Paddle, bearing part, folding paddle, power assembly and unmanned aerial vehicle

Abstract

The utility model provides a paddle, a bearing part, a folding paddle, a power assembly and an unmanned aerial vehicle, the paddle can be installed on the bearing part, the bearing part can be installed on the unmanned aerial vehicle, the paddle is provided with a first locking part, the bearing part is provided with a second locking part matched with the first locking part, and the paddle is rotationally unfolded from a folding state under the action of driving force. The first locking component is locked to the second locking component, and the second locking component is closer to the blade tip position of the unfolded blade compared with the first locking component. The paddles can be mutually locked with the bearing piece after being unfolded, so that the positions of the paddles are kept stable after the paddles are rotated and unfolded, the paddles are kept locked after being unfolded and do not swing or vibrate back and forth, and the rotation stability of the folding paddle is improved; and the probability of arm breakage and unmanned aerial vehicle explosion caused when the rotation frequency of the blades is close to the instability frequency point of the arm is reduced, and then the flight safety of the unmanned aerial vehicle is improved.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to propellers, carriers, folding propellers, power components and unmanned aerial vehicles (UAVs). Background Technology

[0002] Aircraft typically use rotating propellers to provide propulsion. In some related technologies, the blades of folding propellers are not fixed after unfolding. When rotating at high speed, the blades will oscillate horizontally, causing vibration. This vibration can affect the instability frequency of the fuselage arm. When the instability frequency of the arm and the rotational frequency of the propeller blades are close, resonance can occur, leading to arm breakage and potentially causing the aircraft to crash. This method poses a significant risk to flight safety. Utility Model Content

[0003] In view of this, this application proposes a propeller, a carrier, a folding propeller, a power assembly, and a drone, aiming to enable the propeller to lock with the carrier after unfolding, so that the propeller remains locked after unfolding and will not swing back and forth or vibrate, thereby improving the rotational stability of the folding propeller and enhancing the flight safety of the drone.

[0004] The propeller disclosed in the first aspect of this application can be mounted on a carrier, which can be mounted on a drone. The propeller is provided with a first locking component, and the carrier is provided with a second locking component that cooperates with the first locking component. The propeller is rotated and unfolded from a folded state under the action of a driving force, so that the first locking component locks into the second locking component. The second locking component is closer to the tip of the unfolded propeller than the first locking component.

[0005] The second aspect of this application provides a carrier for mounting the propeller blade. The carrier can be mounted on a drone. The propeller blade is provided with a first locking component, and the carrier is provided with a second locking component that cooperates with the first locking component. The propeller blade is rotated and unfolded from a folded state under the action of a driving force, so that the first locking component locks into the second locking component. The second locking component is closer to the tip of the unfolded propeller blade than the first locking component.

[0006] The folding propeller proposed in the third aspect of this application includes a propeller blade and a carrier. The carrier is used to mount the propeller blade and can be mounted on a drone. The propeller blade is provided with a first locking component, and the carrier is provided with a second locking component that cooperates with the first locking component. The propeller blade is rotated and unfolded from a folded state under the action of a driving force so that the first locking component locks into the second locking component. The second locking component is closer to the tip of the unfolded propeller blade than the first locking component.

[0007] The fourth aspect of this application provides a propeller blade that can be mounted on a carrier. The propeller blade is provided with a first locking component, and the carrier is provided with a second locking component that cooperates with the first locking component. During the process of the propeller blade being driven by a first driving device to rotate and unfold from a folded state, the first locking component locks into the second locking component under the action of the centrifugal force generated by the rotation of the propeller blade.

[0008] The fifth aspect of this application provides a carrier capable of supporting a propeller blade and capable of being mounted on a drone. The propeller blade is provided with a first locking component, and the carrier is provided with a second locking component that cooperates with the first locking component. During the process of the propeller blade being rotated and unfolded from a folded state by a first driving device, the first locking component locks into the second locking component under the action of the centrifugal force generated by the rotation of the propeller blade.

[0009] The folding propeller proposed in the sixth aspect of this application includes a propeller blade and a carrier member. The carrier member is capable of supporting the propeller blade and can be installed on a drone. The propeller blade is provided with a first locking member, and the carrier member is provided with a second locking member that cooperates with the first locking member. During the process of the propeller blade being driven by a first driving device to rotate and unfold from a folded state, the first locking member locks into the second locking member under the action of the centrifugal force generated by the rotation of the propeller blade.

[0010] The seventh aspect of this application discloses a power assembly for an unmanned aerial vehicle, comprising a first drive device and a propeller. The first drive device is used to drive the propeller to rotate. The first drive device has a mounting frame capable of supporting the propeller. The propeller is provided with a first locking component, and the mounting frame is provided with a second locking component that cooperates with the first locking component. The propeller rotates and unfolds from a folded state under the action of a driving force, so that the first locking component locks into the second locking component. The second locking component is closer to the tip of the unfolded propeller than the first locking component.

[0011] The power assembly proposed in the eighth aspect of this application includes a first drive device and a folding propeller. The folding propeller includes a blade and a carrier. The blade is pivotally connected to the carrier, and the carrier is connected to the first drive device. The blade is provided with a first locking member, and the carrier is provided with a second locking member that cooperates with the first locking member. The blade is rotated and unfolded from a folded state under the action of a driving force, so that the first locking member locks into the second locking member. The second locking member is closer to the tip of the unfolded blade than the first locking member.

[0012] By adopting the solutions of the first to third and seventh to eighth aspects of this application, a propeller blade with a first locking component and a carrier with a second locking component can be mutually locked after the propeller blade is unfolded. This ensures that the position of the propeller blade remains stable after rotation and unfolding, preventing the propeller blade from swinging or vibrating back and forth after unfolding. This improves the rotational stability of the folding propeller and reduces the probability of arm breakage and drone crash caused by the close proximity of the propeller blade's rotation frequency and the arm's instability frequency, thereby improving the drone's flight safety. In addition, the second locking component on the carrier is closer to the tip of the unfolded propeller blade than the first locking component on the propeller blade. This allows the propeller blade and the carrier to hold each other tightly after the propeller blade is unfolded and locked. The greater the radial centrifugal force of the propeller blade, the tighter the lock between the propeller blade and the carrier is, thus preventing the propeller blade from disengaging from the locked position. This enhances the locking effect of the propeller blade and further improves the drone's flight safety.

[0013] The power assembly proposed in the ninth aspect of this application includes a first drive device and a blade. The first drive device is used to drive the blade to rotate. The first drive device has a mounting frame that can support the blade. The blade is provided with a first locking component. The mounting frame is provided with a second locking component that cooperates with the first locking component. During the process of the blade rotating and unfolding from a folded state under the drive of the first drive device, the first locking component locks into the second locking component under the action of the centrifugal force generated by the rotation of the blade.

[0014] The power assembly proposed in the tenth aspect of this application includes a first drive device and a folding propeller. The folding propeller includes a blade and a carrier. The blade is pivotally connected to the carrier, and the carrier is connected to the first drive device. The blade is provided with a first locking component, and the carrier is provided with a second locking component that cooperates with the first locking component. During the process of the blade rotating and unfolding from a folded state under the drive of the first drive device, the first locking component locks into the second locking component under the action of the centrifugal force generated by the rotation of the blade. The carrier includes a propeller clamp.

[0015] By adopting the solutions of aspects four to six and aspects nine to ten of this application, the propeller rotates under the driving force of the first driving device. The centrifugal force generated during the rotation of the propeller locks the first locking component of the propeller onto the second locking component of the carrier, so that the propeller remains locked after unfolding and will not swing back and forth or vibrate, thereby improving the rotational stability of the folding propeller and reducing the probability of arm breakage and drone crash caused by the close proximity of the rotation frequency of the propeller and the instability frequency of the arm, thus improving the flight safety of the drone. In addition, the propeller can automatically lock with the carrier after unfolding without the need for human intervention, which can reduce the complexity and time consumption of operation, improve the intelligence and automation efficiency of the drone, and thus improve the working efficiency of the drone.

[0016] The unmanned aerial vehicle (UAV) proposed in the eleventh aspect of this application includes a fuselage and the power components described in the foregoing embodiments, with at least one of the power components disposed on the fuselage.

[0017] By adopting the solution of the eleventh aspect of this application, after setting the aforementioned power component on the fuselage, the technical effects brought by the aforementioned power component are achieved. At least the flight safety of the UAV can be improved and the probability of the UAV crashing can be reduced. In some embodiments, the intelligence and automation efficiency of the UAV can also be improved, thereby improving the working efficiency of the UAV. Attached Figure Description

[0018] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a three-dimensional structural diagram of a folding paddle in a folded state according to an embodiment of this application;

[0020] Figure 2 This is a three-dimensional structural diagram of a folding paddle in a fully unfolded state according to an embodiment of this application, wherein the first locking component is a mating protrusion and the second locking component is a limiting groove;

[0021] Figure 3 This is an exploded structural diagram of a folding propeller according to an embodiment of this application;

[0022] Figure 4 This is a cross-sectional view of a folding paddle according to an embodiment of this application;

[0023] Figure 5 This is a longitudinal sectional view of a folding paddle according to an embodiment of this application;

[0024] Figure 6This is another transverse cross-sectional view of a folding paddle proposed in an embodiment of this application, wherein the cross-section of the protrusion is irregularly shaped;

[0025] Figure 7 This is a three-dimensional structural diagram of a carrier component comprising two paddle clamps according to an embodiment of this application;

[0026] Figure 8 This is a three-dimensional structural diagram of a fully unfolded folding paddle according to an embodiment of this application, wherein the first locking component is a limiting groove and the second locking component is a mating protrusion;

[0027] Figure 9 yes Figure 8 A three-dimensional structural diagram of a blade in one embodiment;

[0028] Figure 10 yes Figure 8 A three-dimensional structural schematic diagram of the first carrier in the embodiment;

[0029] Figure 11 This is a three-dimensional structural diagram of a fully unfolded folding propeller according to an embodiment of this application, wherein the first locking component and the second locking component are located in the hollow part between the propeller blade and the carrier;

[0030] Figure 12 yes Figure 11 A side view of the folding paddle in the embodiment;

[0031] Figure 13 yes Figure 11 A three-dimensional structural diagram of a blade in one embodiment;

[0032] Figure 14 yes Figure 11 A three-dimensional structural schematic diagram of the first carrier in the embodiment;

[0033] Figure 15 This is a schematic diagram of the structure of two blades fully deployed in one embodiment of this application;

[0034] Figure 16 This is a schematic diagram of the structure of three blades fully deployed in one embodiment of this application;

[0035] Figure 17 This is a schematic diagram of the structure of four blades fully deployed in one embodiment of this application;

[0036] Figure 18 This is a three-dimensional structural schematic diagram of a power assembly according to an embodiment of this application;

[0037] Figure 19 yes Figure 18 A three-dimensional structural diagram of the exposed first surface of a blade in one embodiment;

[0038] Figure 20 yes Figure 18 A three-dimensional structural diagram of the exposed second surface of a blade in one embodiment;

[0039] Figure 21 This is a three-dimensional structural schematic diagram of the first driving device in an embodiment where the first support component is a mounting frame;

[0040] Figure 22 This is a three-dimensional structural schematic diagram of an aircraft according to an embodiment of this application;

[0041] Figure 23 This is a schematic diagram of the structure of an aircraft with its folding propellers deployed after landing, according to an embodiment of this application.

[0042] Figure 24 This is a schematic diagram of the structure of the control device for an aircraft according to an embodiment of this application;

[0043] Figure 25 This is a schematic diagram of an aircraft proposed in one embodiment of this application.

[0044] Explanation of reference numerals in the attached figures:

[0045] 1000, Folding paddle;

[0046] 100. Blade; 101. Blade tip; 102. Blade root;

[0047] 110. First locking component;

[0048] 121. First blade; 122. Second blade; 123. Third blade; 124. Fourth blade;

[0049] 131. Central axis;

[0050] 200. Load-bearing components;

[0051] 210. Second locking component;

[0052] 221. First load-bearing component; 222. Second load-bearing component;

[0053] 230, propeller clamp; 240, positioning and mounting part; 260, pivot shaft; 270, shaft sleeve;

[0054] 310. Limiting groove; 311. First groove; 312. Second groove;

[0055] 320. Matching protrusions;

[0056] 330. Reception slot;

[0057] 4000, Power assembly; 4010, First drive unit; 4011, Rotary shaft; 4012, Mounting bracket;

[0058] 5000, aircraft;

[0059] 5010. Fuselage; 5011. Arm;

[0060] 5020, Second drive unit; 5030, Mechanical component;

[0061] 6000, Control device; 6010, Processor; 6020, Memory. Detailed Implementation

[0062] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0063] The rotors or propellers on the aircraft 5000 provide thrust, lift, or traction for its flight, enabling it to fly or turn. Among these, the foldable propellers serve as the rotors or propellers of the aircraft 5000. When folded, they occupy little space, are easy to store, transport, and have a wide range of applications. A foldable propeller can include two, three, or four blades. Taking a two-bladed foldable propeller as an example, the blades can rotate freely around a pivot on the propeller clamp. When the foldable propeller is working, the high-speed rotation of the motor causes the two blades to unfold under centrifugal force, forming a straight line.

[0064] In related technologies, the blades of the folding propeller of an aircraft are not fixed after unfolding. When the folding propeller is flying at high speed, the blades are affected by alternating aerodynamic loads on the propeller disk plane. The blades will oscillate horizontally and vibrate, and then repeatedly swing around the unfolded position, showing dynamic instability. The oscillation will amplify the excitation of the blades and affect the instability frequency of the arm. When the instability frequency of the arm and the rotation frequency of the blades are close, resonance will occur, which will lead to the arm breaking and then the aircraft crashing. This method poses a risk to flight safety.

[0065] In related technologies, the blades of the folding propellers of aircraft need to be manually fixed before the blades can be locked to the hub. This method requires human intervention to fix the blades, which is cumbersome and time-consuming, affecting the working efficiency of the aircraft.

[0066] In view of this, the propeller 100, carrier 200, folding propeller 1000, power assembly 4000 and UAV (a type of aircraft 5000) proposed in this application can improve the flight safety performance of aircraft 5000.

[0067] Please see Figure 1 , Figure 2 , Figure 8 and Figure 11 As shown, a folding propeller 1000 according to an embodiment of this application includes a propeller blade 100 and a carrier 200. The carrier 200 is used to mount the propeller blade 100. The carrier 200 provides a certain mounting base for the propeller blade 100, allowing the propeller blade 100 to change position relative to the carrier 200 in different states, and also allowing the propeller blade 100 to be locked in a preset position relative to the carrier 200. Here, the carrier 200 is... Figure 2 The propeller clip 230 is shown in the figure. The folding propeller 1000 in these examples includes one or more blades 100, wherein the plurality of blades 100 includes two, three or four blades 100.

[0068] like Figure 3 , Figure 9 and Figure 13 As shown, the propeller blade 100 is provided with a first locking component 110, such as... Figure 2 , Figure 8 , Figure 12 As shown, the carrier 200 is provided with a second locking component 210 that cooperates with the first locking component 110. Under the action of driving force, the blade 100 moves from... Figure 1 The blade is rotated and unfolded from its folded state, causing the first locking component 110 to lock onto the second locking component 210. The second locking component 210 is closer to the tip 101 of the unfolded blade 100 than the first locking component 110. During the locking process, the first locking component 110 moves a certain distance along with the blade 100, causing the first locking component 110 to move a certain distance closer to the second locking component 210, ultimately locking the first locking component 110 and the second locking component 210 together.

[0069] like Figure 3 , Figure 9 , Figure 13 and Figure 19 As shown, a blade 100 according to an embodiment of this application is capable of being installed on... Figure 2 , Figure 8 , Figure 12 , Figure 21 The carrier 200 is shown. The blade 100 is provided with a first locking component 110, and the carrier 200 is provided with a second locking component 210 that cooperates with the first locking component 110. Under the action of driving force, the blade 100... Figure 1 The blade is rotated out of its folded state so that the first locking component 110 locks into the second locking component 210, wherein the second locking component 210 is closer to the tip 101 of the blade 100 after unfolding than the first locking component 110.

[0070] like Figure 2 , Figure 8 , Figure 12 and Figure 21 As shown, a carrier 200 is provided according to an embodiment of this application. The carrier 200 is used to install, for example... Figure 3 , Figure 9 , Figure 13 and Figure 19 The blade 100 shown has a first locking component 110, and the carrier 200 has a second locking component 210 that cooperates with the first locking component 110. Under the action of driving force, the blade 100 moves from... Figure 1 The blade is rotated out of its folded state to lock the first locking member 110 into the second locking member 210, wherein the second locking member 210 is closer to the tip 101 of the unfolded blade 100 than the first locking member 110. The carrier member 200 here can be... Figure 2 The propeller clip 230 in the middle can also be used as Figure 21 The mounting bracket 4012 is used in these embodiments. The carrier 200 is used to carry one or more blades 100. The plurality of blades 100 includes two, three, four or more blades 100, which can be selected as needed.

[0071] Therefore, as can be seen from the above technical solution, the propeller 100 with the first locking component 110 and the carrier 200 with the second locking component 210 can lock the propeller 100 with the carrier 200 after unfolding, thereby ensuring that the position of the propeller 100 remains stable after it is rotated and unfolded. This prevents the propeller 100 from swinging or vibrating back and forth after unfolding, improves the rotational stability of the folding propeller 1000, and reduces the probability of the arm 5011 breaking or the aircraft 5000 crashing when the rotational frequency of the propeller 100 and the instability frequency of the arm 5011 are close, thereby improving the flight safety of the aircraft 5000.

[0072] The blade 100 of this application, under the action of driving force, moves from... Figure 1 When the blade 100 is rotated and unfolded from its folded state, the first locking component 110 and the second locking component 210 can be locked relatively easily, thereby fixing the position of the blade 100 relative to the carrier 200. No other components need to be pre-locked, and the locking operation of the blade 100 is simple.

[0073] The second locking component 210 on the carrier 200 of this application is closer to the tip 101 of the deployed blade 100 than the first locking component 110 on the blade 100. This allows the blade 100 and the carrier 200 to hold each other tightly after the blade 100 is deployed and locked. The greater the radial centrifugal force of the blade 100, the tighter the blade 100 and the carrier 200 are locked, thus effectively preventing the blade 100 from disengaging from the locked position. This enhances the locking effect of the blade 100 and improves the flight safety of the aircraft 5000.

[0074] Understandably, compared to related technologies where the propeller blades are not fixed after deployment, causing them to swing and affecting the instability frequency of the boom, resonance occurs when the boom instability frequency and the propeller blade rotation frequency are close, leading to boom breakage and crash. The first locking component 110 and the second locking component 210 provided in this application can lock the propeller blades 100 after deployment, thereby keeping the propeller blades 100 in a preset position and preventing them from swinging back and forth. This greatly reduces the probability of crash due to the boom instability frequency being close to the propeller blade rotation frequency.

[0075] Furthermore, the second locking component 210 on the carrier 200 of this application is closer to the tip 101 of the unfolded blade 100 than the first locking component 110 on the blade 100. This allows the blade 100 to be locked in place, and the faster the blade 100 rotates, the tighter it is with the carrier 200. This enhances the locking effect between the blade 100 and the carrier 200, so that the blade 100 can remain in the preset position and not swing back and forth when rotating at high speed. This greatly reduces the probability of the aircraft crashing due to the arm instability frequency being close to the blade rotation frequency.

[0076] Please see Figure 1 , Figure 2 , Figure 8 and Figure 11 As shown, a folding propeller 1000 according to an embodiment of this application includes a propeller blade 100 and a support member 200, the support member 200 being capable of supporting the propeller blade 100. The support member 200 provides a certain mounting base for the propeller blade 100, allowing the propeller blade 100 to change position relative to the support member 200 in different states, and also allowing the propeller blade 100 to be locked in a preset position relative to the support member 200. Here, the support member 200 is... Figure 2 The propeller clip 230 is shown in the figure. The folding propeller 1000 in these examples includes one or more blades 100, wherein the plurality of blades 100 includes two, three, four or more blades 100.

[0077] like Figure 3 , Figure 9 and Figure 13 As shown, the propeller 100 is provided with a first locking component 110, such as... Figure 2 , Figure 8 , Figure 12 As shown, the carrier 200 is provided with a second locking member 210 that cooperates with the first locking member 110, and the blade 100 is driven by the first driving device 4010 (e.g., Figure 18 As the drive unit (shown) rotates from a folded state to unfold, the first locking component 110 locks into the second locking component 210 under the centrifugal force generated by the rotation of the blade 100. The direction of this centrifugal force is from the rotation axis 4011 of the first drive unit 4010 towards a direction away from the rotation axis 4011, for example, from... Figure 21 The direction from the rotating shaft 4011 to the edge of the first drive device 4010.

[0078] like Figure 3 , Figure 9 , Figure 13 and Figure 19 As shown, a blade 100 according to an embodiment of this application is capable of being installed on... Figure 2 , Figure 8 , Figure 12 , Figure 21 The carrier 200 is shown. The blade 100 is provided with a first locking component 110, and the carrier 200 is provided with a second locking component 210 that cooperates with the first locking component 110. During the process of the blade 100 being driven by the first driving device 4010 to rotate and unfold from the folded state, the first locking component 110 locks into the second locking component 210 under the action of the centrifugal force generated by the rotation of the blade 100.

[0079] like Figure 2 , Figure 8 , Figure 12 and Figure 21 As shown, according to an embodiment of this application, a support member 200 is provided. The support member 200 can support a blade 100. The blade 100 is provided with a first locking member 110, and the support member 200 is provided with a second locking member 210 that cooperates with the first locking member 110. During the process of the blade 100 rotating and unfolding from a folded state under the drive of the first driving device 4010, the first locking member 110 locks into the second locking member 210 under the action of the centrifugal force generated by the rotation of the blade 100. Here, the support member 200 can be... Figure 2 The propeller clip 230 in the middle can also be used as Figure 21 The mounting bracket 4012 is used in these embodiments. The carrier 200 is used to carry one or more blades 100. The plurality of blades 100 includes two, three or four blades 100, which can be selected as needed.

[0080] The power source of the first driving device 4010 mentioned above can be electric, pneumatic or hydraulic drive, such as a motor, cylinder, hydraulic cylinder or other device. There is no specific limitation here. As long as it can provide the force to make the blade 100 of this application rotate and unfold, and can continuously drive the blade 100 to rotate, it should be included in the protection scope of this utility model.

[0081] Therefore, as can be seen from the above technical solution, the blade 100 rotates under the driving force of the first drive device 4010. The centrifugal force generated during the rotation of the blade 100 causes the first locking component 110 of the blade 100 to lock onto the second locking component 210 of the carrier 200. This ensures that the blade 100 remains locked after unfolding and will not swing back and forth or vibrate, thereby improving the rotational stability of the folding blade 1000 and reducing the probability of the arm 5011 breaking or the aircraft 5000 crashing when the rotational frequency of the blade 100 and the instability frequency of the arm 5011 are close. This, in turn, improves the flight safety of the aircraft 5000.

[0082] Furthermore, this application can achieve automatic locking between the propeller 100 and the carrier 200 after unfolding without the need for human intervention. The first locking component 110 and the second locking component 210 are automatically locked during the rotation, unfolding and moving process under the action of the first driving device 4010. Therefore, the complexity and time consumption of operation can be reduced, the intelligence and automation efficiency of the aircraft 5000 can be improved, and the working efficiency of the aircraft 5000 can be enhanced.

[0083] Understandably, compared to the folding propellers of aircraft in related technologies, which require manual fixing of the blades to the hub to achieve locking between the blades and the hub, making the operation cumbersome and time-consuming, the propeller 100 of this application can be unfolded under the action of the first drive device 4010. Under the action of the centrifugal force generated by the rotation of the propeller 100, the first locking component 110 and the second locking component 210 are further locked, thereby ensuring that the propeller 100 is in a fixed position relative to the carrier 200 in the unfolded state, without swaying back and forth. The entire process does not require human intervention.

[0084] Furthermore, by adopting the aforementioned embodiments of this application, the torsional mode of the arm 5011 of the aircraft 5000 can be increased. There is no need to thicken or reinforce the arm 5011, nor is it necessary to replace the arm 5011 with a denser material. Simply changing the locking structure between the blade 100 and the carrier 200 can effectively prevent the vibration of the blade 100 from causing the instability frequency of the arm 5011 to drop. It also reduces the probability of the arm 5011 breaking and the aircraft 5000 crashing due to the close proximity of the rotation frequency of the blade 100 and the instability frequency of the arm 5011. This makes the entire aircraft lighter than the folding quick-release propellers in related technologies, and keeps the entire aircraft within a relatively small weight, such as the regulatory weight of 249g. It can also achieve the effects of improving the range, maximum flight speed and maximum flight altitude, which is beneficial for its widespread application in aircraft models with requirements for fuselage weight, range, maximum flight speed and maximum flight altitude.

[0085] The following describes in detail the implementation of the locking structure of the first locking component 110 and the second locking component 210 in the aforementioned examples.

[0086] In some embodiments of this application, the locking structure of the first locking component 110 and the second locking component 210 includes a mechanical locking structure or a magnetic locking structure.

[0087] Among them, the mechanical locking structure includes Figure 3 The limiting groove 310 and mating protrusion 320 shown also include structural forms such as slots and buckles (not shown). The first locking component 110 and the second locking component 210 are respectively selected from one of the corresponding mechanical locking structures. For example, if the first locking component 110 is a limiting groove, then the second locking component 210 is a mating protrusion; if the first locking component 110 is a mating protrusion, then the second locking component 210 is a limiting groove. The mechanical locking structure can enhance the locking between the blade 100 and the carrier 200, prevent the blade 100 from displacing relative to the carrier 200 on its rotational surface after unfolding, improve the effect of the folding propeller 1000 when it rotates and straightens, reduce the small displacement relative to the rotational surface of the blade 100, improve the torsional mode of the arm 5011, and improve the flight safety of the aircraft 5000; achieving the effect of reducing the weight of the whole aircraft, increasing the range and flight speed, and combining the portability of the folding propeller 1000 with the reliability of the straight propeller.

[0088] The magnetic locking structure includes two magnets and a combination of the magnets and a magnetic engaging component. For example, the first locking component 110 and the second locking component 210 are both magnets. Alternatively, one of the first locking component 110 and the second locking component 210 may be a magnet, and the other a magnetic engaging component. This allows the first locking component 110 and the second locking component 210 to achieve magnetic locking under the action of magnetic force when the first locking component 110 approaches the second locking component 210 during the rotation of the propeller 100.

[0089] The following section will further introduce the implementation of the mechanical locking structure when using a matching protrusion and a limiting groove.

[0090] In some embodiments of this application, such as Figure 3 As shown, the mechanical locking structure includes a limiting groove 310 and a mating protrusion 320, wherein the first locking component 110 is the mating protrusion 320 and the second locking component 210 is the limiting groove 310.

[0091] In some alternative examples, the mating protrusion 320 may include one or more, and the limiting groove 310 may include one or more. After the blade 100 is rotated and unfolded, the one or more mating protrusions 320 respectively engage with the one or more limiting grooves 310. That is, one mating protrusion 320 may engage with one limiting groove 310, or multiple mating protrusions 320 may engage with multiple limiting grooves 310.

[0092] In some further examples, the shape of each mating protrusion 320 is adapted to the shape of each limiting groove 310. This allows the mating protrusion 320 and the limiting groove 310 to fit together well, resulting in better clamping during locking and improving locking effect and locking stability.

[0093] For example, the outer peripheral surface of the mating protrusion 320 is curved; correspondingly, the inner peripheral surface of the limiting groove 310 is curved. The smoothness of the curved surfaces reduces the resistance between the mating protrusion 320 and the limiting groove 310 during the movement of the blade 100, allowing the mating protrusion 320 to smoothly enter the limiting groove 310. Simultaneously, the smooth outer surfaces of the limiting groove 310 and the mating protrusion 320 facilitate the user's hand or mechanical force to disengage the mating protrusion 320 from the limiting groove 310. This allows for the disengagement of the first locking component 110 and the second locking component 210 with less force, further reducing the force required for folding and storing the folding propeller 1000, thus facilitating the folding of the propeller 100 and subsequent storage. In these examples, the mating protrusion 320 can also be made shallower, making it easier for the user to apply force to separate the first locking component 110 from the second locking component 210.

[0094] For example, the outer peripheral surface of the mating protrusion 320 is rectangular; correspondingly, the inner peripheral surface of the limiting groove 310 is rectangular. Since the limiting groove 310 and the mating protrusion 320 both have rectangular mating surfaces, they are not easy to fall out after locking, resulting in a good locking effect.

[0095] For example, the cross-section of the mating protrusion 320 is non-rectangular; correspondingly, the cross-section of the limiting groove 310 is also non-rectangular. This non-rectangular shape can be circular, elliptical, or irregular, meaning the cross-sections of the mating protrusion 320 and the limiting groove 310 are respectively circular, elliptical, or irregular. In other examples, the cross-section of the mating protrusion 320 is rectangular; correspondingly, the cross-section of the limiting groove 310 is rectangular. This allows for more flexible shape design of the limiting groove 310 and the mating protrusion 320, enabling the selection of desired shapes and combinations of various shapes as needed; no specific limitations are imposed here. Figure 6 As shown, the cross-section of the mating protrusion 320 is irregular, and the mating protrusion 320 is composed of three protrusions connected together, forming a "trident structure". This improves the wear resistance and structural reliability of the mating protrusion 320. In the "trident structure", at least two of the three protrusions are set at an angle to the other protrusions, so that each protrusion can lock with different positions of the limiting groove 310. The contact area between the limiting groove 310 and the mating protrusion 320 is increased, which can reduce the probability of failure of the locking effect due to excessive rotation and wear. This greatly improves the reliability of the locking between the limiting groove 310 and the mating protrusion 320.

[0096] In some examples, such as Figure 7 , Figure 9 , Figure 14 and Figure 21 As shown, the limiting groove 310 has a first slot 311 on at least one side facing the mating protrusion 320. During the rotation and unfolding of the blade 100, the mating protrusion 320 engages with the limiting groove 310 through the first slot 311. The first slot 311 provides an entrance for the mating protrusion 320 to enter the limiting groove 310 and also provides a certain guiding function for the mating protrusion 320. This allows the blade 100 to move to the first slot 311 first, and then move into the limiting groove 310 through the first slot 311, thus achieving a smooth locking between the limiting groove 310 and the mating protrusion 320.

[0097] In a further example, such as Figure 7 , Figure 9 , Figure 14 and Figure 21As shown, the limiting groove 310 also has a second slot 312 facing the protruding direction of the mating protrusion 320, and the first slot 311 and the second slot 312 are connected. During the rotation and unfolding of the blade 100, the mating protrusion 320 is engaged into the limiting groove 310 through the first slot 311 and the second slot 312. In these examples, the second slot 312 provides an opening for the mating protrusion 320 to enter along its protruding direction, making it easier for the mating protrusion 320 to enter the limiting groove 310 from its protruding direction. The limiting groove 310 also provides the mating protrusion 320 with a capacity corresponding to the degree of protrusion along its protruding direction, so that the mating protrusion 320 can be fully inserted into the limiting groove 310, thereby improving the mating effect between the limiting groove 310 and the mating protrusion 320.

[0098] In some examples, such as Figure 3 , Figure 12 , Figure 19 As shown, the protrusion 320 protrudes along the rotation surface of the blade 100 approximately perpendicular to it. During the rotation of the blade 100, the protrusion 320 mainly contacts the support member 200, which can reduce the intensity of the collision between the blade 100 and the support member 200 during the rotation and unfolding process, and reduce the frictional force between the blade 100 and the support member 200.

[0099] In some examples, combined Figure 3 , Figure 6 , Figure 12 , Figure 15 and Figure 19 As shown, the protrusion 320 aligns with the central axis 131 of the blade root 102 of the blade 100 (as shown). Figure 15 (As shown) is arranged symmetrically along the axis of symmetry. In these examples, when the mating protrusion 320 adopts the above structure, the mating protrusion 320 is easier to process and manufacture, easier to demold, and the centrifugal force on the blade 100 can pass through the geometric center of the mating protrusion 320, so that the blade 100 is more balanced in force after being locked to the bearing 200, and the blade 100 rotates more smoothly.

[0100] In some optional examples, combined Figure 3 and Figure 4 As shown, the limiting groove 310 is a through groove extending through the carrier 200 along a rotational surface approximately perpendicular to the blade 100. This allows the protruding portion of the mating protrusion 320 to be unrestricted by the groove wall of the limiting groove 310, enabling the mating protrusion 320 to extend further into the limiting groove 310, thereby reducing the gap between the blade 100 and the carrier 200. Furthermore, during movement, the mating protrusion 320 also reduces friction with the limiting groove 310, improving the smoothness and efficiency of the blade 100's movement.

[0101] In other examples of this application, combined Figure 8 , Figure 9 and Figure 10 As shown, the mechanical locking structure includes a limiting groove 310 and a mating protrusion 320. The first locking component 110 is the limiting groove 310, and the second locking component 210 is the mating protrusion 320. Where there is no conflict, the structures of the limiting groove 310 and the mating protrusion 320 can refer to the corresponding structures described above, and will not be repeated here.

[0102] In some optional examples, such as Figure 10 As shown, the mating protrusion 320 protrudes approximately perpendicular to the outer surface of the support member 200, with the outer surface facing the blade 100. Therefore, the mating protrusion 320 can be designed to abut against the side of the blade 100. Correspondingly, as... Figure 9 As shown, the limiting groove 310 protrudes along a surface of rotation that is approximately perpendicular to the blade 100. Similarly, the limiting groove 310 can be designed to abut against one side of the support member 200. In this way, when the blade 100 moves relative to the support member 200, at least a portion of the contact surface will be in contact, resulting in more stable movement and reduced noise. At the same time, the mating protrusion 320 can smoothly move into the limiting groove 310, so that after the limiting groove 310 and the mating protrusion 320 are locked together, they can hold each other tightly, and the position between the blade 100 and the support member 200 can remain stable.

[0103] The following describes a scheme in which the first locking component 110 and the second locking component 210 are both located within the receiving slot 330 by adding a receiving slot 330.

[0104] In some embodiments of this application, such as Figure 2 , Figure 6 , Figure 8 and Figure 21As shown, both the first locking component 110 and the second locking component 210 are located within a receiving slot 330. The position of one of the first locking component 110 and the second locking component 210 within the receiving slot 330 can be changed, while the other of the first locking component 110 and the second locking component 210 has a fixed position within the receiving slot 330. Therefore, when the position of the first locking component 110 relative to the receiving slot 330 is changeable, the position of the second locking component 210 relative to the receiving slot 330 is fixed; conversely, when the position of the first locking component 110 relative to the receiving slot 330 is fixed, the position of the second locking component 210 relative to the receiving slot 330 can be changed. The first locking component 110 or the second locking component 210, which can change position, can slide along the receiving groove 330, so that under the guidance of the receiving groove 330, it can smoothly enter the corresponding second locking component 210 or the first locking component 110 which is in a fixed position, thereby effectively improving the efficiency of the movement of the blade 100 and improving the efficiency and stability of the locking between the blade 100 and the carrier 200.

[0105] In some examples, such as Figure 2 , Figure 6 , Figure 8 and Figure 21 As shown, the position of the first locking component 110 within the receiving groove 330 can be changed, while the position of the second locking component 210 within the receiving groove 330 is fixed. That is, in these examples, both the receiving groove 330 and the second locking component 210 are mounted on the carrier 200, while the first locking component 110 is mounted on the blade 100. Under the action of driving force (or centrifugal force), the blade 100 can cause the first locking component 110 to slide along the receiving groove 330 and change position, thereby moving to the position of the second locking component 210 to achieve locking between the first locking component 110 and the second locking component 210.

[0106] In some further examples, such as Figure 3 , Figure 21 As shown, the second locking component 210 is closer to the tip 101 of the deployed blade 100 than the rest of the receiving groove 330. Therefore, when the first locking component 110 moves to engage with the second locking component 210, the engagement position is even closer to the tip 101 of the deployed blade 100. Thus, during the high-speed rotation of the blade 100, the blade 100 is constantly subjected to centrifugal force, and the first locking component 110 will move further toward the second locking component 210, resulting in a tighter engagement. The second locking component 210 is a small slot in the receiving groove 330 near the tip 101 of the deployed blade 100, allowing the first locking component 110 to be received within it after the blade is deployed.

[0107] In some further examples, such as Figure 3 , Figure 21 As shown, the second locking component 210 is located within the receiving groove 330 in a first specific direction, which is the direction of the tip 101 of the unfolded blade 100. Therefore, in these examples, the limitation on the position of the second locking component 210 also ensures that the locking position of the first locking component 110 and the second locking component 210 is closer to the tip 101 of the unfolded blade 100. This allows the first locking component 110 to move further toward the second locking component 210 during high-speed rotation of the blade 100, resulting in a tighter lock between them.

[0108] In other examples, the position of the second locking member 210 within the receiving groove 330 can be changed, while the position of the first locking member 110 within the receiving groove 330 is fixed. Correspondingly, in these examples, the blade 100 is provided with a receiving groove 330 (not shown in the figure), and the first locking member 110 is provided on the blade 100, while the second locking member 210 is provided on the carrier 200. When the blade 100 moves relative to the carrier 200, the position of the second locking member 210 relative to the receiving groove 330 changes.

[0109] Furthermore, the locking positions of the first locking component 110 and the second locking component 210 are further away from the tip 101 of the deployed blade 100 compared to the rest of the receiving groove 330. Therefore, when the first locking component 110 moves to lock with the second locking component 210, the locking position is even further away from the tip 101 of the deployed blade 100. During the high-speed rotation of the blade 100, the first locking component 110 will lock even more tightly with the second locking component 210.

[0110] In some further examples, the locking positions of the first locking member 110 and the second locking member 210 are located in a second specific direction within the receiving groove 330, which is the opposite direction to the direction of the tip 101 of the unfolded blade 100.

[0111] Of course, in this application, the receiving slot 330 may not be provided; instead, a hollow space may be reserved. In these examples, combined with Figure 11 , Figure 12 , Figure 13 and Figure 14As shown, both the first locking component 110 and the second locking component 210 are located in the hollow portion between the blade 100 and the carrier 200. In these examples, when the blade 100 rotates relative to the carrier 200, the first locking component 110 moves within the hollow portion and gradually moves into the second locking component 210, thereby making the structural arrangement of the blade 100 and the carrier 200 lighter and simpler.

[0112] The following describes the structural implementation of the blade 100 in this application when it is fully deployed.

[0113] In some embodiments of this application, the blade 100 from Figure 1 Rotate from folded state to Figure 2 After the blade 100 is fully deployed, the first locking component 110 locks into the second locking component 210. That is, the first locking component 110 can only lock into the second locking component 210 after the blade 100 is fully deployed.

[0114] In a specific example, the second locking component 210 is closer to the tip 101 of the fully deployed blade 100 than the first locking component 110. That is, the position of the second locking component 210 on the support member 200 determines the final locking position between the support member 200 and the blade 100. This locking position is closer to the tip 101 of the fully deployed blade 100 and is set in the direction of the centrifugal force acting on the blade 100. Therefore, after the first locking component 110 locks into the second locking component 210, even if the blade 100 rotates at high speed, the radial centrifugal force acting on the blade 100 will cause the first locking component 110 to further press against the fixed second locking component 210. Thus, the first locking component 110 and the second locking component 210 are locked more tightly at the aforementioned locking position, and the first locking component 110 will not disengage from the second locking component 210 in the direction of the centrifugal force acting on the blade 100.

[0115] In some embodiments of this application, such as Figure 15 , Figure 16 and Figure 17 As shown, the blades 100 include multiple blades. After rotating from a folded state to full deployment, the multiple blades 100 are distributed in a centrally symmetrical structure. The multiple blades 100 can include two, three, or four, and may be more if conditions permit. The centrally symmetrical distribution of the blades 100 allows for more balanced force distribution during high-speed rotation when fully deployed, continuously providing stable lift, tension, or traction.

[0116] Furthermore, after the multiple blades 100 rotate from a folded state to a fully unfolded state, the multiple blades 100 are driven by a first drive device 4010 (such as...) for driving the rotation of the blades 100. Figure 18 The rotating shaft 4011 (as shown) is centrally symmetrically distributed with reference to the reference. The first drive device 4010 can provide the required driving force for the rotation of the blades 100, such as radial centrifugal force and tangential driving force, so that each blade 100 can be rotated out of the folded state and the first locking member 110 can be locked to the second locking member 210. The first drive device 4010 can also drive the entire folding propeller 1000 to rotate, so that each blade 100 can rotate together as a whole during operation, thereby converting the driving force of the first drive device 4010 into the power provided by the blades 100, such as lift, traction or pulling force.

[0117] In some embodiments of this application, such as Figure 15 , Figure 16 and Figure 17 As shown, the propeller blades 100 include multiple blades. After rotating from a folded state to fully unfolded, the included angle between any two adjacent blades 100 is the same. This makes the arrangement of the blades 100 more uniform, and the force on the blades 100 is more balanced during operation. It should be noted that the included angle here is mainly the angle formed by the intersection of the central axis 131 of the root 102 of two adjacent blades 100 with the rotation axis 4011 around which each blade 100 rotates during its rotation.

[0118] For example, such as Figure 15 As shown, there are two blades 100, and the included angle between two adjacent blades 100 is 180 degrees. When the two blades 100 are fully deployed, they form a straight propeller, which has a simple structure and is easy to control.

[0119] For example, such as Figure 16 As shown, there are three blades 100, and the angle between any two adjacent blades 100 is 120 degrees. When all three blades 100 are fully extended, the first locking component 110 on each blade 100 engages with the second locking component 210 on the corresponding support member 200. The three blades 100 and the support member 200 form a rotating unit that rotates stably around a fixed axis. For example, the three blades 100 can be designated as the first blade 121, the second blade 122, and the third blade 123. The fully extended first blade 121, second blade 122, and third blade 123... Figure 16 and Figure 18 The first driving device 4010 shown has a rotating shaft 4011 that rotates on the axis, and is in force balance during rotation.

[0120] For example, such as Figure 17As shown, there are four blades 100, and the angle between any two adjacent blades 100 is 90 degrees. More blades 100 make it easier to maintain balance when fully extended, resulting in more even force distribution and potentially extending the blades' lifespan. The angle of rotation required to move from a folded state to a fully extended state may also be smaller. The four blades 100 in these examples are designated as blade 121, blade 122, blade 123, and blade 124, respectively. The fully extended blades 121, 122, 123, and 124 are... Figure 17 and Figure 18 The first driving device 4010 shown has a rotating shaft 4011 that rotates on the axis, and is in force balance during rotation.

[0121] The specific structural forms of the carrier 200 and the blade 100 are described below.

[0122] In some embodiments of this application, combined with Figure 2 and Figure 15 As shown, the blade 100 includes a first blade 121, and the carrier 200 includes a first carrier 221, the first carrier 221 being pivotally connected to the first blade 121; as Figure 18 As shown, the first support member 221 is used to connect with the first driving device 4010. The first blade 121 is provided with a first locking member 110, and the first support member 221 is provided with a second locking member 210 that cooperates with the first locking member 110 of the first blade 121. After the first blade 121 is rotated and unfolded, the first locking member 110 of the first blade 121 locks with the second locking member 210 of the first support member 221. The first driving device 4010 is used to drive the first blade 121 to rotate. In these examples, the first blade 121 can rotate under the drive of the first driving device 4010, thereby moving the first blade 121 relative to the first support member 221, and then moving until the first locking member 110 and the second locking member 210 lock together.

[0123] In a further example, combining Figure 2 and Figure 15As shown, the propeller 100 also includes a second propeller 122. The first support member 221 is pivotally connected to the second propeller 122. The second propeller 122 is provided with a first locking member 110, and the first support member 221 is provided with a second locking member 210 that cooperates with the first locking member 110 of the second propeller 122. After the second propeller 122 is rotated and unfolded, the first locking member 110 of the second propeller 122 locks into the second locking member 210 of the first support member 221. The first driving device 4010 is also used to drive the second propeller 122 to rotate. In these examples, the first driving device 4010 not only drives the first propeller 121 to rotate, but also drives the second propeller 122 to rotate, so that both the first propeller 121 and the second propeller 122 can rotate relative to the first support member 221 and move to the unfolded state. In the fully unfolded state, the first locking members 110 on the first propeller 121 and the second propeller 122 respectively lock into the corresponding second locking members 210 on the support member 200.

[0124] In some further examples, combined Figure 2 and Figure 5 As shown, the carrier 200 also includes a second carrier 222, which is pivotally connected to the first blade 121. The first blade 121 is provided with a first locking member 110, and the second carrier 222 is provided with a second locking member 210 that cooperates with the first locking member 110 of the first blade 121. After the first blade 121 is rotated and unfolded, the first locking member 110 of the first blade 121 locks into the second locking member 210 of the second carrier 222. In these examples, the first blade 121 is provided with a first locking member 110 that cooperates with the second locking member 210 on the first carrier 221 and a first locking member 110 that cooperates with the second locking member 210 on the second carrier 222. Thus, under the action of the first driving device 4010, the first blade 121 can rotate and unfold simultaneously relative to the first carrier 221 and the second carrier 222 until it is fully unfolded, at which point the first blade 121 locks into the first carrier 221 and the second carrier 222 respectively. As can be seen, the rotational locking structure of the first blade 121 in these examples is more robust, forming double redundancy, which effectively prevents the blade 100 from failing to achieve the straightening effect if one of the first locking components 110 or the second locking component 210 is structurally deformed or damaged.

[0125] In some specific examples, combined Figure 3 and Figure 15As shown, the first support member 221 and the second support member 222 are located on different sides of the first blade 121. Thus, the first blade 121 is sandwiched between the first support member 221 and the second support member 222. During the rotation and movement of the first blade 121, it can move relative to the first support member 221 and the second support member 222 respectively and lock with them, making the engagement more convenient.

[0126] Furthermore, combining Figure 3 and Figure 15 As shown, the first support member 221 and the second support member 222 are located on opposite sides of the first blade 121, and a fixed space is formed between the first support member 221 and the second support member 222, which allows the first blade 121 to move quickly relative to the first support member 221 and the second support member 222, and the blade 100 is not easily separated from each support member 200.

[0127] Furthermore, combining Figure 3 and Figure 15 As shown, the first support member 221 is located on the first surface of the first blade 121, and the second support member 222 is located on the second surface of the first blade 121. For example, the first surface can be the lower surface of the first blade 121, and the second surface can be the upper surface of the first blade 121; in other examples, depending on the installation position of the folding propeller 1000 or the flight attitude of the aircraft 5000, the orientation of the blade 100 and the support member 200 will be different, and the first surface can also be the rear surface of the first blade 121, and the second surface can be the front surface of the first blade 121.

[0128] In some embodiments, such as Figure 2 , Figure 8 , Figure 11 As shown, both the first support member 221 and the second support member 222 are propeller clamps 230. In these examples, the propeller blade 100 is mounted between the two propeller clamps 230, thus forming the main structure of the folding propeller 1000. In specific examples, such as... Figure 5 , Figure 10 , Figure 14 As shown, a rotating sleeve 270 protruding towards the second supporting member 222 is provided on the first supporting member 221. The rotating shaft 4011 of the first driving device 4010 can be installed in the rotating sleeve 270, enabling the first driving device 4010 to drive the first supporting member 221 to rotate. The first supporting member 221 can further transmit the driving force to the blade 100 pivotally connected to the first supporting member 221, causing the blade 100 to straighten and change its state. In this case, the central axis of the rotating sleeve 270 coincides with the central axis of the rotating shaft 4011. The rotating sleeve 270 can also further cooperate with the second supporting member 222 to achieve positioning between the first supporting member 221 and the second supporting member 222. In a specific example, such as... Figure 3As shown, the second support member 222 is provided with a positioning mounting portion 240 extending toward the first support member 221, such as... Figure 5 As shown, a bushing is fitted on the outer side of the positioning and mounting part 240, which serves as the pivot shaft 260 of the blade 100. A slot is provided on the first support member 221, so that the positioning and mounting part 240 fitted with the bushing can be inserted into the slot, further realizing the limiting of the first support member 221 and the second support member 222, so that there is space between the first support member 221 and the second support member 222 to accommodate the blade 100 and space for the blade 100 to rotate and change its posture. At the same time, the blade 100 can be pivotally connected to the outside of the bushing, so that the blade 100 can rotate relative to the first support member 221 and the second support member 222. When the blade 100 rotates to fully unfold, the first locking member 110 on the blade 100 locks with the second locking member 210 on the first support member 221 and the second support member 222 respectively, so that the position of the blade 100 relative to the first support member 221 and the second support member 222 is fixed.

[0129] In other examples, the first carrier 221 is not the propeller clip 230, combined with Figure 18 and Figure 21 As shown, the first support member 221 is a mounting bracket 4012 for the first drive device 4010 used to drive the blade 100 to rotate, and the second support member 222 is a blade clamp 230. In these examples, the folding blade 1000 includes only one blade clamp 230, and the blade 100 is directly connected to the mounting bracket 4012 and rotates and unfolds relative to the mounting bracket 4012 until it is fully unfolded and locked onto the mounting bracket 4012. In specific examples, such as... Figure 19 As shown, a mating protrusion 320 protruding towards the mounting bracket 4012 is provided on the first surface of the blade 100, while a limiting groove 310 is provided on the mounting bracket 4012; Figure 20 As shown, a mating protrusion 320 can also be provided on the second surface of the blade 100, while at the same time... Figure 18The propeller clamp 230 is provided with a corresponding limiting groove 310. The propeller clamp 230 not only prevents the propeller blade 100 from detaching from the mounting frame 4012, but also locks with the propeller blade 100. This allows the propeller blade 100 of the entire folding propeller 100 to have locking structures on both surfaces, achieving double-layer locking and effectively improving the reliability of locking and the stability of relative position after the propeller blade 100 is unfolded. Of course, in other examples, the limiting groove 310 that mates with the propeller blade 100 can be provided only on the mounting frame 4012, without providing the limiting groove 310 that mates with the propeller blade 100 on the propeller clamp 230. This eliminates the need for the mating protrusion 320 on the second surface of the propeller blade 100, making the structure of the folding propeller 1000 simpler and the contact between the propeller clamp 230 and the propeller blade 100 tighter. These examples all fall within the protection scope of this application. Specifically, the first surface of the blade 100 is the lower surface of the blade 100, and the second surface of the blade 100 is the upper surface of the blade 100. It should be noted that... Figure 19 and Figure 20 The description uses the example of different shapes for the mating protrusions 320 on the upper and lower surfaces of the blade 100. In other embodiments, the shapes of the mating protrusions 320 on the upper and lower surfaces of the blade 100 can be the same. For example, the mating protrusions 320 on both the upper and lower surfaces of the blade 100 can be... Figure 19 In the embodiment shown, the structure of a single protrusion, and the mating protrusions 320 on the upper and lower surfaces of the blade 100 can also be... Figure 20 The "trident" structure shown in the illustrated embodiment is not limited in this application embodiment.

[0130] In the example of the aforementioned carrier 200 in this application, which includes a first carrier 221 and a second carrier 222, combined with Figure 3 , Figure 8 , Figure 11 , Figure 15 and Figure 18As shown, the blade 100 also includes a second blade 122. The second support member 222 is pivotally connected to the second blade 122. The second blade 122 is provided with a first locking member 110. The second support member 222 is provided with a second locking member 210 that cooperates with the first locking member 110 of the second blade 122. After the second blade 122 is rotated and unfolded, the first locking member 110 of the second blade 122 locks into the second locking member 210 of the second support member 222. The first drive device 4010 is also used to drive the second blade 122 to rotate. In these examples, the first drive device 4010 not only drives the first blade 121 to rotate, but also drives the second blade 122 to rotate, thereby enabling both the first blade 121 and the second blade 122 to rotate relative to the first support member 221 and the second support member 222 and move to the deployed state. In the fully deployed state, the first locking member 110 on the first blade 121 locks with the corresponding second locking member 210 on the first support member 221, and the first locking member 110 on the second blade 122 locks with the corresponding second locking member 210 on the first support member 221. This allows the straight propeller composed of the two blades 100 to be reliably deployed and is less likely to cause flight force imbalance due to the breakage of one of the blades 100.

[0131] In an alternative example, similar to the arrangement of the first blade 121, the first support member 221 and the second support member 222 are located on different sides of the second blade 122. For example, the first support member 221 and the second support member 222 are located on opposite sides of the second blade 122; or, the first support member 221 is located on the first surface of the second blade 122, and the second support member 222 is located on the second surface of the second blade 122. This creates a fixed space between the first support member 221 and the second support member 222, allowing the second blade 122 to move rapidly relative to the first support member 221 and the second support member 222, respectively, without easily detaching the second blade 122 from the respective support members 200. The definition of the first and second surfaces can be referred to the preceding description and will not be repeated here.

[0132] The following describes the source and type of driving force in the aforementioned embodiment where the blade 100 rotates and unfolds from a folded state under the action of driving force.

[0133] In some embodiments of this application, the driving force is a first driving force, which includes a tangential driving force. Under the action of the tangential driving force, the blade 100 rotates and unfolds from a folded state, so that the first locking member 110 locks into the second locking member 210. The tangential direction is the direction of the tangent to the circumferential surface of the blade 100's rotation. Thus, under the action of the tangential driving force, the blade 100 in the folded state is pulled and its position is changed, achieving unfolding, and locking between the blade 100 and the carrier 200 can be achieved during the unfolding process. Wherein, the blade 100 rotates and unfolds from a folded state under the action of the tangential driving force, so that the first locking member 110 locks into the second locking member 210. The locking structure between the first locking member 110 and the second locking member 210 can be a mechanical locking structure or a magnetic locking structure.

[0134] In a further embodiment, the first driving force includes a radial driving force. The blade 100 translates under the action of the radial driving force so that the first locking member 110 locks into the second locking member 210. The radial direction is from the center of the circumferential surface of the blade 100 to the edge of the circumferential surface. Under the action of the radial driving force, the blade 100 will move further along the radial direction, thereby further locking the first locking member 110 to the second locking member 210. That is, the greater the radial driving force, the tighter the first locking member 110 and the second locking member 210 can be locked. Under the action of a radial driving force, the blade 100 will move further radially, thereby further locking the first locking component 110 to the second locking component 210. The locking structure applicable between the first locking component 110 and the second locking component 210 is a mechanical locking structure, such as a mechanical locking structure with a limiting groove and a mating protrusion. Under the action of a radial driving force, the blade 100 will move further radially, so that the first locking component 110 on the blade 100 can be translated into the locking space of the matching second locking component 210 to achieve a tight lock.

[0135] In some alternative examples, the first driving force is a force applied by a hand, that is, by applying the aforementioned tangential and radial driving forces by hand. After the force is applied by hand, the first locking member 110 and the second locking member 210 can be unlocked relatively easily without deformation of the propeller 100.

[0136] In some alternative examples, the first driving force is mechanical component 5030 (e.g., Figure 23 The force applied (as shown). For example, the first driving force is... Figure 23The mechanical component 5030 is driven by the second drive device 5020, which applies a force. The second drive device 5020 can be a motor, cylinder, hydraulic cylinder, or other similar device; no specific limitation is made here. Any power mechanism that can provide the force to rotate and unfold the propeller 100 and continuously drive its rotation should be included within the scope of protection of this utility model. The mechanical component 5030 can be a rotary folding structure. The second drive device 5020 and the mechanical component 5030 can be mounted on the aircraft 5000, or on the airport / parking platform / takeoff and landing platform of the aircraft 5000.

[0137] In some alternative examples, the first driving force is the centrifugal force generated during the rotation of the blade 100. For example, while the blade 100 is rotated and unfolded by the first driving device 4010, it can be straightened by a radial force, which can reduce the number of hardware and cost.

[0138] The specific movements of the first locking component 110 and the second locking component 210 during the rotation of the blade 100 are described below.

[0139] In some embodiments of this application, during the rotation of the blade 100, the blade 100 drives the first locking member 110 to move, so that the first locking member 110 locks onto the second locking member 210, and the position of the second locking member 210 remains unchanged during the movement of the first locking member 110. Thus, in the initial stage of rotation, the blade 100 moves and changes position relative to the support member 200, while the support member 200 remains in a relatively fixed position relative to the blade 100.

[0140] In some embodiments of this application, during the rotation of the blade 100, the blade 100 drives the first locking member 110 to translate, so that the first locking member 110 locks onto the second locking member 210. Thus, under the action of radial driving force or centrifugal force generated by its own rotation, the blade 100 can cause the first locking member 110 to translate a certain distance radially, thereby making the first locking member 110 and the second locking member 210 lock more tightly.

[0141] In some embodiments of this application, reference is made to Figure 1 and Figure 2During the rotation of the propeller 100, the propeller 100 drives the first locking component 110 to move, so that the first locking component 110 is in an unlocked position and a locked position. When the first locking component 110 is in the unlocked position, the distance of the first locking component 110 relative to the rotation axis 4011 of the first driving device 4010 is different from the distance of the first locking component 110 relative to the rotation axis 4011 when the first locking component 110 is in the locked position. That is to say, after the first locking component 110 moves with the propeller 100, it can be thrown to a farther position when subjected to driving force or centrifugal force, so that the distance of the first locking component 110 relative to the rotation axis 4011 is different in the locked position and the unlocked position.

[0142] In some further examples, combined Figure 1 , Figure 2 , Figure 3 and Figure 18 As shown, when the first locking component 110 is in the unlocked position, the distance between the first locking component 110 and the rotation axis 4011 of the first driving device 4010 is less than the distance between the first locking component 110 and the rotation axis 4011 when the first locking component 110 is in the locked position. Therefore, when the blade 100 is subjected to the driving force from the first driving device 4010, the first locking component 110 can be thrown from a position close to the rotation axis 4011 to a position away from the rotation axis 4011 under the action of the driving force. This allows the blade 100 to unfold while the first locking component 110 moves toward and locks towards the second locking component 210 of the support member 200.

[0143] In some embodiments, such as Figure 3 As shown, the first locking component 110 is located at the root 102 of the blade 100, so that the first locking component 110 can also change position when the root 102 moves, thereby making the second locking component 210 that cooperates with the first locking component 110 more compact, which is beneficial to reduce the overall structure of the carrier 200.

[0144] In some embodiments, such as Figure 2 As shown, the second locking component 210 is located near the outer edge of the carrier 200, so that after the first locking component 110 and the second locking component 210 are engaged, the first locking component 110 can lock the carrier away from the outer edge. Figure 4 One side of the pivot 260 shown is locked.

[0145] In some embodiments of this application, reference is made to Figure 1 and Figure 2During the rotation of the propeller 100, the propeller 100 drives the first locking component 110 to move, so that the first locking component 110 is in an unlocked position and a locked position. The distance of the first locking component 110 relative to the pivot axis 260 of the carrier 200 when the first locking component 110 is in the unlocked position is different from the distance of the first locking component 110 relative to the pivot axis 260 when the first locking component 110 is in the locked position. For example, Figure 4 and Figure 5 As shown, the blade 100 is pivotally connected to the carrier 200 via a pivot shaft 260. The specific structure of the pivot shaft 260 can be found in the previous description and will not be repeated here. Therefore, during the pivoting process of the blade 100, the distance between the first locking component 110 and the pivot shaft 260 can change.

[0146] For example, in a specific example, when the first locking component 110 is in the unlocked position, the distance between the first locking component 110 and the pivot axis 260 of the carrier 200 is less than the distance between the first locking component 110 and the pivot axis 260 of the carrier 200 when the first locking component 110 is in the locked position. This allows the first locking component 110 to be thrown further under the driving force during the unfolding of the blade 100. In these examples, the mating holes on the blade root 102 corresponding to the pivot axis 260 are non-circular holes, such as elliptical holes or oblong holes. When these non-circular holes are fitted with the pivot axis 260, a partial gap can be achieved between them. When different parts of the mating holes are in contact with the pivot axis 260, different distances between the first locking component 110 and the pivot axis 260 can be achieved.

[0147] In some embodiments of this application, during the rotation of the blade 100, the blade 100 drives the first locking member 110 to move, so that the first locking member 110 is in an unlocked position and a locked position. The locked position is further away from the pivot axis 260 of the carrier member 200 than the unlocked position, wherein the blade 100 is pivotally connected to the pivot axis 260 of the carrier member 200. This makes the first locking member 110 and the second locking member 210, which are in the locked position, closer to the edge where the driving force is applied after locking, resulting in a better locking effect.

[0148] In some embodiments of this application, in the aforementioned example where the first locking member 110 locks into the second locking member 210 under the centrifugal force generated by the rotation of the blade 100, the second locking member 210 is closer to the tip 101 of the deployed blade 100 than the first locking member 110. This allows for a tighter fit between the first locking member 110 and the second locking member 210 during the high-speed rotation of the blade 100.

[0149] In some embodiments of this application, the carrier 200 includes, for example: Figure 21 The mounting bracket 4012 of the first drive unit 4010 shown or as Figure 2 The propeller clamp 230 shown includes a first drive device 4010 for driving the propeller blade 100 to rotate. The first drive device 4010 provides the driving force for the rotation of the propeller blade 100 and also provides the required driving force for locking the propeller blade 100. Thus, the propeller blade 100 can achieve simultaneous rotation and locking in the initial stage of operation, and after locking, it forms an integral part with the carrier 200, rotating together at the required speed under the action of the first drive device 4010.

[0150] In some embodiments of this application, the blades 100 include multiple blades, which, in a folded state, such as Figure 1 As shown, the tips 101 of the multiple blades 100 are aligned. In other examples, the tips of the multiple blades 100 overlap. This allows the blades 100 to be retracted together, reducing the space occupied by the blades 100, facilitating storage, and effectively protecting each blade 100 that is not in operation, preventing it from extending outwards in multiple directions and colliding with external objects, thus causing damage.

[0151] In some embodiments of this application, the blades 100 include multiple blades. With the first locking member 110 locked to the second locking member 210, the multiple blades 100 are arranged in a centrally symmetrical manner. That is, the second locking members 210 of this application are uniformly arranged relative to a certain rotation center. When the first locking member 110 of each blade 100 is locked to its corresponding second locking member 210, each blade 100 unfolds and is arranged in a centrally symmetrical manner, facilitating the maintenance of force balance during subsequent rotation.

[0152] In some embodiments of this application, after the propeller blade 100 is installed on the aircraft 5000, the propeller blade 100 can be rotated from a folded state to an unfolded state under the action of a driving force. In these examples, the propeller blade 100 can be individually installed on a specific part of the aircraft 5000, thereby changing its own state under the action of a driving force, and thus realizing unfolding and locking. In these examples, the driving force is the force applied by a hand; or, the driving force is a mechanical component 5030 (such as...). Figure 23 The force applied (as shown); or, the driving force is the centrifugal force generated during the rotation of the blade 100. For example... Figure 23 As shown, the driving force is the force applied to the mechanical component 5030 by the second driving device 5020. The structure of the second driving device 5020 is as described above and will not be repeated here.

[0153] In a further example, after the blade 100 is mounted to the aircraft 5000, the blade 100 can rotate about a pivot axis 260. This pivot axis 260 can be the aforementioned pivot axis 260 provided on the carrier 200, that is, the pivot axis 260 on the carrier 200 used to mount the blade 100, in which case the blade 100 is mounted to the aircraft 5000 through the carrier 200; this pivot axis 260 can also be a screw, in which case the blade 100 does not need to cooperate with the blade clamp 230, but is connected to a specific position on the aircraft 5000 by a screw, thereby achieving both rotation relative to the pivot axis 260 and fixation relative to the aircraft 5000, so that the blade 100 does not detach from the aircraft 5000.

[0154] In some examples, after the propeller 100 is installed on the aircraft 5000, the aircraft 5000 can start working. In this case, the propeller 100 does not need to adjust its attitude before the aircraft 5000 starts working. Instead, after the aircraft 5000 starts working, with the operation of the drive device on the aircraft 5000, the propeller 100 is rotated and deployed by the driving force or centrifugal force, and automatically locks. This saves the start-up preparation time of the aircraft 5000, saves manual operation, and greatly improves the intelligence of the aircraft 5000.

[0155] In some embodiments of this application, the first locking component 110 is disengaged from the second locking component 210 by the action of the second driving force. Therefore, when the propeller 100 is not in operation, or when the aircraft 5000 stops flying, the first locking component 110 disengages from the second locking component 210 under the action of the second driving force, allowing the propeller 100 to be in a folded state for easy storage later.

[0156] In some alternative examples, the second driving force includes a tangential driving force that causes the blade 100 to rotate, thereby disengaging the first locking member 110 from the second locking member 210. The tangential direction is the direction of the tangent to the circumferential surface of the blade 100's rotation. The direction of the tangent of the second driving force should be designed to be opposite to that of the first driving force, thereby unlocking or locking the first locking member 110 relative to the second locking member 210.

[0157] In some alternative examples, the second driving force includes a radial driving force that causes the blade 100 to translate under the action of the radial driving force to disengage the first locking member 110 from the second locking member 210. The radial direction is the direction from the center of the circumferential surface of the blade 100 to the edge of the circumferential surface.

[0158] In some alternative examples, the second driving force is the force applied by a human hand. By turning the paddle 100 by hand, the first locking component 110 can be unlocked relative to the second locking component 210, which is convenient, quick, and flexible in applying force.

[0159] In some alternative examples, the second driving force is mechanical component 5030 (e.g., Figure 23 The force applied (as shown). For example, the second driving force is... Figure 23 The mechanical component 5030 shown is driven by the second drive device 5020, which applies force. Applying force through the mechanical component 5030 can save manpower and the force is applied more evenly.

[0160] The power assembly 4000 proposed in this application will now be described.

[0161] According to the first aspect of the power assembly 4000 proposed in the embodiments of this application, combined with Figure 18 and Figure 21 It includes a first drive unit 4010 and a blade 100. The first drive unit 4010 is used to drive the blade 100 to rotate. The first drive unit 4010 has a mounting bracket 4012, which can support the blade 100, such as... Figure 19 As shown, the propeller blade 100 is provided with a first locking component 110, such as... Figure 21 As shown, the mounting bracket 4012 is provided with a second locking member 210 that cooperates with the first locking member 110. The blade 100 is rotated and unfolded from a folded state under the action of a driving force, so that the first locking member 110 locks into the second locking member 210. The second locking member 210 is closer to the tip 101 of the unfolded blade 100 than the first locking member 110. In these examples, the number of second locking members 210 on the mounting bracket 4012 corresponds one-to-one with the number of first locking members 110 on the blade 100.

[0162] The power assembly 4000 according to the second aspect of the embodiments of this application includes Figure 18 The first drive unit 4010 shown and Figure 2 , Figure 8 , Figure 11 The folding paddle 1000 shown is, for example Figure 1 , Figure 2 , Figure 8 and Figure 11 As shown, the folding propeller 1000 includes a blade 100 and a carrier 200, with the blade 100 pivotally connected to the carrier 200. Figure 18 As shown, the carrier 200 is connected to the first driving device 4010; as Figure 19 As shown, the propeller blade 100 is provided with a first locking component 110, which is combined with... Figure 2 and Figure 3As shown, the carrier 200 is provided with a second locking member 210 that cooperates with the first locking member 110. The blade 100 is rotated and unfolded from a folded state under the action of a driving force, so that the first locking member 110 locks into the second locking member 210. The second locking member 210 is closer to the tip 101 of the unfolded blade 100 than the first locking member 110. The carrier 200 includes a blade clamp 230. In these examples, the number of second locking members 210 on the blade clamp 230 corresponds one-to-one with the number of first locking members 110 on the blade 100.

[0163] Therefore, in the above two embodiments of the power components 4000, regardless of whether the blade 100 is locked with the blade clamp 230 or the blade 100 is locked with the mounting bracket 4012, the locking position of the first locking component 110 and the second locking component 210 is ultimately determined by the position of the second locking component 210. The second locking component 210 is closer to the blade tip 101 of the unfolded blade 100 than the first locking component 110, so that after the blade 100 is unfolded and locked, the blade 100 and the carrier 200 can hold each other tightly. The greater the radial centrifugal force of the blade 100, the tighter the blade 100 and the carrier 200 are locked, thereby effectively preventing the blade 100 from falling out of the locking position, enhancing the locking effect of the blade 100, and thus improving the flight safety of the aircraft 5000.

[0164] Under the action of driving force, the propeller 100 can lock with the carrier 200 after unfolding, thereby keeping the position of the propeller 100 stable after rotation and unfolding. This ensures that the propeller 100 remains locked after unfolding and will not swing back and forth or vibrate, improving the rotational stability of the folding propeller 1000 and reducing the probability of the arm 5011 breaking or the aircraft 5000 crashing when the rotational frequency of the propeller 100 and the instability frequency of the arm 5011 are close, thus improving the flight safety of the aircraft 5000.

[0165] According to the third aspect of the power assembly 4000 proposed in the embodiments of this application, refer to... Figure 18 As shown, it includes a first drive device 4010 and a blade 100, wherein the first drive device 4010 is used to drive the blade 100 to rotate; as Figure 21As shown, the first drive device 4010 has a mounting bracket 4012, which can support the blade 100. The blade 100 is provided with a first locking member 110, and the mounting bracket 4012 is provided with a second locking member 210 that cooperates with the first locking member 110. During the process of the blade 100 rotating and unfolding from a folded state under the drive of the first drive device 4010, the first locking member 110 locks into the second locking member 210 under the action of the centrifugal force generated by the rotation of the blade 100. In these examples, the number of second locking members 210 on the mounting bracket 4012 corresponds one-to-one with the number of first locking members 110 on the blade 100.

[0166] The power assembly 4000 according to the fourth aspect of the embodiments of this application includes, as follows: Figure 18 The first drive unit 4010 and shown Figure 2 , Figure 8 , Figure 11 The illustrated folding propeller 1000 includes a blade 100 and a carrier 200, the blade 100 being pivotally connected to the carrier 200, as shown. Figure 18 As shown, the carrier 200 is connected to the first driving device 4010; as Figure 19 As shown, the propeller blade 100 is equipped with a first locking component 110, which is combined with... Figure 2 and Figure 3 As shown, the carrier 200 is provided with a second locking member 210 that cooperates with the first locking member 110. During the process of the blade 100 rotating and unfolding from the folded state under the drive of the first driving device 4010, the first locking member 110 locks into the second locking member 210 under the action of the centrifugal force generated by the rotation of the blade 100. The carrier 200 includes a blade clamp 230. In these examples, the number of second locking members 210 on the blade clamp 230 corresponds one-to-one with the number of first locking members 110 on the blade 100.

[0167] Therefore, in the embodiments of the power assembly 4000 in the third and fourth aspects mentioned above, regardless of whether the blade 100 is locked with the blade clamp 230 or the blade 100 is locked with the mounting bracket 4012, the blade 100 rotates under the driving force of the first drive device 4010. The centrifugal force generated during the rotation of the blade 100 causes the first locking component 110 of the blade 100 to lock onto the second locking component 210 of the carrier 200, so that the blade 100 remains locked after unfolding and will not swing back and forth or vibrate, thereby improving the rotational stability of the folding blade 1000 and reducing the probability of the arm 5011 breaking or the aircraft 5000 crashing when the rotational frequency of the blade 100 and the instability frequency of the arm 5011 are close, thereby improving the flight safety of the aircraft 5000.

[0168] This application can achieve automatic locking between the propeller 100 and the carrier 200 after unfolding without the need for human intervention. The first locking component 110 and the second locking component 210 are automatically locked during the rotation, unfolding and moving process under the action of the first driving device 4010. Therefore, it can reduce the complexity and time consumption of operation, improve the intelligence and automation efficiency of the aircraft 5000, and thus improve the working efficiency of the aircraft 5000.

[0169] In the embodiments of the power assembly 4000 in the second and fourth aspects of this application, the paddle clamp 230 of the folding paddle 1000 may be provided with a clamping foot facing the first driving device 4010, and a clamping groove may be provided on the first driving device 4010, so that the position of the paddle clamp 230 relative to the first driving device 4010 is fixed, the paddle clamp 230 is installed stably, and it is also beneficial for the first driving device 4010 to drive the paddle clamp 230 to rotate stably.

[0170] In a further example, the first drive unit 4010 is used to drive one or more blades 100 to rotate. For example, the plurality of blades 100 may include two, three, or four blades 100. This allows the first drive unit 4010 to fully exert its driving force, enabling one or more blades 100 to be driven to rotate and engage with the carrier 200.

[0171] In some embodiments, for the power assembly 4000 of the first and third aspects described above, when there is one blade 100, the mounting bracket 4012 is provided with a second locking member 210 to lock with a first locking member 110 of one blade 100. When there are two blades 100, as... Figure 21 As shown, the mounting frame 4012 is provided with two second locking components 210 (e.g., limiting grooves 310) to lock with the first locking components 110 of the two blades 100 respectively. When there are three blades 100, the mounting frame 4012 is provided with three second locking components 210 to lock with the first locking components 110 of the three blades 100 respectively. When there are four blades 100, the mounting frame 4012 is provided with four second locking components 210 to lock with the first locking components 110 of the four blades 100 respectively, and so on. This allows the mounting frame 4012 to lock each blade 100, which is beneficial for the first drive device 4010 to rotate each blade 100 and automatically lock with the mounting frame 4012 through driving force.

[0172] In a further example, multiple second locking components 210 are provided on the mounting bracket 4012 corresponding to the multiple blades 100. The multiple second locking components 210 are evenly spaced about the rotation axis 4011 of the first drive device 4010. This ensures that after each first locking component 110 locks with its corresponding second locking component 210, the locking positions are evenly spaced about the rotation axis 4011 of the first drive device 4010, thus ensuring that the blades 100 are evenly spaced and subjected to uniform force during rotation.

[0173] Provided that the technical solutions are not contradictory or conflicting, the structures of the blades 100, the carrier 200, the first locking component 110, and the second locking component 210 in these power components 4000 can be referred to the above description, and will not be repeated here.

[0174] The aircraft 5000 of this application is described below. The aircraft 5000 of this application embodiment is equipped with a power unit 4000. The aircraft 5000 includes, but is not limited to, manned or unmanned aircraft, specifically including multi-rotor aircraft, fixed-wing aircraft, and aircraft combining rotor and fixed wings. The aircraft 5000 can also be an amphibious aircraft, such as a flying car. The following explanation uses an unmanned aerial vehicle (UAV) as an example to illustrate the implementation of this application. It should be noted that this does not limit the scope of protection of this application.

[0175] Please see Figure 22 An aircraft 5000 according to an embodiment of this application includes a fuselage 5010 and a power assembly 4000 as described in the first to fourth aspects, wherein at least one power assembly 4000 is disposed on the fuselage 5010.

[0176] As can be seen from the above, after the aircraft 5000 of this application is equipped with the aforementioned power component 4000 on the fuselage 5010, it possesses the technical effects brought about by the aforementioned power component 4000. At least it can improve the flight safety of the aircraft 5000 and reduce the probability of the aircraft 5000 crashing. In some embodiments, it can also improve the intelligence and automation efficiency of the aircraft 5000, thereby improving the working efficiency of the aircraft 5000.

[0177] In some embodiments of this application, such as Figure 22 As shown, the fuselage 5010 includes an arm 5011, and the power unit 4000 is located on the arm 5011. When the power unit 4000 is working, it can transmit power to the entire aircraft 5000 through the arm 5011, thereby enabling the aircraft 5000 to fly or change direction.

[0178] Optionally, in this example, the fuselage 5010 includes one or more arms 5011, each arm 5011 having one or more power units 4000 mounted on it. That is, this application can provide the required number of arms 5011 and the required number of power units 4000 mounted on the arms 5011 as needed, thereby providing the required power to the aircraft 5000.

[0179] In other examples of this application, the fuselage 5010 includes a propeller guard, and the power assembly 4000 is housed within the propeller guard (not shown in the figure). When the power assembly 4000 is operating, power can be transmitted to the entire aircraft 5000 through the propeller guard, enabling the aircraft 5000 to fly continuously. At the same time, the propeller guard also provides some protection for the propeller blades 100, effectively preventing the propeller blades 100 from colliding with environmental objects in the surrounding environment during operation and causing damage, thereby making the aircraft 5000 safer to fly and able to adapt to more environments during flight.

[0180] Optionally, in this example, the fuselage 5010 includes one or more propeller guards, each of which is equipped with one or more power units 4000. Therefore, this application can provide the required number of propeller guards and the required number of power units 4000 on each propeller guard as needed, thereby providing the required power to the aircraft 5000.

[0181] The control method of the aircraft 5000 of this application will now be described.

[0182] A control method for an aircraft 5000 according to an embodiment of this application includes:

[0183] Step S10: Obtain control commands. For example, control commands may include takeoff control commands. Another example is landing control commands.

[0184] Step S21: According to the control command, the first drive device 4010 of the aircraft 5000 drives the propeller 100 of the aircraft 5000 to rotate and unfold from the folded state. During the process of rotating and unfolding the propeller 100 from the folded state, under the action of the centrifugal force generated by the rotation of the propeller 100, the first locking component 110 of the propeller 100 locks to the second locking component 210 of the carrier 200. The propeller 100 is mounted on the carrier 200.

[0185] In response to the control command, the first drive unit 4010 starts to work, providing the required driving force to the blade 100, so that the blade 100 can change its state to unfold. At the same time, under the action of centrifugal force, the first locking component 110 and the second locking component 210 lock together, thereby fixing the position of the blade 100 relative to the carrier 200. After unfolding, the blade 100 remains locked and will not swing back and forth or vibrate, reducing the probability of the arm 5011 breaking or the aircraft 5000 crashing when the rotation frequency of the blade 100 and the instability frequency of the arm 5011 are close, thereby improving the flight safety of the aircraft 5000.

[0186] This method embodiment can be executed by the aircraft 5000, or by a control device that has established a communication connection with the aircraft 5000, such as a remote controller, the airport / parking platform / take-off and landing platform of the aircraft 5000. Alternatively, some steps can be executed by the aircraft 5000, while the remaining steps can be executed by the control device of the aircraft 5000. This application embodiment does not limit this.

[0187] Provided that the technical solutions are not contradictory or conflicting, the structures of the propeller 100, the carrier 200, the first locking component 110, and the second locking component 210 on these aircraft 5000 can be referred to the above description, and will not be repeated here.

[0188] In some embodiments, the blades 100 include a plurality of blades, such that when the blades 100 are in a folded state, Figure 1 As shown, the tips 101 of the multiple blades 100 are aligned. In other embodiments, the tips of the multiple blades 100 overlap. This causes each set of blades 100 on the aircraft 5000 to be folded into a specific direction, reducing the space occupied by the blades 100, facilitating the storage of the aircraft 5000, and effectively protecting the blades 100 that are not in operation, preventing them from extending outwards in multiple directions and colliding with external objects and causing damage.

[0189] In some embodiments of this application, the propeller blades 100 include multiple blades. With the first locking member 110 locked to the second locking member 210, the multiple blades 100 are arranged in a centrally symmetrical manner. Thus, when the multiple blades 100 are fully deployed, they can achieve a centrally symmetrical arrangement, thereby achieving force balance and flight stability during the operation of the blades 100.

[0190] Optionally, the aircraft 5000 may be equipped with a second drive device 5020. In some embodiments of this application, the control method of the aircraft 5000 further includes: step S22, controlling the second drive device 5020 of the aircraft 5000 to drive the propeller 100 to rotate from an unfolded state to a folded state, so that the first locking component 110 of the propeller 100 disengages from the second locking component 210 of the carrier 200. In step S22, under the action of the second drive device 5020, the first locking component 110 and the second locking component 210 are unlocked, and the propeller 100 can be switched to a folded state for easy subsequent storage.

[0191] In some examples, such as Figure 23 As shown, the second drive device 5020 can also be installed inside the unmanned drone airport where the aircraft 5000 lands. The second drive device 5020 can drive the rotary folding structure, push the propeller 100, unlock the first locking component 110 and the second locking component 210, and further rotate the propeller 100 from the unfolded state to the folded state, thus realizing the storage of the aircraft 5000. In some other examples, the second drive device 5020 can also be installed on the landing platform / take-off and landing platform where the aircraft 5000 lands. In other examples, the second drive device 5020 can be installed on the fuselage 5010 of the aircraft 5000, so that when the propeller 100 needs to be folded, the second drive device 5020 drives the propeller 100 to fold.

[0192] In an embodiment where the second drive device 5020 is installed in the aircraft 5000, the aircraft 5000 can control the second drive device 5020 of the aircraft 5000 to drive the propeller 100 to rotate from the unfolded state to the folded state, so that the first locking member 110 of the propeller 100 disengages from the second locking member 210 of the carrier 200. Alternatively, the control device 6000 of the aircraft 5000 can control the second drive device 5020 of the aircraft 5000 to drive the propeller 100 to rotate from the unfolded state to the folded state, so that the first locking member 110 of the propeller 100 disengages from the second locking member 210 of the carrier 200.

[0193] In an embodiment where the second drive unit 5020 is installed on the airport / parking platform / take-off and landing platform of the aircraft 5000, the aircraft 5000 can control the second drive unit 5020 on the airport / parking platform / take-off and landing platform to drive the propeller 100 to rotate from the deployed state to the folded state, so that the first locking component 110 of the propeller 100 disengages from the second locking component 210 of the carrier 200. Alternatively, the control device 6000 of the aircraft 5000 can control the second drive unit 5020 on the airport / parking platform / take-off and landing platform to drive the propeller 100 to rotate from the deployed state to the folded state, so that the first locking component 110 of the propeller 100 disengages from the second locking component 210 of the carrier 200.

[0194] In some specific embodiments, step S22, in which the second drive device 5020 controlling the aircraft 5000 drives the propeller 100 to rotate from the deployed state to the folded state, includes: in response to the aircraft 5000 having landed, the second drive device 5020 controlling the aircraft 5000 drives the propeller 100 to rotate from the deployed state to the folded state. That is, when the aircraft 5000 safely lands at the target landing site, the second drive device 5020 can be activated, thereby unlocking the first locking component 110 and the second locking component 210, and thus causing the propeller 100 to fold.

[0195] The control method of the aircraft 5000 in this application relies on the control device 6000 described below. The specific structure of the control device 6000 will be described below.

[0196] A control device 6000 for an aircraft 5000, as proposed in an embodiment of this application, is as follows: Figure 24 As shown, it includes: a processor 6010 and a memory 6020. The memory 6020 is used to store computer program instructions, and the processor 6010 is used to call the computer program instructions to execute the following process: obtaining control instructions; according to the control instructions, controlling the first drive device 4010 of the aircraft 5000 to drive the propeller 100 of the aircraft 5000 to rotate and unfold from the folded state. During the process of rotating and unfolding the propeller 100 from the folded state, under the action of the centrifugal force generated by the rotation of the propeller 100, the first locking component 110 of the propeller 100 locks to the second locking component 210 of the carrier 200. The propeller 100 is mounted on the carrier 200.

[0197] In other examples, the aircraft 5000 also includes a second drive unit 5020. The processor 6010 of the control unit 6000 can also be used to call computer program instructions to execute the following process: obtaining control instructions; according to the control instructions, controlling the second drive unit 5020 of the aircraft 5000 to drive the first locking component 110 of the aircraft 5000 to disengage from the second locking component 210 of the carrier 200, and causing the propeller 100 to rotate from the deployed state to the folded state. The control instructions here can be landing and awaiting storage control instructions, enabling the aircraft 5000 to automatically fold and store after landing under the control of the mechanical component 5030. The mechanical component 5030 can be a rotary folding structure used to drive multiple propeller blades 100 to rotate, so that the multiple propeller blades 100 can be folded together to achieve the effect of storage and volume reduction.

[0198] Provided there are no conflicts, the folded and unfolded states in these examples can be referred to in the relevant descriptions above, and will not be repeated here.

[0199] Therefore, the aforementioned control device 6000 can be installed on the aircraft 5000 or on the control equipment of the aircraft 5000.

[0200] The following describes an aircraft 5000 with a built-in processor 6010 and memory 6020.

[0201] Please see Figure 25 An aircraft 5000 according to an embodiment of this application includes a processor 6010, a memory 6020, and a power assembly 4000. The power assembly 4000 provides power to the aircraft 5000. The memory 6020 stores computer program instructions. The processor 6010 invokes the computer program instructions to execute the following process: acquiring control instructions; and controlling the first drive device 4010 of the aircraft 5000 to drive the propeller 100 of the aircraft 5000 to rotate and unfold from a folded state according to the control instructions. During the rotation and unfolding of the propeller 100, under the action of the centrifugal force generated by the rotation of the propeller 100, the first locking component 110 of the propeller 100 locks to the second locking component 210 of the carrier 200. The propeller 100 is mounted on the carrier 200. In these examples, the aircraft 5000 itself stores computer program instructions. When the computer program instructions are invoked by the processor 6010, the processor 6010 executes the control methods of the aircraft 5000 described in the aforementioned embodiments.

[0202] As can be seen from the above, the aircraft 5000, the control method of the aircraft 5000, and the control device 6000 of the aircraft 5000 of this application use a memory 6020 to store computer program instructions and a processor 6010 to call the computer program instructions, thereby enabling the computer program instructions to execute the control method. This enables the device to control the first drive device 4010 of the aircraft 5000 to drive the propeller 100 of the aircraft 5000 to rotate and unfold from a folded state. During the folding and unfolding process, the centrifugal force generated by the rotation of the propeller 100 causes the first locking component 110 and the second locking component 210 to lock and fit tightly. The greater centrifugal force generated during the high-speed rotation of the propeller 100 makes the first locking component 110 and the second locking component 210 lock even more tightly, ensuring the flight safety of the aircraft 5000.

[0203] Provided that the technical solutions are not contradictory or conflicting, the structure of these power components 4000 can be referred to the above text, and will not be repeated here.

[0204] It should be understood that various parts of this application can be implemented using hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented using software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware as in another embodiment, it can be implemented using any one or a combination of the following techniques known in the art: discrete logic circuits having logic gates for implementing logical functions on data signals, application-specific integrated circuits (ASICs) having suitable combinational logic gates, programmable gate arrays (PGAs), field-programmable gate arrays (FPGAs), etc.

[0205] Those skilled in the art will understand that all or part of the steps of the methods described in the above embodiments can be implemented by a program instructing related hardware. The program can be stored in an aircraft, and when executed, it includes one or a combination of the steps of the method embodiments. The above descriptions are merely specific embodiments of this application, but the scope of protection of this application is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this application, and these modifications or substitutions should all be covered within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A blade, characterized in that, The propeller blade can be mounted on a carrier, which can be mounted on a drone. The propeller blade is provided with a first locking component, and the carrier is provided with a second locking component that cooperates with the first locking component. The propeller blade is rotated and unfolded from a folded state under the action of a driving force, so that the first locking component locks into the second locking component. The second locking component is closer to the tip of the unfolded propeller blade than the first locking component.

2. A carrier component, characterized in that, The carrier is used to install the propeller blade. The carrier can be installed on the drone. The propeller blade is provided with a first locking component. The carrier is provided with a second locking component that cooperates with the first locking component. The propeller blade is rotated and unfolded from a folded state under the action of driving force so that the first locking component locks into the second locking component. The second locking component is closer to the tip of the unfolded propeller blade than the first locking component.

3. A folding paddle, characterized in that, The device includes a propeller and a carrier. The carrier is used to mount the propeller and can be mounted on a drone. The propeller has a first locking component, and the carrier has a second locking component that cooperates with the first locking component. The propeller rotates and unfolds from a folded state under the action of a driving force so that the first locking component locks into the second locking component. The second locking component is closer to the tip of the unfolded propeller than the first locking component.

4. A blade, characterized in that, The propeller can be mounted on a carrier, and the carrier can be mounted on a drone. The propeller is provided with a first locking component, and the carrier is provided with a second locking component that cooperates with the first locking component. During the process of the propeller being driven by a first driving device to rotate and unfold from a folded state, the first locking component locks into the second locking component under the action of the centrifugal force generated by the rotation of the propeller.

5. A carrier component, characterized in that, The carrier can support the propeller blade and can be installed on the drone. The propeller blade is provided with a first locking component, and the carrier is provided with a second locking component that cooperates with the first locking component. During the process of the propeller blade being driven by the first driving device to rotate and unfold from the folded state, the first locking component locks into the second locking component under the action of the centrifugal force generated by the rotation of the propeller blade.

6. A folding paddle, characterized in that, The device includes a propeller and a carrier. The carrier can support the propeller and can be installed on a drone. The propeller is provided with a first locking component, and the carrier is provided with a second locking component that cooperates with the first locking component. During the process of the propeller being driven by a first driving device to rotate and unfold from a folded state, the first locking component locks into the second locking component under the action of the centrifugal force generated by the rotation of the propeller.

7. The blade as described in claim 1 or 4, the carrier as described in claim 2 or 5, and the folding blade as described in claim 3 or 6, characterized in that, The locking structure of the first locking component and the second locking component includes a mechanical locking structure or a magnetic locking structure.

8. The blade, carrier, or folding blade as described in claim 7, characterized in that, The mechanical locking structure includes a limiting groove and a mating protrusion, wherein one of the first locking component and the second locking component is a limiting groove, and the other of the first locking component and the second locking component is a mating protrusion.

9. The blade, carrier, or folding blade as described in claim 8, characterized in that, The outer peripheral surface of the mating protrusion is curved; or, the outer peripheral surface of the mating protrusion is rectangular; or, the cross-section of the mating protrusion is circular, elliptical, or irregular; or, the cross-section of the mating protrusion is rectangular; or, the inner peripheral surface of the limiting groove is curved; or, the inner peripheral surface of the limiting groove is rectangular; or, the cross-section of the limiting groove is circular, elliptical, or irregular; or, the cross-section of the limiting groove is rectangular.

10. The blade, carrier, or folding blade as described in claim 8, characterized in that, The second locking component is a limiting groove, and the first locking component is a mating protrusion.

11. The blade as claimed in claim 1 or 4, the carrier as claimed in claim 2 or 5, and the folding blade as claimed in claim 3 or 6, characterized in that, Both the first locking component and the second locking component are located in a receiving slot. The position of one of the first locking component and the second locking component in the receiving slot can be changed, while the position of the other of the first locking component and the second locking component in the receiving slot is fixed.

12. The blade, carrier, or folding blade as described in claim 11, characterized in that, The position of the first locking component within the receiving groove can be changed, while the position of the second locking component within the receiving groove is fixed, and the carrier is provided with the receiving groove.

13. The blade, carrier, or folding blade as described in claim 12, characterized in that, The second locking component is closer to the tip of the unfolded blade than the rest of the receiving slot; or, the second locking component is located in a first specific direction within the receiving slot, the first specific direction being the tip direction of the unfolded blade.

14. The blade as claimed in claim 1 or 4, the carrier as claimed in claim 2 or 5, and the folding blade as claimed in claim 3 or 6, characterized in that, After the blade rotates from the folded state to the fully unfolded state, the first locking component locks into the second locking component.

15. The blade, carrier, or folding blade as described in claim 14, characterized in that, The blades comprise multiple blades, which, when rotated from a folded state to full deployment, are arranged in a centrally symmetrical structure; or... The blades include multiple blades, and after the multiple blades are rotated from a folded state to a fully unfolded state, the included angle between any two adjacent blades among the multiple blades is the same.

16. The blade as claimed in claim 1 or 4, the carrier as claimed in claim 2 or 5, and the folding blade as claimed in claim 3 or 6, characterized in that, The blade includes a first blade, and the carrier includes a first carrier member. The first carrier member is pivotally connected to the first blade. The first carrier member is used to connect to a first drive device. The first blade is provided with a first locking component. The first carrier member is provided with a second locking component that cooperates with the first locking component of the first blade. After the first blade is rotated and unfolded, the first locking component of the first blade locks into the second locking component of the first carrier member. The first drive device is used to drive the first blade to rotate. The carrier also includes a second carrier, which is pivotally connected to the first blade. The first blade is provided with the first locking component, and the second carrier is provided with a second locking component that cooperates with the first locking component of the first blade. After the first blade is rotated and unfolded, the first locking component of the first blade locks into the second locking component of the second carrier. The first support member and the second support member are located on different sides of the first blade.

17. The blade as claimed in claim 1, the carrier as claimed in claim 2, and the folding blade as claimed in claim 3, characterized in that, The driving force is a first driving force, under which the blade rotates and unfolds from a folded state to lock the first locking component into the second locking component. The first driving force includes a tangential driving force, where the tangential direction is the direction of the tangent to the circumferential surface of the blade's rotation; or, the first driving force includes a radial driving force, under which the blade translates to lock the first locking component into the second locking component. The radial direction is the direction from the center of the circumferential surface of the blade's rotation to the edge of the circumferential surface.

18. The blade as claimed in claim 1 or 4, the carrier as claimed in claim 2 or 5, and the folding blade as claimed in claim 3 or 6, characterized in that, During the rotation of the blade, the blade drives the first locking component to move, so that the first locking component locks onto the second locking component, and the position of the second locking component remains unchanged during the movement of the first locking component; or, During the rotation of the blade, the blade drives the first locking component to translate, so that the first locking component locks into the second locking component; or, During the rotation of the propeller, the propeller drives the first locking component to move, so that the first locking component is in an unlocked position and a locked position. When the first locking component is in the unlocked position, the distance of the first locking component relative to the rotation axis of the first driving device is different from the distance of the first locking component relative to the rotation axis when the first locking component is in the locked position. When the first locking component is in the unlocked position, the distance between the first locking component and the rotation axis of the first driving device is less than the distance between the first locking component and the rotation axis when the first locking component is in the locked position. or, During the rotation of the propeller blade, the propeller blade drives the first locking component to move, so that the first locking component is in an unlocked position and a locked position. When the first locking component is in the unlocked position, the distance between the first locking component and the pivot axis of the carrier member is different from the distance when the first locking component is in the locked position. The propeller blade is pivotally connected to the pivot axis of the carrier member. When the first locking component is in the unlocked position, the distance between the first locking component and the pivot axis of the carrier member is less than the distance when the first locking component is in the locked position. Alternatively... During the rotation of the propeller blade, the propeller blade drives the first locking component to move, so that the first locking component is in an unlocked position and a locked position. The locked position is further away from the pivot axis of the carrier member than the unlocked position, wherein the propeller blade is pivotally connected to the pivot axis of the carrier member; or, After the propeller blades are installed on the drone, the propeller blades can rotate about a pivot axis; or, After the propeller blades are installed on the drone, the drone can start operating; or, The first locking component disengages from the second locking component under the action of a second driving force; the second driving force includes a tangential driving force, under which the blade rotates to disengage the first locking component from the second locking component, wherein the tangential direction is the direction of the tangent to the circumferential surface of the blade's rotation; the second driving force also includes a radial driving force, under which the blade translates to disengage the first locking component from the second locking component, wherein the radial direction is the direction from the center of the circumferential surface of the blade's rotation to the edge of the circumferential surface.

19. A power component for an unmanned aerial vehicle (UAV), characterized in that, The device includes a first drive unit and a blade. The first drive unit drives the blade to rotate. The first drive unit has a mounting bracket capable of supporting the blade. The blade has a first locking component, and the mounting bracket has a second locking component that cooperates with the first locking component. Under the action of a driving force, the blade rotates and unfolds from a folded state, so that the first locking component locks into the second locking component. The second locking component is closer to the tip of the unfolded blade than the first locking component. Alternatively... The power assembly includes a first drive unit and a folding propeller. The folding propeller includes blades and a carrier. The blades are pivotally connected to the carrier, and the carrier is connected to the first drive unit. The blades have a first locking component, and the carrier has a second locking component that engages with the first locking component. Under the action of a driving force, the blades rotate and unfold from a folded state, causing the first locking component to lock into the second locking component. The second locking component is closer to the tip of the unfolded blade than the first locking component. Alternatively... The power assembly includes a first drive unit and a blade. The first drive unit drives the blade to rotate. The first drive unit has a mounting frame capable of supporting the blade. The blade is provided with a first locking component, and the mounting frame is provided with a second locking component that cooperates with the first locking component. During the process of the blade rotating and unfolding from a folded state under the drive of the first drive unit, the first locking component locks into the second locking component under the centrifugal force generated by the rotation of the blade; or... The power assembly includes a first drive device and a folding propeller. The folding propeller includes a blade and a carrier. The blade is pivotally connected to the carrier, and the carrier is connected to the first drive device. The blade is provided with a first locking component, and the carrier is provided with a second locking component that cooperates with the first locking component. During the process of the blade rotating and unfolding from the folded state under the drive of the first drive device, the first locking component locks into the second locking component under the action of the centrifugal force generated by the rotation of the blade.

20. A drone, characterized in that, The device includes a fuselage and a power unit for the drone as described in claim 19, wherein at least one of the power units is disposed on the fuselage.

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