Portable vertical take-off and landing unmanned aerial vehicle

Abstract

The utility model discloses a portable vertical take-off and landing unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles, and comprises a vehicle body provided with a mounting port; the wings are matched with the mounting ports; the two installation rods are installed at the two ends of the wings respectively and movably connected with the wings in a clamped mode, and propellers are installed at the two ends of each installation rod; according to the unmanned aerial vehicle, the wings and the installation rods installed on the wings are arranged to be detachable, the wings and the installation rods installed on the wings can be detached when the unmanned aerial vehicle is transported and stored, therefore, the occupied space can be reduced, and the unmanned aerial vehicle is convenient to carry by a user.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a portable vertical take-off and landing UAV. Background Art

[0002] Currently, drone designs generally utilize an integrated wing-to-body structure. This fixed design offers the advantage of high stability in practical applications. However, this fixed connection is a major factor limiting the drone's portability. Specifically, the inseparable fixed connection between the wings and the body requires the entire drone to be transported or stored as a single, larger unit. This undoubtedly places an additional burden on users who frequently carry drones for outdoor work or travel. To address this issue, the present utility model provides a portable vertical take-off and landing drone. Utility Model Content

[0003] In response to the above-mentioned technical deficiencies, the purpose of the present invention is to provide a portable vertical take-off and landing UAV, in which the wings and the mounting rods installed on the wings are set to be detachable, which can be removed when the UAV is transported and stored, thereby reducing the occupied space and making it easier for users to carry.

[0004] In order to solve the above technical problems, the present invention adopts the following technical solutions: The present invention provides a portable vertical take-off and landing UAV, comprising:

[0005] A machine body, wherein the machine body is provided with a mounting opening;

[0006] a wing, the wing being adapted to fit the mounting opening;

[0007] Two mounting rods, the two mounting rods are respectively mounted on the two ends of the wing and movably connected to the wing, and propellers are mounted on both ends of the mounting rods;

[0008] The clamping assembly is mounted on the fuselage. When the wing is mounted inside the mounting opening, the clamping assembly and the wing are clamped to each other.

[0009] Preferably, when the mounting rod is movably engaged with the wing, it abuts against the lower side of the wing.

[0010] Preferably, a plurality of plug-in blocks are fixedly connected to the mounting rod, and slots adapted to the plug-in blocks are provided on the wing, and the plug-in blocks are movably engaged with the slots.

[0011] Preferably, both sides of one end of the inserting block located inside the slot are folded outwards, and a slot wall of the slot is provided with a card slot adapted to the folded end of the inserting block.

[0012] Preferably, a U-shaped groove is formed at one end of the insert block located inside the slot, and a spring plate is installed between the two side walls of the U-shaped groove, and the spring plate has an elastic force that presses the two side walls of the U-shaped groove in opposite directions. A push rod is fixedly connected to the spring plate, and the end of the push rod away from the spring plate passes through the mounting rod and is flush with the corresponding side of the mounting rod.

[0013] Preferably, the clamping assembly includes:

[0014] a top plate, the top plate being mounted on the machine body;

[0015] A plurality of fixing rods, wherein the fixing rods are fixedly connected to the lower side of the top plate, and the lower ends of the fixing rods extend through the fuselage into the recessed grooves provided on the inner side of the mounting opening, and are movably engaged with the bayonet provided on the wing;

[0016] Among them, the fixing rod is a stepped shaft, and the diameter of the lower end of the fixing rod is larger than the diameter of the upper end. The diameter of the lower end of the fixing rod is adapted to the inner diameter of the sink, and a spring is connected between the step of the fixing rod and the bottom side wall of the sink, and the spring has a pressing force that makes the fixing rod press against the inner wall of the bayonet.

[0017] Preferably, the top plate and the body are fitted together, and the four sides of the top plate are arc edges;

[0018] A sliding groove is provided on the upper side of the top plate, and a spring is slidably connected inside the sliding groove.

[0019] The beneficial effects of the present invention are:

[0020] The utility model realizes a detachable connection between the wing and the body through the arrangement of the mounting port and the snap-on assembly. The wing can be removed from the body when carrying the aircraft, so that the long side of the wing can be placed along the length direction of the body, thereby reducing the space occupied by the wing and the body, making it more convenient for users to carry.

[0021] The utility model realizes a detachable connection between the wing and the mounting rod by setting the insert block and the slot. When carrying, the mounting rod can be removed from the wing, so that the long side of the mounting rod can be placed along the length direction of the body when carrying, thereby further reducing the occupied space and making it more convenient for users to carry. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0023] Figure 1 A schematic structural diagram of a portable vertical take-off and landing UAV provided in an embodiment of the utility model.

[0024] Figure 2 This is an exploded view of the fuselage, wings and mounting rods of the utility model.

[0025] Figure 3 This is an exploded view of the plug-in block and slot of the utility model.

[0026] Figure 4 It is a partial cross-sectional view of the body of the utility model.

[0027] Figure 5 This is an exploded view of the slideway and shrapnel of the utility model.

[0028] Description of reference numerals:

[0029] 1. Body, 2. Mounting port, 3. Wing, 4. Mounting rod, 5. Insert block, 6. Slot, 7. Card slot, 8. U-shaped slot, 9. Spring plate, 10. Push rod, 11. Top plate, 12. Fixing rod, 13. Sink, 14. Bayonet, 15. Spring, 16. Slide, 17. Shrapnel. DETAILED DESCRIPTION

[0030] 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. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0031] The utility model provides a portable vertical take-off and landing UAV, such as Figures 1 to 5 shown.

[0032] Example 1:

[0033] A portable vertical take-off and landing UAV includes a body 1, on which wings 3 are mounted through a mounting opening 2 provided on the body 1. A snap-fit ​​assembly is installed on the body 1. When the wings 3 are mounted inside the mounting opening 2, the snap-fit ​​assembly can fix the wings 3 so that the wings 3 and the body 1 are stably connected together. Both ends of the wings 3 are movably snap-fitted with mounting rods 4, which are located on the lower side of the wings 3, and propellers are installed at both ends of the mounting rods 4. When carrying, the wings 3 and the mounting rods 4 can be removed, and the long sides of the wings 3 and the mounting rods 4 can be placed along the length direction of the body 1, thereby reducing the occupied volume and making it easier for users to carry.

[0034] The cam 6 is provided with a plurality of plug-in blocks 5 fixedly connected to the mounting rod 4, and a slot 6 adapted to the plug-in block 5 is provided on the wing 3. One end of the plug-in block 5 located inside the slot 6 is folded toward both sides, and the folded end on the plug-in block 5 is engaged with the slot 7 on the slot wall of the slot 6. In order to facilitate the user's disassembly and assembly, a U-shaped slot 8 is provided at one end of the plug-in block 5 located inside the slot 6, and a spring plate 9 is provided between the two side groove walls of the U-shaped slot 8. The shape of the spring plate 9 is arc-shaped, and the two ends of the spring plate 9 are fixedly connected to the groove walls on both sides of the U-shaped groove 8 respectively. The spring plate 9 has an elastic force that presses the groove walls on both sides of the U-shaped groove 8 in opposite directions. A push rod 10 is fixedly connected to the spring plate 9. The end of the push rod 10 away from the spring plate 9 passes through the mounting rod 4 and is flush with the side of the mounting rod 4 away from the wing 3. When disassembling, it is necessary to apply pressure to the push rod 10 in the direction of the spring plate 9, so that the folded end of the plug-in block 5 is retracted inwardly through the spring plate 9, reducing the spacing, and then it is convenient for the user to perform disassembly and assembly.

[0035] Example 2:

[0036] Based on the first embodiment, the clamping assembly may adopt the following structure, specifically as follows:

[0037] The clamping assembly includes a top plate 11, which is installed on the fuselage 1 and fits together with the fuselage 1. A plurality of fixing rods 12 are fixedly installed on the lower side of the top plate 11. The lower end of the fixing rod 12 passes through the fuselage 1 and extends to the sinking groove 13 provided on the inner side of the mounting port 2, and is movably clamped with the bayonet 14 provided on the wing 3. The fixing rod 12 is a stepped shaft, and the upper end of the fixing rod 12 is thin and the lower end is thick. The upper end of the fixing rod 12 is fixedly connected to the top plate 11, and the lower end is movably clamped with the bayonet 14. The diameter of the lower end of the fixing rod 12 is adapted to the inner diameter of the sinking groove 13.

[0038] The intersection of the thin end and the thick end of the fixing rod 12 is stepped, and a spring 15 is connected between this step and the side wall of the bottom of the groove 13. The spring 15 has a pressing force that makes the fixing rod 12 press against the inner wall of the bayonet 14. Under the action of this pressing force, the fixing rod 12 is stably engaged with the bayonet 14.

[0039] Furthermore, in order to reduce the resistance of the top plate 11 during flight, the top plate 11 is configured to fit the body 1 , and the four sides of the top plate 11 are configured to be arc sides, thereby reducing the resistance.

[0040] Furthermore, in order to facilitate the staff to pull the top plate 11, a slide groove 16 is provided on the upper side of the top plate 11, and a spring piece 17 is slidably installed inside the slide groove 16. Both sides of the spring piece 17 are provided with protrusions, and the groove wall of the slide groove 16 is provided with slide rails corresponding to the protrusions. The spring piece 17 will be tightly attached to the bottom side wall of the slide groove 16 under its own elastic force. At the same time, the upper side of the spring piece 17 is flush with the upper side of the top plate 11. When it is necessary to pull the top plate 11, the user can squeeze the two ends of the spring piece 17 toward the middle at the same time, so that the middle of the spring piece 17 bulges, so that the user can pull the top plate 11 conveniently. Further, in order to facilitate the user to push the spring piece 17, friction grooves are provided at both ends of the upper side of the spring piece 17, which increases the friction between the spring piece 17 and the user's fingers, making it convenient for the user to push the spring piece 17.

[0041] The side of the top plate 11 away from the body 1 is an upper side, and the end of the fixing rod 12 away from the top plate 11 is a lower end.

[0042] Plugs are provided on the mounting rod 4 and inside the bayonet 14, and corresponding sockets are provided on the wing 3 and the fixing rod 12. When the mounting rod 4 is installed on the wing 3, the plug on the mounting rod 4 and the socket on the wing 3 are plugged into each other. When the fixing rod 12 and the bayonet 14 are engaged with each other, the plug inside the bayonet 14 will be plugged into the socket of the fixing rod 12, so that the propeller on the mounting rod 4 can be electrically connected to the battery inside the body 1. For better display effect, the plugs on the mounting rod 4 and inside the bayonet 14 and the sockets on the wing 3 and the fixing rod 12 are not shown in the drawings.

[0043] Obviously, those skilled in the art may make various modifications and variations to the present invention without departing from the spirit and scope of the present invention. Thus, if such modifications and variations fall within the scope of the claims of the present invention and their equivalents, the present invention is intended to include such modifications and variations.

Claims

1. A portable vertical take-off and landing drone, characterized in that: include: A machine body (1), wherein the machine body (1) is provided with a mounting opening (2); A wing (3), wherein the wing (3) is adapted to fit the mounting opening (2); Two mounting rods (4), the two mounting rods (4) are respectively mounted on two ends of the wing (3) and are movably connected to the wing (3), and propellers are mounted on both ends of the mounting rods (4); A snap-fit ​​assembly is mounted on the body (1); when the wing (3) is mounted inside the mounting opening (2), the snap-fit ​​assembly and the wing (3) are snap-fitted to each other.

2. A portable vertical take-off and landing UAV according to claim 1, characterized in that: When the mounting rod (4) is movably engaged with the wing (3), it presses against the lower side of the wing (3).

3. A portable vertical take-off and landing UAV according to claim 2, characterized in that: A plurality of insert blocks (5) are fixedly connected to the mounting rod (4), and slots (6) adapted to the insert blocks (5) are provided on the wing (3), and the insert blocks (5) and the slots (6) are movably engaged.

4. A portable vertical take-off and landing UAV according to claim 3, characterized in that: The insert block (5) is located inside the slot (6) and has two sides folded outward at one end. A slot (7) adapted to the folded end of the insert block (5) is provided on the slot wall of the slot (6).

5. The portable vertical take-off and landing UAV according to claim 4, characterized in that: A U-shaped groove (8) is formed at one end of the insert block (5) located inside the slot (6), and a spring plate (9) is installed between the two side walls of the U-shaped groove (8), and the spring plate (9) has an elastic force that presses the two side walls of the U-shaped groove (8) in opposite directions. A push rod (10) is fixedly connected to the spring plate (9), and the end of the push rod (10) away from the spring plate (9) passes through the mounting rod (4) and is flush with the side surface corresponding to the mounting rod (4).

6. The portable vertical take-off and landing UAV according to claim 1, characterized in that: The clamping assembly comprises: A top plate (11), the top plate (11) being mounted on the machine body (1); A plurality of fixing rods (12), wherein the fixing rods (12) are fixedly connected to the lower side of the top plate (11), and the lower ends of the fixing rods (12) pass through the body (1) and extend into a sinking groove (13) provided on the inner side of the installation opening (2), and are movably engaged with the bayonet (14) provided on the wing (3); The fixing rod (12) is a stepped shaft, and the diameter of the lower end of the fixing rod (12) is larger than the diameter of the upper end. The diameter of the lower end of the fixing rod (12) is adapted to the inner diameter of the sink (13). A spring (15) is connected between the step of the fixing rod (12) and the side wall of the bottom of the sink (13). The spring (15) has a pressing force that causes the fixing rod (12) to press against the inner wall of the bayonet (14).

7. The portable vertical take-off and landing UAV according to claim 6, characterized in that: The top plate (11) and the body (1) are fitted together, and the four sides of the top plate (11) are arc edges; A sliding groove (16) is provided on the upper side of the top plate (11), and a spring piece (17) is slidably connected inside the sliding groove (16).

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