Unmanned aerial vehicle with wings capable of continuously overturning in two directions

Abstract

The utility model relates to the technical field of unmanned driving, and discloses an unmanned aerial vehicle with wings capable of continuously overturning along two directions, which comprises a fuselage, two wings, two hinge components and an unfolding and folding driving component. The two hinge parts are in one-to-one correspondence with the two wings respectively; the hinge component comprises a first connecting assembly, a second connecting assembly and a hinge shaft. The first connecting assemblies are installed on the fuselage, the second connecting assemblies are installed on the wings, the hinge shafts are installed on the first connecting assemblies and rotationally matched with the second connecting assemblies, and the hinge shafts are obliquely arranged on one side of the fuselage; the unfolding and folding driving part is mounted on the fuselage; the driving ends of the unfolding and folding driving parts are hinged to the wings and are used for driving the wings to rotate around hinge shafts, so that the wings are switched between an unfolding state and a folding state. The wings are driven by the unfolding and folding driving parts to rotate around the hinge shafts, so that the wings are switched between the unfolding state and the folding state, and the problem that the wings of the unmanned aerial vehicle in the prior art cannot be overturned around the X axis and the Y axis at the same time is solved.

Description

Technical Field

[0001] This utility model relates to the field of unmanned driving technology, and in particular to a drone with wings that can continuously rotate in two directions. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft controlled by radio remote control equipment and their own program control devices, or operated autonomously by an onboard computer, either completely or intermittently.

[0003] For drones with fixed wings and fuselages, there is a large space requirement and high takeoff and landing drag, requiring more power to overcome the drag, which affects flight speed and endurance. For drones with partially or fully rotatable (foldable) wings, current wings can typically only rotate 90° around the X-axis or only around the Y-axis. Current drones cannot rotate around both the X-axis and Y-axis simultaneously.

[0004] Therefore, how to enable the wings of a drone to rotate simultaneously around the X and Y axes is a problem that the industry urgently needs to solve. Utility Model Content

[0005] This invention provides a drone with wings that can continuously rotate in two directions, in order to solve the problem that the wings of existing drones cannot rotate around the X-axis and Y-axis simultaneously.

[0006] This utility model provides a drone with wings that continuously rotate in two directions, comprising:

[0007] body;

[0008] Two wings are symmetrically arranged on the left and right sides of the fuselage, respectively;

[0009] Two hinge components correspond one-to-one with the two wings respectively; each hinge component includes a first connecting component, a second connecting component, and a hinge shaft; the first connecting component is mounted on the fuselage, the second connecting component is mounted on the wing, and the hinge shaft is mounted on the first connecting component and rotatably engages with the second connecting component; the hinge shaft is inclinedly arranged on one side of the fuselage.

[0010] An extension and retraction drive component is installed on the fuselage; the drive end of the extension and retraction drive component is hinged to the wing and is used to drive the wing to rotate around the hinge axis, so that the wing switches between the extended state and the retracted state.

[0011] In the deployed state, the lower surfaces of the two wings face the same direction as the bottom of the fuselage, and the ends of the wings away from the fuselage extend along the left-right direction of the fuselage.

[0012] In the retracted state, the lower sides of the two wings face the left and right sides of the fuselage respectively, and the ends of the wings away from the fuselage extend along the front-rear direction of the fuselage.

[0013] According to the UAV with wings that continuously rotate in two directions provided by this utility model, the first connecting component includes:

[0014] The first mounting component is connected to the fuselage;

[0015] A transition connector is installed on the first mounting member and forms a first included angle α with the first mounting member;

[0016] The second mounting member has one end mounted on the end of the transition connector away from the first mounting member, and the other end extending in a direction away from the transition connector, forming a second included angle β with the transition connector.

[0017] According to the UAV with wings that continuously rotate in two directions provided by this utility model, the second connecting component includes:

[0018] The third mounting component is connected to the wing;

[0019] A fourth mounting component is installed at the end of the third mounting component near the first mounting component, and a third included angle γ is formed between the fourth mounting component and the third mounting component.

[0020] According to the present invention, a drone with wings that continuously rotate in two directions is provided, wherein the first included angle α is an obtuse angle, and / or the second included angle β is not less than 90 degrees.

[0021] According to the present invention, a drone with wings that continuously rotate in two directions is provided, wherein the first included angle α and the third included angle γ are complementary angles.

[0022] According to the present invention, a drone with wings that continuously rotate in two directions is provided. A splicing part is formed at one end of the fuselage facing the wing, and a first connecting component is installed at the end of the splicing part away from the fuselage. Along the length direction of the wing, a first groove is formed at one end of the wing facing the fuselage, and a second connecting component is located at the bottom of the first groove.

[0023] In the unfolded state, the splicing part is located in the first groove;

[0024] In the folded state, the splicing part separates from the first groove.

[0025] According to the UAV with wings that continuously rotate in two directions provided by this utility model, the deployment and retraction drive component includes:

[0026] Two transmission components correspond one-to-one with the two wings; the two transmission components are respectively arranged on the left and right sides of the fuselage; the front end of the transmission component is hinged to the wing.

[0027] A drive assembly is mounted on the fuselage; the drive assembly is hinged to the rear ends of the two transmission assemblies, and is used to drive the transmission assemblies to move along the front-rear direction of the fuselage, so that the wing rotates about the hinge axis.

[0028] According to the present invention, a drone with wings that continuously rotate in two directions is provided, wherein an articulated ball is installed on the wing, and a hemispherical second groove is formed at the front end of the transmission component, and the articulated ball rotates in conjunction with the second groove.

[0029] The unmanned aerial vehicle (UAV) with wings that continuously rotate in two directions, as provided by this utility model, further includes:

[0030] A rotor drive component is mounted on the wing and is used to drive the rotor to rotate; in the retracted state, the end of the rotor drive component away from the rotor is used to contact the ground.

[0031] According to the UAV with wings that continuously rotate in two directions provided by this utility model, the rotor drive component includes:

[0032] A rotor drive assembly is mounted on the lower side of the wing; the front end of the rotor drive assembly is used to connect with the rotor to drive the rotor to rotate.

[0033] A support assembly is installed on the rotor drive assembly; in the retracted state, the end of the support assembly away from the rotor is used to contact the ground.

[0034] This utility model provides a drone with wings that can continuously rotate in two directions. By setting up a hinge component and an extension / retraction drive component, the hinge component includes a first connecting component, a second connecting component, and a hinge shaft. The first connecting component is installed on the fuselage, the second connecting component is installed on the wing, and the hinge shaft is installed on the first connecting component and rotates with the second connecting component. The hinge shaft is inclinedly arranged on one side of the fuselage. The drive end of the extension / retraction drive component is hinged to the wing, and the wing can be driven to rotate around the hinge shaft through the extension / retraction drive component, thereby switching the wing between the extended and retracted states. At the same time, it realizes the purpose of the wing rotating around the X-axis and the Y-axis, solving the problem that the wings of existing drones cannot rotate around the X-axis and the Y-axis simultaneously. Attached Figure Description

[0035] To more clearly illustrate the technical solutions in this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0036] Figure 1 This is a three-dimensional structural diagram of the wings of a UAV with wings that continuously rotate in two directions, provided by this utility model, in the unfolded state.

[0037] Figure 2 yes Figure 1 The diagram shown is a top-down view of a drone with wings that continuously rotate in two directions.

[0038] Figure 3 yes Figure 1 The diagram shown is a structural schematic of a drone with wings that continuously rotate in two directions, as viewed from the main perspective.

[0039] Figure 4 yes Figure 1 The diagram shown is a structural schematic of a drone with wings that continuously rotate in two directions, viewed from the right.

[0040] Figure 5 This is a three-dimensional structural diagram of the wing of a UAV with wings that continuously rotate in two directions, provided by this utility model, in the folded state.

[0041] Figure 6 yes Figure 5 The diagram shown is a top-down view of a drone with wings that continuously rotate in two directions.

[0042] Figure 7 yes Figure 5 The diagram shown is a structural schematic of a drone with wings that continuously rotate in two directions, as viewed from the main perspective.

[0043] Figure 8 yes Figure 5 The diagram shown is a structural schematic of a drone with wings that continuously rotate in two directions, viewed from the right.

[0044] Figure 9 yes Figure 1 A magnified structural diagram of point A in the middle.

[0045] Figure 10 yes Figure 7 A magnified structural diagram at point B in the middle.

[0046] Figure label:

[0047] 100. Fuselage; 110. Assembly section;

[0048] 200. Wing; 210. First groove;

[0049] 300, Hinged component; 310, First connecting assembly; 320, Second connecting assembly; 330, Hinged shaft; 311, First mounting member; 312, Second mounting member; 313, Transition connector; 321, Third mounting member; 322, Fourth mounting member;

[0050] 400. Extension / retraction drive component; 410. Transmission assembly; 420. Drive assembly; 421. Mounting base; 422. Lead screw; 423. Slider; 424. Drive component;

[0051] 500. Rotor drive component; 510. Rotor drive assembly; 520. Support assembly;

[0052] 600, rotor. Detailed Implementation

[0053] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0054] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" or "linked" should be interpreted broadly. For example, it can refer to a fixed connection, a detachable connection, or an integral connection; it can refer to a mechanical connection or an electrical connection; it can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this utility model based on the specific circumstances.

[0055] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0056] Before providing a detailed description of the UAV of this utility model, which has wings that continuously rotate in two directions, the following definitions are made.

[0057] The X-axis points in the left-right direction of the fuselage, and the Y-axis points in the up-down direction of the fuselage.

[0058] The following is combined Figures 1 to 10 This invention provides a detailed description of the UAV with wings that continuously rotate in two directions.

[0059] like Figures 1 to 10 As shown, a specific embodiment of this utility model provides a drone with wings that can continuously rotate in two directions. This drone with wings that can continuously rotate in two directions includes a fuselage 100, two wings 200, two hinge components 300, and a retraction / extension drive component 400. The two wings 200 are symmetrically arranged on the left and right sides of the fuselage 100. The two hinge components 300 correspond one-to-one with the two wings 200; each hinge component 300 includes a first connecting assembly 310, a second connecting assembly 320, and a hinge shaft 330; the first connecting assembly 310 is mounted on the fuselage 100, the second connecting assembly 320 is mounted on the wing 200, and the hinge shaft 330 is mounted on the first connecting assembly 310 and rotatably engages with the second connecting assembly 320, with the hinge shaft 330 inclinedly arranged on one side of the fuselage 100; the retraction / extension drive component 400 is mounted on the fuselage 100; the retraction / extension drive component... The drive end of 400 is hinged to the wing 200 and is used to drive the wing 200 to rotate around the hinge axis 330, so that the wing 200 can switch between the deployed state and the retracted state. In the deployed state, the lower sides of the two wings 200 are aligned with the bottom of the fuselage 100, and the ends of the wings 200 away from the fuselage 100 extend along the left and right directions of the fuselage 100. In the retracted state, the lower sides of the two wings 200 are respectively aligned with the left and right sides of the fuselage 100, and the ends of the wings 200 away from the fuselage 100 extend along the front and rear directions of the fuselage 100.

[0060] In this embodiment, by setting a hinge component 300 and a retraction drive component 400, the hinge component 300 includes a first connecting component 310, a second connecting component 320, and a hinge shaft 330. The first connecting component 310 is installed on the fuselage 100, the second connecting component 320 is installed on the wing 200, and the hinge shaft 330 is installed on the first connecting component 310 and rotates with the second connecting component 320. The hinge shaft 330 is inclinedly arranged on one side of the fuselage 100. The drive end of the retraction drive component 400 is hinged to the wing 200, and the wing 200 can be driven to rotate around the hinge shaft 330 through the retraction drive component 400, thereby switching the wing 200 between the deployed and retracted states. At the same time, the wing 200 can be rotated around the X-axis and the Y-axis, solving the problem that the wing 200 of the prior art UAV cannot rotate around the X-axis and the Y-axis at the same time.

[0061] like Figure 9 and Figure 10 As shown, the first connecting component 310 further includes a first mounting member 311, a transition connector 313, and a second mounting member 312; the first mounting member 311 is connected to the fuselage 100; the transition connector 313 is mounted on the first mounting member 311 and forms a first angle α with the first mounting member 311; one end of the second mounting member 312 is mounted on the end of the transition connector 313 away from the first mounting member 311, and the other end extends in a direction away from the transition connector 313 and forms a second angle β with the transition connector 313. Specifically, the first mounting member 311 is mounted on the fuselage 100. The lower end of the transition connector 313 is connected to the first mounting member 311, and the upper end of the transition connector 313 extends upward at an angle away from the first mounting member 311. The left side of the transition connector 313 forms a first angle α with the upper side of the first mounting member 311. The lower end of the second mounting member 312 is connected to the upper end of the transition connector 313, and the upper end of the second mounting member 312 extends away from the transition connector 313. The front side of the second mounting member 312 is coplanar with the front side of the transition connector 313, and the right side of the second mounting member 312 forms a second angle β with the right side of the transition connector 313. This design ensures that the wing 200 can rotate more accurately around the X-axis and Y-axis when rotating around the hinge axis 330, ensuring smooth switching between the deployed and retracted states of the wing 200.

[0062] Furthermore, the first mounting component 311 is made of sheet metal, the transition connector 313 is made of sheet metal, and the second mounting component 312 is made of sheet metal, resulting in a simple structure that is easy to process.

[0063] Preferably, the second mounting member 312 has an opening in the mounting space, and the fourth mounting member 322 is located in the mounting space.

[0064] Specifically, the first included angle α is an obtuse angle, and / or the second included angle β is not less than 90 degrees, to ensure that the wing 200 can more accurately rotate around the X-axis and around the Y-axis to the target angle, for example, to ensure that the wing 200 can more accurately rotate around the X-axis and around the Y-axis by 90 degrees.

[0065] Preferably, the first included angle α is in the range of 120 degrees to 130 degrees. In other words, the first included angle α can be 120 degrees, 130 degrees, or any degree between 120 degrees and 130 degrees.

[0066] Preferably, the second included angle β is in the range of 90 degrees to 135 degrees. In other words, the second included angle β can be 90 degrees, 135 degrees, or any degree between 90 degrees and 135 degrees.

[0067] Furthermore, the second connection assembly 320 includes a third mounting member 321 and a fourth mounting member 322; the third mounting member 321 is connected to the wing 200; the fourth mounting member 322 is mounted on the end of the third mounting member 321 near the first mounting member 311, and a third angle γ is formed between the fourth mounting member 322 and the third mounting member 321.

[0068] Specifically, the first included angle α and the third included angle γ are complementary angles. This design ensures that, in the deployed state, the upper surface of the wing 200 and the upper surface of the fuselage 100 transition horizontally at the connection point. In other words, the upper surface of the wing 200 and the upper surface of the fuselage 100 form a 180-degree angle at the connection point.

[0069] Preferably, the angle range of the third included angle γ is 50 degrees to 60 degrees. In other words, the angle of the third included angle γ can be 50 degrees, 60 degrees, or any degree between 50 degrees and 60 degrees.

[0070] Specifically, the third mounting component 321 is made of sheet metal, and the fourth mounting component 322 is made of sheet metal. The structure is simple and easy to process.

[0071] like Figure 5As shown, in some embodiments, a splicing portion 110 is formed at the end of the fuselage 100 facing the wing 200, and a first connecting component 310 is installed at the end of the splicing portion 110 away from the fuselage 100; along the length direction of the wing 200, a first groove 210 is formed at the end of the wing 200 facing the fuselage 100, and a second connecting component 320 is located at the bottom of the first groove 210; in the deployed state, the splicing portion 110 is located in the first groove 210; in the retracted state, the splicing portion 110 is separated from the first groove 210. By setting the splicing portion 110 and the first groove 210, and through the tight fit between the splicing portion 110 and the first groove 210, stress during flight can be effectively dispersed, enhancing the overall stability of the aircraft structure. This design also helps to reduce structural loosening or damage caused by vibration or airflow. In the deployed state, the tight fit between the splicing portion 110 and the first groove 210 helps to reduce aerodynamic drag and improve the flight efficiency of the aircraft. At the same time, this design also helps maintain the aircraft's streamlined shape, further reducing air resistance.

[0072] like Figure 5 As shown, further, a fifth included angle δ is formed between the first side of the splicing part 110 away from the fuselage 100 and the front side of the splicing part 110, and a sixth included angle ε is formed between the first side and the rear side of the splicing part 110; the fifth included angle δ is an acute angle, and the fifth included angle δ and the sixth included angle ε are complementary angles. Correspondingly, the bottom side of the first groove 210 is parallel to the first side of the splicing part 110; the fourth mounting member 322 is located between the bottom side of the first groove 210 and the first side of the splicing part 110.

[0073] In some embodiments, the retraction drive component 400 includes two transmission components 410 and a drive component 420; the two transmission components 410 correspond one-to-one with the two wings 200; the two transmission components 410 are respectively arranged on the left and right sides of the fuselage 100; the front end of the transmission component 410 is hinged to the wing 200; the drive component 420 is mounted on the fuselage 100; the drive component 420 is hinged to the rear end of the two transmission components 410, for driving the transmission components 410 to move along the front-rear direction of the fuselage 100, causing the wing 200 to rotate around the hinge axis 330. By centrally mounting the drive component 420 on the fuselage 100, the additional equipment on the wing 200 is reduced, making the structure of the wing 200 simpler and more efficient. The hinged design of the transmission component 410 and the wing 200, and the rear end hinge of the drive component 420 and the transmission component 410, make the entire retraction mechanism more coordinated and smooth during operation. Because the drive assembly 420 is hinged to the wing 200 via the transmission assembly 410, it can provide a stable driving force during deployment and retraction, ensuring the wing 200 remains stable when deployed or retracted. This design also helps reduce vibration and sway caused by the movement of the wing 200, improving the overall stability of the aircraft. The drive assembly 420 can directly drive the transmission assembly 410 to move along the fore-and-aft direction of the fuselage 100, thereby quickly and accurately deploying or retracting the wing 200. Compared to other complex transmission methods, this design has a significant advantage in deployment and retraction efficiency. This design can adapt to wings 200 of different sizes and shapes; only the parameters of the transmission assembly 410 and the drive assembly 420 need to be adjusted.

[0074] Furthermore, the front end of the transmission assembly 410 is spherically hinged to the upper side of the wing 200 near the fuselage. Specifically, a hinge ball is installed on the wing 200, and a hemispherical second groove is formed at the front end of the transmission assembly 410, with the hinge shaft 330 rotatably engaging with the second groove. This engagement design of the hinge ball and the hemispherical second groove ensures a more stable connection between the wing 200 and the transmission assembly 410. This design effectively prevents the connection from loosening or detaching due to vibration or airflow, improving the aircraft's flight safety. The rotatable engagement of the hinge ball and the second groove allows the wing 200 to rotate freely within a certain range, meeting the requirement for the wing 200 to simultaneously rotate around the X and Y axes.

[0075] Furthermore, the rear end of the transmission assembly 410 is spherically hinged to the drive end of the drive assembly 420. Specifically, the drive end of the drive assembly 420 is also equipped with a hinge ball, and the rear end of the transmission assembly 410 also has a hemispherical second groove.

[0076] Specifically, the transmission assembly 410 includes a connecting rod, with connecting portions formed at the front and rear ends of the connecting rod; a hemispherical second groove is formed in the connecting portion; a first articulated ball is installed on the upper side of the wing 200 near the fuselage 100, and a second articulated ball is installed at the driving end of the drive assembly 420. The two articulated balls are arranged along the front and rear direction of the fuselage 100, and the two articulated balls correspond one-to-one with the two second grooves and are rotatably engaged.

[0077] Furthermore, the drive assembly 420 includes a linear drive structure for reciprocating along the front-rear direction of the fuselage 100, thereby driving the transmission assembly 410 to move along the front-rear direction of the fuselage 100.

[0078] Furthermore, the drive assembly 420 includes two linear drive structures, each corresponding to one of the two transmission assemblies 410. The two linear drive structures are symmetrically mounted on the upper side of the fuselage 100.

[0079] like Figure 1 and Figure 6As shown, specifically, the linear drive structure includes two mounting bases 421, a lead screw 422, a slider 423, and a drive component 424. The two mounting bases 421 are mounted on the upper side of the machine body 100 along the front-rear direction. The two ends of the lead screw 422 are rotatably engaged with the two mounting bases 421 respectively. The slider 423 is threadedly engaged with the lead screw 422, and the slider 423 is spherically hinged to the rear end of the transmission assembly 410. The drive component 424 is connected to the lead screw 422 and is used to drive the lead screw 422 to rotate, causing the slider 423 to drive the transmission assembly 410 to move along the front-rear direction of the machine body 100. When the drive component 424 drives the lead screw 422 to rotate, the slider 423 moves linearly along the axial direction of the lead screw 422, and the slider 423 drives the transmission assembly 410 to move along the front-rear direction of the machine body 100. Two mounting bases 421 are installed on the upper side of the fuselage 100 along the front-rear direction. The two ends of the lead screw 422 are rotatably engaged with the mounting bases 421. This layout makes the entire drive structure compact and space-saving. The slider 423 is threadedly engaged with the lead screw 422. Driven by the drive component 424, the slider 423 can move linearly along the lead screw 422, driving the transmission assembly 410 to achieve the extension and retraction of the wing 200, resulting in high transmission efficiency. The threaded engagement between the lead screw 422 and the slider 423 has high precision, enabling precise control of the slider 423's position. This helps ensure accurate positioning of the wing 200 during extension or retraction, improving aircraft stability and safety. The lead screw drive structure can withstand large loads and is suitable for driving the extension and retraction of large wings 200. This design allows the aircraft to maintain stable flight performance even in adverse weather or complex flight conditions. The components in the linear drive structure are relatively independent, making them easy to disassemble and install. This helps reduce maintenance costs and improve aircraft availability and reliability. This drive structure can adapt to wings 200 of different sizes and shapes, requiring only adjustments to the parameters of the lead screw 422, slider 423, and transmission assembly 410. This design makes the drive structure widely applicable in different types of aircraft.

[0080] Specifically, the two lead screws 422 are arranged symmetrically with respect to the central axis of the fuselage 100, which helps to balance the weight of the aircraft and ensure flight stability.

[0081] like Figure 2 As shown, specifically, the central axis of the lead screw 422 and the central axis of the machine body 100 form a fourth included angle θ, which ranges from 0 degrees to 5 degrees. In other words, the angle of the fourth included angle θ can be 0 degrees, 5 degrees, or any degree within the range of 0 to 5 degrees.

[0082] Specifically, the travel range of the lead screw 422 is 60mm to 64mm. In other words, the sliding block 423 moves 0mm to Lmm on the lead screw 422, where L ranges from 60mm to 64mm.

[0083] Furthermore, the drive component 424 includes a first drive motor and a gear set; the gear set includes a driving gear and a driven gear that mesh with each other; the driving gear is mounted on the drive shaft of the first drive motor, and the driven gear is mounted on the front or rear end of the lead screw 422. The first drive motor drives the driving gear to rotate, and the driving gear drives the lead screw 422 to rotate through the driven gear.

[0084] In some embodiments, the UAV with wings that can continuously rotate in two directions further includes a rotor drive component 500; the rotor drive component 500 is mounted on the wing 200 and is used to drive the rotor 600 to rotate; in the retracted state, the end of the rotor drive component 500 away from the rotor 600 is used to contact the ground. With this design, the end of the rotor drive component 500 away from the rotor 600 can directly serve as landing gear, thereby eliminating the need for landing gear and reducing the operating cost of the UAV.

[0085] Furthermore, the rotor drive component 500 includes a rotor drive assembly 510 and a support assembly 520; the rotor drive assembly 510 is mounted on the lower side of the wing 200; the front end of the rotor drive assembly 510 is used to connect with the rotor 600 to drive the rotor 600 to rotate; the support assembly 520 is mounted on the rotor drive assembly 510; in the retracted state, the end of the support assembly 520 away from the rotor 600 is used to contact the ground. By setting the support assembly 520, the rotor drive assembly 510 can be lengthened without changing its structure, allowing the support assembly 520 to function as the landing gear of the UAV.

[0086] Furthermore, the rotor drive assembly 510 includes a second drive motor.

[0087] Specifically, the support assembly 520 includes a support shell with a circular cross-section. The front end of the support shell is connected to the rotor drive assembly 510. Along the direction from the front end to the rear end of the fuselage 100, the diameter of the cross-section of the support shell gradually decreases, which can reduce flight drag.

[0088] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A drone with wings that continuously rotate in two directions, characterized in that, include: fuselage (100); Two wings (200) are symmetrically arranged on the left and right sides of the fuselage (100); Two hinge components (300) correspond one-to-one with the two wings (200); each hinge component (300) includes a first connecting assembly (310), a second connecting assembly (320), and a hinge shaft (330); the first connecting assembly (310) is mounted on the fuselage (100), the second connecting assembly (320) is mounted on the wing (200), and the hinge shaft (330) is mounted on the first connecting assembly (310) and rotatably engages with the second connecting assembly (320); the hinge shaft (330) is obliquely arranged on one side of the fuselage (100). An extension and retraction drive component (400) is installed on the fuselage (100); the drive end of the extension and retraction drive component (400) is hinged to the wing (200) and is used to drive the wing (200) to rotate around the hinge axis (330) so that the wing (200) switches between the extended state and the retracted state. In the deployed state, the lower sides of the two wings (200) face the same direction as the bottom of the fuselage (100), and the end of the wing (200) away from the fuselage (100) extends along the left and right direction of the fuselage (100). In the retracted state, the lower sides of the two wings (200) face the left and right sides of the fuselage (100) respectively, and the end of the wing (200) away from the fuselage (100) extends along the front-rear direction of the fuselage (100).

2. The UAV with wings that continuously rotate in two directions according to claim 1, characterized in that, The first connection component (310) includes: The first mounting component (311) is connected to the fuselage (100); A transition connector (313) is installed on the first mounting member (311) and forms a first included angle α with the first mounting member (311); The second mounting member (312) has one end mounted on the end of the transition connector (313) away from the first mounting member (311), and the other end extends in a direction away from the transition connector (313) and forms a second included angle β with the transition connector (313).

3. The UAV with wings that continuously rotate in two directions according to claim 2, characterized in that, The second connection component (320) includes: The third mounting component (321) is connected to the wing (200); A fourth mounting member (322) is mounted on the end of the third mounting member (321) near the first mounting member (311), and a third included angle γ is formed between the fourth mounting member (322) and the third mounting member (321).

4. The UAV with wings that continuously rotate in two directions according to claim 3, characterized in that, The first included angle α is an obtuse angle, and / or the second included angle β is not less than 90 degrees.

5. The UAV with wings that continuously rotate in two directions according to claim 4, characterized in that, The first included angle α and the third included angle γ are complementary angles.

6. The UAV with wings that continuously rotate in two directions according to claim 1, characterized in that, The fuselage (100) has a splicing portion (110) at one end facing the wing (200), and the first connecting component (310) is installed at the end of the splicing portion (110) away from the fuselage (100); along the length direction of the wing (200), the wing (200) has a first groove (210) at one end facing the fuselage (100), and the second connecting component (320) is located at the bottom of the first groove (210); In the unfolded state, the splicing part (110) is located in the first groove (210). In the folded state, the splicing part (110) separates from the first groove (210).

7. The UAV with wings that continuously rotate in two directions according to claim 1, characterized in that, The deployment and retraction drive component (400) includes: Two transmission components (410) correspond one-to-one with the two wings (200); the two transmission components (410) are respectively arranged on the left and right sides of the fuselage (100); the front end of the transmission component (410) is hinged to the wing (200); A drive assembly (420) is mounted on the fuselage (100); the drive assembly (420) is hinged to the rear ends of the two transmission assemblies (410) for driving the transmission assemblies (410) to move along the front-rear direction of the fuselage (100) so that the wing (200) rotates about the hinge axis (330).

8. The UAV with wings that continuously rotate in two directions according to claim 7, characterized in that, A hinge ball is mounted on the wing (200), and a hemispherical second groove is formed at the front end of the transmission assembly (410), with the hinge ball rotating in conjunction with the second groove.

9. The unmanned aerial vehicle (UAV) with wings that continuously rotate in two directions according to any one of claims 1 to 8, characterized in that, Also includes: A rotor drive component (500) is mounted on the wing (200) and is used to drive the rotor (600) to rotate; In the retracted state, the end of the rotor drive component (500) away from the rotor (600) is used to contact the ground.

10. The UAV with wings that continuously rotate in two directions according to claim 9, characterized in that, The rotor drive component (500) includes: A rotor drive assembly (510) is mounted on the lower side of the wing (200); the front end of the rotor drive assembly (510) is used to connect with the rotor (600) to drive the rotor (600) to rotate. A support assembly (520) is installed on the rotor drive assembly (510); in the retracted state, the end of the support assembly (520) away from the rotor (600) is used to abut against the ground.

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