Propeller protection assembly, rotor unmanned aerial vehicle and rotor unmanned aerial vehicle kit

Abstract

The utility model provides a propeller protection assembly, a rotor unmanned aerial vehicle and a rotor unmanned aerial vehicle suite, the propeller protection assembly comprises a protection cover and a first propeller, and the protection cover is used for providing protection for the first propeller; wherein the propeller protection assembly is configured to be detachably connected with an aircraft body of the unmanned rotorcraft, and after the propeller protection assembly is installed on the unmanned rotorcraft, the first propeller is used for being in transmission connection with a power assembly of the unmanned rotorcraft, so that flight power is provided for the unmanned rotorcraft; wherein the propeller protection assembly is not provided with a power assembly, and the power assembly is arranged on the rotor unmanned aerial vehicle. The propeller protection assembly, the rotor unmanned aerial vehicle and the rotor unmanned aerial vehicle kit provided by the utility model can protect the propeller.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a propeller protection component, a rotary-wing drone, and a rotary-wing drone kit. Background Technology

[0002] Aircraft typically include a propeller, which propels the aircraft through rotation. However, sometimes due to pilot error or loss of control, the high-speed rotation of the propeller may cause it to collide with hard objects, resulting in damage, or the propeller may injure people or objects. Therefore, it is necessary to design a propeller protection component to protect the propeller. Utility Model Content

[0003] This invention provides a propeller protection component, a rotary-wing drone, and a rotary-wing drone kit, designed to protect the propeller.

[0004] The first embodiment of this utility model provides a propeller protection assembly, including:

[0005] Protective shield; and

[0006] The first propeller, the protective cover is used to provide protection for the first propeller;

[0007] The propeller protection assembly is configured to be detachably connected to the main body of the rotorcraft drone. After the propeller protection assembly is installed on the rotorcraft drone, the first propeller is used to drive the power assembly of the rotorcraft drone, thereby providing flight power for the rotorcraft drone. The propeller protection assembly does not have the power assembly installed on it; the power assembly is installed on the rotorcraft drone.

[0008] The second embodiment of this utility model provides a rotary-wing unmanned aerial vehicle, including:

[0009] The main body of the aircraft is configured to be detachably connected to the propeller protection assembly; and

[0010] A power assembly; wherein the propeller protection assembly includes a protective cover and a first propeller, the protective cover being used to provide protection for the first propeller, and after the propeller protection assembly is installed on the aircraft body, the first propeller being used to drive the power assembly, thereby providing flight power for the rotary-wing UAV; wherein the propeller protection assembly does not include the power assembly.

[0011] The third embodiment of this utility model provides a rotary-wing drone kit, including:

[0012] Rotary-wing drones; and

[0013] The propeller protection assembly described in the first embodiment is detachably connected to the main body of the rotary-wing UAV.

[0014] The fourth embodiment of this utility model provides a rotary-wing unmanned aerial vehicle (UAV) kit, characterized in that it includes:

[0015] A rotary-wing unmanned aerial vehicle, the rotary-wing unmanned aerial vehicle including a power unit;

[0016] The propeller protection assembly described in the first embodiment is detachably connectable to the main body of the rotary-wing UAV; and

[0017] The second propeller is configured to be detachably connected to the main body of the aircraft. The first and second propellers can be selectively connected to the same power unit of the rotorcraft to provide flight power to the rotorcraft.

[0018] The propeller protection assembly, rotary-wing UAV, and rotary-wing UAV kit provided in this utility model embodiment reduce the probability of the first propeller colliding directly with obstacles and being damaged, and also reduce the safety risk of the first propeller causing cuts to the external environment during rotation, thus improving the safety of the aircraft. When the propeller protection assembly is not needed, it can be detached from the aircraft body. Furthermore, since the propeller protection assembly has a first propeller but no power component, after installation, the first propeller can be connected to the aircraft's power component to provide flight power. This optimizes, expands, and enriches the design of the propeller protection assembly, meeting the needs of more scenarios. Moreover, the absence of a power component means that when the propeller protection assembly needs to be replaced, the power component does not need to be replaced simultaneously, reducing maintenance and after-sales costs. Additionally, the absence of a power component reduces the weight and size of the propeller protection assembly itself.

[0019] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit the disclosure of the embodiments of this utility model. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the structure of an aircraft or aircraft kit provided in one embodiment of the present invention;

[0022] Figure 2 This is a schematic diagram of an aircraft or aircraft kit provided in an embodiment of the present invention;

[0023] Figure 3 This is a schematic diagram of an aircraft provided in one embodiment of the present invention;

[0024] Figure 4 This is a schematic diagram of the structure of an aircraft provided in one embodiment of the present invention;

[0025] Figure 5 This is a partial structural schematic diagram of an aircraft or aircraft kit provided in an embodiment of the present invention, showing a propeller protection assembly and part of the aircraft body;

[0026] Figure 6 This is a schematic diagram of the structure of a propeller protection assembly provided in an embodiment of the present invention;

[0027] Figure 7 This is an exploded view of a propeller protection assembly provided in an embodiment of the present invention;

[0028] Figure 8 This is a partial structural schematic diagram of an aircraft or aircraft kit provided in an embodiment of the present invention, showing a propeller protection assembly and part of the aircraft body, with the first connecting part connected to the second connecting part;

[0029] Figure 9 This is a partial structural schematic diagram of an aircraft or aircraft kit provided in an embodiment of the present invention, showing a propeller protection assembly and part of the aircraft body, with the first connecting part and the second connecting part not connected in place;

[0030] Figure 10 This is a schematic diagram of a pressing component provided in an embodiment of the present invention;

[0031] Figure 11 This is a partial structural schematic diagram of an aircraft or aircraft kit provided in an embodiment of the present invention, showing a propeller protection assembly and part of the aircraft body;

[0032] Figure 12 This is a partial structural schematic diagram of an aircraft or aircraft kit provided in an embodiment of the present invention, showing a protective cover and a quick-release structure;

[0033] Figure 13This is a schematic diagram of the storage of all propeller protection components of an aircraft after they have been removed from the main body of the aircraft, according to an embodiment of this utility model;

[0034] Figure 14 This is a schematic diagram of the storage of all propeller protection components of an aircraft after they have been removed from the main body of the aircraft, according to an embodiment of this utility model;

[0035] Figure 15 This is a schematic diagram of the storage of the two propeller protection components of the aircraft after they have been removed from the main body of the aircraft, according to an embodiment of this utility model.

[0036] Explanation of reference numerals in the attached figures:

[0037] 100. Aircraft;

[0038] 10. Main body of the aircraft; 11. Fuselage; 12. Arms; 13. Visual sensor; 14. Heat dissipation unit;

[0039] 20. Propeller; 21. First propeller; 211. Transmission assembly; 22. Second propeller;

[0040] 30. Powertrain components; 31. Transmission unit;

[0041] 40. Propeller protection assembly; 41. Protective cover; 411. Enclosure; 4110. Accommodation space; 4111. First mesh; 4112. Second mesh; 412. Assembly part; 42. Flow guide; 44. Second chute; 45. Third connecting part; 46. Fourth connecting part;

[0042] 50. Quick-release structure; 51. First connecting part; 52. Second connecting part; 53. Pressing part; 531. First force-applying part; 532. Second force-applying part; 54. Locking part;

[0043] 60. Structural components. Detailed Implementation

[0044] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are some embodiments of the present utility model, but not all embodiments.

[0045] In the description of this utility model, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of the stated features. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0046] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the present invention. As used in this specification and the appended claims, unless the context clearly indicates otherwise, the singular forms "a," "an," and "the" are intended to include the plural forms. In this invention, "at least one" means one or more, and "more" means two or more. "And / or" describes the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can mean: A exists alone, A and B exist simultaneously, or B exists alone, where A and B can be singular or plural. The character " / " generally indicates that the preceding and following related objects are in an "or" relationship. "At least one of the following" or similar expressions refer to any combination of these items, including any combination of single or plural items. For example, at least one of a, b, or c can be represented as: a, b, c, a and b, a and c, b and c, or a and b and c, where a, b, and c can be a single item or multiple items.

[0047] This utility model provides an aircraft. The aircraft may include a rotorcraft, a fixed-wing aircraft, or a hybrid fixed-wing / rotorcraft. The aircraft may be manned or unmanned. The rotorcraft may be a single-rotor or multi-rotor aircraft, and the multi-rotor aircraft may include: dual-rotor, tri-rotor, quadcopter, hexacopter, octocopter, decacopter, dodecocter, etc. For example, the aircraft includes a rotorcraft drone.

[0048] Aircraft typically include a propeller, which rotates to propel the aircraft. However, sometimes due to pilot error or loss of control, the high-speed rotation of the propeller may cause it to collide with hard objects, resulting in damage, or the propeller may cut people or objects. Therefore, propeller protection components can be installed on aircraft to reduce the probability of the propeller colliding directly with obstacles and causing damage, and to reduce the safety risk of the propeller cutting the external environment (such as people or other objects) while rotating, thereby improving the safety of aircraft use. To achieve independent and portable storage of the aircraft and propeller protection components, and to facilitate the individual replacement of the propeller protection components, the installation method of the propeller protection components and the aircraft can be designed to be detachable. This allows for easy installation of the propeller protection components when needed to protect the aircraft's propellers, thereby improving the aircraft's operational safety. With these safety protection measures in place, the aircraft can perform some close-range shooting functions, such as palm-held takeoff / landing and one-click short video recording within a small area (e.g., follow, orbit, launch, fade-out, etc.). Users can walk up to the aircraft and use the controls on the aircraft body. These shooting functions can be triggered by physical buttons or virtual buttons on the display screen, thus expanding the aircraft's functionality and allowing for closer shooting distances to the target (such as people or animals), enriching the camera movement effects. When the propeller protection component is not needed to protect the propeller, it can be removed from the aircraft, facilitating lighter flight and improving endurance. Even without the propeller protection component, the user can trigger the aircraft to perform corresponding functions via a control device connected to the aircraft (such as a mobile phone or remote control). Based on this, this invention provides a quick-release structure for the propeller protection component and the aircraft to meet both usage scenarios where the propeller protection component is needed and not needed. Furthermore, this invention also provides a solution for the portable storage of the propeller protection component after removal from the aircraft, thereby reducing the storage volume of multiple propeller protection components.

[0049] The following detailed description, in conjunction with the accompanying drawings, outlines some embodiments of the present invention. Unless otherwise specified, the following embodiments and features can be combined with each other.

[0050] Please see Figure 1The aircraft 100 includes an aircraft body 10. Exemplarily, the aircraft body 10 includes a fuselage 11. Exemplarily, the aircraft body 10 may also include an arm 12 connected to the fuselage 11. Optionally, the arm 12 and the fuselage 11 may be detachably connected; or they may be non-detachably connected. In some embodiments, the arm 12 and the fuselage 11 may be movably connected, and their relative position can be adjusted when connected, allowing the arm 12 to be deployed or folded. The number of arms 12 can be designed according to actual needs, such as one, two, three, four, or more. Exemplarily, the number of arms 12 includes multiple arms 12 extending radially from the fuselage 11. Exemplarily, the aircraft 100 includes a plurality of arms 12, a portion of which is movably connected to the fuselage 11, and another portion of which is not movably connected to the fuselage 11; alternatively, each arm 12 may be movably connected to the fuselage 11. In other embodiments, the arms 12 may be omitted. Exemplarily, the aircraft 100 may also include landing gear 15 (e.g., Figure 9 As shown), optionally, each arm 12 of the aircraft 100 may be equipped with a landing gear 15. In other embodiments, not every arm 12 may be equipped with a landing gear 15. Landing gear 15 may be installed on some arms 12. For example, the two front arms 12 of the aircraft 100 may be equipped with landing gear 15, while the two rear arms 12 of the aircraft 100 may not be equipped with landing gear 15.

[0051] Please see Figure 1 In some embodiments, the aircraft 100 includes a propeller 20 capable of movement, thereby providing flight propulsion for the aircraft 100. The number of propellers 20 can be set according to actual needs, such as one, two, three, four, or more. Exemplarily, the aircraft 100 includes a power assembly 30 for transmission connection with the propeller 20, thereby providing flight propulsion for the aircraft 100. The propeller 20 can be detachably connected to the power assembly 30 or non-detachably connected to the power assembly 30.

[0052] In some embodiments, the power source of the power assembly 30 includes at least one of the following: electricity, magnetism, gravity, wind power, water power, hydraulic drive, fuel, etc. Exemplarily, the power assembly 30 may include a power motor for transmission connection with the propeller 20, enabling the power motor to drive the propeller 20 to rotate, thereby providing flight power for the aircraft 100. It should be understood that the power motor can be a DC motor or an AC motor. Additionally, the power motor can be a brushless motor or a brushed motor.

[0053] The power assembly 30 can be installed in any suitable location according to actual needs. For example, the power assembly 30 can be installed on the arm 12 or fuselage 11 of the aircraft 100. Alternatively, the power assembly 30 can be installed on the propeller protection assembly 40 in any suitable embodiment of this invention (see [link to relevant documentation]). Figure 1 ) or protective cover 41 (see Figure 1 The power unit 30 can be non-detachably connected to the propeller 20, or it can be detachably connected to the propeller 20. For example, if the power unit 30 is detachably connected to the propeller 20, and either the propeller 20 or the power unit 30 is damaged and needs to be replaced, it is not necessary to replace both the propeller 20 and the power unit 30 at the same time, which helps to reduce maintenance and after-sales costs. In addition, since the power unit 30 is detachably connected to the propeller 20, the same power unit 30 of the aircraft 100 can be adapted to multiple propellers 20 with different or the same parameters. Thus, the same power unit 30 of the aircraft 100 can be adapted to different propellers 20, expanding the application scenarios of the aircraft 100 and meeting the needs of more scenarios.

[0054] The propeller 20 can be positioned at any suitable location according to actual needs. For example, the propeller 20 can be located on the fuselage 11. Alternatively, the propeller 20 can be located on the arm 12. Yet another example is that the propeller 20 can be located on the propeller protection assembly 40 or the protective cover 41 in any suitable embodiment of this utility model.

[0055] Please see Figure 1 In some embodiments, the aircraft 100 includes a propeller protection assembly 40. The number of propeller protection assemblies 40 may include one; or multiple, such as two, three, or more. Exemplarily, the propeller protection assembly 40 includes a protective cover 41 for providing protection for the propeller 20. The protective cover 41 can reduce the probability of the propeller 20 being damaged by direct collision with an obstacle, and reduce the safety risk of the propeller 20 causing cuts to the external environment (such as people or other objects) when rotating, thereby improving the safety of the aircraft 100. In other embodiments, the propeller protection assembly 40 may not be part of the aircraft 100. The propeller protection assembly 40 may be detachably connected to the aircraft 100, and the propeller protection assembly 40 and the aircraft 100 may cooperate to form an aircraft kit. When the aircraft 100 needs to use the propeller protection assembly 40, it is installed on the aircraft 100; when the propeller protection assembly 40 is not needed, the aircraft 100 can be used independently without it.

[0056] In some embodiments, the propeller protection assembly 40 is detachably connected to the aircraft body 10. For example, the propeller protection assembly 40 is connected to the fuselage 11 and / or arm 12 of the aircraft 100. Exemplarily, the protective shield 41 is connected to the aircraft body 10. For example, the protective shield 41 is connected to the fuselage 11 and / or arm 12 of the aircraft 100.

[0057] For example, the propeller protection assembly 40 is connected to the fuselage 11 of the aircraft 100. In this case, the aircraft 100 may include an arm 12, or the arm 12 may be omitted. For instance, the aircraft 100 includes a fuselage 11, an arm 12, and a propeller protection assembly 40, with the propeller protection assembly 40 connected to the fuselage 11, and at least one of the power unit 30 and the propeller 20 disposed on the arm 12 and / or the propeller protection assembly 40. Alternatively, the arm 12 may be omitted, and the aircraft 100 includes a fuselage 11 and a propeller protection assembly 40, with the propeller protection assembly 40 connected to the fuselage 11, and at least one of the power unit 30 and the propeller 20 disposed on the propeller protection assembly 40, or at least one of the power unit 30 and the propeller 20 disposed on the fuselage 11. In other embodiments, the aircraft body 10 may not have the propeller protection assembly 40 installed.

[0058] For example, the propeller protection assembly 40 is connected to a connected component (which may include at least one of the fuselage 11 and the arm 12). The propeller protection assembly 40 and the connected component can be detachably connected. For example, the number of propeller protection assemblies 40 may include multiple assemblies, with some of the multiple propeller protection assemblies 40 being detachably connected to the connected component, and other portions of the multiple propeller protection assemblies 40 being non-detachably connected to the connected component. Alternatively, each propeller protection assembly 40 may be detachably connected to the connected component.

[0059] For example, the propeller protection assembly 40 is not movably connected to the connected member, and after the propeller protection assembly 40 is connected to the connected member, the positions of the propeller protection assembly 40 and the connected member remain relatively fixed. For example, the propeller protection assembly 40 is movably connected to the connected member so that the propeller protection assembly 40 can be folded or unfolded, thereby reducing the volume of the aircraft 100 in the stored state.

[0060] For example, the number of propeller protection assemblies 40 includes multiple assemblies, where a portion of the protective cover 41 of the multiple propeller protection assemblies 40 is movably connected to the connected component, and another portion of the protective cover 41 of the multiple propeller protection assemblies 40 is not movably connected to the connected component; or, the protective cover 41 of each propeller protection assembly 40 is movably connected to the connected component, or the protective cover 41 of each propeller protection assembly 40 is not movably connected to the connected component.

[0061] The number of propeller protection components 40 may be the same as or different from the number of propellers 20. Please refer to [link / reference]. Figure 1 For example, at least one propeller protection assembly 40 corresponds to one propeller 20. See also Figure 1 For example, at least one propeller protection assembly 40 does not have a propeller 20, which is located on the aircraft body 10. See also... Figure 3 For example, at least one propeller protection assembly 40 corresponds to two or more propellers 20. For instance, the number of propeller protection assemblies 40 includes two, with each propeller protection assembly 40 corresponding to two propellers 20.

[0062] Exemplarily, the propeller 20 includes a first propeller 21 according to any embodiment of the present invention, and at least one propeller protection component 40 is provided with the first propeller 21. The number of propeller protection components 40 may be the same as or different from the number of first propellers 21. Please refer to Figure 1 In some embodiments, at least one propeller protection assembly 40 is provided with a first propeller 21. For example, each propeller protection assembly 40 is provided with a first propeller 21. In this way, the structure of the propeller protection assembly 40 is simple, and the replacement or maintenance of the propeller protection assembly 40 is easier. Please refer to Figure 3 In some embodiments, at least one propeller protection component 40 is provided with multiple first propellers 21. For example, each propeller protection component 40 is provided with multiple first propellers 21, that is, two, three or more first propellers 21. In this way, multiple first propellers 21 can share one propeller protection component 40, reducing the number of components and improving assembly efficiency. In addition, when the propeller protection component 40 is detachably connected to the aircraft body 10, it is also convenient to store all the propeller protection components 40 of the aircraft 100 after all the propeller protection components 40 of the aircraft 100 are removed from the aircraft body 10, reducing the probability that the propeller protection components 40 of the aircraft 100 are easily lost.

[0063] Please see Figure 1 In some embodiments, the aircraft 100 includes at least two propeller protection assemblies 40, thus allowing for more flexible installation of the propeller protection assemblies 40. In other embodiments, the aircraft 100 may also include only one propeller protection assembly 40.

[0064] Please see Figure 3In some embodiments, each propeller protection assembly 40 is provided with at least two first propellers 21, each first propeller 21 being driven to be connected to different power components 30 of the aircraft 100. For example, the aircraft 100 includes four power components 30 and two propeller protection assemblies 40, each propeller protection assembly 40 including two first propellers 21. The two first propellers 21 of one propeller protection assembly 40 are driven to two of the power components 30 respectively, and the two first propellers 21 of the other propeller protection assembly 40 are driven to be connected to the other two power components 30 respectively. It is understood that the structures of the different power components 30 can be the same or different.

[0065] Please see Figure 1 In some embodiments, after at least two propeller protection assemblies 40 are installed on the aircraft 100, the propeller protection assemblies 40 are spaced apart. This helps to reduce the total weight of all propeller protection assemblies 40 on the aircraft 100, save materials, reduce costs, and extend the flight time of the aircraft 100. In addition, the spaced arrangement of the propeller protection assemblies 40 can also reduce the probability that the propeller protection assemblies 40 of the aircraft 100 will obstruct the sensors of the aircraft 100 (such as the vision sensor 13), thereby ensuring the perception capability of the aircraft 100 and improving the flight safety of the aircraft 100. The spaced arrangement is different from the integrated arrangement or the contact arrangement. The propeller protection assemblies 40 are spaced apart, for example, the propeller protection assemblies 40 can be non-contact, with a certain distance between each propeller protection assembly 40, thereby avoiding the obstruction of the perception range of the sensors on the aircraft 100 caused by the contact arrangement of the propeller protection assemblies 40.

[0066] Please see Figure 1 In some embodiments, the propeller 20 includes a first propeller 21 according to any embodiment of the present invention. See also... Figure 4In some embodiments, the propeller 20 includes a second propeller 22 according to any embodiment of the present invention. In some embodiments, the number of propellers 20 includes multiple propellers, each of which can be a first propeller 21 or a second propeller 22. In some embodiments, the number of propellers 20 includes multiple propellers, with a portion of the propellers 20 being first propellers 21 and another portion being second propellers 22. In some embodiments, the propeller itself disposed on the propeller protection assembly 40 is a first propeller 21, while other propellers adapted to the aircraft 100 can be second propellers 22, which are not disposed on the propeller protection assembly 40. The parameters of the first propeller 21 and the second propeller 22 can be the same or different. For example, the size of the first propeller 21 can be smaller than the size of the second propeller 22, or the weight of the first propeller 21 can be less than the weight of the second propeller 22.

[0067] Please see Figure 4 In some embodiments, the propeller protection assembly 40 itself is provided with a first propeller 21. After the propeller protection assembly 40 is installed on the aircraft 100, the power assembly 30 of the aircraft 100 can be driven to the first propeller 21 of the propeller protection assembly 40, thereby driving the first propeller 21 to rotate and provide flight power for the aircraft 100. In addition, the aircraft body 10 of the aircraft 100 is also used to detachably connect with the second propeller 22. After the propeller protection assembly 40 is removed from the aircraft 100, the power assembly 30 can be driven to the second propeller 22, thereby driving the second propeller 22 to rotate. The second propeller 22 is used to provide flight power for the aircraft 100. The parameters of the second propeller 22 are different from the parameters of the first propeller 21. For example, the size of the first propeller 21 is smaller than the size of the second propeller 22. In this embodiment, the same power unit 30 of the aircraft 100 can be adapted to propellers 20 with different parameters. Thus, even with the propeller protection component 40 installed, the same power unit 30 of the aircraft 100 can be adapted to the first propeller 21. Figure 1 As shown; without the propeller protection assembly 40 installed, the same power assembly 30 of the aircraft 100 is adapted to the second propeller 22, as... Figure 4 As shown, the application scenarios of the aircraft 100 can be expanded.

[0068] For example, the propeller protection component 40 can be selected for installation depending on the actual usage scenario. For instance, in scenarios such as using the aircraft 100 for racing or controlling its flight via a remote control, the propeller protection component 40 can be removed, and the second propeller 22 can be connected to the power component 30. This results in a lighter and smaller aircraft 100, allowing for higher flight speeds, increased flight maneuverability, and extended flight time. Alternatively, when using the aircraft 100 outdoors, such as in a populated park, the propeller protection component 40 can be installed on the aircraft body 10 to prevent the propeller 20 from accidentally injuring people or objects and causing damage to the propeller 20, providing a safe operating environment for the user. Furthermore, when the aircraft 100 needs to take off and / or land on the user's hand, the propeller protection component 40 can be installed on the aircraft body 10 to prevent the propeller 20 from accidentally injuring the user and causing damage to the propeller 20, providing a safe operating environment for the user.

[0069] Understandably, the parameters of propeller 20 include at least one of the following: size, weight, structure, etc. In some embodiments, the size of the first propeller 21 is smaller than the size of the second propeller 22. Exemplarily, the aircraft 100 has a visual sensor 13, and the visual sensor 13 is typically located around the aircraft 100 (e.g., around the perimeter of the aircraft 100). Figure 1As shown in the diagram, the propeller 20 is typically located on the arm 12 extending from the main body 10 of the aircraft. Therefore, when the aircraft 100 is in operation, an excessively large size (or length / diameter) of the propeller 20 may affect the sensing range of the vision sensor 13, thereby affecting the perception capability of the aircraft 100. The size of the propeller 20 is related to the power parameters of the aircraft 100; generally speaking, the larger the size of the propeller 20, the greater the power it can generate. Therefore, the design of the propeller 20 takes into account the sensing range of the vision sensor 13, and tries to achieve a balance between size and not obstructing the vision sensor 13. Thus, the size of the second propeller 22 installed on the aircraft 100 without the propeller protection component 40 is often made as large as possible while ensuring that the excessive size of the propeller 20 does not obstruct the sensing range of the vision sensor 13. The propeller protection component 40 is typically located outside the propeller 20. Therefore, the size of the propeller protection component 40 is usually larger than the size of the propeller 20. If the propeller protection component 40 itself does not house the first propeller 21 but is adapted to the second propeller 22, then placing the propeller protection component 40 on the second propeller 22 mounted on the aircraft 100 might cause the propeller protection component 40 to be too large, thus obstructing the sensing range of the visual sensor 13. Therefore, in the solution provided by this invention, the aircraft 100 can adapt to two different sizes of propeller 20. This is achieved when the aircraft 100 is not equipped with the propeller protection component 40. The aircraft 100 can be adapted to a larger second propeller 22 to improve the flight power of the aircraft 100 without obstructing the perception range of the visual sensor 13. When the aircraft 100 is equipped with the propeller protection component 40, the aircraft 100 can be adapted to a smaller first propeller 21. This avoids obstructing the perception range of the visual sensor 13 due to the addition of the propeller protection component 40. Therefore, regardless of whether the aircraft 100 is equipped with the propeller protection component 40, it will not affect the sensing range of the visual sensor 13 of the aircraft 100, thereby ensuring the perception capability of the aircraft 100 and improving the flight safety of the aircraft 100.

[0070] In some embodiments, the weight of the first propeller 21 is less than the weight of the second propeller 22. By reducing the weight of the first propeller 21, the overall weight of the propeller protection assembly 40 is reduced, avoiding a situation where the flight time of the aircraft 100 is excessively reduced compared to the situation where the second propeller 22 is installed after the propeller protection assembly 40 is installed on the aircraft 100.

[0071] In some embodiments, when the propeller protection assembly 40 is installed on the aircraft body 10 of the aircraft 100, the propeller protection assembly 40 remains fixed relative to the aircraft body 10, and the first propeller 21 is rotatable relative to the aircraft body 10. Exemplarily, when the propeller protection assembly 40 is installed on the aircraft body 10, the protective cover 41 remains fixed relative to the aircraft body 10, and the first propeller 21 is rotatable relative to the aircraft body 10. This ensures that the propeller protection assembly 40 is reliably installed on the aircraft body 10, and that the power assembly 30 can drive the first propeller 21 to rotate, thereby providing flight power to the aircraft 100.

[0072] Please see Figure 5 In some embodiments, the protective cover 41 includes an enclosure portion 411 and an assembly portion 412. The assembly portion 412 is connected to the enclosure portion 411, and the enclosure portion 411 forms an accommodating space 4110. The first propeller 21 is at least partially disposed within the accommodating space 4110, and the first propeller 21 is connected to the assembly portion 412. The enclosure portion 411 is used to prevent the first propeller 21 from colliding with people or objects outside the enclosure portion 411 when rotating, so that the protective cover 41 can both protect the first propeller 21 and prevent the first propeller 21 from damaging people or objects outside the enclosure portion 411 when rotating. The first propeller 21 and the assembly portion 412 can be detachably connected or non-detachably connected. Exemplarily, the connection method between the first propeller 21 and the assembly portion 412 can include at least one of the following: magnetic connection, snap-fit ​​connection, screw locking connection, adhesive connection, etc.

[0073] Please see Figure 5 In some embodiments, the enclosure 411 includes a first mesh 4111 connected to the mounting portion 412, with the first propeller 21 positioned above or below the first mesh 4111. In this case, the propeller protection assembly 40 can protect the first propeller 21 with only one mesh, saving on the overall weight of the propeller protection assembly 40. The enclosure 411 includes the first mesh 4111, which has a mesh structure. Thus, the first mesh 4111 not only provides protection but also reduces the weight of the propeller protection assembly 40, thereby reducing the weight of the aircraft 100 and improving its endurance. The first mesh 4111 can be made of lightweight materials such as carbon fiber or rope to reduce the overall weight of the propeller protection assembly 40 and improve the endurance of the aircraft 100 after installation.

[0074] Please see Figure 5In some embodiments, the enclosure portion 411 includes a first mesh 4111 and a second mesh 4112, at least one of the first mesh 4111 and the second mesh 4112 being connected to the assembly portion 412, and the first propeller 21 being disposed between the first mesh 4111 and the second mesh 4112. The first mesh 4111 and the second mesh 4112 are arranged vertically, forming an accommodating space 4110 between them. In this configuration, the propeller protection assembly 40 can achieve enclosed protection of the first propeller 21 by using only two meshes, thereby improving the protection capability of the propeller protection assembly 40 for the first propeller 21. The enclosure 411 includes both a first net body 4111 and a second net body 4112, which can improve the degree of enclosure of the first propeller 21. Therefore, during the rotation of the first propeller 21, in the event of a possible collision, the protective cover 41 can protect the first propeller 21, people, or objects. It can also prevent the first propeller 21 from flying out of the protective cover 41 and injuring people in the event of abnormal propeller ejection. Furthermore, it can effectively reduce the probability of interference from adverse factors such as branches and leaves to the first propeller 21. For example, the first net body 4111 and / or the second net body 4112 can be made of lightweight materials such as carbon fiber or ropes to reduce the overall weight of the propeller protection assembly 40, thereby improving the endurance of the aircraft 100 after the propeller protection assembly 40 is installed on the aircraft 100.

[0075] Please see Figure 5 In some embodiments, the shape of the surrounding portion 411 includes an annular shape. Exemplarily, the first mesh body 4111 and the second mesh body 4112 belong to the surrounding portion 411. For example, the first mesh body 4111 and the second mesh body 4112 are spaced apart and opposite to each other, and the first mesh body 4111 and the second mesh body 4112 are respectively connected to each other by connectors. In some embodiments, the shape of the surrounding portion 411 includes an annular shape, which includes circular annular or non-circular annular shapes. Exemplarily, non-circular annular shapes include at least one of the following: rectangle, rhombus, square, triangle, parallelogram, trapezoid, other arbitrary regular or irregular shapes, etc.

[0076] In some embodiments of this utility model, the propeller protection assembly 40 is provided with a propeller 20 but without a power assembly 30. The propeller protection assembly 40 can be installed on the aircraft 100 through the quick-release structure 50 to expand and enrich the form design of the propeller protection assembly 40 and meet the usage needs in more scenarios.

[0077] For this purpose, please refer to Figure 1 and Figure 6This utility model embodiment provides a propeller protection assembly 40, including a protective cover 41 and a first propeller 21. The protective cover 41 is used to provide protection for the first propeller 21. The propeller protection assembly 40 is configured to be detachably connected to the aircraft body 10 of the aircraft 100. After the propeller protection assembly 40 is installed on the aircraft 100, the first propeller 21 is used for transmission connection with the power assembly 30 of the aircraft 100, thereby providing flight power to the aircraft 100. The propeller protection assembly 40 does not have the power assembly 30 installed; the power assembly 30 is located on the aircraft 100.

[0078] The propeller protection component 40 provided in the above embodiment can be quickly and easily connected to the aircraft 100. This reduces the probability of the first propeller 21 colliding directly with an obstacle and being damaged, and also reduces the safety risk of the first propeller 21 causing cuts to the external environment (such as people or other objects) when rotating, thus improving the safety of the aircraft 100. When the propeller protection component 40 is not needed, it can be detached from the aircraft body 10. Furthermore, since the propeller protection assembly 40 has a first propeller 21 but no power assembly 30, after the propeller protection assembly 40 is installed on the aircraft 100, the first propeller 21 can be connected to the power assembly 30 of the aircraft 100 to provide flight power for the aircraft 100. This optimizes, expands, and enriches the form design of the propeller protection assembly 40, meeting the needs of more usage scenarios. Moreover, since the propeller protection assembly 40 does not have a power assembly 30, it is possible to replace the propeller protection assembly 40 without simultaneously replacing the power assembly 30, reducing maintenance and after-sales costs. Additionally, the absence of a power assembly 30 in the propeller protection assembly 40 reduces its individual weight and size.

[0079] Please see Figure 5 In some embodiments, the propeller protection assembly 40 is detachably connected to the aircraft body 10 of the aircraft 100 via a quick-release structure 50. This facilitates rapid assembly and disassembly of the propeller protection assembly 40 and the aircraft body 10, resulting in a modular structure. This allows for the individual replacement of the propeller protection assembly 40 or the aircraft body 10 without the need for a complete replacement of both, reducing maintenance and after-sales costs. It also facilitates the separate storage of the propeller protection assembly 40 or the aircraft body 10, reducing storage volume.

[0080] Please see Figure 5In some embodiments, the quick-release structure 50 includes a first connecting portion 51 and a second connecting portion 52. The first connecting portion 51 can cooperate with the second connecting portion 52 to allow the propeller protection assembly 40 to be detachably connected to the aircraft body 10. The configuration of the first connecting portion 51 and the second connecting portion 52 provides a guarantee for the detachable connection between the propeller protection assembly 40 and the aircraft body 10.

[0081] Please see Figure 5 In some embodiments, the first connecting portion 51 and the second connecting portion 52 include a non-magnetic connection structure. Understandably, a non-magnetic connection structure means that the connection between the first connecting portion 51 and the second connecting portion 52 is not achieved through the action of a magnetic field; that is, the connection is achieved through a connection method other than magnetic attraction. Thus, even in environments with strong magnetic fields or electromagnetic interference, the connection or disconnection of the first connecting portion 51 and the second connecting portion 52 is less susceptible to magnetic interference, improving the reliability of the connection between the propeller protection assembly 40 and the aircraft body 10, and avoiding the probability of the first connecting portion 51 and the second connecting portion 52 accidentally separating due to an external magnetic field, thereby improving the operational safety of the aircraft 100. Furthermore, since the first connecting portion 51 and the second connecting portion 52 are not magnetically connected, there is no need to use expensive magnetic materials, and the manufacturing process is simple, which helps to reduce costs.

[0082] Please see Figure 5 In some embodiments, the non-magnetic connection structure includes a mechanical engagement structure. For example, the first connecting portion 51 can engage with the second connecting portion 52 to allow the propeller protection assembly 40 to be detachably connected to the aircraft body 10. This facilitates the disassembly and assembly of the propeller protection assembly 40 and the aircraft body 10, and the mechanical engagement structure provides a locking function, reducing the probability of easy detachment and improving safety. Furthermore, because the non-magnetic connection structure includes a mechanical engagement structure, the connection between the first connecting portion 51 and the second connecting portion 52 is reliable, the structure is simple, has few components, and is low-cost. In other embodiments, the non-magnetic structure may also include at least one of the following: threaded connection, screw-locking connection, etc.

[0083] Please see Figure 5 and Figure 7In some embodiments, one of the first connecting portion 51 and the second connecting portion 52 includes a latching protrusion or hook, and the other includes a slot. Thus, the first connecting portion 51 and the second connecting portion 52 can be reliably connected, and the connection or disconnection between them can be quickly achieved. Assembly and disassembly of the propeller protection assembly 40 and the aircraft body 10 can be completed quickly without additional fasteners or tools, making the operation simple and cost-effective. For example, the first connecting portion 51 includes a latching protrusion or hook, and the second connecting portion 52 includes a slot, so that the first connecting portion 51 can engage with the second connecting portion 52. Alternatively, the first connecting portion 51 includes a slot, and the second connecting portion 52 includes a latching protrusion or hook.

[0084] In some embodiments, the first connecting portion 51 and the second connecting portion 52 include a magnetic connection structure. Thus, the connection between the first connecting portion 51 and the second connecting portion 52 does not require precise alignment; they automatically magnetically attract each other when brought close together, making operation simple and quick.

[0085] In some embodiments, both the first connecting portion 51 and the second connecting portion 52 are magnets. In some embodiments, one of the first connecting portion 51 and the second connecting portion 52 is a magnet, and the other is a magnetic attraction component that can magnetically engage with the magnet.

[0086] Please see Figure 7 In some embodiments, the first connecting portion 51 is disposed on the propeller protection assembly 40, and the second connecting portion 52 is disposed on the aircraft body 10 of the aircraft 100. This simplifies the structure of the quick-release structure 50 and improves the connection reliability between the first connecting portion 51 and the second connecting portion 52, thereby improving the connection reliability between the propeller protection assembly 40 and the aircraft body 10. Exemplarily, the first connecting portion 51 is disposed on the propeller protection assembly 40 or the protective cover 41, and the second connecting portion 52 is disposed on the aircraft body 10. In other embodiments, the first connecting portion 51 and the second connecting portion 52 may both be disposed on the propeller protection assembly 40 or the protective cover 41; or, the first connecting portion 51 and the second connecting portion 52 may both be disposed on the aircraft body 10. In some embodiments, the first connecting portion 51 is disposed below the first propeller 21.

[0087] Please see Figure 5In some embodiments, the second connection portion 52 is disposed on a structural member 60 for supporting the power assembly 30, and the structural member 60 is disposed on the aircraft body 10 of the aircraft 100. Thus, the structural shape of the aircraft body 10 is minimally affected. Exemplarily, the structural member 60 includes a motor mount. Exemplarily, the structural member 60 is disposed on the arm 12 and / or fuselage 11 of the aircraft 100. For example, the structural member 60 is disposed on the arm 12; or, the structural member 60 is disposed on the fuselage 11; or, a portion of the structural member 60 is disposed on the arm 12 and another portion on the fuselage 11. The structural member 60 may be integrally formed with at least a portion of the aircraft body 10, or may be disposed separately.

[0088] In some embodiments, one of the first connecting portion 51 and the second connecting portion 52 can move toward the other, so that the first connecting portion 51 can be connected to the second connecting portion 52. This facilitates rapid connection between the first connecting portion 51 and the second connecting portion 52, thereby enabling rapid assembly of the propeller protection assembly 40 and the aircraft body 10. For example, the first connecting portion 51 can move toward a direction closer to itself, so that the first connecting portion 51 can be connected to the second connecting portion 52. Similarly, the second connecting portion 52 can move toward a direction closer to itself, so that the first connecting portion 51 can be connected to the second connecting portion 52.

[0089] In some embodiments, one of the first connecting portion 51 and the second connecting portion 52 can move away from the other, so that the first connecting portion 51 can be disconnected from the second connecting portion 52. This facilitates rapid disconnection of the first connecting portion 51 from the second connecting portion 52, thereby enabling quick disassembly of the propeller protection assembly 40 from the aircraft body 10. For example, the first connecting portion 51 can move away from the first connecting portion 51 to disconnect it from the second connecting portion 52. Similarly, the second connecting portion 52 can move away from the first connecting portion 51 to disconnect it from the first connecting portion 51.

[0090] Please see Figure 5 and Figure 7In some embodiments, the quick-release structure 50 further includes a pressing member 53. A first connecting portion 51 or a second connecting portion 52 is disposed on the pressing member 53. The pressing member 53 is movably connected to the protective cover 41 or the aircraft body 10. By pressing the pressing member 53, the first connecting portion 51 and the second connecting portion 52 can be connected and / or disconnected. In this way, the connection or disconnection between the propeller protection assembly 40 and the aircraft body 10 is simple and convenient, and the connection between the first connecting portion 51 and the second connecting portion 52 is reliable. This helps to improve the connection reliability between the propeller protection assembly 40 and the aircraft body 10, and ensures the safe use of the aircraft 100. For example, the pressing member 53 is movably connected to the protective cover 41, and the first connecting portion 51 is disposed on the pressing member 53. By pressing the pressing member 53, the first connecting portion 51 and the second connecting portion 52 can be connected or disconnected. In other embodiments, the pressing member 53 may not be part of the propeller protection assembly 40. For example, the pressing member 53 may be movably connected to the fuselage 11 or the arm 12, and the second connecting part 52 may be provided on the pressing member 53.

[0091] For example, pressing the pressing member 53 connects the first connecting part 51 and the second connecting part 52. For example, pressing the pressing member 53 disconnects the first connecting part 51 and the second connecting part 52. For example, pressing the pressing member 53 connects the first connecting part 51 and the second connecting part 52; and pressing the pressing member 53 disconnects the first connecting part 51 and the second connecting part 52. In this way, the connection and disconnection of the first connecting part 51 and the second connecting part 52 are not easily affected by the external environment or accidental operation. The disassembly and assembly operations between the propeller protection assembly 40 and the aircraft body 10 are simple, convenient, easy, and highly reliable. For example, the first connecting part 51 can engage with the second connecting part 52. When the propeller protection assembly 40 needs to be installed onto the aircraft body 10, the first connecting part 51 and the second connecting part 52 can be engaged by pressing the pressing member 53, thereby reliably connecting the propeller protection assembly 40 to the aircraft body 10. When the propeller protection assembly 40 needs to be disassembled from the aircraft body 10, the first connecting part 51 and the second connecting part 52 can be disengaged by pressing the pressing member 53, thereby deconnecting the propeller protection assembly 40 from the aircraft body 10. The connection and disconnection of the first connecting part 51 and the second connecting part 52 are both achieved by pressing the pressing member 53, making disassembly and assembly simpler and more convenient. The connection between the first connecting part 51 and the second connecting part 52 is more reliable, which helps to further improve the connection reliability between the propeller protection assembly 40 and the aircraft body 10, ensuring the safe use of the aircraft 100. For example, the number of pressing members 53 includes two, which can form a clamp-type pressing structure. In the natural state where the clamp-type pressing structure is not subjected to external force, there is a first distance between the first connecting portions 51 on the two pressing members 53. When the first connecting portion 51 on each pressing member 53 is connected to the corresponding second connecting portion 52, there is still a first distance between the first connecting portions 51 on the two pressing members 53. When it is necessary to connect the first connecting portion 51 and the second connecting portion 52, the first connecting portions 51 of the two pressing members 53 can be moved away from each other by pressing the pressing members 53, so that there is sufficient distance between the first connecting portion 51 and the second connecting portion 52 to achieve alignment and installation. After releasing, the first connecting portion 51 of each pressing member 53 is connected to the corresponding second connecting portion 52. When it is necessary to disconnect the first connecting part 51 and the second connecting part 52, the first connecting parts 51 of the two pressing members 53 can be moved away from each other by pressing the pressing member 53, thereby disconnecting the first connecting part 51 of each pressing member 53 from the corresponding second connecting part 52. In this case, the clip-type pressing structure is retracted by default and needs to be pressed to connect or disconnect the first connecting part 51 and the second connecting part 52.

[0092] Please see Figure 8 and Figure 9 ,in, Figure 8 The first connecting part 51 and the second connecting part 52 are connected in place; Figure 9 The first connecting part 51 and the second connecting part 52 are not properly connected. Please refer to [link / reference]. Figure 8 and Figure 9 In some embodiments, one of connecting and disconnecting is achieved by pressing the pressing member 53, and the other of connecting and disconnecting is achieved by prying open the pressing member 53. For example, when it is necessary to install the propeller protection assembly 40 to the aircraft body 10, the first connecting portion 51 can be connected to the second connecting portion 52 by pressing the pressing member 53; when it is necessary to disassemble the propeller protection assembly 40 from the aircraft body 10, the first connecting portion 51 can be disconnected from the second connecting portion 52 by prying open the pressing member 53. For example, the first connecting part 51 can engage with the second connecting part 52; when it is necessary to install the propeller protection assembly 40 onto the aircraft body 10, the first connecting part 51 and the second connecting part 52 can be engaged by pressing the pressing member 53, thereby reliably connecting the propeller protection assembly 40 to the aircraft body 10; when it is necessary to disassemble the propeller protection assembly 40 from the aircraft body 10, the first connecting part 51 and the second connecting part 52 can be disengaged by prying open the pressing member 53, thereby deconnecting the propeller protection assembly 40 from the aircraft body 10. Exemplarily, the number of pressing members 53 includes two, and the two pressing members 53 can form a clamp-type pressing structure. In the natural state where the clamp-type pressing structure is not subjected to external force, there is a first distance between the first connecting parts 51 on the two pressing members 53; when the first connecting part 51 on each pressing member 53 is connected to the corresponding second connecting part 52, there is a second distance between the first connecting parts 51 on the two pressing members 53, and the first distance is greater than the second distance. When it is necessary to disconnect the first connecting part 51 and the second connecting part 52, the first connecting parts 51 of the two pressing parts 53 can be pried open to move them away from each other, thereby disconnecting the first connecting part 51 of each pressing part 53 from the corresponding second connecting part 52. In this case, the clip-type pressing structure is open by default and needs to be pressed to connect the first connecting part 51 and the second connecting part 52. In other embodiments, when it is necessary to install the propeller protection assembly 40 to the aircraft body 10, the first connecting part 51 and the second connecting part 52 can be connected by prying open the pressing part 53; when it is necessary to disassemble the propeller protection assembly 40 from the aircraft body 10, the first connecting part 51 and the second connecting part 52 can be disconnected by pressing the same pressing part 53.

[0093] Please see Figure 10In some embodiments, one of connecting and disconnecting is achieved by applying force to the first force-applying portion 531 of the pressing member 53, and the other of connecting and disconnecting is achieved by applying force to the second force-applying portion 532 of the pressing member 53. The first force-applying portion 531 and the second force-applying portion 532 are different. Exemplarily, applying force to the first force-applying portion 531 of the pressing member 53 connects the first connecting portion 51 to the second connecting portion 52, and applying force to the second force-applying portion 532 of the pressing member 53 disconnects the first connecting portion 51 from the second connecting portion 52. Exemplarily, applying force to the second force-applying portion 532 of the pressing member 53 connects the first connecting portion 51 to the second connecting portion 52, and applying force to the first force-applying portion 531 of the pressing member 53 disconnects the first connecting portion 51 from the second connecting portion 52. In other embodiments, the first force-applying portion 531 may be the same as the second force-applying portion 532.

[0094] For example, the first force-applying part 531 and the second force-applying part 532 may be located on different sides of the pressing member 53. For instance, the first force-applying part 531 and the second force-applying part 532 may be located on opposite sides of the pressing member 53, such as the first force-applying part 531 being located on the outer side of the pressing member 53 and the second force-applying part 532 being located on the inner side of the pressing member 53. By pressing the first force-applying part 531 of the pressing member 53, the first connecting part 51 and the second connecting part 52 can be connected; by prying the second force-applying part 532 of the pressing member 53 outward, the first connecting part 51 and the second connecting part 52 can be disconnected. In other embodiments, the first force-applying part 531 and the second force-applying part 532 may also be located in different areas on the same side of the pressing member 53.

[0095] In some embodiments, the direction of force applied to the first force-applying part 531 is different from the direction of force applied to the second force-applying part 532. For example, the direction of force applied to the first force-applying part 531 is opposite to the direction of force applied to the second force-applying part 532. For instance, the first force-applying part 531 is located on the outer side of the pressing member 53, and the second force-applying part 532 is located on the inner side of the pressing member 53. By pressing the first force-applying part 531 of the pressing member 53, the first connecting part 51 and the second connecting part 52 can be connected; by prying the second force-applying part 532 of the pressing member 53 outward, the first connecting part 51 and the second connecting part 52 can be disconnected. In other embodiments, the direction of force applied to the first force-applying part 531 is not parallel to the direction of force applied to the second force-applying part 532.

[0096] In some embodiments, the pressing member 53 can be subjected to a first force to connect the first connecting portion 51 and the second connecting portion 52, and the pressing member 53 can be subjected to a second force to disconnect the first connecting portion 51 and the second connecting portion 52, wherein the first force and the second force are applied in the same direction.

[0097] In some embodiments, each propeller protection assembly 40 is provided with one or more pressing members 53, and each pressing member 53 is provided with at least one first connecting portion 51. For example, each propeller protection assembly 40 is provided with one pressing member 53, which is provided with at least one first connecting portion 51. Alternatively, each propeller protection assembly 40 is provided with multiple pressing members 53, such as two, three, four or more; each pressing member 53 is provided with at least one first connecting portion 51. In this way, the connection and / or disconnection between each propeller protection assembly 40 and the aircraft body 10 is simple and convenient, and each propeller protection assembly 40 can be reliably connected to the aircraft body 10, which is beneficial to improving the safety performance of the aircraft 100.

[0098] For example, the number of propeller protection components 40 includes multiple components, and the number of pressing members 53 provided in each propeller protection component 40 may be the same; or they may be different; or, some of the propeller protection components 40 may have the same number of pressing members 53, while some of the propeller protection components 40 may have different numbers of pressing members 53.

[0099] Please see Figure 9 In some embodiments, each propeller protection assembly 40 is provided with a plurality of pressing members 53, and second connecting parts 52 on the aircraft body 100 corresponding to at least two of the first connecting parts 51 of each pressing member 53 are spaced apart. For example, one propeller protection assembly 40 is provided with a plurality of pressing members 53, the first connecting part 51 of one of the pressing members 53 can cooperate with one of the second connecting parts 52a of the aircraft body 10, the first connecting part 51 of another pressing member 53 can cooperate with another second connecting part 52b of the aircraft body 10, and the second connecting parts 52a and 52b are spaced apart on the aircraft body 10.

[0100] In some embodiments, each propeller protection assembly 40 is provided with multiple pressing members 53. By pressing the multiple pressing members 53, the first connecting part 51 and the second connecting part 52 are connected and / or disconnected, thereby connecting or disconnecting the propeller protection assembly 40 from the aircraft body 10 of the aircraft 100. Thus, multiple pressing members 53 need to be pressed to connect or disconnect the propeller protection assembly 40 from the aircraft body 10, preventing accidental triggering of a single pressing member 53 that could lead to disconnection, thus improving the reliability and safety of the connection between the propeller protection assembly 40 and the aircraft body 10. Furthermore, by using multiple pressing members 53 to cooperate in connecting and / or disconnecting the first connecting part 51 and the second connecting part 52, the distance between the first connecting part 51 and the second connecting part 52 is greater, making it easier to connect and / or disconnect the first connecting part 51 and the second connecting part 52.

[0101] In some embodiments, at least two of the plurality of pressing members 53 have different pressing directions. This facilitates easier and more convenient assembly or disassembly of the propeller protection assembly 40, thus improving the user experience. For example, at least two of the plurality of pressing members 53 have opposite pressing directions, which further facilitates easier and more convenient assembly or disassembly of the propeller protection assembly 40, further enhancing the user experience.

[0102] In some embodiments, multiple pressing members 53 are pressed together to connect and / or disconnect the first connecting portion 51 and the second connecting portion 52, thereby connecting or disconnecting the propeller protection assembly 40 from the aircraft body 10. Thus, by pressing multiple pressing members 53 together, the propeller protection assembly 40 can be connected or disconnected from the aircraft body 10, preventing accidental contact with a single pressing member 53 or impact from an external force on a single pressing member 53, thereby improving the reliability of the connection between the propeller protection assembly 40 and the aircraft body 10. Exemplarily, multiple pressing members 53 are pressed together to connect the first connecting portion 51 and the second connecting portion 52, thereby connecting the propeller protection assembly 40 to the aircraft body 10 of the aircraft 100. Exemplarily, multiple pressing members 53 are pressed together to disconnect the first connecting portion 51 and the second connecting portion 52, thereby disconnecting the propeller protection assembly 40 from the aircraft body 10 of the aircraft 100. For example, multiple pressing members 53 are pressed together to connect the first connecting part 51 and the second connecting part 52, thereby connecting the propeller protection assembly 40 to the aircraft body 10 of the aircraft 100; multiple pressing members 53 are pressed together to disconnect the first connecting part 51 and the second connecting part 52, thereby disconnecting the propeller protection assembly 40 from the aircraft body 10 of the aircraft 100.

[0103] In some embodiments, the plurality of pressing members 53 includes two pressing members 53, which simplifies the structure and enables the propeller protection assembly 40 to have good connection reliability with the aircraft body 10. Exemplarily, a user can simultaneously press both pressing members 53 of the same propeller protection assembly 40 with one hand to connect and / or disconnect the propeller protection assembly 40 from the aircraft body 10, improving operational efficiency and user experience. Exemplarily, the two pressing members 53 of the same propeller protection assembly 40 are arranged opposite each other, allowing the user to press both pressing members 53 simultaneously with one hand more easily and effortlessly, making the assembly and / or disassembly of the propeller protection assembly 40 more effortless and convenient.

[0104] In some embodiments, the pressing member 53 includes a clip-type pressing member. This allows for easier and less strenuous removal of the propeller protection assembly 40, improving the user experience. See also... Figure 5 For example, the number of pressing members 53 includes two, and the two pressing members 53 can form a clamp-type pressing structure. The connection and disconnection between the first connecting part 51 and the corresponding second connecting part 52 of each pressing member 53 are achieved by pressing the pressing member 53.

[0105] In some embodiments, the first connecting portions 51 of the plurality of pressing members 53 included in each propeller protection assembly 40 are spaced apart. Exemplarily, the same propeller protection assembly 40 includes a plurality of pressing members 53, and the first connecting portions 51 of the plurality of pressing members 53 of the same propeller protection assembly 40 are spaced apart. Thus, when connecting or disconnecting the propeller protection assembly 40 from the aircraft body 10, the first connecting portions 51 of different pressing members 53 of the same propeller protection assembly 40 will not interfere with each other, and it also provides the user with more operating space, ensuring smooth and convenient pressing of multiple pressing members 53 to achieve rapid assembly or disassembly of the propeller protection assembly 40. In some embodiments, the first connecting portions 51 of the plurality of pressing members 53 included in each propeller protection assembly 40 are arranged opposite each other. For example, the same propeller protection assembly 40 includes a plurality of pressing members 53, and the first connecting portions 51 of the plurality of pressing members 53 of the same propeller protection assembly 40 are arranged opposite to each other, so that the user can press at least two of the plurality of pressing members 53 simultaneously with one hand with less effort and more convenient, making the assembly and / or disassembly of the propeller protection assembly 40 more effortless and convenient.

[0106] Please see Figure 11 In some embodiments, the first connecting portion 51 and the second connecting portion 52 are rotatable relative to each other, allowing the first connecting portion 51 to connect with or disconnect from the second connecting portion 52. For example, when the propeller protection assembly 40 needs to be installed on the aircraft body 10, one of the first connecting portion 51 and the second connecting portion 52 can be rotated relative to the other, so that the first connecting portion 51 and the second connecting portion 52 remain connected. When the propeller protection assembly 40 needs to be disassembled from the aircraft body 10, one of the first connecting portion 51 and the second connecting portion 52 can be rotated relative to the other, so that the first connecting portion 51 and the second connecting portion 52 can be disconnected. Thus, the quick-release structure 50 has a reasonable and ingenious structural design, occupies little space, and helps to reduce the volume of the aircraft 100 on which the propeller protection assembly 40 is installed.

[0107] In some embodiments, the propeller protection assembly 40 is provided with a first groove (not shown), and the second connecting portion 52 can slide relative to the first groove, so that the second connecting portion 52 can rotate relative to the propeller protection assembly 40 until the second connecting portion 52 is reliably connected to the first connecting portion 51, thereby reliably connecting the propeller protection assembly 40 to the aircraft body 10. The first groove can reduce the probability of the connection between the first connecting portion 51 and the second connecting portion 52 easily becoming loose and separating, which is beneficial to improving the connection reliability between the propeller protection assembly 40 and the aircraft body 10, and reducing the probability that the propeller protection assembly 40 and the aircraft body 10 are easily separated due to external interference. For example, the second connecting portion 52 can slide relative to the first groove, so that the second connecting portion 52 can rotate relative to the propeller protection assembly 40 until the second connecting portion 52 is far away from or disengaged from the first connecting portion 51, thereby deconnecting the first connecting portion 51 and the second connecting portion 52, and deconnecting the propeller protection assembly 40 from the aircraft body 10.

[0108] Please see Figure 11 In some embodiments, the aircraft body 10 of the aircraft 100 is provided with a second slide groove 44, and the first connecting portion 51 can slide relative to the second slide groove 44, so that the first connecting portion 51 can rotate relative to the aircraft body 10 of the aircraft 100 until the first connecting portion 51 and the second connecting portion 52 are connected. The second slide groove 44 can reduce the probability of the connection between the first connecting portion 51 and the second connecting portion 52 easily becoming loose and separating, which is beneficial to improving the connection reliability between the propeller protection assembly 40 and the aircraft body 10, and reducing the probability that the propeller protection assembly 40 and the aircraft body 10 are easily separated due to interference from external factors. For example, the first connecting portion 51 can slide relative to the second slide groove 44, so that the first connecting portion 51 can rotate relative to the aircraft body 10 of the aircraft 100 until the first connecting portion 51 and the second connecting portion 52 are far apart or separated, thereby deconnecting the first connecting portion 51 and the second connecting portion 52, and deconnecting the propeller protection assembly 40 from the aircraft body 10.

[0109] Please see Figure 12In some embodiments, both the first connecting portion 51 and the second connecting portion 52 are disposed on the propeller protection assembly 40. After the first connecting portion 51 and the second connecting portion 52 are connected, the quick-release structure 50 and / or at least part of the protective cover 41 can surround at least part of the aircraft body 10 of the aircraft 100, so that the quick-release structure 50 can be fitted onto at least part of the aircraft body 10 of the aircraft 100, thereby connecting the propeller protection assembly 40 to the aircraft body 10. The fact that both the first connecting portion 51 and the second connecting portion 52 are disposed on the propeller protection assembly 40 is beneficial to reducing the weight and volume of the aircraft body 10, and can avoid slotting on the aircraft body 10, which is beneficial to the structural aesthetics of the aircraft; the design of the quick-release structure 50 is reasonable and simple. After the propeller protection assembly 40 is removed from the aircraft body 10, the weight of the aircraft body 10 is reduced, which is beneficial to extending the flight time of the aircraft 100 as much as possible. For example, the quick-release structure 50 and at least part of the protective cover 41 can surround at least part of the aircraft body 10 of the aircraft 100 so that the quick-release structure 50 can be fitted onto at least part of the aircraft body 10 of the aircraft 100. Alternatively, the quick-release structure 50 or at least part of the protective cover 41 can surround at least part of the aircraft body 10 of the aircraft 100 so that the quick-release structure 50 can be fitted onto at least part of the aircraft body 10 of the aircraft 100. For example, after the first connecting part 51 and the second connecting part 52 are connected, the quick-release structure 50 can be fitted onto the arm 12 of the aircraft 100.

[0110] Please see Figure 12 In some embodiments, the second connecting portion 52 is disposed on the protective cover 41, and the quick-release structure 50 further includes a locking member 54. The locking member 54 has a first connecting portion 51 and is movably connected to the protective cover 41, so that the first connecting portion 51 and the second connecting portion 52 can be connected or disconnected. In some embodiments, the locking member 54 may include a pressing member 53 of any suitable embodiment of the present invention. In other embodiments, the locking member 54 may also have any other suitable structure. For example, the locking member 54 may have a first connecting portion 51 that can magnetically engage with the second connecting portion 52. When connecting or disconnecting the first connecting portion 51 and the second connecting portion 52, it is not necessary to press the locking member 54; it can be achieved by pulling, pushing, or rotating the locking member 54. For example, the locking member 54 is provided with a first connecting part 51 that can magnetically engage with the second connecting part 52. By pulling, pushing, or rotating the locking member 54, the first connecting part 51 and the second connecting part 52 can be brought closer together and magnetically attracted, or the first connecting part 51 and the second connecting part 52 can be moved away from each other and the magnetic connection can be released. Exemplarily, the locking member 54 and the protective cover 41 can be movably connected in at least one of the following ways: rotational connection, sliding connection, etc.

[0111] In some embodiments, when the quick-release structure 50 is connected to the aircraft body 10, the mounting portion 412 of the locking member 54 and the protective cover 41 can surround the arm 12 of the aircraft 100. In this way, the propeller protection assembly 40 can be connected to the aircraft body 10 by surrounding and clamping the arm 12. The aircraft body 10 does not need to have a separate structure for connecting to the propeller protection assembly 40. The structure is simple and the number of parts is small, which helps to reduce cost and weight.

[0112] In some embodiments, the locking member 54 can surround at least a portion of the arm 12 of the aircraft 100 so that the locking member 54 or the quick-release structure 50 can be fitted onto the arm 12. This improves the reliability of the connection between the quick-release structure 50 and the arm 12, thereby improving the reliability of the connection between the propeller protection assembly 40 and the aircraft body 10. For example, the locking member 54 can surround a portion of the arm 12, and the mounting portion 412 of the protective cover 41 can surround a portion of the arm 12. The locking member 54 and the mounting portion 412 can cooperate to form a ring structure that can be fitted onto the arm 12. Alternatively, the locking member 54 can surround at least a portion of the arm 12, and the locking member 54 can cooperate to form a ring structure that can be fitted onto the arm 12.

[0113] Please see Figure 1 and Figure 5 In some embodiments, the propeller protection assembly 40 is provided with a flow guide 42, which corresponds to the heat dissipation section 14 of the aircraft body 10 of the aircraft 100. When the propeller protection assembly 40 is installed on the aircraft 100, the flow guide 42 is used to deliver at least a portion of the airflow generated by the rotation of the first propeller 21 to the heat dissipation section 14. In this way, the rotation of the first propeller 21 can not only provide flight power for the aircraft 100, but also dissipate heat for the aircraft body 10, thus expanding the function of the first propeller 21. The heat dissipation section 14 may include heat dissipation grooves or heat dissipation holes, etc. The heat dissipation section 14 may be disposed adjacent to the components to be cooled on the aircraft body 10. The components to be cooled may include the circuit board, sensors, power supply, or any other components of the aircraft 100 that require heat dissipation.

[0114] For example, the flow guide 42 can be integrally formed and connected to the protective cover 41. For example, the flow guide 42 is an independent component, and the flow guide 42 is connected to the protective cover 41. The connection method can include at least one of the following: adhesive connection, snap connection, screw locking connection, magnetic connection, etc.

[0115] The flow guide 42 can be designed into any suitable structure according to actual needs. In some embodiments, the flow guide 42 includes a flow guide groove. Exemplarily, the shape of the flow guide groove includes at least one of the following: straight, bent, etc. In other embodiments, the flow guide 42 may also include a flow guide hole or a flow guide surface, etc.

[0116] In some embodiments, no heat dissipation device is provided inside the aircraft body 10 of the aircraft 100. Thus, the airflow generated by the rotation of the first propeller 21 can dissipate heat from the aircraft body 10, eliminating the need for an additional heat dissipation device. This reduces the number of components, lightens the weight of the aircraft 100, and lowers costs. Exemplarily, a heat dissipation device includes a fan.

[0117] In some embodiments, after the propeller protection assembly 40 is installed on the aircraft 100, the airflow guide 42 is closer to the heat dissipation section 14 of the aircraft body 10 than the non-airflow guide section (not shown) in the propeller protection assembly 40. This allows the airflow generated by the rotation of the first propeller 21 to be delivered to the heat dissipation section 14 of the aircraft body 10 to the maximum extent, thereby improving the heat dissipation efficiency of the aircraft body 10. Exemplarily, the non-airflow guide section refers to the area in the propeller protection assembly 40 other than the airflow guide 42.

[0118] For example, each propeller protection assembly 40 may be provided with one or more flow guides 42. See also Figure 1 and Figure 5 In some embodiments, each propeller protection assembly 40 is provided with two airflow guides 42, which are symmetrically arranged on the propeller protection assembly 40. This allows users to blindly install the propeller protection assembly 40 without alignment, reducing the difficulty of installing the propeller protection assembly 40 to the aircraft body 10. For example, the installation direction of the first connecting part 51 and the second connecting part 52 corresponds to the position of the airflow guide 42 on the propeller protection assembly 40, such as being perpendicular to each other. In this way, the user can install the propeller protection assembly 40 without considering the orientation of the propeller protection assembly 40 by means of the mechanical installation position. After the propeller protection assembly 40 is installed, the airflow guide 42 can be aligned with the heat dissipation part 14.

[0119] Please see Figure 1 and Figure 5 For example, each propeller protection assembly 40 is provided with two airflow guides 42, which are symmetrically arranged on the propeller protection assembly 40. After the propeller protection assembly 40 is installed on the aircraft 100, one of the airflow guides 42 is closer to the heat dissipation part 14 than the non-airflow guides in the propeller protection assembly 40. In some embodiments, the two airflow guides 42 are symmetrically arranged on the propeller protection assembly 40 about the central axis of the propeller protection assembly 40, thus allowing the user to blindly install the propeller protection assembly 40. For example, the airflow guide 42 is connected to at least one of the surrounding part 411 and the mounting part 412 of the protective cover 41. For example, the airflow guide 42 is connected to the first mesh 4111 and / or the second mesh 4112 of the surrounding part 411.

[0120] In some embodiments, the propeller protection assembly 40 includes a first propeller 21 but no power assembly 30, while the aircraft 100 or the aircraft body 10 includes a power assembly 300. The first propeller 21 is detachably connected to the power assembly 30 of the aircraft 100. Thus, when the first propeller 21 is damaged, it is not necessary to replace the power assembly 30 simultaneously, reducing maintenance and after-sales costs. Furthermore, it allows the aircraft 100 to be adapted to different propellers 20. With the propeller protection assembly 40 installed, the same power assembly 30 of the aircraft 100 can be adapted to the first propeller 21; without the propeller protection assembly 40 installed, the same power assembly 30 of the aircraft 100 can be adapted to another propeller 20, thereby expanding the application scenarios of the aircraft 100.

[0121] Please see Figure 7 In some embodiments, the power assembly 30 includes a transmission part 31, and the first propeller 21 includes a transmission engagement part 211. The transmission part 31 can be connected to the transmission engagement part 211 in a transmission manner, so that the power assembly 30 can drive the first propeller 21 to move, thereby providing flight power for the aircraft 100.

[0122] In some embodiments, neither the transmission part 31 nor the transmission mating part 211 is a cylindrical shaft. Thus, without the need for additional structures, the transmission part 31 and the transmission mating part 211 can be relatively fixed, thereby achieving a transmission connection between them. The non-cylindrical shaft allows for better transmission of the torque from the power assembly 30 to the first propeller 21; the number of components is reduced, and the structure is simple. In some embodiments, one of the transmission part 31 and the transmission mating part 211 includes a key shaft, and the other includes a keyway. The key shaft can be transmissionally connected to the keyway so that the power assembly 30 is connected to the first propeller 21 by a key connection. The key shaft and keyway mating structure is simple, easy to install and disassemble, and the connection between the first propeller 21 and the power assembly 30 is reliable. Furthermore, the key shaft and keyway mating enables direct power transmission between the power assembly 30 and the first propeller 21, reducing energy loss and improving transmission efficiency. For example, one of the transmission part 31 and the transmission mating part 211 includes a splined shaft and the other includes a splined groove, and the splined shaft can be driven into the splined groove. The splined shaft and splined groove mating structure is simple, making installation and disassembly more convenient, and the connection between the first propeller 21 and the power assembly 30 is more reliable, with high transmission efficiency. The splined shaft can achieve a better effect of transmitting the torque of the power assembly 30 to the first propeller 21.

[0123] In some embodiments, one of the transmission part 31 and the transmission mating part 211 includes a non-cylindrical shaft, and the other includes a mating groove, wherein the non-cylindrical shaft can be driven into the mating groove. For example, the cross-sectional shape of the non-cylindrical shaft may include any of the following: elliptical, polygonal, oblong, other regular or irregular shapes besides a circle, etc.

[0124] In other embodiments, the transmission part 31 or the transmission mating part 211 may also be a cylindrical shaft. For example, the transmission part 31 includes a cylindrical shaft, and the transmission mating part 211 includes a transmission mating hole. The cylindrical shaft mates with the transmission mating hole to enable the power assembly 30 to be connected to the first propeller 21 in a transmission manner. Optionally, a structural component can also be used to transmit the torque of the power assembly 30 to the first propeller 21. For example, the first propeller 21 on the propeller protection assembly 40 can be fixedly mounted to the motor mount of the power assembly 30 through a structural component, so that the power of the power assembly 30 can be transmitted to the first propeller 21 through the structural component.

[0125] Furthermore, this utility model also provides a method for storing the propeller protection assembly 40. Please refer to [link / reference]. Figure 13 For example, after all propeller protection assemblies 40 of the aircraft 100 have been removed from the aircraft body 10 of the aircraft 100, each propeller protection assembly 40 can be installed together. Thus, after all propeller protection assemblies 40 of the aircraft 100 have been removed from the aircraft body 10, multiple propeller protection assemblies 40 can be stored without the aircraft body 10, thereby reducing the storage volume of the multiple propeller protection assemblies 40 and achieving portable and quick storage of the propeller protection assemblies 40; it also reduces the probability of the propeller protection assemblies 40 being easily lost after being removed from the aircraft body 10; and it also reduces the storage volume of the aircraft body 10. After all propeller protection assemblies 40 are assembled together, if it is necessary to install the propeller protection assemblies 40 onto the aircraft body 10, the multiple propeller protection assemblies 40 installed together can be quickly disassembled and separated.

[0126] Please see Figure 13In some embodiments, after all propeller protection components 40 of the aircraft 100 have been removed from the aircraft body 10, the propeller protection components 40 can be stacked together. Thus, after all propeller protection components 40 of the aircraft 100 have been removed from the aircraft body 10, multiple propeller protection components 40 can be stacked and stored, meaning that multiple propeller protection components 40 can be stored without the aircraft body 10, reducing the storage volume of the multiple propeller protection components 40 and the storage volume of the aircraft body 10; it also reduces the probability of the propeller protection components 40 being easily lost after being removed from the aircraft body 10. After all the propeller protection components 40 are stacked together, if it is necessary to install the propeller protection components 40 onto the aircraft body 10, the stacked multiple propeller protection components 40 can be quickly disassembled and separated.

[0127] Please see Figure 13 In some embodiments, when the propeller protection assemblies 40 are stacked together, adjacent propeller protection assemblies 40 are not misaligned, or the pressing members 53 of adjacent propeller protection assemblies 40 are not misaligned. This allows the propeller protection assemblies 40 to be more compact when stored, minimizing the total storage volume of the aircraft 100's propeller protection assemblies 40. For example, when the propeller protection assemblies 40 are stacked together, adjacent propeller protection assemblies 40 are stacked in the same direction, or the pressing members 53 of adjacent propeller protection assemblies 40 are stacked in the same direction. This allows the total propeller protection assemblies 40 of the aircraft 100 to be more compact when stored, minimizing the total storage volume of the aircraft 100's propeller protection assemblies.

[0128] Please see Figure 14 In some embodiments, when the propeller protection assemblies 40 are stacked together, adjacent propeller protection assemblies 40 are staggered, or the pressing members 53 of adjacent propeller protection assemblies 40 are staggered. This prevents interference between the structural parts (such as the pressing members 53 or the first connecting part 51) of adjacent propeller protection assemblies 40, and facilitates a more compact arrangement of the propeller protection assemblies 40 during storage, minimizing the storage volume of each propeller protection assembly 40.

[0129] Please see Figure 13 and Figure 15In some embodiments, the propeller protection assembly 40 further includes a third connecting portion 45. After all propeller protection assemblies 40 of the aircraft 100 have been removed from the aircraft body 10 of the aircraft 100, the third connecting portion 45 is used to connect with the fourth connecting portion 46 of other propeller protection assemblies 40, so that the propeller protection assembly 40 can be installed together with other propeller protection assemblies 40. In this way, after all propeller protection assemblies 40 with the first propeller 21 have been removed from the aircraft 100, multiple propeller protection assemblies 40 can be stored without the aircraft body 10, thereby reducing the storage volume of multiple propeller protection assemblies 40 and realizing the portable and quick storage of propeller protection assemblies 40; it can also reduce the probability of easy loss after all propeller protection assemblies 40 of the aircraft 100 are removed from the aircraft body 10. Exemplarily, the third connecting portion 45 or the fourth connecting portion 46 is provided on the protective cover 41. For example, the plurality of propeller protection assemblies 40 includes four propeller protection assemblies 40; after the propeller protection assemblies 40 of the aircraft 100 are removed from the aircraft body 10, each propeller protection assembly 40 includes a third connecting portion 45 and a fourth connecting portion 46, the third connecting portion 45 and the fourth connecting portion 46 being located on different sides of the propeller protection assembly 40, for example, the third connecting portion 45 being located on the first mesh 4111 of the propeller protection assembly 40, and the fourth connecting portion 46 being located on the second mesh 4112 of the propeller protection assembly 40. Optionally, the third connecting portion 45 may be located at the outer edge of the first mesh 4111, and the fourth connecting portion 46 may be located at the outer edge of the second mesh 4112 of the propeller protection assembly 40. The third connecting portion 45 of each propeller protection component 40 is used to connect to the fourth connecting portion 46 of another adjacent propeller protection component 40, and the fourth connecting portion 46 of each propeller protection component 40 is used to connect to the third connecting portion 45 of another adjacent propeller protection component 40, so that the four propeller protection components 40 are installed together. Each propeller protection component 40 is provided with a third connecting portion 45 and a fourth connecting portion 46, which enables multiple propeller protection components 40 to be stacked arbitrarily without considering the stacking order.For example, the plurality of propeller protection assemblies 40 includes four propeller protection assemblies 40. After the propeller protection assemblies 40 of the aircraft 100 are removed from the aircraft body 10, the two outermost propeller protection assemblies 40 after stacking may only include a third connecting part 45 or a fourth connecting part 46, while the two middle propeller protection assemblies 40 after stacking need to be provided with a third connecting part 45 and a fourth connecting part 46. In this way, the third connecting part 45 of the outermost propeller protection assembly 40 is used to connect to the fourth connecting part 46 of the second propeller protection assembly 40, the third connecting part 45 of the second propeller protection assembly 40 is used to connect to the fourth connecting part 46 of the third propeller protection assembly 40, and the third connecting part 45 of the third propeller protection assembly 40 is also used to connect to the fourth connecting part 46 of the last propeller protection assembly 40, so that the four propeller protection assemblies 40 are installed together. In this case, when stacking and storing the plurality of propeller protection assemblies 40, the stacking order needs to be considered. For example, the number of propeller protection components 40 includes two, one of which includes a third connecting part 45 and the other includes a fourth connecting part 46; after all the propeller protection components 40 of the aircraft 100 are removed from the aircraft body 10, the two propeller protection components 40 can be installed by the cooperation of the third connecting part 45 and the fourth connecting part 46.

[0130] Exemplarily, the number of third connecting portions 45 or fourth connecting portions 46 of the same propeller protection assembly 40 can be set according to actual needs, such as one, two, three, or more. Exemplarily, the number of third connecting portions 45 or fourth connecting portions 46 of the same propeller protection assembly 40 includes multiple portions, which facilitates more reliable installation of the propeller protection assembly 40 together with other propeller protection assemblies 40. Exemplarily, the number of third connecting portions 45 of the same propeller protection assembly 40 includes multiple portions, and the multiple third connecting portions 45 are arranged circumferentially spaced along the propeller protection assembly 40. Exemplarily, the number of fourth connecting portions 46 of the same propeller protection assembly 40 includes multiple portions, and the multiple fourth connecting portions 46 are arranged circumferentially spaced along the propeller protection assembly 40.

[0131] Please see Figure 13 and Figure 15In some embodiments, after all propeller protection components 40 of the aircraft 100 have been removed from the aircraft body 10 of the aircraft 100, the third connecting portion 45 is used to connect with the fourth connecting portion 46 of other propeller protection components 40, so that the propeller protection components 40 are stacked together with other propeller protection components 40. In this way, after all propeller protection components 40 with propellers 20 have been removed from the aircraft 100, multiple propeller protection components 40 can be stacked and stored, so that multiple propeller protection components 40 can be stored without the aircraft body 10, thereby reducing the storage volume of multiple propeller protection components 40 and realizing the portable and quick storage of propeller protection components 40; it can also reduce the probability of easy loss after all propeller protection components 40 of the aircraft 100 are removed from the aircraft body 10.

[0132] In some embodiments, after all propeller protection assemblies 40 of the aircraft 100 have been removed from the aircraft body 10 of the aircraft 100, the third connecting portion 45 is used to connect with the fourth connecting portions 46 of other propeller protection assemblies 40, so that each propeller protection assembly 40 is stacked together along the rotation axis of the first propeller 21, the central axis of the first propeller 21, or the central axis of the propeller protection assembly 40. Thus, after all propeller protection assemblies 40 of the aircraft 100 are removed from the aircraft body 10, the propeller protection assemblies 40 are stacked and stored together, resulting in a more compact structure and minimizing the storage volume of all propeller protection assemblies 40 of the aircraft 100, facilitating portable and rapid storage of each propeller protection assembly 40 without the aircraft body 10.

[0133] Please see Figure 1 In some embodiments, the number of propeller protection assemblies 40 of the aircraft 100 includes multiple assemblies. When each propeller protection assembly 40 is connected to the aircraft body 10 of the aircraft 100, adjacent propeller protection assemblies 40 are spaced apart. Thus, when each propeller protection assembly 40 is connected to the aircraft body 10 of the aircraft 100, the propeller protection assembly 40 does not need to extend into the space between adjacent propeller protection assemblies 40. Given a fixed space, this helps to reduce the size and weight of a single propeller protection assembly 40, thereby reducing the weight of the aircraft 100, and also reducing the probability that the propeller protection assemblies 40 of the aircraft 100 will obstruct the sensors (e.g., the vision sensor 13) of the aircraft 100. In other embodiments, when each propeller protection assembly 40 is connected to the aircraft body 10 of the aircraft 100, adjacent propeller protection assemblies 40 may not be spaced apart; for example, two adjacent propeller protection assemblies 40 may be in contact with each other.

[0134] Please see Figure 1In some embodiments, the number of propeller protection assemblies 40 of the aircraft 100 includes multiple components. When each propeller protection assembly 40 is connected to the aircraft body 10 of the aircraft 100, none of the propeller protection assemblies 40 are in contact with each other. This reduces the probability of mutual interference when the propeller protection assemblies 40 are installed on the aircraft body 10. Furthermore, since each propeller protection assembly 40 is connected to the aircraft body 10 of the aircraft 100 and none of the propeller protection assemblies 40 are in contact with each other, the propeller protection assemblies 40 do not need to extend into the space between them. Given a fixed space, this helps to reduce the size and weight of each individual propeller protection assembly 40, thereby reducing the weight of the aircraft 100 and reducing the probability that the propeller protection assemblies 40 of the aircraft 100 will obstruct the sensors of the aircraft 100.

[0135] In some embodiments, the number of propeller protection assemblies 40 of the aircraft 100 includes multiple components. When each propeller protection assembly 40 is connected to the aircraft body 10 of the aircraft 100, the third connecting portion 45 of the propeller protection assembly 40 and the fourth connecting portion 46 of the adjacent propeller protection assembly 40 are spaced apart. In this way, when adjacent propeller protection assemblies 40 are installed to the aircraft body 10, the third connecting portion 45 and the fourth connecting portion 46 are less likely to interfere with the installation of the propeller protection assembly 40, thus ensuring that each propeller protection assembly 40 can be smoothly installed to the aircraft body 10. Furthermore, when each propeller protection component 40 is connected to the main body 10 of the aircraft 100, the propeller protection component 40 does not need to extend to the space between the third connecting part 45 of the propeller protection component 40 and the fourth connecting part 46 of the adjacent propeller protection component 40. Given a fixed space, this is beneficial to reduce the size and weight of a single propeller protection component 40, thereby reducing the weight of the aircraft 100 and reducing the probability that each propeller protection component 40 of the aircraft 100 will obstruct the sensors of the aircraft 100.

[0136] In some embodiments, the number of propeller protection assemblies 40 of the aircraft 100 includes multiple components. When each propeller protection assembly 40 is connected to the aircraft body 10 of the aircraft 100, the third connecting portion 45 of the propeller protection assembly 40 does not contact the fourth connecting portion 46 of other propeller protection assemblies 40. In this way, the probability that the third connecting portion 45 and the fourth connecting portion 46 may easily interfere with the installation of the propeller protection assembly 40 when it is installed to the aircraft body 10 can be reduced. Furthermore, when each propeller protection component 40 is connected to the main body 10 of the aircraft 100, under certain spatial conditions, the third connecting portion 45 of the propeller protection component 40 does not contact the fourth connecting portion 46 of other propeller protection components 40. The propeller protection component 40 does not need to extend into the space between the third connecting portion 45 of the propeller protection component 40 and the fourth connecting portion 46 of other propeller protection components 40. Under certain spatial conditions, this is beneficial to reduce the size and weight of a single propeller protection component 40, thereby reducing the weight of the aircraft 100, and reducing the probability that each propeller protection component 40 of the aircraft 100 will obstruct the sensors of the aircraft 100.

[0137] In some embodiments, the detachable connection between the third connecting part 45 and the fourth connecting part 46 includes at least one of the following: snap-fit, magnetic engagement, screw locking connection, etc. Thus, the disassembly and installation between the third connecting part 45 and the fourth connecting part 46 are convenient and quick, thereby making the disassembly and installation of adjacent propeller protection assemblies 40 convenient and quick.

[0138] In some embodiments, the detachable connection between the third connecting part 45 and the fourth connecting part 46 includes a snap-fit ​​connection, where one of the third connecting part 45 and the fourth connecting part 46 includes a snap-fit ​​protrusion or hook, and the other includes a snap-fit ​​groove. Thus, the third connecting part 45 and the fourth connecting part 46 can be reliably connected, and the connection or disconnection can be quickly achieved without additional fasteners or tools. The assembly and disassembly of each propeller protection component 40 can be completed quickly, making the operation simple and cost-effective.

[0139] In some embodiments, the detachable connection between the third connecting part 45 and the fourth connecting part 46 includes a magnetic attraction method, where both the third connecting part 45 and the fourth connecting part 46 are magnets; or, one of the third connecting part 45 and the fourth connecting part 46 is a magnet, and the other is a magnetic attraction component. The magnetic attraction method enables the rapid installation and storage of multiple propeller protection assemblies 40, facilitating quick assembly and storage of the propeller protection assemblies 40; when it is necessary to install the propeller protection assemblies 40 onto the aircraft body 10, the multiple propeller protection assemblies 40 installed together can be quickly disassembled and separated.

[0140] The structures of the third connecting part 45 and the fourth connecting part 46 may be the same or different, and no restriction is imposed here.

[0141] In other embodiments, the third connecting part 45 and the fourth connecting part 46 may also be omitted. After all the propeller protection components 40 of the aircraft 100 are removed from the aircraft body 10 of the aircraft 100, multiple propeller protection components 40 can be installed or stacked together by means of adhesive bonding or other methods.

[0142] The positions of the third connecting portion 45 and the fourth connecting portion 46 on the protective cover 41 can be designed based on actual needs. For example, the third connecting portion 45 and the fourth connecting portion 46 can be located at the outer edge of the protective cover 41 to achieve portable installation and storage of multiple propeller protection components 40. In other embodiments, the third connecting portion 45 and the fourth connecting portion 46 can be located at other parts of the protective cover 41, and this embodiment of the present invention does not limit this.

[0143] This utility model embodiment also provides an aircraft 100, including:

[0144] The aircraft body 10 is configured to be detachably connected to the propeller protection assembly 40; and

[0145] The propeller protection assembly 40 includes a protective cover 41 and a first propeller 21. The protective cover 41 is used to provide protection for the first propeller 21. After the propeller protection assembly 40 is installed on the aircraft body 10, the first propeller 21 is used to drive the propeller to the propeller protection assembly 30, thereby providing flight power to the aircraft 100. The propeller protection assembly 40 does not include the propeller protection assembly 30.

[0146] In the above embodiment, the propeller protection assembly 40 of the aircraft 100 can be quickly and easily connected to the aircraft 100. This reduces the probability of the first propeller 21 colliding directly with an obstacle and being damaged, and also reduces the safety risk of the first propeller 21 causing cuts to the external environment (such as people or other objects) when rotating, thus improving the safety of the aircraft 100. When the propeller protection assembly 40 is not needed, it can be detached from the aircraft body 10. Furthermore, since the propeller protection assembly 40 has a first propeller 21 but no power assembly 30, after the propeller protection assembly 40 is installed on the aircraft 100, the first propeller 21 can be connected to the power assembly 30 of the aircraft 100 to provide flight power for the aircraft 100. This optimizes, expands, and enriches the form design of the propeller protection assembly 40, meeting the needs of more usage scenarios. Moreover, since the propeller protection assembly 40 does not have a power assembly 30, it is possible to replace the propeller protection assembly 40 without simultaneously replacing the power assembly 30, reducing maintenance and after-sales costs. Additionally, the absence of a power assembly 30 in the propeller protection assembly 40 reduces its individual weight and size.

[0147] Exemplary, the aircraft 100 includes the aircraft 100 of any of the above embodiments. The aircraft body 10 includes the aircraft body 10 of any of the above embodiments. The power assembly 30 includes the power assembly 30 of any of the above embodiments. The propeller protection assembly 40 includes the propeller protection assembly 40 of any of the above embodiments. The protective cover 41 includes the protective cover 41 of any of the above embodiments. The first propeller 21 includes the first propeller 21 of any of the above embodiments.

[0148] This utility model embodiment also provides an aircraft kit, including:

[0149] Aircraft 100; and

[0150] The propeller protection assembly 40 in any of the above embodiments is detachably connected to the aircraft body 10 of the aircraft 100.

[0151] Exemplary, the aircraft 100 includes the aircraft 100 of any of the above embodiments. The aircraft body 10 includes the aircraft body 10 of any of the above embodiments. The propeller protection assembly 40 includes the propeller protection assembly 40 of any of the above embodiments.

[0152] This utility model embodiment also provides an aircraft kit, including:

[0153] Aircraft 100, which includes a power unit 30;

[0154] The propeller protection assembly 40 of any of the above embodiments is detachably connected to the aircraft body 10 of the aircraft 100; and

[0155] The second propeller 22 is configured to be detachably connected to the aircraft body 10 of the aircraft 100. The first propeller 21 and the second propeller 22 can be selectively connected to the same power unit 30 of the aircraft 100 to provide flight power to the aircraft 100.

[0156] In the aircraft kit of the above embodiment, the same power unit 30 of the aircraft 100 can be adapted to different propellers 20. Thus, when the propeller protection component 40 is installed, the same power unit 30 of the aircraft 100 can be adapted to the first propeller 21; when the propeller protection component 40 is not installed, the same power unit 30 of the aircraft 100 can be adapted to the second propeller 22, expanding the application scenarios of the aircraft 100. It is understood that in this embodiment, the installation of the propeller protection component 40 can be selected according to the actual usage scenario. For example, in scenarios such as using the aircraft 100 for racing or controlling the aircraft 100 via a remote control device, the propeller protection component 40 can be removed, and the second propeller 22 can be connected to the power unit 30. In this way, the aircraft 100 is lighter and smaller, can achieve higher flight speeds, increases flight flexibility, and extends flight time. For example, when using the aircraft 100 outdoors, such as in a populated park, the propeller protection component 40 can be installed on the aircraft body 10 to prevent the propeller 20 from accidentally injuring people or objects and causing damage to the propeller 20, thus providing a safe operating environment for the user. Furthermore, when the aircraft 100 needs to take off and / or land by hand, the propeller protection component 40 can be installed on the aircraft body 10 to prevent the propeller 20 from accidentally injuring the user and causing damage to the propeller 20, thus providing a safe operating environment for the user.

[0157] In some embodiments, when the aircraft 100 is in a first mode, the power unit 30 is disconnected from the second propeller 22, the aircraft body 10 of the aircraft 100 is connected to the propeller protection assembly 40, and the power unit 30 is drivenly connected to the first propeller 21, thereby providing flight power to the aircraft 100. When the aircraft 100 is in a second mode, the aircraft body 10 is disconnected from the propeller protection assembly 40, the power unit 30 is disconnected from the first propeller 21, and the power unit 30 is drivenly connected to the second propeller 22, thereby providing flight power to the aircraft 100. Thus, when the propeller protection assembly 40 is installed, the same power unit 30 of the aircraft 100 can be adapted to the first propeller 21; when the propeller protection assembly 40 is not installed, the same power unit 30 of the aircraft 100 can be adapted to the second propeller 22, expanding the application scenarios of the aircraft 100.

[0158] Exemplary, the aircraft 100 includes the aircraft 100 of any of the above embodiments. The aircraft body 10 includes the aircraft body 10 of any of the above embodiments. The power assembly 30 includes the power assembly 30 of any of the above embodiments. The propeller protection assembly 40 includes the propeller protection assembly 40 of any of the above embodiments. The protective cover 41 includes the protective cover 41 of any of the above embodiments. The first propeller 21 includes the first propeller 21 of any of the above embodiments. The second propeller 22 includes the second propeller 22 of any of the above embodiments.

[0159] In related technologies, the propeller protection component 40 is detachably connected to the aircraft body 10. It is usually quick-released by prying the buckle by hand, which is relatively laborious and not conducive to easy and portable disassembly of the propeller protection component 40.

[0160] Please see Figure 5 This utility model embodiment provides a propeller protection assembly 40, including:

[0161] Protective shield 41; and

[0162] Pressing member 53 is movably connected to the protective cover 41 or the aircraft body 10 of the aircraft 100. Pressing member 53 is provided with a first connecting part 51, which is configured to be detachably connected to a second connecting part 52 of the aircraft body 100 of the aircraft 100.

[0163] Each propeller protection component 40 is provided with multiple pressing parts 53. By pressing the multiple pressing parts 53 together, the first connecting part 51 and the second connecting part 52 are disconnected, thereby disassembling and separating the propeller protection component 40 from the aircraft body 10 of the aircraft 100. At least two of the multiple pressing parts 53 are pressed in opposite directions.

[0164] In the above embodiment, the propeller protection assembly 40 is provided with multiple pressing members 53. By pressing the multiple pressing members 53 together, the first connecting part 51 and the second connecting part 52 are disconnected, thereby allowing the propeller protection assembly 40 to be disassembled from the aircraft body 10 of the aircraft 100. Since at least two of the multiple pressing members 53 are pressed in opposite directions, the propeller protection assembly 40 can be assembled or disassembled more easily, effortlessly, and conveniently, which is beneficial to improving the user experience.

[0165] By way of example, without conflict, aircraft 100 includes aircraft 100 of any of the above embodiments. Without conflict, aircraft body 10 includes aircraft body 10 of any of the above embodiments. Without conflict, propeller protection assembly 40 includes propeller protection assembly 40 of any of the above embodiments. Without conflict, protective cover 41 includes protective cover 41 of any of the above embodiments. Without conflict, pressing member 53 includes pressing member 53 of any of the above embodiments.

[0166] In some embodiments, the propeller protection assembly 40 is connected to the aircraft body 10 of the aircraft 100 by pressing a plurality of pressing members 53 to connect the first connecting part 51 and the second connecting part 52.

[0167] In some embodiments, the first connection portion 51 is configured to be detachably connected to the second connection portion 52 of the arm 12 or fuselage 11 of the aircraft 100.

[0168] In some embodiments, the propeller protection assembly 40 does not have a propeller 20, and the aircraft body 10 of the aircraft 100 has a first propeller 21. After the propeller protection assembly 40 is installed on the aircraft body 10 of the aircraft 100, the first propeller 21 is at least partially disposed in the receiving space 4110 of the propeller protection assembly 40.

[0169] In some embodiments, the propeller protection assembly 40 is provided with a first propeller 21 and a power assembly 30. After the propeller protection assembly 40 is installed on the aircraft body 10 of the aircraft 100, the first propeller 21 is used to provide flight power for the aircraft 100.

[0170] In some embodiments, the propeller protection assembly 40 is provided with a first propeller 21, and the propeller protection assembly 40 is not provided with a power assembly 30 that is driven to the first propeller 21. After the propeller protection assembly 40 is installed on the aircraft body 10 of the aircraft 100, the first propeller 21 is used to drive to the power assembly 30 of the aircraft 100, and the power assembly 30 is provided on the aircraft 100.

[0171] It should be noted that, unless otherwise specified, any parts not mentioned in the embodiments of this utility model may be referred to the foregoing. Figures 1-15 The relevant descriptions of the embodiments shown will not be repeated here.

[0172] This utility model embodiment also provides an aircraft 100, including:

[0173] The aircraft body 10 is provided with a second connecting part 52, which is configured to be detachably connected to the first connecting part 51 of the propeller protection assembly 40, so as to realize the detachable connection between the propeller protection assembly 40 and the aircraft body 10; wherein, the propeller protection assembly 40 includes a protective cover 41 and a pressing member 53, the pressing member 53 is movably connected to the protective cover 41, and the first connecting part 51 is provided on the pressing member 53;

[0174] Each propeller protection assembly 40 is provided with multiple pressing parts 53. By pressing the multiple pressing parts 53 together, the first connecting part 51 and the second connecting part 52 are disconnected, thereby allowing the propeller protection assembly 40 to be disassembled and separated from the aircraft body 10. At least two of the multiple pressing parts 53 are pressed in opposite directions.

[0175] In the above embodiment of the aircraft 100, since each propeller protection component 40 is provided with multiple pressing parts 53, the first connecting part 51 and the second connecting part 52 are disconnected by pressing the multiple pressing parts 53 together, thereby disassembling and separating the propeller protection component 40 from the aircraft body 10 of the aircraft 100. Since at least two of the multiple pressing parts 53 are pressed in opposite directions, the propeller protection component 40 can be assembled or disassembled more easily, effortlessly, and conveniently, which is beneficial to improving the user experience.

[0176] By way of example, without conflict, aircraft 100 includes aircraft 100 of any of the above embodiments. Without conflict, aircraft body 10 includes aircraft body 10 of any of the above embodiments. Without conflict, propeller protection assembly 40 includes propeller protection assembly 40 of any of the above embodiments. Without conflict, first connection portion 51 includes first connection portion 51 of any of the above embodiments. Without conflict, second connection portion 52 includes second connection portion 52 of any of the above embodiments. Without conflict, pressing member 53 includes pressing member 53 of any of the above embodiments.

[0177] This utility model embodiment also provides an aircraft kit, including:

[0178] Aircraft 100; and

[0179] The propeller protection assembly 40 in any of the above suitable embodiments is detachably connected to the aircraft body 10 of the aircraft 100.

[0180] By way of example, without conflict, aircraft 100 includes aircraft 100 of any of the above embodiments. Without conflict, aircraft body 10 includes aircraft body 10 of any of the above embodiments. Without conflict, propeller protection assembly 40 includes propeller protection assembly 40 of any of the above embodiments.

[0181] This utility model embodiment also provides an aircraft kit, including:

[0182] Aircraft 100, including power unit 30;

[0183] The propeller protection assembly 40 of any of the above suitable embodiments is detachably connected to the aircraft body 10 of the aircraft 100; and

[0184] The second propeller 22 is configured to be detachably connected to the aircraft body 10 of the aircraft 100. The first propeller 21 and the second propeller 22 can be selectively connected to the same power unit 30 of the aircraft 100 to provide flight power to the aircraft 100.

[0185] By way of example, without conflict, aircraft 100 includes aircraft 100 of any of the above embodiments. Without conflict, aircraft body 10 includes aircraft body 10 of any of the above embodiments. Without conflict, power assembly 30 includes power assembly 30 of any of the above embodiments. Without conflict, propeller protection assembly 40 includes propeller protection assembly 40 of any of the above embodiments. Without conflict, first propeller 21 includes first propeller 21 of any of the above embodiments. Without conflict, second propeller 22 includes second propeller 22 of any of the above embodiments.

[0186] In related technologies, propeller protection components 40 with propellers 20 can only be folded and stored when connected to the main body 10 of the aircraft, making it impossible to store them in a smaller volume.

[0187] Please see Figure 14 and Figure 15This utility model embodiment provides a propeller protection assembly 40, including a first propeller 21 and a third connecting part 45. The propeller protection assembly 40 can be detachably connected to the aircraft body 10 of the aircraft 100. After all the propeller protection assemblies 40 of the aircraft 100 are removed from the aircraft body 10 of the aircraft 100, the third connecting part 45 is used to connect with the fourth connecting part 46 of other propeller protection assemblies 40, so that the propeller protection assemblies 40 are stacked together with other propeller protection assemblies 40.

[0188] In the above embodiment, after all propeller protection components 40 are removed from the aircraft 100, multiple propeller protection components 40 can be stacked and stored. This allows for storage of multiple propeller protection components 40 without the aircraft body 10, thereby reducing the storage volume of the multiple propeller protection components 40 and achieving portable and rapid storage. It also reduces the probability of losing all propeller protection components 40 after removal from the aircraft body 100, and further reduces the storage volume of the aircraft body 10. The third connecting part 45 and the fourth connecting part 46 enable quick and convenient stacking of multiple propeller protection components 40.

[0189] For example, after all the propeller protection components 40 are stacked together, if it is necessary to install the propeller protection components 40 onto the aircraft body 10, the stacked propeller protection components 40 can be quickly disassembled and separated.

[0190] By way of example, without conflict, aircraft 100 includes aircraft 100 of any of the above embodiments. Without conflict, aircraft body 10 includes aircraft body 10 of any of the above embodiments. Without conflict, propeller protection assembly 40 includes propeller protection assembly 40 of any of the above embodiments. Without conflict, first propeller 21 includes first propeller 21 of any of the above embodiments. Without conflict, third connection portion 45 includes third connection portion 45 of any of the above embodiments. Without conflict, fourth connection portion 46 includes fourth connection portion 46 of any of the above embodiments.

[0191] In some embodiments, after all propeller protection components 40 of the aircraft 100 have been removed from the aircraft body 10 of the aircraft 100, the third connection portion 45 is used to connect with the fourth connection portion 46 of other propeller protection components 40, so that each propeller protection component 40 is stacked along the rotation axis of the first propeller 21, the central axis of the first propeller 21, or the central axis of the propeller protection component 40.

[0192] In some implementations, the number of propeller protection components 40 of the aircraft 100 includes multiple components, and when each propeller protection component 40 is connected to the aircraft body 10 of the aircraft 100, adjacent propeller protection components 40 are spaced apart.

[0193] In some embodiments, the number of propeller protection components 40 of the aircraft 100 includes multiple components, and when each propeller protection component 40 is connected to the aircraft body 10 of the aircraft 100, each propeller protection component 40 does not contact each other.

[0194] In some embodiments, the number of propeller protection components 40 of the aircraft 100 includes multiple components. When each propeller protection component 40 is connected to the aircraft body 10 of the aircraft 100, the third connecting portion 45 of the propeller protection component 40 is spaced apart from the fourth connecting portion 46 of the adjacent propeller protection component 40.

[0195] In some embodiments, the number of propeller protection components 40 of the aircraft 100 includes multiple components. When each propeller protection component 40 is connected to the aircraft body 10 of the aircraft 100, the third connection portion 45 of the propeller protection component 40 does not contact the fourth connection portion 46 of other propeller protection components 40.

[0196] In some embodiments, the detachable connection between the third connecting part 45 and the fourth connecting part 46 includes at least one of the following: snap-fit, magnetic engagement, and screw locking connection.

[0197] In some embodiments, the detachable connection between the third connecting portion 45 and the fourth connecting portion 46 includes a snap-fit ​​connection; one of the third connecting portion 45 and the fourth connecting portion 46 includes a snap-fit ​​protrusion or a snap-fit ​​hook, and the other includes a snap-fit ​​groove.

[0198] In some embodiments, the detachable connection between the third connecting part 45 and the fourth connecting part 46 includes a magnetic attraction engagement; both the third connecting part 45 and the fourth connecting part 46 are magnets; or, one of the third connecting part 45 and the fourth connecting part 46 is a magnet and the other is a magnetic attraction engagement component.

[0199] In some embodiments, after all propeller protection components 40 of the aircraft 100 have been removed from the aircraft body 10 of the aircraft 100, the aircraft 100 is used to connect a second propeller 22, which is used to provide flight power to the aircraft 100.

[0200] In some embodiments, the propeller protection assembly 40 does not have a power assembly 30, and the power assembly 30 is located on the aircraft 100. After the propeller protection assembly 40 is installed on the aircraft 100, the first propeller 21 can be driven to the power assembly 30 to provide flight power for the aircraft 100. After the propeller protection assembly 40 is removed from the aircraft 100, the second propeller 22 of the aircraft 100 can be driven to the power assembly 30 to provide flight power for the aircraft 100.

[0201] It should be noted that, unless otherwise specified, any parts not mentioned in the embodiments of this utility model may be referred to the foregoing. Figures 1-15 The relevant descriptions of the embodiments shown will not be repeated here.

[0202] This utility model embodiment also provides an aircraft 100, including:

[0203] The main body of the aircraft 10 is configured to be detachably connected to the propeller protection assembly 40;

[0204] The propeller protection assembly 40 includes a first propeller 21 and a third connecting part 45. After all the propeller protection assemblies 40 of the aircraft 100 are removed from the aircraft body 10, the third connecting part 45 is used to connect with the fourth connecting part 46 of the other propeller protection assemblies 40 of the aircraft 100, so that the propeller protection assembly 40 is stacked with the other propeller protection assemblies 40.

[0205] In the above embodiment of the aircraft 100, after all propeller protection components 40 are removed from the aircraft 100, multiple propeller protection components 40 can be stacked and stored. This allows for the storage of multiple propeller protection components 40 without the main body 10 of the aircraft, thereby reducing the storage volume of the multiple propeller protection components 40 and achieving portable and rapid storage of the propeller protection components 40. It also reduces the probability of losing all propeller protection components 40 after they are removed from the main body 10 of the aircraft 100, and further reduces the storage volume of the main body 10 of the aircraft. The third connecting part 45 and the fourth connecting part 46 enable quick and convenient stacking of multiple propeller protection components 40.

[0206] For example, after all the propeller protection components 40 are stacked together, if it is necessary to install the propeller protection components 40 onto the aircraft body 10, the stacked propeller protection components 40 can be quickly disassembled and separated.

[0207] By way of example, without conflict, aircraft 100 includes aircraft 100 of any of the above embodiments. Without conflict, aircraft body 10 includes aircraft body 10 of any of the above embodiments. Without conflict, propeller protection assembly 40 includes propeller protection assembly 40 of any of the above embodiments. Without conflict, first propeller 21 includes first propeller 21 of any of the above embodiments. Without conflict, third connection portion 45 includes third connection portion 45 of any of the above embodiments. Without conflict, fourth connection portion 46 includes fourth connection portion 46 of any of the above embodiments.

[0208] This utility model embodiment also provides an aircraft kit, including:

[0209] Aircraft 100; and

[0210] The propeller protection assembly 40 of any of the above suitable embodiments is detachably connected to the aircraft body 10 of the aircraft 100.

[0211] By way of example, without conflict, aircraft 100 includes aircraft 100 of any of the above embodiments. Without conflict, aircraft body 10 includes aircraft body 10 of any of the above embodiments. Without conflict, propeller protection assembly 40 includes propeller protection assembly 40 of any of the above embodiments.

[0212] In related technologies, propeller protection components 40 are usually stored using a snap-fit ​​method, which cannot achieve quick storage.

[0213] This utility model embodiment provides a propeller protection component 40, including a first magnetic part. The propeller protection component 40 can be detachably connected to the aircraft body 10 of the aircraft 100. The first magnetic part is used to connect with the second magnetic part of other propeller protection components 40 that have been removed from the aircraft body 100 after the propeller protection component 40 is removed from the aircraft body 10, so that the propeller protection component 40 can be installed together with other propeller protection components 40.

[0214] The propeller protection components 40 in the above embodiment can be stored without the main body 10 of the aircraft after all propeller protection components 40 have been removed from the aircraft 100. This reduces the storage volume of the propeller protection components 40, enabling portable and quick storage. It also reduces the probability of losing all propeller protection components 40 after removal from the main body 10. Furthermore, it reduces the storage volume of the main body 10. The magnetic structure allows for quicker and more convenient installation of multiple propeller protection components 40.

[0215] By way of example, without conflict, aircraft 100 includes aircraft 100 of any of the above embodiments. Without conflict, aircraft body 10 includes aircraft body 10 of any of the above embodiments. Without conflict, propeller protection assembly 40 includes propeller protection assembly 40 of any of the above embodiments. Without conflict, third connection portion 45 of any of the above embodiments includes first magnetic attraction portion. Without conflict, fourth connection portion 46 of any of the above embodiments includes second magnetic attraction portion.

[0216] In some embodiments, after the propeller protection assembly 40 is removed from the aircraft 100, it is connected to the second magnetic part of other propeller protection assemblies 40 removed from the aircraft 100, so that the propeller protection assembly 40 is stacked together with other propeller protection assemblies 40.

[0217] In some embodiments, after all propeller protection components 40 of the aircraft 100 have been removed from the aircraft body 10 of the aircraft 100, the first magnetic part is used to connect with the second magnetic part of other propeller protection components 40, so that each propeller protection component 40 is stacked along the central axis of the propeller protection components 40.

[0218] In some embodiments, the number of propeller protection components 40 of the aircraft 100 includes multiple components, and when each propeller protection component 40 is connected to the aircraft body 10 of the aircraft 100, adjacent propeller protection components 40 are spaced apart.

[0219] The number of propeller protection components 40 of the aircraft 100 includes multiple components. When each propeller protection component 40 is connected to the aircraft body 10 of the aircraft 100, each propeller protection component 40 does not contact each other.

[0220] In some embodiments, the number of propeller protection components 40 of the aircraft 100 includes multiple components. When each propeller protection component 40 is connected to the aircraft body 10 of the aircraft 100, the third connecting portion 45 of the propeller protection component 40 is spaced apart from the fourth connecting portion 46 of the adjacent propeller protection component 40.

[0221] The number of propeller protection components 40 of the aircraft 100 includes multiple components. When each propeller protection component 40 is connected to the aircraft body 10 of the aircraft 100, the third connection part 45 of the propeller protection component 40 does not contact the fourth connection part 46 of other propeller protection components 40.

[0222] In some embodiments, both the first magnetic attraction part and the second magnetic attraction part are magnets; or, one of the first magnetic attraction part and the second magnetic attraction part is a magnet, and the other is a magnetic attraction fitting part.

[0223] In some embodiments, the propeller protection assembly 40 includes a first propeller 21.

[0224] In some embodiments, after all propeller protection components 40 of the aircraft 100 have been removed from the aircraft body 10 of the aircraft 100, the aircraft 100 is used to connect a second propeller 22, which is used to provide flight power to the aircraft 100.

[0225] In some embodiments, the propeller protection assembly 40 does not have a power assembly 30, and the power assembly 30 is located on the aircraft 100. After the propeller protection assembly 40 is installed on the aircraft 100, the first propeller 21 can be driven to the power assembly 30 to provide flight power for the aircraft 100. After the propeller protection assembly 40 is removed from the aircraft 100, the second propeller 22 of the aircraft 100 can be driven to the power assembly 30 to provide flight power for the aircraft 100.

[0226] In some embodiments, the propeller protection assembly 40 does not include the propeller 20.

[0227] It should be noted that, unless otherwise specified, any parts not mentioned in the embodiments of this utility model may be referred to the foregoing. Figures 1-15 The relevant descriptions of the embodiments shown will not be repeated here.

[0228] This utility model embodiment also provides an aircraft 100, including:

[0229] The main body of the aircraft 10 is configured to be detachably connected to the propeller protection assembly 40;

[0230] The propeller protection assembly 40 includes a first magnetic part, which is used to connect with the second magnetic part of other propeller protection assemblies 40 that have been removed from the aircraft body 10 after the propeller protection assembly 40 has been removed from the aircraft body 10, so that the propeller protection assembly 40 can be installed together with other propeller protection assemblies 40.

[0231] In the above embodiment of the aircraft 100, after all propeller protection assemblies 40 are removed from the aircraft 100, multiple propeller protection assemblies 40 can be stored without the aircraft body 10, thereby reducing the storage volume of the multiple propeller protection assemblies 40 and achieving portable and quick storage of the propeller protection assemblies 40; it also reduces the probability of all propeller protection assemblies 40 being easily lost after being removed from the aircraft body 10; in addition, it also reduces the storage volume of the aircraft body 10; and it also reduces the probability of all propeller protection assemblies 40 being easily lost after being removed from the aircraft body 10. The magnetic structure allows for faster and more convenient installation of multiple propeller protection assemblies 40.

[0232] By way of example, without conflict, aircraft 100 includes aircraft 100 of any of the above embodiments. Without conflict, aircraft body 10 includes aircraft body 10 of any of the above embodiments. Without conflict, propeller protection assembly 40 includes propeller protection assembly 40 of any of the above embodiments. Without conflict, third connection portion 45 of any of the above embodiments includes first magnetic attraction portion. Without conflict, fourth connection portion 46 of any of the above embodiments includes second magnetic attraction portion.

[0233] This utility model embodiment also provides an aircraft kit, including:

[0234] Aircraft 100; and

[0235] The propeller protection assembly 40 of any of the above suitable embodiments is detachably connected to the aircraft body 10 of the aircraft 100.

[0236] By way of example, without conflict, aircraft 100 includes aircraft 100 of any of the above embodiments. Without conflict, aircraft body 10 includes aircraft body 10 of any of the above embodiments. Without conflict, propeller protection assembly 40 includes propeller protection assembly 40 of any of the above embodiments.

[0237] For example, the propeller protection assembly 40 with the first propeller 21 can be quickly removed from or installed on the aircraft body 10 by means of quick removal, which is simple and convenient.

[0238] For example, the propeller protection assembly 40 is provided with a pressable pressing member 53, which has a hook. The structural member 60 (such as a motor mounting base) below the power assembly 30 on the arm 12 is provided with a corresponding slot. By pressing the pressing member 53, the hook and the slot can be engaged and disengaged to realize the installation and quick removal of the propeller protection assembly 40.

[0239] For example, the propeller protection assembly 40 has a built-in first propeller 21 but no power assembly 30.

[0240] For example, each propeller protection assembly 40 has a built-in first propeller 21. The aircraft 100 may be a quadcopter drone.

[0241] For example, a typical quick-release propeller, such as the second propeller 22, is directly connected to the through hole on the propeller cap of the second propeller 22 through the shaft of the motor's outer rotor of the power assembly. The lower propeller cap is equipped with a quick-release structure adapted to the propeller seat of the power assembly 30. Using this quick-release structure, the propeller cap is inserted into the propeller seat above the power assembly 30 and pressed down completely. The second propeller 22 is then rotated to the bottom in the locking direction. After releasing, the second propeller 22 springs up and locks. The second propeller 22 includes two blades, with two blades mounted on the propeller cap. The propeller cap has two pivot shafts, and the two blades are each mounted on one pivot shaft to rotate around the pivot shaft, achieving folding and unfolding. Previously, this type of quick-release propeller transmitted torque through mechanical transmission, transmitting the motor's torque to drive the blades to rotate. That is, the propeller cap is fixed to the propeller seat of the power assembly 30; the rotation of the power assembly 30 drives the propeller seat to rotate, thereby driving the propeller cap to rotate, and ultimately driving the blades of the second propeller 22 to rotate.

[0242] For example, the first propeller 21 is built into the propeller protection assembly 40. Since the propeller protection assembly 40 is fixedly installed on the mounting base below the power assembly 30 by means of clips and slots, it is difficult to transmit torque through conventional mechanical means when the power assembly 30 rotates. It is necessary to change the ordinary cylindrical shaft to a non-cylindrical shaft, such as a spline shaft, so as to transmit the torque of the power assembly 30 through the spline, so as to transmit the torque of the power assembly 30 to the first propeller 21, thereby driving the first propeller 21 to rotate.

[0243] For example, the power assembly 30 includes a power motor.

[0244] For example, the propeller protection assembly 40 is provided with a flow guide 42, which includes a flow guide groove. The flow guide groove is aligned with the heat dissipation groove on the aircraft body 10, and can guide the propeller airflow of the propeller 20 in the propeller protection assembly 40 to the heat dissipation groove of the aircraft body 10 for propeller air cooling of the aircraft 100 without a fan.

[0245] For example, the four quick-release propeller protection assemblies 40 with the first propeller 21 can be stacked together magnetically to achieve portable quick-release storage and save space.

[0246] For example, each propeller protection component 40 has a magnetic attraction part on its outer surface. Two propeller protection components 40 can be magnetically attracted to each other through the magnetic attraction part, so as to achieve stacking and storage around the central axis of the propeller protection component 40, the central axis of the first propeller 21, or the rotation axis of the first propeller 21.

[0247] For example, since the propeller protection assembly 40 has a built-in clip-type quick-release structure, two adjacent propeller protection assemblies 40 need to be staggered when stacked to avoid mutual interference. If there is space within two adjacent propeller protection assemblies 40, they do not need to be staggered.

[0248] Understandably, Figure 3 and Figure 10 The illustration is merely illustrative and does not represent the views of the author. Figure 3 and Figure 10 The structure, shape, location, and / or number of components shown impose limitations. In practical applications, Figure 3 and Figure 10 The structure, shape, location, and / or quantity of the components shown can be changed according to actual needs.

[0249] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," "mechanical coupling," and "coupling" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection. They can refer to a mechanical connection or an electrical connection. They can refer to a direct connection or an indirect connection through an intermediate medium, and can refer to the internal communication of two components or the interaction between two components. Mechanical coupling or coupling between two components includes direct coupling and indirect coupling, such as a direct fixed connection or a connection through a transmission mechanism. Mechanical coupling between two components can be understood as the existence of a mechanical connection and / or mechanical interaction between the two components. Mechanical connection includes, but is not limited to, at least one of the following: rotational connection, movable connection, sliding connection, and abutment. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.

[0250] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0251] The foregoing disclosure provides many different embodiments or examples for implementing various structures of this utility model. To simplify the disclosure, specific examples of components and arrangements are described above. These are merely examples and are not intended to limit the scope of the utility model. Furthermore, reference numerals and / or letters may be repeated in different examples; such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed. In addition, examples of various specific processes and materials are provided in this utility model; however, those skilled in the art will recognize the application of other processes and / or the use of other materials.

[0252] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., indicate that a specific method step, feature, structure, material, or characteristic described in connection with an embodiment or example is included in at least one embodiment or example of this utility model. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific method steps, features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0253] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model 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 utility model, and these modifications or substitutions should all be covered within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the scope of the claims.

Claims

1. A propeller protection assembly, characterized in that, include: Protective shield; as well as The first propeller, the protective cover is used to provide protection for the first propeller; The propeller protection assembly is configured to be detachably connected to the main body of the rotorcraft drone. After the propeller protection assembly is installed on the rotorcraft drone, the first propeller is used to drive the power assembly of the rotorcraft drone, thereby providing flight power for the rotorcraft drone. The propeller protection assembly does not have the power assembly installed on it; the power assembly is installed on the rotorcraft drone.

2. The propeller protection assembly according to claim 1, characterized in that, The power assembly is located on the arm or fuselage of the aircraft body; and / or, the power source of the power assembly includes at least one of the following: electricity, magnetism, gravity, wind power, water power, hydraulic drive, and fuel.

3. The propeller protection assembly according to claim 1, characterized in that, The propeller protection assembly is detachably connected to the main body of the rotary-wing UAV via a quick-release structure; the quick-release structure includes: First connecting part; The second connecting part is capable of cooperating with the first connecting part to allow the propeller protection assembly to be detachably connected to the main body of the rotary-wing UAV.

4. The propeller protection assembly according to claim 3, characterized in that, The first connecting portion and the second connecting portion include a non-magnetic connection structure; or, the first connecting portion and the second connecting portion include a magnetic connection structure.

5. The propeller protection assembly according to claim 4, characterized in that, The non-magnetic connection structure includes a mechanical locking structure; or... One of the first connecting portion and the second connecting portion includes a latching protrusion or a latching hook, and the other includes a latching groove; or, Both the first connecting part and the second connecting part are magnets; or, One of the first connecting part and the second connecting part is a magnet, and the other is a magnetic attraction component.

6. The propeller protection assembly according to claim 3, characterized in that, The first connecting part is located on the propeller protection assembly, and the second connecting part is located on the aircraft body of the rotary-wing UAV.

7. The propeller protection assembly according to claim 6, characterized in that, One of the first connecting portion and the second connecting portion can move toward the other, so that the first connecting portion can connect with the second connecting portion; or, One of the first connecting portion and the second connecting portion can move away from the other, so that the first connecting portion can be decoupled from the second connecting portion; or, The first connecting part and the second connecting part can rotate relative to each other, so that the first connecting part can be connected to or disconnected from the second connecting part.

8. The propeller protection assembly according to claim 3, characterized in that, The quick-release structure also includes: A pressing member is provided with the first connecting part or the second connecting part, and the pressing member is movably connected to the protective cover or the aircraft body; pressing the pressing member can connect and / or disconnect the first connecting part and the second connecting part.

9. The propeller protection assembly according to claim 8, characterized in that, One of connecting and disconnecting can be achieved by pressing the pressing member, and the other of connecting and disconnecting can be achieved by prying open the pressing member; or... One of the connection and the disconnection is achieved by applying force to a first force-applying portion of the pressing member, and the other of the connection and the disconnection is achieved by applying force to a second force-applying portion of the pressing member, wherein the first force-applying portion and the second force-applying portion are different; or... Each propeller protection assembly is provided with a plurality of pressing members. By pressing the plurality of pressing members, the first connecting part and the second connecting part are connected and / or disconnected, thereby connecting or disconnecting the propeller protection assembly from the main body of the rotary-wing UAV; or, Each propeller protection assembly is provided with a plurality of pressing elements, at least two of the pressing elements having different pressing directions; or, Each of the propeller protection assemblies is provided with a plurality of the pressing elements, at least two of the pressing elements having opposite pressing directions; or, Each propeller protection assembly is provided with a plurality of pressing members, which are pressed together to connect and / or disconnect the first connecting part and the second connecting part, thereby connecting or disconnecting the propeller protection assembly from the aircraft body of the rotary-wing UAV.

10. The propeller protection assembly according to claim 8, characterized in that, Each of the propeller protection assemblies is provided with multiple pressing elements, the multiple pressing elements including two pressing elements; and / or, The pressing component includes a clip-type pressing component.

11. The propeller protection assembly according to any one of claims 1-10, characterized in that, The propeller protection assembly is provided with a flow guide, which is correspondingly arranged with the heat dissipation part of the main body of the rotorcraft drone; when the propeller protection assembly is installed on the rotorcraft drone, the flow guide is used to deliver at least part of the air generated by the rotation of the first propeller of the rotorcraft drone to the heat dissipation part; no heat dissipation device is provided inside the main body of the rotorcraft drone.

12. The propeller protection assembly according to any one of claims 1-10, characterized in that, After all the propeller protection components of the rotary-wing UAV have been removed from the main body of the UAV, the propeller protection components can be stacked together.

13. The propeller protection assembly according to claim 12, characterized in that, When the propeller protection assemblies are stacked together, adjacent propeller protection assemblies are not misaligned, or the pressing parts of adjacent propeller protection assemblies are not misaligned; or... When the propeller protection assemblies are stacked together, adjacent propeller protection assemblies are stacked in the same direction, or the pressing members of adjacent propeller protection assemblies are stacked in the same direction; or... When the propeller protection components are stacked together, the adjacent two propeller protection components are staggered, or the pressing parts of the adjacent two propeller protection components are staggered.

14. The propeller protection assembly according to any one of claims 1-10, characterized in that, The propeller protection assembly also includes a third connecting part, which is used to connect with the fourth connecting part of other propeller protection assemblies after all propeller protection assemblies of the rotary-wing UAV have been removed from the main body of the rotary-wing UAV, so that the propeller protection assembly can be stacked together with other propeller protection assemblies.

15. The propeller protection assembly according to claim 14, characterized in that, After all the propeller protection components of the rotorcraft UAV have been removed from the main body of the rotorcraft UAV, the third connection is used to connect with the fourth connection of other propeller protection components, so that each propeller protection component is stacked together along the rotation axis of the first propeller, the central axis of the first propeller, or the central axis of the propeller protection component.

16. The propeller protection assembly according to claim 14, characterized in that, The rotorcraft drone has multiple propeller protection components. When each propeller protection component is connected to the main body of the rotorcraft drone, the third connecting portion of the propeller protection component is not in contact with the fourth connecting portion of the other propeller protection components; and / or, The detachable connection method between the third connecting part and the fourth connecting part includes at least one of the following: snap-fit, magnetic attraction, and screw locking connection.

17. A rotary-wing unmanned aerial vehicle, characterized in that, include: The main body of the aircraft is configured to be detachably connected to the propeller protection assembly; as well as A power assembly; wherein the propeller protection assembly includes a protective cover and a first propeller, the protective cover being used to provide protection for the first propeller, and after the propeller protection assembly is installed on the aircraft body, the first propeller being used to drive the power assembly, thereby providing flight power for the rotary-wing UAV; wherein the propeller protection assembly does not include the power assembly.

18. A rotary-wing unmanned aerial vehicle kit, characterized in that, include: Rotary-wing drones; as well as The propeller protection assembly according to any one of 1-16, wherein the propeller protection assembly is detachably connected to the aircraft body of the rotary-wing UAV.

19. A rotary-wing unmanned aerial vehicle kit, characterized in that, include: A rotary-wing unmanned aerial vehicle, the rotary-wing unmanned aerial vehicle including a power unit; The propeller protection assembly according to any one of 1-16, wherein the propeller protection assembly is detachably connected to the aircraft body of the rotary-wing UAV; as well as The second propeller is configured to be detachably connected to the main body of the aircraft. The first and second propellers can be selectively connected to the same power unit of the rotorcraft to provide flight power to the rotorcraft.

20. The rotary-wing unmanned aerial vehicle kit according to claim 19, characterized in that, In the first mode of the rotary-wing drone, the power unit is disconnected from the second propeller, the main body of the rotary-wing drone is connected to the propeller protection assembly, and the power unit is driven by the first propeller, thereby providing flight power for the rotary-wing drone; in the second mode of the rotary-wing drone, the main body of the rotary-wing drone is disconnected from the propeller protection assembly, the power unit is disconnected from the first propeller, and the power unit is driven by the second propeller, thereby providing flight power for the rotary-wing drone.

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