Locking assembly, foldable paddle, power device and aircraft

Abstract

The embodiment of the utility model discloses a locking assembly, a foldable paddle, a power device and an aircraft. The locking assembly comprises a mounting base and a locking piece. The mounting base is used for mounting the propeller blade of the aircraft, the propeller blade comprises a propeller tip part located at one end and a propeller root part located at the other opposite end, and the propeller root part can rotate around a preset axis to achieve folding and unfolding of the propeller blade. The locking piece can rotate relative to the mounting base so that the locking piece can be switched between the first state and the second state. Wherein in the first state, the locking piece is at least used for preventing the propeller root part from rotating around a preset axis relative to the mounting base in the flight process of the aircraft; and in the second state, the locking piece is used for relieving the blocking on the root part of the paddle.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to a locking assembly, a foldable propeller, a power device and an aircraft. Background Art

[0002] The propeller blades of an aircraft require a certain amount of play to facilitate folding. However, during flight, this play can cause the propeller blades to rotate unexpectedly relative to the mounting base / motor rotor, causing the aircraft arm to become unstable and unable to provide normal flight power. Utility Model Content

[0003] The present application provides a locking assembly, a foldable propeller, a power device and an aircraft.

[0004] The locking assembly provided in the present application includes a mounting seat and a locking member. The mounting seat is used to mount the blade of the aircraft, and the blade includes a tip portion located at one end and a root portion located at the other opposite end. The root portion can rotate around a preset axis to achieve the folding and unfolding of the blade. The locking member can rotate relative to the mounting seat to achieve the switching of the locking member between a first state and a second state. In the first state, the locking member is at least used to prevent the root portion from rotating relative to the mounting seat around the preset axis during the flight of the aircraft; in the second state, the locking member is used to release the blocking of the root portion.

[0005] In some embodiments, in the first state, the paddles are in an unfolded state, and in the second state, the paddles are in a folded state.

[0006] In some embodiments, in the first state, the upper surface of the top of the locking member and the upper surface of the top of the mounting seat form a first angle; in the second state, the upper surface of the top of the locking member and the upper surface of the top of the mounting seat form a second angle; wherein the first angle is smaller than the second angle.

[0007] In some embodiments, in the first state, the lower surface of the top of the locking member abuts the upper surface of the top of the mounting seat; in the second state, the lower surface of the top of the locking member is separated from the upper surface of the top of the mounting seat.

[0008] In certain embodiments, the first angle is substantially 0 degrees.

[0009] In certain embodiments, the second angle ranges from 15 degrees to 25 degrees.

[0010] In some embodiments, in the first state, the locking member abuts against the blade root to prevent the blade root from rotating about the preset axis relative to the mounting seat during flight.

[0011] In some embodiments, in the first state, side surfaces of the locking member respectively interfere with two opposite side edges of the oar root, and in the second state, the locking member is separated from the two opposite side edges of the oar root.

[0012] In some embodiments, the locking member includes a first locking member and a second locking member disposed at intervals. The propeller blades include a first blade and a second blade disposed at intervals and rotating synchronously. In the first state, the first locking member is configured to at least prevent the first blade from rotating relative to the mounting base during flight, and the second locking member is configured to at least prevent the second blade from rotating relative to the mounting base during flight.

[0013] In some embodiments, the first locking member and the second locking member are symmetrically distributed at two ends of the mounting base.

[0014] In some embodiments, when switching from the first state to the second state, the first locking member and the second locking member rotate in opposite directions; when switching from the second state to the first state, the first locking member and the second locking member rotate in opposite directions.

[0015] In some embodiments, the locking assembly further includes a rotating shaft and an elastic member, the locking member is rotatably connected to the mounting seat via the rotating shaft, the elastic member is sleeved on the rotating shaft to provide a rotational reset force, one end of the elastic member abuts against the mounting seat, and the other end of the elastic member abuts against the locking member.

[0016] In some embodiments, the rotating shaft meets any of the following conditions: a stop member is provided at the first end of the rotating shaft; a stop structure is provided at the second end of the rotating shaft; the rotating shaft is basically parallel to the width direction of the mounting base; the rotating shaft is provided on the side of the mounting base away from the blade.

[0017] In certain embodiments, when the locking member includes a first locking member and a second locking member that are spaced apart, the stop member corresponding to the first locking member and the stop member corresponding to the second locking member are diagonally arranged.

[0018] In certain embodiments, when the locking member includes a first locking member and a second locking member that are spaced apart, the stop structure corresponding to the first locking member and the stop structure corresponding to the second locking member are diagonally arranged.

[0019] In some embodiments, the locking member further has a third state, in which the locking member is configured to prevent the paddle in the folded state from further folding inward.

[0020] In some embodiments, when the locking member includes a first locking member and a second locking member that are spaced apart, in the third state, the tip portion of the blade corresponding to the first locking member and the tip portion of the blade corresponding to the second locking member partially overlap.

[0021] In some embodiments, a clamping portion is provided at one end of the side surface of the locking member away from its upper surface, and the clamping portion includes a bayonet recessed toward the upper surface of the locking member. In the third state, the bayonet is used to abut against the upper edge of the paddle root to prevent the paddle in the folded state from continuing to fold inward.

[0022] In some embodiments, a guide portion is provided on one end of the side surface of the locking member away from the upper surface thereof, and the guide portion includes an outwardly opened guide slope, and the guide slope is used to guide the blade to enter the first state when it is unfolded.

[0023] In some embodiments, the locking member also meets any of the following conditions: a weight-reducing structure is provided on the upper surface and / or side surface of the locking member; the locking member is provided with a handle portion, and the handle portion is used for the user to carry and rotate the locking member; a notch is provided on the upper surface of the locking member, and the notch is used to provide an escape space for the disassembly and assembly of the blade on the mounting seat; a buffer structure is provided at the portion where the locking member abuts the blade; the top and side of the locking member enclose a receiving space, and in the first state, the receiving space is used to receive at least a portion of the root of the blade.

[0024] The present application provides a foldable paddle. The foldable paddle comprises: a locking assembly as described in any one of the above embodiments, a paddle blade, and a connecting shaft. The connecting shaft is used to mount the paddle blade to the mounting seat of the locking assembly.

[0025] The present application provides a power device. The power device includes the foldable paddle described in any of the above embodiments and a power assembly. The paddle is connected to the power assembly via the connecting shaft and rotates under the drive of the power assembly.

[0026] The present application provides an aircraft, which includes the locking assembly described in any one of the above embodiments; or the foldable propeller described in any one of the above embodiments; or the power device described in any one of the above embodiments.

[0027] The locking assembly, foldable propeller, power unit, and aircraft of the present application are characterized in that, during flight, the locking member can be switched to a first state and prevent the propeller root from rotating relative to the mounting seat about a preset axis during flight, thereby maintaining the relative stillness of the propeller root and the mounting seat during flight, preventing unnecessary vibration or other movement of the propeller blades, and ensuring that the propeller blades can effectively provide flight power. The locking member can be rotated relative to the mounting seat to switch to a second state, releasing the block on the propeller root, allowing the propeller root to rotate relative to the mounting seat about a preset axis to fold the propeller blades, thereby reducing the volume occupied by the propeller blades when the aircraft is idle.

[0028] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become obvious from the description below, or will be learned through practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0030] Figure 1 is a perspective schematic diagram of a power device according to some embodiments of the present application;

[0031] Figure 2 yes Figure 1 The schematic diagram of the three-dimensional structure of the foldable paddle shown;

[0032] Figure 3 yes Figure 2 An exploded schematic diagram of a portion of the structure of the foldable paddle shown;

[0033] Figure 4 yes Figure 2 A schematic diagram of a partial structure of a foldable paddle is shown;

[0034] Figure 5 It is a three-dimensional schematic diagram of an aircraft in some embodiments of the present application.

[0035] Description of main component numbers:

[0036] Aircraft 10000; power unit 1000; foldable propeller 100; locking assembly 10; mounting base 11; upper surface 111; lower surface 113; extension portion 1131; locking member 13; top portion 131; upper surface 1311; notch 13111; lower surface 1313; side portion 132; side surface 1321; retaining portion 13211; bayonet 13213; guide portion 13215; groove 1323; first locking member 1301; Second locking member 1302; rotating shaft 133; first end 1331; stop member 13311; second end 1332; stop structure 13321; elastic member 134; weight-reducing structure 135; handle portion 136; buffer structure 137; accommodating space 138; blade 30; tip portion 31; root portion 33; side edge 331; upper edge 333; first blade 301; second blade 302; connecting shaft 50; preset axis A; power assembly 300. DETAILED DESCRIPTION

[0037] In the description of this application, some of the disclosed contents are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The contents described below with reference to the accompanying drawings are illustrative and are only used to explain this application, and are not to be construed as limiting this application.

[0038] In the description of the present application, many different contents or examples are disclosed to implement different structures of the present application. In order to simplify the disclosure of the present application, the components and settings of specific examples are described below. Of course, they are only examples and are not intended to limit the present application.

[0039] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the described features. Throughout the description of this application, "plurality" means two or more, unless otherwise specifically defined.

[0040] In the description of this application, it should be understood that the terms used to indicate orientation or positional relationships (such as "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", etc.) are based on the orientation or positional relationships shown in the accompanying drawings, and are only for the convenience of describing this application and facilitating the understanding of the corresponding implementation methods, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, the terms used to indicate orientation or positional relationships cannot be understood as limiting this application.

[0041] In the description of this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature includes the first feature being directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0042] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed connections, detachable connections, or integral connections. They can refer to mechanical connections or electrical connections. They can refer to direct connections or indirect connections through an intermediary. They can refer to internal communication between two components or interactions between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.

[0043] See also Figure 1 and Figure 5 , the power unit 1000 is a device in the aircraft 10000 for providing power output. Under the action of the power unit 1000, the aircraft 10000 can perform various maneuvers such as take-off and landing, hovering and sailing. The power unit 1000 includes a power component 300 and a foldable propeller 100, and the power component 300 is used to provide power for the foldable propeller 100. The power component 300 can be a power source such as a motor, and this application does not limit this. Furthermore, the power unit 1000 of the present application can be an outer rotor motor, and the foldable propeller 100 is connected to the rotor part of the outer rotor motor to drive the rotation of the foldable propeller, thereby providing effective flight power.

[0044] The foldable paddle 100 includes a locking assembly 10, a blade 30, and a connecting shaft 50. The connecting shaft 50 is used to mount the blade 30 to the mounting base 11 of the locking assembly 10. During flight, the blade 30 of the foldable paddle 100 is in an unfolded state. There is no relative rotation between the blade 30 and the mounting base 11. The blade 30 and the mounting base 11 rotate as a whole, so that the blade 30 can interact with the air during rotation, generating lift and thrust, thereby moving the aircraft 10000. After the flight, it is usually necessary to store the aircraft 10000. The blade 30 can be rotated about the connecting shaft 50 to be in a folded state to accommodate the blade 30. Therefore, the blade 30 requires a certain amount of wiggle room to facilitate folding of the blade 30. However, during flight, this wiggle room can cause the blade 30 to rotate unexpectedly relative to the mounting base or the power assembly, causing the aircraft arm to become unstable and unable to provide normal flight power.

[0045] In this application, one power assembly 300 can control one or more foldable paddles 100, which is not limited thereto. One locking assembly 10 can be mounted on one or more blades 30. This application illustrates a case where one power assembly 300 controls one foldable paddle 100 and one locking assembly 10 mounts two blades 30.

[0046] Based on this, see Figures 1 to 3 The locking assembly 10 provided in the present application includes a mounting seat 11 and a locking member 13. The mounting seat 11 is used to mount the blade 30 of the aircraft 10000. The blade 30 includes a tip portion 31 located at one end and a root portion 33 located at the other opposite end. The root portion 33 can rotate around a preset axis A to achieve the folding and unfolding of the blade 30. The locking member 13 can rotate relative to the mounting seat 11 to achieve the switching of the locking member 13 between a first state and a second state. In the first state, the locking member 13 is at least used to prevent the root portion 33 from rotating relative to the mounting seat 11 around the preset axis A during flight; in the second state, the locking member 13 is used to release the blockage of the root portion 33.

[0047] In an embodiment of the present application, the locking member 13 can be flipped up and down relative to the mounting base 11 to switch the locking member 13 between the first state and the second state. In other embodiments of the present application, the locking member 13 can be swung left and right relative to the mounting base 11 to switch the locking member 13 between the first state and the second state.

[0048] In the embodiment of the present application, the locking member 13 is mounted on the mounting base 11 to facilitate storage of the locking member 13 and prevent loss of the locking member. In other embodiments of the present application, the locking member 13 can also be mounted on other components, such as an arm or a motor.

[0049] Specifically, the blade 30 includes a tip portion 31 and a root portion 33. The tip portion 31 is located at the end of the blade 30 away from the mounting seat 11; the root portion 33 is located at the end of the blade 30 close to the mounting seat 11 and is connected to the mounting seat 11 through a connecting shaft 50. The mounting seat 11 can fix the blade 30 to the aircraft 10000 to prevent the blade 30 from loosening or deflecting, thereby ensuring flight stability. Specifically, the mounting seat 11 and the blade 30 are both provided with mounting holes, and the connecting shaft 50 passes through the mounting holes and is connected to the mounting seat 11 and the blade 30. The connecting shaft 50 is generally cylindrical to ensure that the connecting shaft 50 can rotate smoothly in the mounting hole. The blade 30 can rotate freely around a preset axis A. Among them, the preset axis A is the axial direction of the connecting shaft 50 in the embodiment of the present application. In the embodiment of the present application, the length direction of the mounting base 11 is defined as the first direction X, the width direction of the mounting base 11 is defined as the second direction Y, and the thickness direction of the mounting base 11 is defined as the third direction Z. The extension direction of the blade 30 is defined as the direction from the blade root 33 to the blade tip 31. In the deployed state, the extension direction of the blade 30 is substantially aligned with the first direction X. In the folded state, the extension direction of the blade 30 is substantially aligned with the second direction Y. That is, the angle between the extension direction of the blade 30 in the deployed state and the first direction X is smaller than the angle between the extension direction of the blade 30 in the folded state and the first direction X.

[0050] The locking member 13 can rotate relative to the mounting base 11 to switch between the first state and the second state. In the first state (see Figure 1 ), locking member 13 is used to prevent blade root 33 from rotating about a predetermined axis A during flight, thereby maintaining the deployed state of blades 30. In the first state, locking member 13 is generally in contact with the surface of mounting base 11, with its upper surface or side surface 1321 in close contact with the surface of blade root 33, thereby forming a forced stop.

[0051] In the second state (see Figure 2 ), locking member 13 can rotate a certain angle relative to mounting base 11, releasing the restriction on propeller root 33. In this second state, locking member 13 no longer restricts propeller root 33, allowing propeller root 33 to rotate about predetermined axis A, allowing the propeller to rotate from the deployed state to the folded state. This allows propeller blades 30 to be stowed when not in flight, reducing space usage and protecting them from collision damage.

[0052] During flight of aircraft 10000, locking member 13 of locking assembly 10 of the present application can be switched to a first state, preventing blade root 33 from rotating relative to mounting base 11 about a preset axis A during flight, thereby maintaining relative stillness between blade root 33 and mounting base 11 during flight, preventing unnecessary rotation and vibration of blade 30, and ensuring that blade 30 can provide flight power. Locking member 13 can be rotated relative to mounting base 11 to switch to a second state, releasing the block on blade root 33, allowing blade root 33 to rotate relative to mounting base 11 about the preset axis A to retract blade 30 and reduce the space occupied by blade 30.

[0053] See also Figures 1 to 3 In some embodiments, in the first state, the paddle 30 is in an unfolded state, and in the second state, the paddle 30 is in a folded state.

[0054] Specifically, the blades 30 are in the unfolded state ( Figure 1 ), the locking member 13 can prevent the blade root 33 from rotating around the preset axis A during flight, avoiding relative movement between the blade root 33 and the mounting base 11, ensuring that the blade 30 remains in the deployed state, providing flight power for the aircraft 10000. When the blade 30 needs to be switched from the deployed state to the folded state ( Figure 2 ), locking member 13 can flip away from mounting base 11, releasing the obstruction on paddle root 33, allowing paddle root 33 to rotate freely about predetermined axis A, thereby folding paddle blade 30. Folding paddle blade 30 not only reduces the space occupied by foldable paddle 100 when parked, but also protects paddle blade 30 from collision damage, thereby extending its service life.

[0055] Among them, in an embodiment in which two blades 30 are provided in the length direction of a single mounting base 11, the unfolded state of the blades 30 is that the extension directions of the two blades 30 are basically the same and are in the first direction X. At this time, the blade tips 31 of the two blades 30 are far apart, and sufficient flight power can be provided during the rotation process; the folded state of the blades 30 is that the blade tips 31 of the two blades 30 are close to each other, and the extension directions of the two blades 30 are basically the same and are in the second direction Y. In this way, the two blades 30 can be in a folded state, reducing the occupied space.

[0056] See also Figure 1 and Figure 2 In some embodiments, in the first state, the upper surface 1311 of the top 131 of the locking member 13 and the upper surface 111 of the top 131 of the mounting base 11 form a first angle; in the second state, the upper surface 1311 of the top 131 of the locking member 13 and the upper surface 111 of the top 131 of the mounting base 11 form a second angle A; wherein the first angle is smaller than the second angle A.

[0057] Specifically, the top 131 of the locking member 13 includes an opposing upper surface 1311 and a lower surface 1313, with the upper surface 1311 being further away from the mounting base 11 than the lower surface 1313. The smaller the first angle, the closer the upper surface 1311 of the top 131 of the locking member 13 is to the upper surface 111 of the top 131 of the mounting base 11. This effectively limits the rotation of the propeller root 33 about the preset axis A during flight, ensuring that the propeller root 33 is securely locked in the first state and preventing accidental rotation during flight. In the embodiment of the present application, the first angle is smaller. The larger second angle A allows the locking member 13 to flip and move away from the mounting base 11, releasing the obstruction on the propeller root 33 and allowing it to rotate freely about the preset axis A. The larger second angle A provides sufficient rotational space for the propeller root 33, allowing it to smoothly rotate and switch to the folded state.

[0058] See also Figure 1 and Figure 2 In some embodiments, in the first state, the lower surface 1313 of the top 131 of the locking member 13 abuts the upper surface 111 of the top 131 of the mounting seat 11; in the second state, the lower surface 1313 of the top 131 of the locking member 13 is separated from the upper surface 111 of the top 131 of the mounting seat 11.

[0059] Specifically, the lower surface 1313 of the top portion 131 of the locking member 13 abuts the upper surface 111 of the top portion 131 of the mounting base 11. Thus, in the first state, the upper surface 111 of the top portion 131 of the mounting base 11 can support the locking member 13, preventing the locking member 13 from shaking or rotating relative to the mounting base 11 during flight. In the second state, the user flips the locking member 13, separating the lower surface 1313 of the top portion 131 of the locking member 13 from the upper surface 111 of the top portion 131 of the mounting base 11. Accordingly, the locking member 13 moves away from the propeller blade 30 mounted on the mounting base 11, thereby releasing the obstruction on the propeller root 33 and allowing the propeller root 33 to rotate freely about the predetermined axis A.

[0060] See also Figure 1 In some embodiments, the first angle is substantially 0 degrees.

[0061] Specifically, the first angle is basically 0 degrees, that is, the upper surface 1311 of the top 131 of the locking member 13 is basically parallel to the upper surface 111 of the top 131 of the mounting seat 11. In this way, the displacement of the blade 30 relative to the mounting seat 11 in the third direction Z can be limited, thereby avoiding the shaking of the blade 30 in the third direction Z during flight, and ensuring the stability of the foldable propeller 100 during operation.

[0062] See also Figure 2In some embodiments, the second angle A ranges from 15 degrees to 25 degrees.

[0063] Specifically, the second angle A can be 15 degrees, 16 degrees, 17 degrees, 18 degrees, 19 degrees, 20 degrees, 21 degrees, 22 degrees, 23 degrees, or 25 degrees. If the second angle A is less than 15 degrees, the rotation angle of the locking member 13 switching between the first and second states is too small, which can easily lead to accidental activation of the locking member 13, causing an erroneous switch between the first and second states, resulting in the blades 30 being unable to maintain the deployed state during flight. If the second angle A is greater than 25 degrees, the rotation angle of the locking member 13 switching between the first and second states is too large, and multiple rotations can easily cause wear of the locking member 13, shortening the life of the locking member 13. The second angle A ranges from 15 degrees to 25 degrees, which can control the rotation angle of the locking member 13 switching between the first and second states within a reasonable range, preventing erroneous switching between the first and second states while ensuring the life of the locking member 13.

[0064] See also Figure 1 and Figure 3 In some embodiments, in the first state, the locking member 13 abuts against the blade root 33 to prevent the blade root 33 from rotating around the preset axis A relative to the mounting seat 11 during flight.

[0065] Specifically, the locking member 13 includes a top 131 and two side portions 132 at both ends of the top 131 in the second direction Y. In the first state, the two side portions 132 at both ends of the second direction Y abut against the propeller root 33, thereby limiting the rotation of the propeller root 33 relative to the mounting base 11 during flight.

[0066] See also Figures 1 to 3 Furthermore, in some embodiments, in the first state, the side surface 1321 of the locking member 13 respectively contacts the two opposite side edges 331 of the oar root 33 to limit the displacement of the oar root 33 relative to the locking member 13; in the second state, the locking member 13 is separated from the two opposite side edges 331 of the oar root 33 to contact the locking member 13 to limit the positioning of the oar root 33.

[0067] Specifically, the side surface 1321 of the locking member 13 is the side portion 132 of the locking member 13, and the two opposing side edges 331 of the oar root 33 are the two opposing side edges 331 of the oar root 33 in the second direction Y. In the first state, the side surfaces 1321 of the locking member 13 respectively contact the two opposing side edges 331 of the oar root 33. For example, when the oar root 33 is subjected to an external force (such as airflow or movement of the foldable oar 100), the side surface 1321 of the locking member 13 exerts a reaction force at the side edges 331 of the oar root 33. The reaction force can offset the rotational tendency of the oar root 33 caused by the external force, thereby ensuring that the oar root 33 and the mounting base 11 do not rotate relative to each other. In the second state, the locking member 13 is separated from the two opposite side edges 331 of the oar root 33. In this way, when the oar root 33 is subjected to external force, the locking member 13 is not restricted in the direction of rotation of the oar root 33 around the preset axis A, and the oar root 33 can rotate relative to the preset axis A.

[0068] See also Figures 1 to 3 In some embodiments, locking member 13 includes a first locking member 1301 and a second locking member 1302 spaced apart. Blades 30 include first blades 301 and second blades 302 spaced apart and rotating synchronously. In a first state, first locking member 1301 is at least configured to prevent first blade 301 from rotating relative to mounting base 11 during flight, and second locking member 1302 is at least configured to prevent second blade 302 from rotating relative to mounting base 11 during flight.

[0069] Specifically, a first locking member 1301 and a second locking member 1302 are spaced apart in the length direction of the mounting base 11. Correspondingly, a first blade 301 and a second blade 302 are spaced apart in the length direction of the mounting base 11. The first locking member 1301 is used to control the rotation of the root 33 of the first blade 301 relative to the mounting base 11, and the second locking member 1302 is used to control the rotation of the root 33 of the second blade 302 relative to the mounting base 11, so as to ensure that during flight, the rotation of each blade 30 relative to the mounting base 11 can be independently controlled to avoid affecting another blade 30 when adjusting a single blade 30. The first locking member 1301 and the second locking member 1302 that are spaced apart can also be independent of each other to avoid mutual influence. The two locking members 13 can also provide a redundant design. When the first locking member 1301 or the second locking member 1302 fails, the other locking member 13 can work normally.

[0070] See also Figure 2 In some embodiments, the first locking member 1301 and the second locking member 1302 are symmetrically distributed at both ends of the mounting base 11.

[0071] Specifically, the symmetrical distribution can ensure that the forces exerted by the first locking member 1301 and the second locking member 1302 on the mounting seat 11 are symmetrically distributed in the first direction X. On the one hand, it reduces the deformation or stress concentration of the mounting seat 11 caused by the imbalance of the forces, avoids a certain part of the mounting seat 11 from being subjected to excessive forces, and thus extends the service life of the mounting seat 11. On the other hand, it ensures that during flight, the forces exerted by the airflow on the first locking member 1301 and the second locking member 1302 will be evenly distributed at both ends of the mounting seat 11, avoiding lateral deviation or instability of the foldable paddle 100 due to asymmetry.

[0072] See also Figure 1 and Figure 2 In some embodiments, when switching from the first state to the second state, the rotation directions of the first locking member 1301 and the second locking member 1302 are opposite; when switching from the second state to the first state, the rotation directions of the first locking member 1301 and the second locking member 1302 are opposite.

[0073] Specifically, the rotation directions of the first locking member 1301 and the second locking member 1302 are opposite. For example, in the embodiment of the present application, when switching from the first state to the second state, Figure 2 From the perspective of the first locking member 1301, the first locking member 1301 rotates clockwise, and the second locking member 1302 rotates counterclockwise. Thus, when simultaneously switching between the states of the first locking member 1301 and the second locking member 1302, the forces applied by the user to the first locking member 1301 and the second locking member 1302 are directed in different directions. This balances the torque transmitted to the mounting base 11, preventing the foldable paddle 100 from being displaced by the force when rotating the first locking member 1301 and the second locking member 1302. The same is true when switching from the second state to the first state, which will not be described in detail here.

[0074] See also Figure 3 In some embodiments, the locking assembly 10 further includes a rotating shaft 133 and an elastic member 134. The locking member 13 is rotatably connected to the mounting seat 11 via the rotating shaft 133. The elastic member 134 is sleeved on the rotating shaft 133 to provide a rotational reset force. One end of the elastic member 134 abuts against the mounting seat 11, and the other end of the elastic member 134 abuts against the locking member 13.

[0075] Specifically, the mounting base 11 further includes a lower surface 113 opposite the upper surface 111. The lower surface 113 is provided with an extension 1131 extending away from the lower surface 113. The rotation shaft 133 passes through the extension 1131 to be mounted on the mounting base 11. The elastic member 134 is compressed and is used to cause the locking member 13 to rotate toward the upper surface 111 near the top 131 of the mounting base 11. The elastic member 134 can be a structure with elastic deformation. In the embodiment of the present application, the elastic member 134 is a torsion spring.

[0076] When the locking member 13 is in the first state, the elastic member 134 is used to make the lower surface 1313 of the top 131 of the locking member 13 abut against the upper surface 111 of the top 131 of the mounting seat 11. In this way, in the absence of an external force acting on the locking member 13, the elastic member 134 can fix the locking member 13 to the mounting seat 11, preventing the locking member 13 from rotating relative to the mounting seat 11; when the locking member 13 switches from the first state to the second state, the user applies a force opposite to the compression force of the elastic member 134 to the locking member 13, so that the lower surface 1313 of the top 131 of the locking member 13 is separated from the upper surface 111 of the top 131 of the mounting seat 11, so that the locking member 13 is in the second state.

[0077] In the second state, the elastic member 134 is still in a compressed state, and the compression deformation of the elastic member 134 in the second state is greater than the compression deformation of the elastic member 134 in the first state. In this way, after the user cancels the force applied to the locking member 13, the elastic member 134 can provide a rotational reset force for the locking member 13, so that the locking member 13 automatically rotates toward the upper surface 111 close to the top 131 of the mounting seat 11 to restore to the first state.

[0078] See also Figure 3 and Figure 5 In some embodiments, the rotation axis 133 is substantially parallel to the width direction (second direction Y) of the mounting base 11 .

[0079] Specifically, the extension direction of the rotation axis 133 is substantially consistent with the second direction Y. This ensures that the force exerted by the rotation axis 133 on the mounting seat 11 is symmetrically distributed in the second direction Y, reducing deformation or stress concentration of the mounting seat 11 caused by uneven force, preventing a portion of the mounting seat 11 from being subjected to excessive force, and thus extending the service life of the mounting seat 11. Furthermore, during flight, the force exerted by the airflow on the rotation axis 133 is evenly distributed across the width of the mounting seat 11, preventing lateral deviation or instability of the aircraft 10000 due to asymmetry. Furthermore, the force exerted by the locking member 13 on the mounting seat 11 is evenly distributed in the second direction Y, reducing torque imbalance caused by improper layout and lateral force caused by rotation, thereby ensuring the flight stability of the aircraft 10000.

[0080] See also Figure 3 In some embodiments, a stopper 13311 is provided at the first end 1331 of the rotating shaft 133 .

[0081] Specifically, the rotating shaft 133 includes a first end 1331 and a second end 1332 relative to each other. The stopper 13311 is sleeved on the first end 1331 of the rotating shaft 133 and is located between the locking member 13 and the rotating shaft 133, and is used to limit the movement of the rotating shaft 133 along the extension direction of the rotating shaft 133, and prevent the rotating shaft 133 from axially displacing due to external force or vibration and falling off from the mounting seat 11. The material of the stopper 13311 includes but is not limited to plastic, silicone or metal. In the case where the material of the stopper 13311 is plastic, the stopper 13311 is light in weight, low in cost, and easy to process. In the case where the material of the stopper 13311 is metal, the stopper 13311 is strong, has a long service life, and is easy to clean and maintain.

[0082] See also Figure 3 In some embodiments, the second end 1332 of the rotating shaft 133 has a stop structure 13321.

[0083] Specifically, in some embodiments, the stop structure 13321 and the rotating shaft 133 are integrally formed, that is, the stop structure 13321 and the rotating shaft 133 are a single, integrated structure. This enhances the bonding strength between the stop structure 13321 and the rotating shaft 133, preventing separation during operation of the locking member 13, thereby ensuring the stability and reliability of the locking member 13. In other embodiments, the stop structure 13321 and the rotating shaft 133 are separate structures, that is, the stop structure 13321 and the rotating shaft 133 are two different structures. In one example, the stop structure 13321 and the rotating shaft 133 can be connected together using a detachable connection, including but not limited to a snap connection or a threaded connection. In another example, the stop structure 13321 and the rotating shaft 133 can be connected together using a non-detachable connection, including but not limited to bonding or welding.

[0084] The stop structure 13321 in the present application is a protrusion with a runway-shaped cross-section. The stop structure 13321 can limit the rotation of the rotating shaft 133 to prevent the rotating shaft 133 from being damaged due to excessive rotation.

[0085] See also Figure 3 In some embodiments, the rotating shaft 133 is disposed on a side of the mounting base 11 away from the blade 30 , which can leave an accommodating space 138 for the blade 30 , thereby facilitating the rotation of the blade 30 .

[0086] See also Figure 3In some embodiments, when the locking member 13 includes a first locking member 1301 and a second locking member 1302 that are spaced apart, the stop member 13311 corresponding to the first locking member 1301 and the stop member 13311 corresponding to the second locking member 1302 are diagonally arranged.

[0087] Specifically, the diagonally arranged stoppers 13311 allow both the first locking member 1301 and the second locking member 1302 to be provided with stoppers 13311, and the mounting base 11 is provided with stoppers 13311 on opposite sides in the second direction Y. This balances the torque generated by the locking member 13 during operation, reducing deviation and wear of the rotating shaft 133 in its own extension direction caused by torque imbalance. Furthermore, the first locking member 1301 and the second locking member 1302 can be interchanged without requiring separate installation, thereby improving reusability.

[0088] See also Figure 3 In some embodiments, when the locking member 13 includes a first locking member 1301 and a second locking member 1302 that are spaced apart: the stop structure 13321 corresponding to the first locking member 1301 and the stop structure 13321 corresponding to the second locking member 1302 are diagonally arranged.

[0089] Specifically, the diagonally arranged stop structures 13321 allow both the first locking member 1301 and the second locking member 1302 to be provided with stop structures 13321, and the mounting base 11 is provided with stop structures 13321 on opposite sides in the second direction Y. This balances the torque generated by the locking member 13 during operation, reducing deviation and wear of the rotating shaft 133 in the self-rotational direction caused by torque imbalance. Furthermore, the first locking member 1301 and the second locking member 1302 can be interchanged without requiring separate installation, thereby improving reusability.

[0090] See also Figure 4 In some embodiments, the locking member 13 further has a third state. In the third state, the locking member 13 is used to prevent the paddle 30 in the folded state from continuing to fold inward.

[0091] Specifically, in the third state, the blade 30 is in a folded state, and the locking member 13 is at least partially in contact with the blade 30 to prevent the blade 30 from continuing to fold inward, that is, the locking member 13 prevents the first blade 301 and the second blade 302 from continuing to approach each other, resulting in mutual wear and extrusion between the first blade 301 and the second blade 302, causing damage to the first blade 301 and the second blade 302.

[0092] In some embodiments, when the locking member 13 includes a first locking member 1301 and a second locking member 1302 that are spaced apart, in the third state, the tip portion 31 of the blade 30 corresponding to the first locking member 1301 and the tip portion 31 of the blade 30 corresponding to the second locking member 1302 partially overlap.

[0093] Specifically, the tip portion 31 of the blade 30 corresponding to the first locking member 1301 and the tip portion 31 of the blade 30 corresponding to the second locking member 1302 partially overlap. In this way, in the third state, the space occupied by the first locking member 1301 corresponding to the blade 30 and the first locking member 1301 corresponding to the blade 30 can be further reduced.

[0094] In some embodiments, a clamping portion 13211 is provided at one end of the side surface 1321 of the locking member 13 away from its upper surface 1311, and the clamping portion 13211 includes a latch 13213 recessed toward the upper surface 1311 of the locking member 13. In the third state, the latch 13213 is used to abut against the upper edge 333 of the paddle root 33 to prevent the paddle 30 in the folded state from continuing to fold inward.

[0095] exist Figure 4 In this case, the first locking member 1301 prevents the first blade 301 from continuing to rotate counterclockwise (folding inward), but the first blade 301 can still rotate clockwise. The second locking member 1302 prevents the second blade 302 from continuing to rotate clockwise (folding inward), but the second blade 302 can still rotate counterclockwise. The root portion 33 of the paddle is partially located in the buckle. In this way, after the root portion 33 of the paddle is folded inward to a certain angle, the portion of the retaining portion 13211 close to the rotation axis 133 can abut the side edge 331 of the root portion 33, preventing the blade 30 from continuing to fold. In this way, the first blade 301 and the second blade 302 can be prevented from being over-folded, which would cause compression and wear of the first blade 301 and the second blade 302.

[0096] In some embodiments, a guide portion 13215 is provided at one end of the side surface 1321 of the locking member 13 away from the upper surface 1311 thereof. The guide portion 13215 includes an outwardly opened guide slope for guiding the blade 30 to enter the first state when it is unfolded.

[0097] Specifically, the guide portion 13215 is outwardly flared, that is, it extends away from the mounting base 11, thereby forming a guide slope. The guide slope has a certain angle with the third direction Z. In this way, when the blade 30 rotates from the folded state to the unfolded state, the guide portion 13215 can guide the blade 30 to a certain extent, allowing the blade 30 to stably enter the first state.

[0098] See also Figure 3In some embodiments, the upper surface 1311 and / or the side surface 1321 of the locking member 13 is provided with a weight-reducing structure 135 .

[0099] Specifically, the weight-reducing structure 135 can be in various forms such as notches, grooves, and openings, and is not limited in the present application. The weight-reducing structure 135 can be provided on the upper surface 1311 of the locking member 13, or on the side surface 1321 of the locking member 13, or the weight-reducing structure 135 can be provided on both the upper surface 1311 and the side surface 1321 of the locking member 13. In one embodiment of the present application, the weight-reducing structure 135 is two through holes that pass through the side surface 1321 of the locking member 13. The shape of the cross section of the through hole includes, but is not limited to, a perfect circle, an ellipse, or a polygon, etc. In the present application, it is a runway shape, which has no dead angles and is not easy to hide dirt and grime. The weight-reducing structure 135 can reduce the weight of the locking member 13 to reduce the overall weight of the aircraft 10000.

[0100] See also Figure 3 In some embodiments, the locking member 13 is provided with a handle portion 136 , which is used for the user to carry and rotate the locking member 13 .

[0101] Specifically, in some embodiments, the handle 136 and the locking member 13 are integrally structured, that is, the handle 136 and the locking member 13 are a single, integrated structure. This enhances the strength of the connection between the handle 136 and the locking member 13, preventing the handle 136 and the locking member 13 from separating when the user is carrying the handle 136. In other embodiments, the handle 136 and the locking member 13 are separate structures, that is, the handle 136 and the locking member 13 are two different structures. The handle 136 provides a secure grip for the user, allowing the user to better control the rotation direction and angle of the locking member 13.

[0102] See also Figure 3 In some embodiments, a notch 13111 is formed on the upper surface 1311 of the locking member 13 , and the notch 13111 is used to provide an escape space for the blade 30 to be assembled and disassembled on the mounting seat 11 .

[0103] Specifically, in the XY projection plane, the connecting shaft 50 is located within the projection plane of the notch 13111. In this way, when the blade 30 needs to be removed from the mounting seat 11, the user does not need to rotate the locking member 13. The user can directly remove the connecting shaft 50 in the notch 13111 to release the installation relationship between the blade 30 and the mounting seat 11. Conversely, when the blade 30 needs to be installed on the mounting seat 11, the user does not need to rotate the locking member 13. The user can directly pass the connecting shaft 50 through the notch 13111 to install the blade 30 on the mounting seat 11, thereby improving installation efficiency. The shape of the notch 13111 in the XY projection plane includes but is not limited to a perfect circle, an ellipse, or a polygon. In addition, the notch 13111 can also serve as a weight-reducing structure 135 to reduce the weight of the locking member 13.

[0104] See also Figure 3 In some embodiments, a buffer structure 137 is provided at the portion where the locking member 13 abuts the blade 30 .

[0105] Specifically, the buffer structure 137 can be one or more. The present application includes two buffer structures 137, one located on each side 132 of the locking member 13. The buffer structure 137 can be made of a soft and elastic material, such as silicone, rubber, or polyvinyl chloride. Rubber includes, but is not limited to, natural rubber, nitrile rubber, fluororubber, polyurethane rubber, EPDM rubber, or silicone rubber. The buffer structure 137 can return to its original shape after being subjected to an applied force, thereby absorbing and dispersing the force. When the locking member 13 is in the first state, the buffer structure 137 can absorb the force generated by the tendency of the propeller root 33 to rotate about the preset axis A, preventing direct contact and wear between the propeller roots 33. When the locking member 13 switches from the first state to the second state, the locking member 13 rotates relative to the mounting base 11, and the buffer structure 137 can prevent the locking member 13 from scratching the propeller root 33 during rotation. In one example, the buffer structure 137 can be directly attached to the side of the locking member 13 close to the blade 30; in another example, the side 132 of the locking member 13 is provided with a groove 1323, and the buffer structure 137 is accommodated in the groove 1323, so that the buffer structure 137 can be better fixed and replaced.

[0106] See also Figure 3 In some embodiments, the top 131 and the side 132 of the locking member enclose a receiving space 138 . In the first state, the receiving space 138 is used to receive at least a portion of the paddle root 33 .

[0107] Specifically, in the first state, at least a portion of the blade root 33 is contained within the accommodating space 138. This helps ensure that the blade root 33 is not easily displaced when deployed, reducing accidental displacement or loosening during flight. The upper surface 1311 and side surfaces 1321 of the locking member 13 also provide protection for the blade root 33, preventing foreign objects from striking the blade root 33 during flight and reducing the force interference from air resistance on the blade root 33 during rotation.

[0108] See also Figure 1 、 Figure 2 and Figure 4 The present application provides a foldable paddle 100. The foldable paddle 100 includes the locking assembly 10 of any one of the above embodiments, a paddle 30, and a connecting shaft 50. The connecting shaft 50 is used to mount the paddle 30 to the mounting seat 11 of the locking assembly 10.

[0109] During flight, the foldable paddle 100 of the present application can have its locking member 13 switched to a first state, preventing the root portion 33 from rotating relative to the mounting base 11 about a predetermined axis A. This maintains the relative stillness of the root portion 33 and the mounting base 11 during flight, preventing unnecessary rotation and vibration of the blade 30 and ensuring that the blade 30 can provide flight power. The locking member 13 can then be rotated relative to the mounting base 11 to switch to a second state, releasing the block on the root portion 33. The root portion 33 can then rotate relative to the mounting base 11 about the predetermined axis A to fold the blade 30, reducing the space occupied by the blade 30.

[0110] See also Figure 1 The present application provides a power device 1000. The power device 1000 includes the foldable paddle 100 of any one of the above embodiments and a power assembly 300. The paddle 30 is connected to the power assembly 300 via a connecting shaft 50 and rotates under the drive of the power assembly 300.

[0111] During flight of the aircraft 10000 of the present application, the locking member 13 of the power unit 1000 can be switched to a first state, preventing the blade root 33 from rotating relative to the mounting seat 11 about a preset axis A during flight, thereby maintaining the relative stillness of the blade root 33 and the mounting seat 11 during flight, preventing unnecessary rotation and vibration of the blade 30, and ensuring that the blade 30 can provide flight power. The locking member 13 can be rotated relative to the mounting seat 11 to switch to a second state, and after releasing the block on the blade root 33, the blade root 33 can rotate relative to the mounting seat 11 about the preset axis A to retract the blade 30, reducing the space occupied by the blade 30.

[0112] See also Figure 5The present application provides an aircraft 10000. In one embodiment, the aircraft 10000 includes the locking assembly 10 according to any of the above embodiments. In another embodiment, the aircraft 10000 includes the foldable propeller 100 according to any of the above embodiments; in yet another embodiment, the aircraft 10000 includes the power plant 1000 according to any of the above embodiments.

[0113] The aircraft 10000 of the present application may include but is not limited to any one of an inspection / surveillance drone, an agricultural drone, a meteorological drone, an exploration drone, a mapping drone, a reconnaissance drone, a decoy drone, an electronic warfare drone, and a communication relay drone. During the flight of the aircraft 10000 of the present application, the locking member 13 can be switched to a first state and prevent the propeller root 33 from rotating relative to the mounting seat 11 around a preset axis A during flight, so as to maintain the relative stillness of the propeller root 33 and the mounting seat 11 during flight, avoid unnecessary rotation and vibration of the blade 30, and ensure that the blade 30 can provide flight power. The locking member 13 can be rotated relative to the mounting seat 11 to switch to a second state, and when the obstruction on the propeller root 33 is released, the propeller root 33 can rotate relative to the mounting seat 11 around the preset axis A to retract the propeller 30 and reduce the space occupied by the propeller 30.

[0114] Although the embodiments of the present application have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments of the present application without departing from the principles and purpose of the present application, and that the scope of the present application is defined by the claims and their equivalents.

Claims

1. A locking assembly, characterized in that: include: A mounting base for mounting a propeller blade of an aircraft, wherein the propeller blade includes a tip portion at one end and a root portion at the other opposite end, wherein the root portion is capable of rotating about a preset axis to achieve folding and unfolding of the propeller blade; as well as a locking member, wherein the locking member is rotatable relative to the mounting seat to enable the locking member to switch between a first state and a second state; Wherein, (a) in the first state, the locking member is at least used to prevent the root of the propeller from rotating around the preset axis relative to the mounting seat during the flight of the aircraft; (b) in the second state, the locking member is used to release the blocking of the root of the propeller.

2. The locking assembly according to claim 1, wherein: In the first state, the paddles are in an unfolded state, and in the second state, the paddles are in a folded state.

3. The locking assembly according to claim 1, wherein: In the first state, the upper surface of the top of the locking member and the upper surface of the top of the mounting seat form a first angle; in the second state, the upper surface of the top of the locking member and the upper surface of the top of the mounting seat form a second angle; wherein the first angle is smaller than the second angle; and / or In the first state, the lower surface of the top of the locking member abuts against the upper surface of the top of the mounting seat; in the second state, the lower surface of the top of the locking member is separated from the upper surface of the top of the mounting seat.

4. The locking assembly according to claim 3, wherein: The first angle is substantially 0 degrees, and / or the second angle is in the range of 15 degrees to 25 degrees.

5. The locking assembly according to claim 1, wherein in the first state, the locking member abuts against the propeller root to prevent the propeller root from rotating around the preset axis relative to the mounting seat during flight.

6. The locking assembly according to claim 5, wherein: In the first state, side surfaces of the locking member respectively contact two opposite side edges of the oar root, and in the second state, the locking member is separated from the two opposite side edges of the oar root.

7. The locking assembly according to claim 1, wherein: The locking member includes a first locking member and a second locking member that are arranged at intervals, and the blades include a first blade and a second blade that are arranged at intervals and rotate synchronously. In the first state, the first locking member is at least used to prevent the first blade from rotating relative to the mounting seat during flight, and the second locking member is at least used to prevent the second blade from rotating relative to the mounting seat during flight.

8. The locking assembly according to claim 7, wherein: The first locking member and the second locking member are symmetrically distributed at two ends of the mounting base.

9. The locking assembly according to claim 7 or 8, characterized in that: When switching from the first state to the second state, the first locking member and the second locking member rotate in opposite directions; when switching from the second state to the first state, the first locking member and the second locking member rotate in opposite directions.

10. The locking assembly according to claim 1, wherein: The locking assembly also includes a rotating shaft and an elastic member, the locking member is rotatably connected to the mounting seat via the rotating shaft, the elastic member is sleeved on the rotating shaft to provide a rotational reset force, one end of the elastic member abuts against the mounting seat, and the other end of the elastic member abuts against the locking member.

11. The locking assembly according to claim 10, wherein: The rotating shaft meets any of the following conditions: A stopper is provided at the first end of the rotating shaft; The second end of the rotating shaft has a stop structure; The rotation axis is substantially parallel to the width direction of the mounting seat; The rotating shaft is arranged on a side of the mounting base away from the blade.

12. The locking assembly according to claim 11, wherein: When the locking member includes a first locking member and a second locking member that are spaced apart: The stopper corresponding to the first locking member and the stopper corresponding to the second locking member are arranged diagonally; and / or The stop structure corresponding to the first locking member and the stop structure corresponding to the second locking member are arranged diagonally.

13. The locking assembly according to claim 1, wherein: The locking member further has a third state. In the third state, the locking member is used to prevent the paddle in the folded state from continuing to fold inward.

14. The locking assembly according to claim 13, wherein: When the locking member includes a first locking member and a second locking member that are spaced apart, in the third state, the tip portion of the blade corresponding to the first locking member and the tip portion of the blade corresponding to the second locking member partially overlap.

15. The locking assembly according to claim 13 or 14, characterized in that: A latching portion is provided on one end of a side surface of the locking member away from the upper surface thereof, the latching portion including a latch recessed toward the upper surface of the locking member, wherein in the third state, the latch is configured to abut against an upper edge of the root of the paddle to prevent the paddle in the folded state from further folding inward; and / or A guide portion is provided on one end of the side surface of the locking member away from the upper surface thereof. The guide portion includes an outwardly opened guide slope. The guide slope is used to guide the blade to enter the first state when it is unfolded.

16. The locking assembly according to claim 1, wherein: The locking member also meets any of the following conditions: The upper surface and / or side surface of the locking member is provided with a weight-reducing structure; The locking member is provided with a handle portion, and the handle portion is used for a user to carry and rotate the locking member; A notch is formed on the upper surface of the locking member, and the notch is used to provide an escape space for the blade to be disassembled and assembled on the mounting seat; A buffer structure is provided at the portion where the locking member contacts the blade; The top and side portions of the locking member enclose a receiving space, and in the first state, the receiving space is used to receive at least a portion of the paddle root.

17. A foldable paddle, characterized in that: include: The locking assembly according to any one of claims 1 to 16; paddle blades; A connecting shaft is used to mount the blade to the mounting seat of the locking assembly.

18. A power device, characterized in that: include: The foldable paddle of claim 17; and The blades are connected to the power assembly via the connecting shaft and rotate under the drive of the power assembly.

19. An aircraft, characterized in that: include: The locking assembly according to any one of claims 1 to 16; or, The foldable paddle of claim 17; or, The power device according to claim 18.

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