 1. Since the combined width of the two motor supports 403 is the same as the width of the central wing 201, there is no need to disassemble the vertical tail 406 and the tail rear beam 401. When installation is required, the two outer wings 202 are respectively inserted into the inner cavity of the central wing 201 through the mounting holes, and the locking block 204 is inserted into the inner cavity of the mounting block 205. After the two outer wings 202 are installed and connected to the central wing 201, the second plug-in mounting rod 405 is inserted into the inner cavity of the connecting seat 404, and the locking block 410 is inserted into the inner cavity of the fixing block 409, thereby completing the purpose of quick installation.

[0042] It should be noted that, in this document, relational terms such as first and second, etc. are merely used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations.

[0043] While the present invention has been described above with reference to preferred embodiments, this is not intended to limit the present invention. Persons skilled in the art will readily appreciate that various modifications and variations may be made without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention shall be determined by the claims.

Claims

1. An unmanned eVTOL that can be quickly assembled, disassembled, and transported, comprising a fuselage main structure (1), characterized in that: A wing structure (2) is provided on the top of the main fuselage structure (1), motor arms (3) are detachably connected to both sides of the bottom of the wing structure (2), and a tail structure (4) is provided on the rear side of the main fuselage structure (1); The fuselage main structure (1) comprises a frame (101), a skin (102) is fixedly connected to the surface of the frame (101), a door (103) is detachably connected to the front side, the right side and the top of the fuselage main structure (1), and the surface of the door (103) is detachably connected to the skin (102); The wing structure (2) includes a central wing (201) located on the top of the fuselage main structure (1), outer wings (202) are provided on both sides of the central wing (201), one side of the outer wing (202) is fixedly connected to two plug-in mounting rods (203), one end of the plug-in mounting rod (203) passes through the inner cavity of the central wing (201), mounting holes adapted to the plug-in mounting rod (203) are provided on both sides of the central wing (201), and locking blocks (204) are fixedly connected to both sides of the central wing (201); The tail structure (4) includes a tail rear beam (401) that is arranged to penetrate the fuselage main structure (1), and both sides of the surface of the tail rear beam (401) are fixedly connected with fusion-type airfoils (402), and the opposite sides of the two fusion-type airfoils (402) are in contact with the skin (102), and one side of the inner cavity of the fusion-type airfoil (402) is fixedly connected with a motor support (403), and the motor support (403) is fixedly connected to the tail rear beam (401) by bolts. The side is fixedly connected with a connecting seat (404), the top of the connecting seat (404) passes through the top of the skin (102), the inner cavity of the connecting seat (404) is embedded with an inserted mounting rod 2 (405), the surface of the inserted mounting rod 2 (405) is fixedly connected with a vertical tail (406), the surface of the skin (102) is fixedly connected with two symmetrically arranged fixing blocks (409), and both sides of the surface of the vertical tail (406) are fixedly connected with a card block (410) adapted to the fixing block (409).

2. The unmanned eVTOL capable of rapid installation, disassembly, and transportation according to claim 1, characterized in that: The top of the frame (101) is fixedly connected to the fixing frame (104), and the inner cavity of the fixing frame (104) is fixedly connected to the central wing (201).

3. The unmanned eVTOL capable of rapid installation, disassembly, and transportation according to claim 1, characterized in that: A mounting block (205) is fixedly connected to one side of the bottom of the outer wing (202), and the mounting block (205) is adapted to the locking block (204).

4. The unmanned eVTOL capable of rapid installation, disassembly, and transportation according to claim 1, characterized in that: Both sides of the connecting seat (404) are fixedly connected with positioning plates (407), the positioning plates (407) are located in the inner cavity of the frame (101), the surfaces of the positioning plates (407) are fixedly connected to the frame (101), and the opposite sides of the two positioning plates (407) are in contact with the rear beam (401) of the tail wing.

5. The unmanned eVTOL capable of rapid installation, disassembly, and transportation according to claim 1, characterized in that: Two symmetrically arranged through holes (408) are provided on one side of the tail rear beam (401), and the through holes (408) and the motor support (403) are located on the same horizontal line.

6. The unmanned eVTOL capable of rapid installation, disassembly, and transportation according to claim 1, characterized in that: The four sides of the frame (101) are fixedly connected with leaf spring landing gears (5) by means of bolts, and the surface of the leaf spring landing gears (5) penetrates to the outside of the skin (102).

7. The unmanned eVTOL capable of rapid installation, disassembly, and transportation according to claim 1, characterized in that: The bottoms of the two outer wings (202) are fixedly connected to support blocks (6), and the inner cavity of the support blocks (6) is adapted to the motor support arm (3).

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