Pure electric long-endurance unmanned aerial vehicle

Abstract

The pure electric long-endurance unmanned aerial vehicle comprises a vehicle body, a left main wing and a right main wing, and the left main wing and the right main wing are both connected to the vehicle body. The supporting rods are arranged at the bottoms of the left main wing and the right main wing; the propellers are arranged on each supporting rod, and the two propellers are arranged on each supporting rod; one connecting cylinder is detachably arranged on each supporting rod, and the other connecting cylinder is detachably arranged on the other supporting rod; the empennage assembly is connected to the two connecting cylinders; the empennage assembly is convenient to transport or carry, and accurate installation of the empennage assembly can be guaranteed conveniently.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a pure electric long-flight UAV. Background Art

[0002] Pure electric long-flight UAVs are an important development direction of UAV technology. They combine the advantages of pure electric power systems and long-flight capabilities, providing greater space for the application of UAVs in multiple fields. However, existing pure electric long-flight UAVs are usually integrated structures, which are inconvenient for partial disassembly and separation. Since the entire UAV occupies a large area, it often causes inconvenience when transporting or carrying it. Utility Model Content

[0003] The purpose of the present invention is to provide a pure electric long-flight UAV to solve the problems raised in the above background technology.

[0004] In order to solve the above technical problems, the present invention provides the following technical solutions: a pure electric long-flight UAV, comprising a fuselage, a left main wing, and a right main wing, wherein the left main wing and the right main wing are both connected to the fuselage; further comprising: a support rod, wherein the bottom of the left main wing and the bottom of the right main wing are both provided with the support rod; a propeller, wherein each of the support rods is provided with two of the propellers; a connecting tube, wherein each of the support rods is respectively provided with a detachable connecting tube; and a tail assembly, wherein the tail assembly is connected to the two connecting tubes.

[0005] Furthermore, it also includes: a supporting tube, which has two supporting tubes, and the two supporting tubes are detachably arranged on the two supporting rods; a fixed threaded sleeve, a fixed threaded sleeve is provided on one end of each supporting rod; a connecting threaded sleeve, and the connecting threaded sleeve is adapted to the fixed threaded sleeve; wherein, the connecting tube is provided with a threaded structure adapted to the connecting threaded sleeve at one end close to the supporting rod, and the threaded structure on the connecting tube and the threaded structure on the fixed threaded sleeve are spliced ​​to form a complete and continuous threaded structure.

[0006] Furthermore, it also includes: a connecting head, which is provided at one end of the support tube, and a part of the connecting head is located inside the support tube; wherein, a threaded hole is provided at one end of the support rod close to the tail wing assembly, and the connecting head is threadedly connected to the threaded hole.

[0007] Furthermore, the connecting head includes: a connecting block, which is a cylindrical structure and is coaxially arranged in the support tube; a connecting stud, a connecting stud is coaxially arranged at one end of the connecting block, and the connecting stud is threadedly fitted in the threaded hole.

[0008] Furthermore, an open slot is provided through the support tube, and a clamping block is provided inside the connecting tube, and the clamping block is fitted in the open slot.

[0009] Furthermore, the tail wing assembly includes a left tail wing piece and a right tail wing piece, the left tail wing piece and the right tail wing piece are fixedly connected to two connecting tubes respectively, and the left tail wing piece and the right tail wing piece form an inverted V shape.

[0010] Furthermore, a circular arc transition is provided at the connection between the left tail wing piece and the right tail wing piece.

[0011] Furthermore, the left tail fin piece and the right tail fin piece are both provided with connecting parts, and the connecting parts are fixedly connected to the connecting tube.

[0012] Compared with the prior art, the beneficial effects achieved by the present invention are: the connecting tube is threadedly connected by connecting the threaded sleeve, and the connecting tube can be quickly installed and fixed by utilizing the cooperation of the open groove and the clamping block; since the support tube and the tail assembly are detachable, it is convenient to transport or carry the entire drone; through the cooperation of the open groove and the clamping block, it is easy to ensure that the installation angle of the tail assembly is accurate. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] 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:

[0014] Figure 1 This is a schematic diagram of the overall structure of the first embodiment of the present utility model;

[0015] Figure 2 This is a schematic diagram of the overall structure of the second embodiment of the present utility model;

[0016] Figure 3 This is a schematic diagram of the cooperation between the fixed threaded sleeve, the connecting threaded sleeve and the connecting cylinder in the second embodiment of the present utility model;

[0017] Figure 4 This is a schematic diagram of the disconnected state of the connecting tube of the second embodiment of the present invention;

[0018] Figure 5 This is a schematic structural diagram of the connecting tube of the second embodiment of the present utility model;

[0019] Figure 6 This is a schematic diagram of the cooperation between the connector and the support rod in the third embodiment of the present invention;

[0020] In the figure: 1. Fuselage; 2. Left main wing; 3. Right main wing; 4. Support rod; 41. Fixing threaded sleeve; 42. Threaded hole; 5. Propeller; 6. Connecting tube; 61. Block; 7. Connecting threaded sleeve; 8. Tail assembly; 81. Left tail piece; 82. Right tail piece; 83. Connecting part; 84. Arc transition; 9. Support tube; 91. Opening groove; 92. Connecting head; 921. Connecting block; 922. Connecting stud. DETAILED DESCRIPTION

[0021] 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.

[0022] Example 1

[0023] See also Figure 1 The utility model provides a technical solution: a pure electric long-flight UAV, comprising a fuselage 1 provided with a left main wing 2 and a right main wing 3, a support rod 4 fixedly provided on the left main wing 2 and the right main wing 3, respectively, and the two support rods 4 are symmetrically arranged on both sides of the fuselage 1; two propellers 5 are movably provided on each support rod 4, specifically, the propellers 5 are movably provided on the support rods 4 through a rotating shaft, and a motor that can drive the rotating shaft connected to the propellers 5 to rotate is installed in the support rods 4; such as Figure 1 As shown, each propeller 5 is located below the support rod 4; in another alternative, each propeller 5 is located above the support rod 4.

[0024] Example 2

[0025] See also Figure 2-Figure 5 This embodiment is based on the first embodiment, and a connecting tube 6 is detachably provided on each support rod 4. The two connecting tubes 6 are symmetrically arranged on both sides of the fuselage 1, and the ends of the two connecting tubes 6 away from the support rod 4 are commonly connected to a tail assembly 8.

[0026] In addition, a support tube 9 is detachably provided at one end of each support rod 4 near the tail of the fuselage 1, and two connecting tubes 6 are respectively sleeved and fitted on the outside of the two support tubes 9; one end of the support rod 4 near the tail of the fuselage 1 is a cylindrical structure, and the end of the support rod 4 near the tail of the fuselage 1 is coaxially provided with a fixed threaded tube, which can be fixedly connected to the support rod 4 by welding, screws, etc., and one end of the fixed threaded tube is flush with the end of the support rod 4 near the tail of the fuselage 1; a threaded structure is provided at one end of the support tube 9 away from the tail assembly 8; when the end of the connecting tube 6 away from the tail assembly 8 contacts the end of the fixed threaded tube, and the connecting tube 6 is coaxial with the end of the support rod 4, the threaded structure on the connecting tube 6 and the threaded structure on the fixed threaded sleeve 41 are spliced ​​to form a complete and continuous threaded structure; in addition, a connecting threaded sleeve 7 is also provided, which is adapted to the threaded structures on the connecting tube 6 and the fixed threaded sleeve 41, that is, the splicing of the connecting tube 6 and the fixed threaded sleeve is achieved through the connecting threaded sleeve 7.

[0027] The tail wing assembly 8 includes a left tail wing piece 81 and a right tail wing piece 82, which are respectively fixedly connected to the ends of the two connecting tubes 6 away from the support rod 4; the left tail wing piece 81 and the right tail wing piece 82 are combined to form an inverted V shape, and a circular arc transition 84 is provided at the connection between the left tail wing piece 81 and the right tail wing piece 82; at the same time, a connecting part 83 is provided on the left tail wing piece 81 and the right tail wing piece 82, and the two connecting parts 83 are respectively fixedly connected to the ends of the two connecting tubes 6 away from the support rod 4.

[0028] In this embodiment, the connecting tube 6 is supported by the supporting tube 9, and the supporting tube 9 is made of aluminum to enhance the stability of the connecting tube 6; the left tail wing piece 81 and the right tail wing piece 82 form an inverted V shape, and the angle between the left tail wing piece 81 and the right tail wing piece 82 is an acute angle; by setting the tail assembly 8, the long-flight UAV is helped to achieve longitudinal stability when vertically taking off and laterally stability when flying level.

[0029] In addition, an open groove 91 is provided through the support tube 9, and a clamping block 61 is provided inside the connecting tube 6, and the clamping block 61 is adapted to the open groove 91; that is, when the connecting tube 6 is sleeved on the outside of the supporting tube 9, the clamping block 61 needs to be aligned with the position of the open groove 91, so as to avoid inaccurate installation angle of the connecting tube 6, thereby ensuring the matching of the connecting threaded tube and the supporting tube 9, and also ensuring the accurate installation angle of the tail wing assembly 8.

[0030] like Figure 4As shown, when the connecting threaded sleeve 7 is rotated so that the connecting threaded sleeve 7 moves toward the head of the fuselage 1 and the connecting threaded sleeve 7 is separated from the connecting tube 6, the connecting tube 6 can be separated from the fixed sleeve. At this time, the two connecting tubes 6 and the tail assembly 8 are moved away from the support rod 4 so that the two connecting tubes 6 are separated from the two supporting tubes 9 respectively, and the connecting tube 6 and the tail assembly 8 can be disassembled. In addition, the supporting tube 9 is detachably arranged on the support rod 4, that is, the supporting tube 9 and the entire tail assembly 8 are detachable, thereby facilitating the transportation or carrying of the entire UAV and avoiding occupying a large space. The connecting tube 6 is threadedly connected to the connecting threaded sleeve 7, and the cooperation of the opening groove 91 and the block 61 is utilized to facilitate the quick installation of the connecting tube 6.

[0031] In this embodiment, the entire UAV adopts a pure electric power system, and the propulsion motor of the fixed-wing part and the motor of the rotor part of the UAV are powered by an independent battery system; the UAV has the ability to carry a variety of mission equipment (radar, pod, camera, etc.) and can adapt to more mission scenarios and needs; the UAV can be equipped with an intelligent battery to realize the automatic heating function requirements; at the same time, the propeller 5 can be provided with a locking structure (the locking structure adopts existing technology). In the level flight mode, the propeller 5 remains locked in the feathering position, which can reduce aerodynamic resistance.

[0032] Example 3

[0033] See also Figure 2-Figure 6 , this embodiment is based on the second embodiment, and a connecting head 92 is fixedly provided on the support tube 9, and the connecting head 92 includes a connecting block 921 with a cylindrical structure, and the connecting block 921 is coaxially arranged in the end of the support tube 9, one end of the connecting block 921 is coplanar with one end of the support tube 9, and the connecting block 921 is fixedly connected to the support tube 9; a connecting stud 922 is coaxially provided at one end of the connecting block 921, and the connecting stud 922 extends out of the support tube 9; at the same time, a threaded hole 42 that is adapted to the connecting stud 922 is coaxially provided at one end of the support rod 4 near the tail of the fuselage 1, and the support tube 9 can be detachably provided on the support rod 4 by fitting the connecting stud 922 in the threaded hole 42; that is, when installing the support tube 9, the support tube 9 can be quickly installed by screwing the connecting stud 922 into the threaded hole 42, and the end of the support tube 9 contacts the end of the support rod 4 with the threaded hole 42.

[0034] It should be noted that, in this document, relational terms such as first and second, etc., are used only 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. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

Claims

1. A pure electric long-flight UAV, comprising a fuselage (1), a left main wing (2), and a right main wing (3), wherein the left main wing (2) and the right main wing (3) are both connected to the fuselage (1); characterized in that: Also includes: A support rod (4), the bottom of the left main wing (2) and the bottom of the right main wing (3) are both provided with the support rod (4); Propellers (5), two propellers (5) are provided on each of the support rods (4); A connecting tube (6), each of the support rods (4) is detachably provided with a connecting tube (6); A tail assembly (8), wherein the tail assembly (8) is connected to the two connecting tubes (6).

2. The pure electric long-flight UAV according to claim 1, characterized in that: Also includes: A support cylinder (9), wherein the support cylinders (9) are provided in two pieces, and the two support cylinders (9) are detachably arranged on the two support rods (4); A fixed threaded sleeve (41), wherein one end of each support rod (4) is fixedly provided with a fixed threaded sleeve (41); A connecting threaded sleeve (7), wherein the connecting threaded sleeve (7) is adapted to the fixed threaded sleeve (41); Wherein, one end of the connecting tube (6) close to the support rod (4) is provided with a threaded structure adapted to the connecting threaded sleeve (7), and the threaded structure on the connecting tube (6) and the threaded structure on the fixed threaded sleeve (41) are spliced ​​to form a complete and continuous threaded structure.

3. The pure electric long-flight UAV according to claim 2, characterized in that: Also includes: A connector (92), one end of the support tube (9) is provided with the connector (92), and a portion of the connector (92) is located inside the support tube (9); A threaded hole (42) is provided at one end of the support rod (4) close to the tail assembly (8), and the connecting head (92) is threadedly connected to the threaded hole (42).

4. The pure electric long-flight UAV according to claim 3, characterized in that: The connector (92) comprises: A connecting block (921), the connecting block (921) is a cylindrical structure, and the connecting block (921) is coaxially arranged in the supporting cylinder (9); A connecting stud (922) is coaxially provided on one end of the connecting block (921), and the connecting stud (922) is threadedly engaged in the threaded hole (42).

5. The pure electric long-flight UAV according to claim 2, characterized in that: An open slot (91) is provided through the support tube (9), and a clamping block (61) is provided inside the connecting tube (6), and the clamping block (61) is fitted in the open slot (91).

6. The pure electric long-flight UAV according to claim 1, characterized in that: The tail assembly (8) comprises a left tail piece (81) and a right tail piece (82), wherein the left tail piece (81) and the right tail piece (82) are fixedly connected to two connecting tubes (6) respectively, and the left tail piece (81) and the right tail piece (82) form an inverted V shape.

7. The pure electric long-flight UAV according to claim 6, characterized in that: A circular arc transition (84) is provided at the connection between the left tail wing piece (81) and the right tail wing piece (82).

8. The pure electric long-flight UAV according to claim 6, characterized in that: The left tail fin piece (81) and the right tail fin piece (82) are both provided with a connecting portion (83), and the connecting portion (83) is fixedly connected to the connecting tube (6).

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