Long straight-wing airfoil surface rotating and folding mechanism suitable for small-sized patrol unmanned aerial vehicle

Abstract

The utility model discloses a long straight wing airfoil surface rotating and folding mechanism suitable for a small-sized patrol unmanned aerial vehicle. The long straight wing airfoil surface rotating and folding mechanism comprises a fuselage, and wings and a folding mechanism are arranged on the fuselage; the folding mechanism comprises an upper rotating shaft, a lower rotating shaft, an upper blocking cover and a lower blocking cover; the upper blocking cover is fixedly arranged on the machine body, a connecting bolt is arranged in the middle of the upper rotating shaft, and the connecting bolt penetrates through the upper blocking cover and is fixedly connected with the lower rotating shaft; the lower blocking cover is fixed on the machine body; the upper rotating shaft and the lower rotating shaft are connected through a bolt and are rotationally connected with the upper blocking cover and the lower blocking cover through bearings; the wings are fixed on the upper rotating shaft through bolts. According to the unmanned aerial vehicle, when the electromagnet loses attraction force when powered on, the fixed attraction force of the electromagnet to the attraction block disappears, at the moment, the torsion spring drives the lower rotating shaft to rotate so as to drive the upper rotating shaft and the wings to rotate together, folding and unfolding of the wings can be achieved, and the portability and the storage space utilization rate of the unmanned aerial vehicle are improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles, in particular to a long straight wing surface rotating and folding mechanism suitable for a small-sized patrol unmanned aerial vehicle. Background Art

[0002] A patrol drone is a drone that is deployed using an existing platform or launched by a launcher. It can patrol a predetermined area at a specified altitude and speed, and can perform multiple tasks such as reconnaissance, strike, communication, and interference. In order to achieve long-term flight at a specific design point, the wingspan of patrol drones is usually relatively large, but like conventional ammunition, it is constrained by the size of the launch or the geometric space of the launcher. Therefore, patrol drones usually use foldable and unfoldable long straight wings with a large aspect ratio.

[0003] In the prior art, for example, the technical solution described in the patent with the announcement number: CN214648992U: a foldable fixed-wing UAV, by providing a rotatable main wing root and a driving mechanism, realizes the automatic deployment of the UAV wing, avoiding the problem of time-consuming manual deployment. At the same time, because the roots of the left main wing and the right main wing are located in the same concave plane.

[0004] In the prior art, wing folding is mostly achieved by an actuator or a servo plus spring mechanism, so that the drone can be mounted on an existing carrier platform or launched through a launch device. The solutions in the prior art are either complex and unreliable, or have high costs, which greatly increases costs for price-sensitive small patrol drones. Utility Model Content

[0005] The purpose of the utility model is to provide a long straight wing wing surface rotation and folding mechanism suitable for a small patrol UAV, so as to solve the problem that the wing folding mechanism is complicated in the prior art proposed in the background technology, resulting in low reliability and high cost of mechanism implementation.

[0006] In order to solve the above technical problems, the technical solution adopted by the utility model is:

[0007] A long straight wing surface rotation and folding mechanism suitable for a small patrol UAV comprises a fuselage, a wing and a folding mechanism are arranged on the fuselage; the wing is connected to the fuselage through a folding structure; wherein the wing is fixedly connected to the folding mechanism;

[0008] The folding mechanism comprises an upper rotating shaft, a lower rotating shaft, an upper baffle and a lower baffle; wherein the upper baffle is fixedly arranged on the fuselage, the upper rotating shaft is arranged above the upper baffle, a connecting bolt is arranged in the middle of the upper rotating shaft, the connecting bolt passes through the upper baffle and is fixedly connected to the lower rotating shaft; the upper rotating shaft is also fixedly connected to the wing;

[0009] The lower cover is arranged on the machine body, the lower shaft is rotatably connected with the lower cover, a torsion spring is sleeved on the outer side of the shaft, one end of the torsion spring is fixedly connected with the lower shaft, and the other end of the torsion spring is fixedly connected with the upper cover.

[0010] According to the above technical solution, a mounting groove is arranged on the fuselage, and the upper end cover is arranged inside the mounting groove.

[0011] According to the above technical solution, a positioning column is arranged inside the installation groove, and a corresponding installation hole is arranged on the upper end cover. The installation hole cooperates with the positioning column and is used for connecting the upper end cover with the fuselage.

[0012] According to the above technical solution, a first connecting hole is also provided on the upper rotating shaft, and a second connecting hole corresponding to the first connecting hole is provided on the wing. Indexing pins are installed inside the first connecting hole and the second connecting hole, and the indexing pins are used to fix the connection between the wing and the upper rotating shaft.

[0013] According to the above technical solution, a limiting column is further provided at the end of the upper baffle, and a first limiting groove is provided at the end of the limiting column, and the first limiting groove is used to fix the end of the torsion spring.

[0014] According to the above technical solution, a connecting plate is further provided on the lower rotating shaft, and a second limiting groove is provided at the end of the connecting plate, and the second limiting groove is used to fix the other end of the torsion spring.

[0015] According to the above technical solution, a first installation cavity is provided in the middle of the upper baffle, a first bearing is provided inside the first installation cavity, and the first bearing sleeve is arranged outside the connecting bolt.

[0016] According to the above technical solution, a second installation cavity is provided in the middle of the lower baffle, a rotating shaft is provided below the lower rotating shaft, and the rotating shaft is provided inside the second installation cavity for rotationally connecting the lower rotating shaft with the lower baffle.

[0017] According to the above technical solution, a second rotating shaft is further arranged inside the second installation cavity, and the second rotating shaft is sleeved on the outer side of the rotating shaft.

[0018] According to the above technical solution, a suction block is provided at one end of the wing, and an electromagnet is provided on the fuselage. The electromagnet cooperates with the suction block to fix the wing and the fuselage.

[0019] Compared with the prior art, the utility model has the following beneficial effects:

[0020] In the utility model, a de-energized electromagnet-suction block combination is used as the wing folding and fixing power, and a torsion spring is used as the wing rotation power. When the electromagnet is not energized, the electromagnet and the suction block are fixed together to offset the torsion of the torsion spring so as to fold and fix the wing. When the electromagnet loses suction when energized, the fixing suction of the electromagnet on the suction block disappears. At this time, the lower rotating shaft rotates under the drive of the torsion spring, thereby driving the upper rotating shaft and the wing to rotate together, so that the wing can be folded and unfolded, and the portability and storage space utilization rate of the UAV are improved. At the same time, the folding mechanism has a simple structure and is easy to operate, which can effectively reduce the flight resistance of the UAV and improve the flight efficiency and stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0022] Figure 2 This is a schematic diagram of the internal structure of the utility model;

[0023] Figure 3 This is a partial enlarged structural diagram of the utility model at A;

[0024] Figure 4 It is a schematic diagram of the folding mechanism structure of the utility model.

[0025] Markings in the figure: 100-fuselage, 200-wing, 300-upper rotating shaft, 400-lower rotating shaft, 500-upper baffle, 600-lower baffle, 700-connecting bolt, 800-torsion spring, 900-installing groove, 110-positioning column, 111-first connecting hole, 112-second connecting hole, 113-first limiting groove, 114-connecting plate, 115-second limiting groove, 116-first bearing, 117-second rotating shaft, 118-suction block, 119-electromagnet, 120-indexing pin. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0027] Embodiment 1

[0028] like Figure 1 As shown, a long straight wing wing surface rotation folding mechanism suitable for a small cruise UAV includes a fuselage 100, a wing 200 and a folding mechanism are arranged on the fuselage 100; the wing 200 is connected to the fuselage 100 through a folding structure; wherein the wing 200 is fixedly connected to the folding mechanism;

[0029] like Figure 3 and Figure 4 As shown, the folding mechanism includes an upper rotating shaft 300, a lower rotating shaft 400, an upper blocking cover 500 and a lower blocking cover 600; wherein the upper blocking cover 500 is fixedly arranged on the fuselage 100, the upper rotating shaft 300 is arranged above the upper blocking cover 500, a connecting bolt 700 is arranged in the middle of the upper rotating shaft 300, and the connecting bolt 700 passes through the upper blocking cover 500 and is fixedly connected to the lower rotating shaft 400; the upper rotating shaft 300 is also fixedly connected to the wing 200;

[0030] The lower cover 600 is arranged on the fuselage 100, the lower shaft 400 is rotatably connected to the lower cover 600, a torsion spring 800 is sleeved on the outer side of the shaft, one end of the torsion spring 800 is fixedly connected to the lower shaft 400, and the other end of the torsion spring 800 is fixedly connected to the upper cover 500.

[0031] In the present invention, the torsion spring 800 is used as the power to drive the lower rotating shaft 400 to rotate, thereby driving the upper rotating shaft 300 and the wing 200 to rotate together, so that the wing 200 can be folded and unfolded, thereby improving the portability and storage space utilization of the drone. At the same time, the folding mechanism has a simple structure and is easy to operate, which can effectively reduce the flight resistance of the drone and improve the flight efficiency and stability.

[0032] Embodiment 2

[0033] This embodiment is a further refinement of the first embodiment.

[0034] Further, such as Figure 2 As shown, the interior of the fuselage 100 is hollow. The lower shaft 400, the lower cover 600 and the torsion spring 800 of the folding mechanism are arranged inside the fuselage 100; the upper cover 500 is arranged on the fuselage 100; one end of the upper shaft 300 is fixedly connected to the wing 200, and the connecting bolt 700 of the upper shaft 300 extends to the interior of the fuselage 100 and is fixedly connected to the lower shaft 400.

[0035] Furthermore, the upper rotating shaft 300 and the lower rotating shaft 400 can be fixed by means of snap connection, threaded connection or welding.

[0036] like Figure 2 As shown, a mounting groove 900 is provided on the fuselage 100, and the upper end cover is arranged inside the mounting groove 900. A positioning column 110 is arranged inside the mounting groove 900, and a corresponding mounting hole is provided on the upper end cover, and the mounting hole cooperates with the positioning column 110 for connecting the upper end cover with the fuselage 100.

[0037] Specifically, the mounting groove 900 is arranged along the longitudinal direction of the fuselage 100, and the positioning column 110 is arranged in the middle of the mounting groove 900. The mounting groove 900 and the positioning column 110 cooperate with the upper block cover 500 to fix the upper block cover 500 on the fuselage 100 to prevent the upper block cover 500 from moving.

[0038] like Figure 3 As shown, a limiting column is further provided at the end of the upper baffle, and a first limiting groove 113 is provided at the end of the limiting column. The first limiting groove 113 is used to fix the end of the torsion spring 800 .

[0039] Specifically, a through hole is further provided at the end of the mounting groove 900 , and a limiting column is provided at the end of the upper blocking cover 500 . The limiting column passes through the through hole and extends to the interior of the fuselage 100 .

[0040] like Figure 1 and Figure 4 As shown, a first connecting hole 111 is also provided on the upper rotating shaft 300, and a second connecting hole 112 corresponding to the first connecting hole 111 is provided on the wing 200. Indexing pins 120 are installed inside the first connecting hole 111 and the second connecting hole 112, and the indexing pins 120 are used to fix the connection between the wing 200 and the upper rotating shaft 300.

[0041] Furthermore, the indexing pin 120 adopts an existing device, such as the KPY self-locking indexing pin 120 produced by Fanyi (Guangdong) Industrial Technology Co., Ltd.

[0042] Specifically, the indexing pin 120 passes through the first connecting hole 111 and the second connecting hole 112 to fix the wing 200 and the upper rotating shaft 300 .

[0043] When the upper rotating shaft 300 and the wing 200 rotate, the first connecting hole 111 and the second connecting hole 112 are aligned with the mounting holes on the upper baffle, and the lower end of the indexing pin 120 is popped out under the action of the spring force, so that the lower end of the indexing pin 120 extends to the inside of the mounting hole, which is used to fix the upper rotating shaft 300, the wing 200 and the fuselage 100.

[0044] A connecting plate 114 is further provided on the lower rotating shaft 400 . A second limiting groove 115 is provided at the end of the connecting plate 114 . The second limiting groove 115 is used to fix the other end of the torsion spring 800 .

[0045] Specifically, Figure 4As shown, one end of the torsion spring 800 is fixed to the lower rotating shaft 400, and the other end of the torsion spring 800 is fixed to the upper baffle, which is fixedly connected to the fuselage 100. When the wing 200 is folded, the wing 200 remains parallel to the lateral direction of the fuselage 100; at this time, the torsion spring 800 of the folding mechanism is compressed, and when the wing 200 needs to be unfolded, the wing 200 is unfolded by the reaction force of the torsion spring 800.

[0046] like Figure 3 As shown, a first mounting cavity is provided in the middle of the upper baffle, a first bearing 116 is provided inside the first mounting cavity, and the first bearing 116 is sleeved on the outside of the connecting bolt 700. A second mounting cavity is provided in the middle of the lower baffle, a rotating shaft is provided below the lower rotating shaft 400, and the rotating shaft is provided inside the second mounting cavity for the rotational connection between the lower rotating shaft 400 and the lower baffle. A second rotating shaft 117 is also provided inside the second mounting cavity, and the second rotating shaft 117 is sleeved on the outside of the rotating shaft.

[0047] Specifically, by arranging bearings inside the two mounting cavities, the rotation between the connecting bolt 700 and the upper baffle plate and the rotation between the rotating shaft and the lower baffle plate are smoother, thereby reducing friction.

[0048] like Figure 2 As shown, a suction block 118 is provided at one end of the fuselage wing 200 (the suction block 118 is made of a metal material that can be adsorbed by a de-energized electromagnet 119, such as iron), and a de-energized electromagnet 119 is provided on the fuselage 100. The electromagnet 119 cooperates with the suction block 118 to fix the wing 200 and the fuselage 100.

[0049] Specifically, by setting a de-energized electromagnet 119 on the fuselage 100 and setting a suction block 118 on the wing 200, when the wing 200 is in an unfolded state, the wing 200 and the fuselage 100 are connected to the suction block 118 through the electromagnet 119 without power.

[0050] Furthermore, since the wing 200 is long and inconvenient to manufacture directly, the wing 200 is manufactured by splicing. The wing 200 includes a connecting rod, a connecting section, and two sections of the wing 200 body. The two sections of the wing 200 body are respectively arranged on both sides of the connecting section. The connecting section and the two sections of the wing 200 body are connected by a connecting rod, so that the wing 200 remains fixed.

[0051] Furthermore, the second connecting hole 112 is provided on the connecting section, and the wing 200 is fixedly connected to the upper rotating shaft 300 via the connecting section.

[0052] Furthermore, it is well known to those skilled in the art that a UAV should include a nose and a tail. In the present invention, only the fuselage 100, the wings 200 and the folding structure need to be displayed, so the nose and the tail are not drawn in the accompanying drawings.

[0053] The working principle of the utility model is as follows: when in use, firstly, the electromagnet is energized to make the electromagnet 119 lose its magnetism, and then the wing 200 is disconnected from the fuselage 100; the wing 200 starts to rotate under the reaction force of the torsion spring 800.

[0054] The upper rotating shaft 300 is driven to rotate by the lower rotating shaft 400, thereby driving the wing 200 to rotate 90°. After the wing 200 rotates 90°, the first connecting hole 111 and the second connecting hole 112 provided on the upper rotating shaft 300 and the wing 200 are aligned with the mounting hole on the upper end cover, and the lower end of the indexing pin 120 is ejected under the action of the spring force, so that the lower end of the indexing pin 120 extends to the inside of the mounting hole, which is used to fix the upper rotating shaft 300, the wing 200 and the fuselage 100.

[0055] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0056] Finally, it should be noted that the above description is only a preferred embodiment of the utility model and is not intended to limit the utility model. Although the utility model is described in detail with reference to the above embodiments, those skilled in the art can still modify the technical solutions recorded in the above embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. A long straight wing rotating and folding mechanism suitable for a small cruise UAV, characterized by: The invention comprises a fuselage (100), on which a wing (200) and a folding mechanism are arranged; the wing (200) is connected to the fuselage (100) via the folding structure; wherein the wing (200) is fixedly connected to the folding mechanism; The folding mechanism comprises an upper rotating shaft (300), a lower rotating shaft (400), an upper blocking cover (500) and a lower blocking cover (600); wherein the upper blocking cover (500) is fixedly arranged on the fuselage (100), the upper rotating shaft (300) is arranged above the upper blocking cover (500), a connecting bolt (700) is arranged in the middle of the upper rotating shaft (300), and the connecting bolt (700) passes through the upper blocking cover (500) and is fixedly connected to the lower rotating shaft (400); the upper rotating shaft (300) is also fixedly connected to the wing (200); The lower cover (600) is arranged on the body (100), the lower rotating shaft (400) is rotatably connected to the lower cover (600), a torsion spring (800) is sleeved on the outer side of the rotating shaft, one end of the torsion spring (800) is fixedly connected to the lower rotating shaft (400), and the other end of the torsion spring (800) is fixedly connected to the upper cover (500).

2. The long straight wing wing surface rotation and folding mechanism suitable for a small cruise UAV according to claim 1 is characterized in that: A mounting groove (900) is provided on the body (100), and the upper end cover is arranged inside the mounting groove (900).

3. The long straight wing wing surface rotation and folding mechanism suitable for a small cruise UAV according to claim 2 is characterized in that: A positioning column (110) is arranged inside the installation groove (900), and a corresponding installation hole is arranged on the upper end cover, and the installation hole cooperates with the positioning column (110) to connect the upper end cover with the fuselage (100).

4. The long straight wing wing surface rotation and folding mechanism suitable for a small cruise UAV according to claim 3 is characterized by: The upper rotating shaft (300) is also provided with a first connecting hole (111), and the wing (200) is provided with a second connecting hole (112) corresponding to the first connecting hole (111). Indexing pins (120) are installed inside the first connecting hole (111) and the second connecting hole (112), and the indexing pins (120) are used to fix the connection between the wing (200) and the upper rotating shaft (300).

5. The long straight wing wing surface rotation and folding mechanism suitable for a small cruise UAV according to claim 1 is characterized in that: A limiting column is also provided at the end of the upper baffle plate, and a first limiting groove (113) is provided at the end of the limiting column. The first limiting groove (113) is used to fix the end of the torsion spring (800).

6. The long straight wing wing surface rotation and folding mechanism suitable for a small cruise UAV according to claim 1 is characterized in that: A connecting plate (114) is also provided on the lower rotating shaft (400), and a second limiting groove (115) is provided at the end of the connecting plate (114). The second limiting groove (115) is used to fix the other end of the torsion spring (800).

7. The long straight wing wing surface rotation and folding mechanism suitable for a small cruise UAV according to claim 1 is characterized in that: A first installation cavity is arranged in the middle of the upper baffle, a first bearing (116) is arranged inside the first installation cavity, and the first bearing (116) is sleeved on the outside of the connecting bolt (700).

8. The long straight wing wing surface rotation and folding mechanism suitable for a small cruise UAV according to claim 1 is characterized in that: A second installation cavity is arranged in the middle of the lower baffle, and a rotating shaft is arranged below the lower rotating shaft (400). The rotating shaft is arranged inside the second installation cavity and is used for the rotational connection between the lower rotating shaft (400) and the lower baffle.

9. The long straight wing wing surface rotation and folding mechanism suitable for a small cruise UAV according to claim 8, characterized in that: A second rotating shaft (117) is also arranged inside the second installation cavity, and the second rotating shaft (117) is sleeved on the outside of the rotating shaft.

10. The long straight wing wing surface rotation and folding mechanism suitable for a small cruise UAV according to claim 1, characterized in that: A suction block (118) is arranged at one end of the wing (200), and a de-energized electromagnet (119) is arranged on the fuselage (100). The de-energized electromagnet (119) cooperates with the suction block (118) to fix the wing (200) and the fuselage (100).

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