Aerial vehicle

Abstract

An aerial mobility vehicle includes a wing extending from a fuselage of the aerial mobility vehicle; a folding portion disposed at an edge portion of the wing, configured to extend from the wing to form a portion of the wing during unfolding of the folding portion, and configured to move to coincide with the wing to reduce an air resistance area of the wing in a vertical direction during folding of the folding portion; an actuator connected to the folding portion and configured to power the folding portion to unfold or fold to the wing; and a controller connected to the actuator and configured to control the actuator to fold the folding portion during vertical takeoff and landing of the fuselage, and configured to control the actuator to unfold the folding portion during cruising of the fuselage.

Description

Technical Field

[0001] This invention relates to an aerial maneuvering vehicle, and more particularly to a technique for folding the wings of an aerial maneuvering vehicle. Background Technology

[0002] Recently, aerial mobility tools (such as drones) have been actively developed and applied in multiple fields, and manned drones configured for carrying people have also been developed and entered the practical application stage.

[0003] Traditional aerial vehicles can take off and land vertically using rotors. After taking off vertically, they can cruise via fixed-wing aircraft, which can improve the fuel efficiency or electrical efficiency of the aerial vehicles.

[0004] However, a problem with traditional air-mobile vehicles is that during vertical takeoff or landing via rotors, the air resistance generated by the fixed wings increases the power required by the air-mobile vehicles.

[0005] The information disclosed in this background section is intended only to enhance the understanding of the general background of the invention and should not be construed as an admission or any implication that the information constitutes prior art known to those skilled in the art. Summary of the Invention

[0006] Various aspects of the present invention aim to provide an air maneuvering vehicle in which a folding portion, as part of a wing, folds and overlaps with the wing via an actuator during vertical takeoff or landing of the air maneuvering vehicle to reduce air resistance, and unfolds during cruise of the air maneuvering vehicle to improve the fuel efficiency or electrical efficiency of the air maneuvering vehicle.

[0007] In various aspects of the present invention, an air maneuvering vehicle is provided. The air maneuvering vehicle includes: a wing extending from the fuselage of the air maneuvering vehicle; a folding portion disposed at the edge of the wing, configured to extend from the wing to form part of the wing during folding to form the wing during folding and to move to coincide with the wing during folding, thereby reducing the air drag area of ​​the wing in the vertical direction; an actuator connected to the folding portion and configured to provide power to the folding portion to cause the folding portion to unfold or fold into the wing; and a controller connected to the actuator and configured to control the actuator to cause the folding portion to fold during vertical takeoff and landing of the fuselage, and configured to control the actuator to unfold the folding portion during cruise of the fuselage.

[0008] The wing and the folding section can be positioned to make surface contact with each other, and the aerial maneuver can include: an articulation section coupled to the lower part of the wing and the folding section and enabling the folding section to rotate relative to the wing, wherein an actuator can be configured to rotate the folding section about the articulation section, so that the folding section can be unfolded or folded.

[0009] The actuator may include: a drive unit located in the wing and driven by a controller to rotate the drive shaft of the drive unit; and a linkage configured such that a first end is connectable to the drive shaft of the drive unit and a second end is connectable to the folding portion to unfold or fold the folding portion in response to the drive unit.

[0010] The linkage may include: a first member connected at its first end to a drive shaft of a drive unit and configured to rotate by rotation of the drive shaft; and a second member rotatably connected at its first end to a second end of the first member and rotatably connected at its second end to a lower portion of a folding portion, wherein the folding portion may be configured to unfold or fold by rotation of the first linkage and displacement of the second linkage.

[0011] The wing may include a first limiting portion configured to limit the rotation angle of the first member during the unfolding or folding of the fold.

[0012] The wing may include a second limiting portion configured to limit the displacement of the second rod during the folding of the folding portion.

[0013] The aerial maneuvering vehicle may include: a first magnetic module, including a magnet located in the wing and a fixing part located in the folding part at a position corresponding to the magnet, wherein the first magnetic module may be configured to fix the wing and the folding part during the unfolding of the folding part and to separate the wing and the folding part from each other during the folding part folding when power is applied to the first magnetic module to change the direction of the magnetic circuit.

[0014] The controller can be connected to the first magnetic module and configured to control the first magnetic module to provide power to the magnet of the first magnetic module, so as to fix the fold to the wing during the unfolding of the fold.

[0015] The aerial maneuvering vehicle may include: a second magnetic module, comprising a magnet located in the wing and a fixing part located in the folding part at a position corresponding to the magnet, wherein the second magnetic module may be configured to separate the wing and the folding part from each other during the folding part unfolding when power is applied to the second magnetic module to change the direction of the magnetic circuit, and to fix the wing and the folding part during the folding part folding.

[0016] The controller can be connected to the second magnetic module and configured to control the second magnetic module so that the fold can be fixed to the wing during the folding process.

[0017] The controller can be configured to control the actuator to fold the folding section during the vertical takeoff of the air-mobile vehicle and to unfold the folding section during cruise after the vertical takeoff of the air-mobile vehicle.

[0018] The controller can be configured to control the actuator so that the landing is vertical with the folded part unfolded, and the folded part can be folded after vertical landing.

[0019] According to the present invention, the air maneuvering vehicle is configured such that the actuator is connected to the wing and the folding portion is operated to fold during vertical takeoff or landing of the air maneuvering vehicle. Therefore, air resistance generated during vertical takeoff or landing of the air maneuvering vehicle can be reduced and the fuel efficiency or electrical energy efficiency of the air maneuvering vehicle can be improved.

[0020] The air maneuvering vehicle is configured such that the folding section unfolds during cruise to expand the wings. Therefore, fuel efficiency or electrical efficiency during air maneuvering can be improved.

[0021] In aerial maneuvers, the folding section is securely held in place by a magnetic module during deployment or folding. This reduces the likelihood of damage due to collisions between the folding section and the wings during rotation.

[0022] The methods and apparatus of the present invention have other features and advantages, which will become apparent or are set forth in more detail in the accompanying drawings, which, together with the following detailed description, serve to explain certain principles of the invention. Attached Figure Description

[0023] Figure 1 This is a side view illustrating an aerial maneuvering vehicle according to various exemplary embodiments of the present invention;

[0024] Figure 2 This is a side view illustrating the operation of an aerial maneuvering vehicle according to an exemplary embodiment of the present invention;

[0025] Figure 3 This is a rear view illustrating the operation of an aerial maneuvering vehicle according to an exemplary embodiment of the present invention;

[0026] Figure 4 This is a side view illustrating the operation of the first and second magnetic modules of an aerial maneuvering vehicle according to an exemplary embodiment of the present invention;

[0027] Figure 5 and Figure 6 This is an enlarged view showing the second magnetic module.

[0028] It is understood that the accompanying drawings are not necessarily drawn to scale and present slightly simplified representations of various features illustrating the basic principles of the invention. Specific design features of the invention as included herein, including, for example, specific dimensions, orientations, positions, and shapes, will be determined in part by the particular intended application and environment of use.

[0029] In the accompanying drawings, reference numerals throughout the various figures refer to the same or equivalent parts of the invention. Detailed Implementation

[0030] Reference will now be made in detail to various embodiments of the invention, examples of which are shown in the accompanying drawings and described below. While the invention will be described in conjunction with exemplary embodiments thereof, it should be understood that this description is not intended to limit the invention to those exemplary embodiments. On the other hand, the invention is intended to cover not only the exemplary embodiments thereof, but also various alternatives, modifications, equivalents and other embodiments that may be included within the spirit and scope of the invention as defined in the appended claims.

[0031] The specific structural or functional descriptions of the embodiments of the invention set forth in the following description are provided exemplarily to illustrate exemplary embodiments of the invention. However, the invention may be implemented in various alternative forms and should not be construed as limited to the exemplary embodiments set forth herein.

[0032] Various modifications and changes can be made to exemplary embodiments of the present invention, and therefore specific embodiments of the present invention will be shown in the accompanying drawings and described in detail in the following description of exemplary embodiments of the present invention. However, it should be understood that providing exemplary embodiments of the present invention is solely for the purpose of fully disclosing the present invention and covers modifications, equivalents, or substitutions that fall within the scope and technical range of the present invention.

[0033] It should be understood that although the terms first and / or second, etc., may be used herein to describe various elements, these elements may not be limited by these terms. These terms are only used to distinguish one element from another. For example, the first element discussed below may be referred to as a second element that is not separate from the teachings of this invention. Similarly, the second element may also be referred to as the first element.

[0034] It can be understood that when a component is involved in being "coupled" or "connected" to another component, it can be directly coupled or connected to the other component or have an intermediate component in between. Conversely, it should be understood that when a component is involved in being "directly coupled" or "directly connected" to another component, there is no intermediate component. Other expressions explaining the relationship between components, such as "between," "directly between," "adjacent," or "directly adjacent," should be understood in the same way.

[0035] The techniques used herein are for the purpose of describing particular embodiments only and are not intended to be limiting. In this invention, the singular form is also intended to include the plural form, unless explicitly stated otherwise. It can be further understood that the terms "comprising" or "having," when used in the specification, detail the features, integers, steps, operations, elements, components, and / or combinations thereof specified in the description.

[0036] Unless otherwise specified, all terms used herein, including technical and scientific terms, have the same meaning as commonly understood by those skilled in the art. It can be further understood that the terms used herein are to be interpreted in the same manner as the content of this specification and related art, and that, unless explicitly defined herein, the terms are not to be interpreted in an idealized or overly formal sense.

[0037] Hereinafter, various embodiments of the invention will be described in detail, examples of which are shown in the accompanying drawings and described below. In the drawings, even when the same or similar elements are depicted in different drawings, they are indicated by the same reference numerals.

[0038] The controller 10 according to various exemplary embodiments of the present invention may be implemented via non-volatile memory and configured to store data of algorithms relating to the operation of various elements configured to control a vehicle or software commands for reproducing the algorithms, and the processor is configured to use data stored in the respective memory to perform operations described below. Here, the memory and processor may be implemented via separate chips. Alternatively, the memory and processor may be implemented via a single integrated chip. Here, the processor may be configured as at least one processor.

[0039] Figure 1 This is a side view illustrating an aerial maneuvering vehicle according to various exemplary embodiments of the present invention. Figure 2 This is a side view illustrating the operation of an aerial maneuvering vehicle according to an exemplary embodiment of the present invention.

[0040] Figure 3 This is a rear view illustrating the operation of an aerial maneuvering vehicle according to an exemplary embodiment of the present invention.

[0041] Figure 4 This is a side view illustrating the operation of the first magnetic module 500 and the second magnetic module 600 of an aerial maneuvering vehicle according to an exemplary embodiment of the present invention. Figure 5 and Figure 6 This is an enlarged view showing the second magnetic module.

[0042] refer to Figure 1 , Figure 2 , Figure 3 and Figure 4 This section will describe aerial maneuvers according to various exemplary embodiments of the present invention.

[0043] The air maneuvering vehicle configurations according to various exemplary embodiments of the present invention are designed for vertical takeoff and landing, and are intended to reduce air resistance during vertical takeoff and landing due to the fixed wings of the air maneuvering vehicle.

[0044] An airborne maneuvering vehicle according to various exemplary embodiments of the present invention may include: a wing 100 extending from the fuselage of the airborne maneuvering vehicle; a folding portion 200 disposed at the edge of the wing 100, configured to extend from the wing 100 to form part of the wing 100 during the deployment of the folding portion 200, and configured to move to overlap with the wing 100 during the folding of the folding portion 200, thereby reducing the air resistance area of ​​the wing 100 in the vertical direction; an actuator 300 configured to provide power to the folding portion 200 to cause the folding portion 200 to deploy or fold to the wing 100; and a controller 10 configured to control the actuator 300 to fold the folding portion 200 during vertical takeoff or landing of the fuselage, and configured to control the actuator 300 to deploy the folding portion 200 during cruise of the fuselage.

[0045] like Figure 1 , Figure 2 and Figure 3 As shown, in an air maneuvering vehicle, a wing 100 extends from the fuselage and is used during the flight of the air maneuvering vehicle, and a folding section 200 extends from the wing 100 and forms a fixed wing of the air maneuvering vehicle by combining the folding section with the wing 100 during the flight.

[0046] The fold 200 is movably coupled to the wing 100 and can move toward the wing 100 to overlap with the wing 100 in order to reduce the air resistance area in the vertical direction of the wing 100 during takeoff or landing of the air-maneuvering vehicle.

[0047] The actuator 300 provides power to the folding section 200, causing the folding section 200 to move toward the wing section 100. As a result, when the air vehicle takes off or lands, the area of ​​the folding section that generates air resistance in the vertical direction can be reduced.

[0048] When the folding section 200 is folded, the minimum power required for the air maneuvering vehicle during vertical takeoff and landing can be reduced. Furthermore, during the air maneuvering vehicle's cruise, the folding section 200 unfolds to increase the total area of ​​the wing section 100, thus reducing the power required for cruise.

[0049] The wing 100 and the folding portion 200 are positioned so that their surfaces are in contact with each other. An aerial maneuvering vehicle according to various exemplary embodiments of the invention includes a hinge 400 coupled to the lower portions of the wing 100 and the folding portion 200 to enable the folding portion 200 to rotate. An actuator 300 can rotate the folding portion 200 about the hinge 400 to allow the folding portion 200 to unfold or fold.

[0050] like Figure 2 As shown, the wing 100 and the folding portion 200 can be connected to each other via a hinge 400. The hinge 400 is provided at the lower part of the wing 100 and the folding portion 200, as shown... Figure 2 As shown. However, the hinge portion 400 may be provided on the upper part of the wing and the folding portion.

[0051] The folding portion 200 can rotate about the hinge portion 400, and the actuator 300 can provide power to the folding portion 200 so that the folding portion can rotate about the hinge portion 400.

[0052] The actuator 300 may include: a drive unit 310 located in the wing 100 and driven to rotate the drive shaft of the drive unit; and a link configured to connect its first end to the drive shaft of the drive unit 310 and its second end to the folding portion 200 to unfold or fold in response to the drive of the drive unit 310.

[0053] The actuator 300 includes a drive unit 310 located in the wing 100 and a linkage connected to the drive unit 310 and operated in response to the operation of the drive unit 310. Thus, the displacement of the linkage changes in response to the operation of the drive unit 310, and the folding portion 200 can be folded or unfolded.

[0054] In an exemplary embodiment of the present invention, the drive device 310 is a motor, such as a servo motor.

[0055] The linkage includes: a first member 320, the first end of which is connected to the drive shaft of a drive motor and rotates by rotation of the drive shaft 305; a second member 330, the first end of which is rotatably connected to the second end of the first member 320, and the second end of the second member 330 is rotatably connected to the lower part of the folding portion 200. The folding portion 200 unfolds and folds by rotation of the first member 320 and displacement change of the second member 330.

[0056] The linkage includes: a first link 320, which is rotatable via a drive shaft 305 connected to a drive unit 310; and a second link 330, which is rotatably connected at a first end to the first link 320 and at a second end to the folding portion 200. Thus, power from the drive unit 310 can be transmitted to the folding portion 200 via the first link 320 and the second link 330, allowing the folding portion 200 to be folded or unfolded by the drive unit 310.

[0057] In an exemplary embodiment of the present invention, although the link operates via the first link 320 and the second link 330, the link can be formed in various types.

[0058] In an exemplary embodiment of the present invention, the end of the first rod 320 is directly connected to the drive device 310, and the drive device 310 is a servo motor, thereby directly controlling the rotation angle of the first rod 320 through the drive device 310.

[0059] In an exemplary embodiment of the present invention, a portion of the first link 320 is pivotally connected to the wing 100, such that the first link 320 is pivoted by the movement of the drive shaft 305.

[0060] The wing 100 may include a first limiting portion 110 configured to limit the rotation angle of the first rod 320 during the unfolding or folding of the folding portion 200.

[0061] like Figure 2 As shown, the wing 100 has a first limiting part 110 that limits the rotation angle of the first rod 320. Therefore, when the actuator 300 folds or unfolds the folding part 200, the folding part 200 can be folded or unfolded precisely.

[0062] Furthermore, even if the drive unit 310 malfunctions, the rotation angle of the first rod 320 is limited by the first limiting part 110, thus preventing damage caused by collision between the folding part 200 and the wing part 100 during the folding or unfolding of the folding part 200.

[0063] The wing 100 may include a second limiting portion 120, which limits the displacement movement of the second rod 330 during the folding of the folding portion 200.

[0064] A second limiting part 120 that restricts the movement of the second rod 330 and a first limiting part 110 that restricts the rotation of the first rod 320 are simultaneously provided in the wing 100 to restrict the movement of the second rod 330.

[0065] Therefore, even if the drive unit 310 fails, the second limiting part 120 restricts the movement of the second rod 330, thus preventing a collision between the folding part 200 and the wing part 100 during the folding of the folding part 200.

[0066] The aerial maneuvering vehicle may include a first magnetic module 500. The first magnetic module 500 includes: a magnet 510 located in the wing portion 100; and a fixing portion 520 located in the folding portion 200 at a position corresponding to the magnet 510. When the direction of the magnetic circuit changes due to a power source, the first magnetic module 500 fixes the wing portion 100 and the folding portion 200 to each other during the deployment of the folding portion 200, and separates the wing portion 100 and the folding portion 200 from each other during the folding of the folding portion 200.

[0067] like Figure 4 As shown, in order to fix the folding part 200 and the wing 100 during the unfolding of the folding part 200, a first magnetic module 500 located at the position where the folding part 200 and the wing 100 are in contact with each other can fix the folding part 200 and the wing 100 to each other by magnetic force.

[0068] The first magnetic module 500 may include a magnet 510, in which magnetic material is located, and a fixing part 520 is fixed to the magnet 510. The magnet 510 may be located in the wing 100, and the fixing part 520 may be located in the folding part 200 at a position corresponding to the magnet 510.

[0069] Magnets 510 and 610 can be configured such that a permanent magnet is located inside and is a neodymium (Nd-Fe-B) magnet, the outer side of the magnet is formed by a conductor, and the fixing parts 520 and 620 are formed by a conductor.

[0070] Magnets 510 and 610 can be electrically connected. When magnet 510 and fixing part 520 come into contact with each other, the direction of the magnetic circuit can be changed towards fixing part 520 by transmitting an electrical signal, and magnet 510 and fixing part 520 can be firmly fixed to each other by magnetic force.

[0071] A coil is wound around the outside of magnets 510 and 610 to create an electromagnet, and the N and S poles of the electromagnet can be changed by the direction of current flow in the coil. For example... Figure 6 As shown, when current flows in the coil, the flow of the magnetic field can be arranged so that the N pole of the electromagnet is in the same direction as the N pole of the permanent magnet, and the S pole of the electromagnet is in the same direction as the S pole of the permanent magnet. Therefore, the fixing parts 520, 620 and the magnets 510, 610 can be firmly fixed to each other by magnetic force.

[0072] Furthermore, when current flows in the coil, the flow of the magnetic field can be arranged so that the N pole of the electromagnet and the S pole of the permanent magnet are in the same direction, and the S pole of the electromagnet and the N pole of the permanent magnet are in the same direction. Therefore, the fixed state of the fixing parts 520, 620 and the magnets 510, 610 can be released by magnetic force.

[0073] The magnet 510 and the fixing part 520 can change their positions relative to each other. However, since the volume of the magnet 510 is larger than the volume of the fixing part 520, the magnet 510 is located in the wing part 100.

[0074] The controller 10 can be connected to the first magnetic module 500 and can control the first magnetic module 500 to provide power to the magnet 510 so as to fix the fold 200 to the wing 100 during the unfolding of the fold 200.

[0075] The controller 10 can operate the actuator 300 to unfold the folding portion 200. When the folding portion 200 is fully unfolded, the magnet 510 of the first magnetic module 500 and the folding portion 200 can come into contact with each other.

[0076] After the folding part 200 is unfolded, the controller 10 can transmit an electrical signal to the magnet 510 of the first magnetic module 500 to fix the magnet 510 and the fixing part 520 to each other.

[0077] Therefore, during the cruise phase after the aerial vehicle has taken off vertically, it is possible to prevent the aerial vehicle from crashing due to damage to the fuselage during the folding of the folding section 200.

[0078] The aerial maneuvering vehicle may include a second magnetic module 600. The second magnetic module 600 includes a magnet 610 located in the wing portion 100 and a fixing portion 620 located in the folding portion 200 at a position corresponding to the magnet 610. When the direction of the magnetic circuit changes due to a power source, the second magnetic module 600 separates the wing portion 100 from the folding portion 200 during deployment and fixes the wing portion 100 and the folding portion 200 during folding.

[0079] like Figure 4 and Figure 5 As shown, during the folding of the folding section 200, the second magnetic module 600, like the first magnetic module 500, can be located at the position where the folding section and the wing section 100 are connected.

[0080] The magnet 610 of the second magnetic module 600 is located in the wing 100 at the position where the folding portion 200 folds toward the wing 100, and the fixing portion 620 of the second magnetic module 600 can be located in the folding portion 200 at the position corresponding to the magnet 610.

[0081] Thus, during the folding of the folding part 200, the folding part 200 can be firmly fixed to the wing part 100 by magnetic force.

[0082] The controller 10 is connected to the second magnetic module 600 and can control the second magnetic module 600 to fix the fold 200 to the wing 100 during folding.

[0083] To fold the folding part 200, the controller 10 terminates the coupling of the first magnetic module 500 and then operates the actuator 300 to fold the folding part 200. When the folding part 200 is folded, the controller 10 can transmit an electrical signal to the magnet 610 of the second magnetic module 600 to fix the folding part 200 in the folded state.

[0084] This prevents damage to the fuselage caused by the movement of the folding section 200 during the vertical takeoff or landing of the airborne vehicle.

[0085] The controller 10 can control the actuator 300 to fold the folding part 200 during the vertical takeoff of the air-mobile vehicle, and unfold the folding part 200 during the cruise after the vertical takeoff.

[0086] To reduce vertical air resistance during the vertical takeoff of the aerial vehicle, the controller 10 can operate the actuator 300 to fold the folding section 200. During cruise after the aerial vehicle has taken off vertically, the controller 10 can operate the actuator 300 to unfold the folding section 200.

[0087] This reduces vertical air resistance and the amount of power generated during vertical takeoff. Consequently, the electrical or fuel efficiency of aerial vehicles can be improved.

[0088] The controller 10 can control the actuator 300 to unfold the folding section 200 while the air maneuvering vehicle is landing vertically, and to fold the folding section 200 after the air maneuvering vehicle has landed vertically.

[0089] The controller 10 allows the aerial maneuvering vehicle to land safely while the folding section is in the deployed state to receive air resistance during landing.

[0090] Therefore, the controller 10 can operate the actuator 300 to fold the folding part 200 after the aerial vehicle has landed.

[0091] Therefore, the present invention can reduce the hangar space required to accommodate airborne vehicles.

[0092] For ease of interpretation and accurate definition of the appended claims, the terms “upper,” “lower,” “inner,” “outer,” “up,” “lower,” “upward,” “downward,” “front,” “rear,” “back,” “inside,” “outside,” “inward,” “outer,” “internal,” “external,” “inner,” “outer,” “forward,” and “backward” are used to describe features of exemplary embodiments with reference to the positions of these features shown in the figures. It will be further understood that the term “connection” or its derivatives refer to both direct and indirect connections.

[0093] For purposes of illustration and description, the foregoing description of specific exemplary embodiments of the invention has been presented. They are not intended to be exhaustive or to limit the invention to the precise forms disclosed, and it will be apparent that many modifications and variations are possible in light of the foregoing teachings. Exemplary embodiments were chosen and described to explain certain principles of the invention and its practical application, enabling those skilled in the art to make and utilize various exemplary embodiments of the invention, as well as various alternatives and modifications thereof. The scope of the invention is intended to be defined by the appended claims and their equivalents.

Claims

1. An aerial maneuvering vehicle, comprising: Wings, extending from the fuselage of the aerial vehicle; A folding portion is provided at the edge of the wing portion, the folding portion being configured to extend from the wing portion during the unfolding of the folding portion to form a part of the wing portion, and the folding portion being configured to move to coincide with the wing portion during the folding of the folding portion, so as to reduce the air resistance area of ​​the wing portion in the vertical direction; An actuator, connected to the fold and configured to provide power to the fold to cause the fold to unfold or fold into the wing via the actuator; as well as A controller, engaged with and configured to control the actuator to fold the folding section during vertical takeoff and landing of the fuselage, and configured to control the actuator to unfold the folding section during cruise of the fuselage. The wing and the folding portion are positioned such that, in both the folded and unfolded states, their surfaces selectively contact each other. The aerial maneuvering vehicle further includes a hinge joint coupled to the lower part of the wing and the lower part of the folding section, allowing the folding section to rotate relative to the wing. The actuator is configured to selectively rotate the folding portion about the hinge portion according to a signal from the controller, such that the folding portion unfolds or folds. The actuator includes: A drive unit, located in the wing and connected to the controller for being driven by the controller; and A connecting rod is coupled to the drive device and the folding portion to unfold or fold the folding portion in response to the drive device. The connecting rod includes: A first rod, connected to the drive mechanism and configured to rotate via the drive mechanism; and The second rod has a first end pivotally connected to the end of the first rod and a second end pivotally connected to the lower part of the fold. The folding part is configured to unfold or fold when the first rod is rotated and the displacement of the second rod is changed by the driving device. The wing includes a first limiting part, which is configured to limit the rotation angle of the first rod during the unfolding or folding of the folding part; Furthermore, a portion of the wing is recessed from the outer surface of the wing to form the first limiting portion having an acute-angled recess.

2. The aerial maneuvering vehicle according to claim 1, wherein, The wing includes a second limiting portion configured to limit the displacement of the second rod during the folding of the folding portion.

3. The aerial maneuvering vehicle according to claim 2, wherein, A portion of the wing is recessed from the outer surface of the wing to form the second limiting portion having an obtuse-angled recess.

4. The aerial maneuvering vehicle according to claim 1, further comprising: A first magnetic module, comprising a magnet located in the wing and a fixing part located in the folding portion at a position corresponding to the magnet. The first magnetic module is configured to fix the wing and the fold during the unfolding of the fold when power is applied to the first magnetic module and the direction of the magnetic circuit changes, and to separate the wing and the fold from each other during the folding of the fold.

5. The aerial maneuvering vehicle according to claim 4, wherein, The controller is connected to the first magnetic module and configured to control the first magnetic module to provide power to the magnet of the first magnetic module, such that the fold is secured to the wing during the unfolding of the fold.

6. The aerial maneuvering vehicle according to claim 1, further comprising: The second magnetic module includes a magnet located in the wing and a fixing part located in the folding part at a position corresponding to the magnet. The second magnetic module is configured to separate the wing and the folding portion from each other during the unfolding of the folding portion and to fix the wing and the folding portion during the folding portion folding when power is applied to the second magnetic module and the direction of the magnetic circuit changes.

7. The aerial maneuvering vehicle according to claim 6, wherein, The controller is connected to the second magnetic module and configured to control the second magnetic module such that the fold portion is fixed to the wing portion during folding.

8. The aerial maneuvering vehicle according to claim 1, wherein, The controller is configured to control the actuator to fold the folding section during the vertical takeoff of the air maneuvering vehicle and to unfold the folding section during cruise after the vertical takeoff of the air maneuvering vehicle.

9. The aerial maneuvering vehicle according to claim 1, wherein, The controller is configured to control the actuator so that the folded portion lands vertically with the folded portion unfolded, and the folded portion is folded after vertical landing.

10. An aerial maneuvering vehicle, comprising: Wings, extending from the fuselage of the aerial vehicle; A folding portion is provided at the edge of the wing portion, the folding portion being configured to extend from the wing portion during the unfolding of the folding portion to form a part of the wing portion, and the folding portion being configured to move to coincide with the wing portion during the folding of the folding portion, so as to reduce the air resistance area of ​​the wing portion in the vertical direction; An actuator, connected to the fold and configured to provide power to the fold to cause the fold to unfold or fold into the wing via the actuator; as well as A controller, engaged with and configured to control the actuator to fold the folding section during vertical takeoff and landing of the fuselage, and configured to control the actuator to unfold the folding section during cruise of the fuselage. The wing and the folding portion are positioned such that, in both the folded and unfolded states, their surfaces selectively contact each other. The aerial maneuvering vehicle further includes a hinge joint coupled to the lower part of the wing and the lower part of the folding section, allowing the folding section to rotate relative to the wing. The actuator is configured to selectively rotate the folding portion about the hinge portion according to a signal from the controller, causing the folding portion to unfold or fold. The actuator includes: A drive unit, located in the wing and driven by the controller to rotate the drive shaft of the drive unit; and A link, wherein a first end of the link is pivotally connected to the drive shaft of the drive device, and a second end of the link is pivotally connected to the folding portion to unfold or fold the folding portion in response to the drive of the drive device; The connecting rod includes: A first link, wherein a first end of the first link is pivotally connected to the drive shaft of the drive device and configured to rotate by rotation of the drive shaft; and The second rod has a first end pivotally connected to a second end of the first rod, and a second end pivotally connected to the lower end of the fold. The folding portion is configured to unfold and fold when the first rod is rotated and the displacement of the second rod is changed by the driving device. Wherein, a portion of the first rod between the first end and the second end is pivotally coupled to the wing; The wing includes a first limiting part, which is configured to limit the rotation angle of the first rod during the unfolding or folding of the folding part; Furthermore, a portion of the wing is recessed from the outer surface of the wing to form the first limiting portion having an acute-angled recess.

11. The aerial maneuvering vehicle according to claim 10, wherein, The wing includes a second limiting portion configured to limit the displacement of the second rod during folding of the folding portion.

12. The aerial maneuvering vehicle according to claim 11, wherein, A portion of the wing is recessed from the outer surface of the wing to form the second limiting portion having an obtuse-angled recess.

Images