Rotor Mounting Kit

Abstract

A rotor mounting assembly (10) comprises a rotor seat (11) and an elastic member (12). The rotor seat (11) comprises a base (111) and a locking structure (112), wherein the locking structure is arranged at the base (111). The locking structure (112) comprises a recess (1141) opening toward the base (111), wherein the recess is configured to receive a portion of a rotor blade assembly (320). The elastic member (12) is configured to provide elastic force to a portion of the rotor blade assembly (320) so as to constrain a portion of the rotor blade assembly (320) in the recess (1141).

Description

Technical Field

[0001] The present disclosure relates to technologies related to unmanned aerial vehicles (UAVs), and more particularly, to a rotor mounting assembly, a propulsion system having the rotor mounting assembly, and an unmanned aerial vehicle (UAV). Background Art

[0002] Unmanned aerial vehicles (UAVs) use a rotor-based propulsion system to provide lift to the UAV, allowing it to fly in the air and move forward and backward. The propulsion system typically includes a plurality of rotor blade assemblies, such as four, six, or eight rotor blade assemblies, each of which is mounted to the fuselage of the UAV or the arm of the UAV via a rotor mounting assembly.

[0003] In conventional technology, the rotor mounting assembly and the corresponding rotor blade assembly have matching parts that match each other to clamp and fix the rotor blade assembly to the rotor mounting assembly. The mating surfaces of such matching parts are easily worn, thereby reducing the reliability of the propulsion system. Summary of the invention

[0004] According to the present disclosure, a rotor mounting assembly is provided, comprising: a rotor seat and an elastic member. The rotor seat comprises a base and a locking structure, and the locking structure is arranged at the base. The locking structure comprises a recess opening toward the base, and the recess is configured to accommodate a portion of a rotor blade assembly. The elastic member is configured to provide elastic force to a portion of the rotor blade assembly to constrain the portion of the rotor blade assembly in the recess.

[0005] According to the present disclosure, a rotor mount is also provided, comprising: a base; a first locking structure, which is arranged at the base and includes a first recess opening toward the base; and a second locking structure, which is arranged at the base and includes a second recess opening toward the base.

[0006] According to the present disclosure, a propulsion device is also provided, including a rotor blade assembly and a rotor mounting assembly. The rotor mounting assembly includes a rotor seat and an elastic member. The rotor seat includes: a base; a first locking structure, the first locking structure is arranged at the base; and a second locking structure, the second locking structure is arranged at the base. The first locking structure includes a first recess, the first recess is open toward the base and is configured to accommodate a first part of a portion of the rotor blade assembly. The second locking structure includes a second recess, the second recess is open toward the base and is configured to accommodate a second part of a portion of the rotor blade assembly. The elastic member is configured to provide an elastic force to a portion of the rotor blade assembly to constrain a portion of the rotor blade assembly in the first recess and the second recess.

[0007] According to the present disclosure, a propulsion system is also provided, comprising a first propulsion device and a second propulsion device. The first propulsion device comprises a first rotor blade assembly and a first rotor mounting assembly. The first rotor blade assembly comprises a first portion. The first rotor mounting assembly comprises a first rotor seat and a first elastic member. The first rotor seat comprises: a first base; a first locking structure, the first locking structure being arranged at the first base; and a second locking structure, the second locking structure being arranged at the first base. The first locking structure comprises a first recess, the first recess being open toward the first base and being configured to accommodate a first portion of the first portion. The second locking structure comprises a second recess, the second recess being open toward the first base and being configured to accommodate a second portion of the first portion. The first elastic member is configured to provide an elastic force to the first portion to constrain the first portion in the first recess and the second recess. The second propulsion device comprises a second rotor blade assembly and a second rotor mounting assembly. The second rotor blade assembly comprises a second portion. The second rotor mounting assembly comprises a second rotor seat and a second elastic member. The second rotor mount includes: a second base; a third locking structure, the third locking structure is arranged at the second base; and a fourth locking structure, the fourth locking structure is arranged at the second base. The third locking structure includes a third recess, the third recess is open toward the second base and is configured to receive the first part of the second part. The fourth locking structure includes a fourth recess, the fourth recess is open toward the second base and is configured to receive the second part of the second part. The second elastic member is configured to provide an elastic force to the second part to constrain the second part in the third recess and the fourth recess.

[0008] According to the present disclosure, a drone is also provided, comprising: a fuselage frame; and a propulsion system coupled to the fuselage frame. The propulsion system comprises: a first propulsion device and a second propulsion device. The first propulsion device comprises a first rotor blade assembly and a first rotor mounting assembly. The first rotor blade assembly comprises a first portion. The first rotor mounting assembly comprises a first rotor seat and a first elastic member. The first rotor seat comprises: a first base; a first locking structure, the first locking structure being arranged at the first base; and a second locking structure, the second locking structure being arranged at the first base. The first locking structure comprises a first recess, the first recess is open toward the first base and is configured to accommodate a first portion of the first portion. The second locking structure comprises a second recess, the second recess is open toward the first base and is configured to accommodate a second portion of the first portion. The first elastic member is configured to provide an elastic force to the first portion to constrain the first portion in the first recess and the second recess. The second propulsion device comprises a second rotor blade assembly and a second rotor mounting assembly. The second rotor blade assembly comprises a second portion. The second rotor mounting assembly comprises a second rotor seat and a second elastic member. The second rotor mount includes: a second base; a third locking structure, the third locking structure is arranged at the second base; and a fourth locking structure, the fourth locking structure is arranged at the second base. The third locking structure includes a third recess, the third recess is open toward the second base and is configured to receive the first part of the second part. The fourth locking structure includes a fourth recess, the fourth recess is open toward the second base and is configured to receive the second part of the second part. The second elastic member is configured to provide an elastic force to the second part to constrain the second part in the third recess and the fourth recess.

[0009] According to the present disclosure, a rotor mounting assembly for a drone is also provided, comprising: a base; and a plurality of cantilever structures arranged on the base. Each of the plurality of cantilever structures comprises an arm-shaped portion and is configured to accommodate a portion of a rotor blade assembly of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figures 1A to 1C An exemplary rotor mounting assembly according to the present disclosure is schematically illustrated.

[0011] Figure 2 is a schematic diagram of an exemplary shaft according to the present disclosure.

[0012] Figure 3 An exemplary propulsion device according to the present disclosure is schematically illustrated.

[0013] FIG. 4A to FIG. 4CAn exemplary process according to the present disclosure of mounting a rotor blade assembly to a rotor mounting assembly is schematically illustrated.

[0014] Figure 5 An exemplary aircraft according to the present disclosure is schematically illustrated.

[0015] Figure 6 An exemplary propulsion system having an exemplary fool-proof design according to the present disclosure is schematically illustrated.

[0016] Figure 7 Another exemplary propulsion system having another exemplary fool-proof design according to the present disclosure is schematically illustrated.

[0017] Figure 8 Another exemplary propulsion system having another exemplary fool-proof design according to the present disclosure is schematically illustrated.

[0018] Fig. 9A and Fig. 9B Another exemplary propulsion system having another exemplary fool-proof design according to the present disclosure is schematically illustrated. DETAILED DESCRIPTION

[0019] Hereinafter, embodiments according to the present disclosure will be described with reference to the accompanying drawings, which are examples for illustrative purposes only and are not intended to limit the scope of the present disclosure. In all drawings and descriptions, the same reference numerals will be used as much as possible to refer to the same or similar parts.

[0020] As used in this disclosure, when a first component is referred to as being "fixed to" a second component, it is intended that the first component may be directly attached to the second component, or may be indirectly attached to the second component via another component. When a first component is referred to as being "connected to" a second component, it is intended that the first component may be directly connected to the second component, or may be indirectly connected to the second component via a third component between the first and second components. The terms "vertical", "horizontal", "left", "right" and similar expressions used in this disclosure are for description only.

[0021] Unless otherwise defined, all technical terms and scientific terms used in this disclosure have the same or similar meanings as those generally understood by those of ordinary skill in the art. As described in this disclosure, the terms used in the specification of this disclosure are intended to describe example embodiments rather than to limit this disclosure. The term "and / or" used in this disclosure includes any suitable combination of one or more of the listed related items.

[0022] Figure 1A is a perspective view of an exemplary rotor mount assembly 10 according to an embodiment of the present disclosure. Figure 1B is a side view of rotor mounting assembly 10 . Figure 1C1 is another perspective view of the rotor mounting assembly 10 from another perspective. The rotor mounting assembly 10 may be used in a propulsion system of a rotor-based aircraft, such as a propulsion system of a rotor-based unmanned aerial vehicle (UAV). The UAV may be, for example, a single-rotor UAV, or a multi-rotor UAV, such as a two-rotor UAV, a three-rotor UAV, a four-rotor UAV, a six-rotor UAV, an eight-rotor UAV, etc. The rotor mounting assembly 10 may be used to mount a rotor blade assembly (in Figures 1A to 1C ), and can drive the rotor blade assembly to rotate to provide lift for the aircraft.

[0023] like Figures 1A to 1C As shown, the rotor mounting assembly 10 includes a rotor seat 11 and an elastic member 12. The rotor seat 11 includes a base 111 and a plurality of locking structures 112 arranged at the base 111. The plurality of locking structures 112 can cooperate with the elastic member 12 to lock the rotor blade assembly to the rotor mounting assembly 10. The installation of the rotor blade assembly to the rotor mounting assembly 10 will be described in more detail later in this specification.

[0024] In some embodiments, the top surface of base 111 or a portion of the top surface of base 111 may be substantially coincident with or substantially parallel to the rotation plane of rotor mount assembly 10. The rotation plane of rotor mount assembly 10 may refer to a plane defined by the motion path of any point on rotor mount assembly 10 when rotor mount assembly 10 rotates, i.e., a plane in which the motion path of any point lies. In some other embodiments, the top surface of base 111 may include a plane or a portion of a plane that is not parallel to the rotation plane of rotor mount assembly 10. In some embodiments, the top surface of base 111 may include a non-planar surface or a non-planar portion. The non-planar surface or the non-planar portion may be convex or partially convex, concave or partially concave, or partially convex and partially concave.

[0025] In some embodiments, Figures 1A to 1C As shown, the base 111 includes a motor 1111 and a fixing member 1112. The motor 1111 can drive the rotor mounting assembly 10, and thus drive the rotor blade assembly mounted on the rotor mounting assembly 10 to rotate, thereby providing lift for the aircraft. The motor 1111 can be, for example, an outer rotor motor, in which the motor rotor (also referred to as a "mover") of the motor 1111 is configured to surround the stator of the motor 1111.

[0026] The fixing member 1112 may include a plate or a disk, and may be fixed to the motor 1111 by various means (eg, one or more screws). Figures 1A to 1CIn the example shown, the plurality of locking structures 112 are arranged on and fixed to the fixing member 1112. In some other embodiments, the base 111 may not include the fixing member 1112, and the plurality of locking structures 112 may be directly arranged on and fixed to the motor 1111. For example, the plurality of locking structures 112 may be directly arranged on and fixed to the mover of the motor 1111 or fixed to another component, such as a housing of the motor 1111 connected to the mover of the motor 1111.

[0027] In some embodiments, Figures 1A to 1C As shown, a plurality of locking structures 112 are arranged along the peripheral portion of the base 111. In some embodiments, the plurality of locking structures 112 may be identical or substantially identical to each other. In addition, the plurality of locking structures 112 may be arranged axially symmetrically with respect to the rotation axis of the rotor mount assembly 10, which may also be the rotation axis of the base 111. In some embodiments, one or more of the plurality of locking structures 112 may be mirror-symmetrical with another one or more of the plurality of locking structures 112 with respect to the plane in which the rotation axis of the rotor mount assembly 10 lies.

[0028] In some embodiments, Figures 1A to 1C As shown, in addition to being arranged on the base 111, the multiple locking structures 112 can also be separate structures that are not connected to each other. In some other embodiments, some or all of the multiple locking structures 112 can be connected to each other via components other than the base 111, such as a protective ring or a reinforcement structure arranged above the base 111.

[0029] exist Figures 1A to 1C In the example shown, the rotor mounting assembly 10 includes two locking structures 112. In the present disclosure, the two locking structures 112 of the same rotor mounting assembly 10 may also be referred to as a first locking structure and a second locking structure, respectively. The two locking structures 112 may be arranged axially symmetrically with respect to the rotation axis of the rotor mounting assembly 10. In some other embodiments, the rotor mounting assembly 10 may include one locking structure 112, or may include three or more locking structures 112.

[0030] In some embodiments, Figures 1A to 1CAs shown, each locking structure 112 includes a cantilever structure. The cantilever structure includes a support member 1130 extending from the base 111 and an extension 1140 connected to the support member 1130. The first end of the support member 1130 can be connected to the base 111, that is, in contact with the base 111. The extension 1140 can be connected to the support member 1130 at the second end of the support member 1130 opposite to the first end, or connected to the support member 1130 at any appropriate position between the first end of the support member 1130 and the second end of the support member 1130, for example, connected to the support member 1130 at a position close to the second end of the support member 1130.

[0031] In some embodiments, support member 1130 may include a strut protruding from a base, wherein a first end of the strut is connected to the base. In some embodiments, support member 1130, such as a strut, may be substantially perpendicular to the plane of rotation of rotor mount assembly 10. In some other embodiments, support member 1130, such as a strut, may form an angle with respect to the plane of rotation of rotor mount assembly 10 that is less than 90° but greater than 0°. For example, the angle may be 45°, 60°, or 80°.

[0032] Support member 1130 need not be a pillar, but may have any other form suitable for supporting extension 1140. For example, support member 1130 may be formed of two or more pillars, may have a shape that is entirely or partially curved (e.g., an arc shape), may have a shape that includes one or more curves, or may include two or more substantially straight parts that are continuously connected to each other. In some embodiments, support member 1130 may have a hollow configuration.

[0033] The extension 1140 may have the form of an arm-like structure, for example, including an arm. In some embodiments, the arm may include a beam. The extension 1140 such as an arm may be rigid or elastic, for example, the extension 1140 such as an arm may be made of a rigid material such as metal or hard plastic, or made of an elastic material such as rubber.

[0034] The extension 1140, such as an arm-shaped portion, may extend generally laterally from the support member 1130. That is, a first end of the extension 1140 may be coupled to the support member 1130 (and thus coupled to the base 111 through the support member 1130), and a second end of the extension 1140 opposite the first end of the extension 1140 is spaced apart from the base 111. In this way, the support member 1130 and the extension 1140 may form a cantilever structure.

[0035] In some embodiments, extension 1140 may be substantially perpendicular to support member 1130 and / or substantially parallel to the rotational plane of rotor mount assembly 10. Extension 1140 being parallel to the rotational plane of rotor mount assembly 10 may mean that the entire extension 1140 is substantially parallel to the rotational plane of rotor mount assembly 10, or a major portion of extension 1140 is substantially parallel to the rotational plane of rotor mount assembly 10. In some other embodiments, extension 1140, such as an arm-shaped portion, may form an angle relative to the rotational plane of rotor mount assembly 10. For example, the angle may be greater than approximately 0° and less than approximately 90°.

[0036] In some embodiments, extension 1140, such as an arm, may be curved. In some embodiments, extension 1140, such as an arm, may be curved in one or more directions, such as in one or more directions substantially perpendicular to the plane of rotation of rotor mount assembly 10 (e.g., Figures 1A to 1C The Z direction in FIG. 1 and the Z direction in FIG. 1 are bent and bent along one or more directions substantially parallel to the plane of rotation of the rotor mount assembly 10 (e.g., Figures 1A to 1C The Y direction in the figure is bent.

[0037] According to an embodiment of the present disclosure, each locking structure 112 (e.g., a cantilevered structure) of the rotor mounting assembly 10 can be configured to surround a portion of the rotor blade assembly, thereby mounting and securing the rotor blade assembly to the rotor mounting assembly 10. A portion of the rotor blade assembly is also referred to as a "mounting portion" or a "locking portion" and can include, for example, a center portion of the rotor blade assembly. In some embodiments, the rotor blade assembly may include a foldable rotor blade assembly including two rotor blades connected to each other via a hub (also referred to as a "connecting portion"). In these embodiments, the mounting portion of the rotor blade assembly surrounded by the locking structure 112 can be a hub.

[0038] The mounting portion of the rotor blade assembly may be received by extension portion 1140, such as by an arm portion. Figures 1A to 1C As shown, extension 1140 includes a recess 1141. For example, recess 1141 may include a groove extending transversely across extension 1140. Recess 1141 opens toward base 111 and is configured to receive a mounting portion of a rotor blade assembly.

[0039] like Figures 1A to 1C As shown, recess 1141 includes a bottom surface 1142 and two side surfaces 1143 extending from bottom surface 1142 toward the top surface of base 111. Bottom surface 1142 can be substantially parallel to the rotation plane of rotor mounting assembly 10. Two side surfaces 1143 can be substantially parallel to each other. In some embodiments, two side surfaces 1143 can be substantially perpendicular to the rotation plane of rotor mounting assembly 10.

[0040] In some embodiments, a first side of side 1143 may be continuously connected to a side of support member 1130. In other words, the first side of side 1143 may be considered to extend to base 111. A second side of side 1143 may be spaced apart from base 111. In this way, an opening may be formed between the second side of side 1143 and base 111, which opening is also referred to as a "vertical opening". During the process of mounting the rotor blade assembly to rotor mounting assembly 10, the opening may allow the mounting portion of the rotor blade assembly to pass through and then be received in recess 1141, which will be described in more detail below.

[0041] In some embodiments, Figures 1A to 1C As shown, the locking structure 112 also includes an inclined surface 1144 extending from the outer side 1145 of the locking structure 112 toward the top 1146 of the recess 1141. The inclined surface 1144 can be inclined at an angle greater than 0° and less than 90° relative to the rotation plane of the rotor mounting assembly 10. For example, the angle between the inclined surface 1144 and the rotation plane of the rotor mounting assembly 10 can be in the range of about 10° to about 45°, such as about 15°, about 20°, about 25°, about 30°, about 35°, about 40°, or about 45°. The inclined surface 1144 can allow the mounting portion of the rotor blade assembly to be more easily and / or smoothly rotated to the opening between the second side of the side 1143 and the base 111 and rotated into the recess 1141.

[0042] exist Figures 1A to 1C In the example shown, rotor mount assembly 10 includes two locking structures 112, which are arranged along the peripheral portion of base 111 and are arranged axially symmetrically with respect to the rotation axis of rotor mount assembly 10. In some embodiments, the two locking structures 112 can be identical or nearly identical to each other. For example, the sizes of the respective corresponding parts of the two locking structures 112 can be substantially the same.

[0043] In some embodiments, the support members 1130 of the two locking structures 112 may be substantially parallel to each other. In some embodiments, the extensions 1140 of the two locking structures 112 may be substantially parallel to each other and extend from one end of the corresponding support member 1130 in substantially opposite directions. Figure 1A and Figure 1C As shown, one of the two extending portions 1140 extends in the positive X-direction, and the other of the two extending portions 1140 extends in the negative X-direction.

[0044] like Figure 1A and Figure 1CAs shown, the two locking structures 112 are spaced apart from each other, and thus the two extensions 1140 of the two locking structures 112 are also spaced apart from each other. An opening 1150 is formed between the two locking structures 112, for example, between the extensions 1140 of the two locking structures 112. The opening 1150 is also referred to as a horizontal opening or groove. In some embodiments, the opening 1150 may extend in a direction parallel to the extension direction of the extension 1140. For example, as Figure 1A and Figure 1C As shown, both the opening 1150 and the extension portion 1140 may extend along the X direction in the figure. In some other embodiments, the extension direction of the opening 1150 and the extension direction of the extension portion 1140 may form an angle greater than 0° and less than 90°.

[0045] Opening 1150 is configured to receive a mounting portion of a rotor blade assembly and to allow the mounting portion of the rotor blade assembly to pass through the opening and rotate to a position to be received by (e.g., surrounded by) locking structure 112. In some embodiments, the width of opening 1150 may be greater than the width of the mounting portion of the rotor blade assembly to allow the mounting portion of the rotor blade assembly to pass through the opening. In some embodiments, the width of opening 1150 may be approximately equal to or slightly greater than the width of the mounting portion of the rotor blade assembly. For example, the width of opening 1150 may be approximately 1%, approximately 5%, or approximately 10% greater than the width of the mounting portion of the rotor blade assembly.

[0046] like Figure 1A As shown, each of the two extensions 1140 of the two locking structures 112 includes a recess 1141 that opens toward the base 111. The two recesses 1141 can each be configured to receive a corresponding portion of the mounting portion of the rotor blade assembly. For example, one of the two recesses 1141 can be configured to receive a first portion of the mounting portion including or near a first end of the mounting portion, and the other of the two recesses 1141 can be configured to receive a second portion of the mounting portion including or near a second end of the mounting portion opposite to the first end. The mounting portion of the rotor blade assembly can be inserted into the opening 1150, then pressed downward to pass through the opening 1150 and exceed the extension 1140 (for example, exceed the top 1146 of the extension 1140), then rotated to pass through each opening between the second side of the side 1143 of the corresponding extension 1140 and the base 111, and then pushed into the recess 1141 by the elastic member 12. In some embodiments, the opening between the second side surface of the side surfaces 1143 of the extension portion 1140 and the base 111 may also be the opening between the top 1146 of the extension portion 1140 and the base 111 .

[0047] In some embodiments, the recesses 1141 of the two locking structures 112 may be substantially symmetrical with respect to the rotation axis of the rotor mount assembly 10. In some embodiments, the recesses 1141 of the two locking structures 112 may be substantially parallel to each other, for example, substantially parallel to each other in their transverse direction (also referred to as the "width direction"). Figures 1A to 1C In the example shown, the transverse direction of the recess 1141 may be along the X direction in the figure. In some embodiments, each of the two recesses 1141 may extend through and penetrate the width direction of the corresponding extension 1140, and such a direction is also referred to as the longitudinal direction (also referred to as the "length direction") of the recess 1141. Figures 1A to 1C In the example shown, the longitudinal direction of the recess 1141 may be along the Y direction in the figure. Each recess 1141 may be symmetrical with respect to the middle plane of the corresponding recess 1141. The middle plane is also referred to as the longitudinal symmetry plane of the corresponding recess 1141. In some embodiments, the longitudinal symmetry planes of the two recesses 1141 may substantially coincide with each other.

[0048] The extending direction of the recess 1141, i.e., the longitudinal direction, may be along the first direction, and the extending direction of the opening 1150 may be along the second direction. In some embodiments, the first direction may not be parallel to the second direction. In some embodiments, the first direction may be substantially perpendicular to the second direction. For example, the first direction may be along Figures 1A to 1C The Y direction in the second direction can be along Figures 1A to 1C The X direction in .

[0049] According to an embodiment of the present disclosure, elastic member 12 may be configured to provide elastic force to the mounting portion of the rotor blade assembly to push the mounting portion of the rotor blade assembly to abut against bottom surface 1142 of recess 1141, so as to constrain the mounting portion of the rotor blade assembly in recess 1141. In this way, the rotor blade assembly may be mounted and fixed to rotor mounting assembly 10. In some embodiments, elastic member 12 may be arranged at the top surface and configured to abut against the mounting portion of the rotor blade assembly to provide elastic force to the mounting portion of the rotor blade assembly.

[0050] The elastic member 12 may have a structure that can provide elastic force, or may be made of a material that can provide elastic force. In some embodiments, the combination of the structure and material of the elastic member 12 may allow the elastic member 12 to provide elastic force. For example, the elastic member 12 may be made of an elastic material such as an elastomer or a metal, or a combination of elastic materials such as an elastomer and a metal. In some embodiments, the elastic member 12 may include a spring structure. For example, the elastic member 12 may include an air spring or a mechanical spring. For example, the mechanical spring may be a leaf spring, a cantilever spring, or a spring such as a spring. Figures 1A to 1C Coil spring shown.

[0051] In some embodiments, Figures 1A to 1C As shown, rotor mount assembly 10 further includes shaft 13. Shaft 13 may be disposed at the center of base 111 and substantially perpendicular to the rotation plane of rotor mount assembly 10. In addition, the axis of shaft 13 may coincide with the rotation axis of rotor mount assembly 10. In some embodiments, shaft 13 may be configured to rotate with motor 1111.

[0052] Shaft 13 may be configured to be inserted into an axial hole in a mounting portion of the rotor blade assembly, and may help stabilize the rotor blade assembly when the rotor mounting assembly 10 drives the rotor blade assembly to rotate. In some embodiments, shaft 13 may be positioned in the axial hole of the rotor blade assembly. In some other embodiments, shaft 13 may be rotated into the axial hole of the rotor blade assembly. For example, shaft 13 may include an external thread at its end for inserting into the axial hole, and the axial hole may correspondingly include an internal thread that matches the external thread of shaft 13. The fit between the external thread and the internal thread may help the rotor blade assembly be more stably fixed to shaft 13.

[0053] In some embodiments, Figures 1A to 1C As shown, the elastic member 12 may be sleeved on the shaft 13. For example, the elastic member 12 may include a coil spring and be sleeved around the shaft 13.

[0054] In some embodiments, the shaft 13 may include a simple rod structure, and the elastic member 12 may directly abut the base 111. In some embodiments, the shaft 13 may have another configuration that allows the elastic member 12 to abut the shaft 13 instead of the base 111. Figure 2 is a schematic diagram of an exemplary shaft 13 according to the present disclosure. Figure 2 In the example shown, shaft 13 includes a first end 131 and a second end 132. First end 131 may be configured to be coupled to a mounting portion of a rotor blade assembly, for example, inserted into an axial hole of the mounting portion of the rotor blade assembly, and is also referred to as the "free end" of shaft 13. Second end 132 may be configured to be fixed to motor 1111, so that second end 132 can rotate together with motor 1111, and is also referred to as the "fixed end" of shaft 13. Figure 2 As shown, the shaft 13 includes a step portion 133. When the rotor blade assembly is installed, the elastic member 12 can abut between the step portion 133 and the mounting portion of the rotor blade assembly. For example, one end of the elastic member 12 can abut the step portion 133, and the other end of the elastic member 12 can abut the mounting portion of the rotor blade assembly.

[0055] In the above mentioned Figures 1A to 1CIn the illustrated embodiment, rotor mount assembly 10 includes shaft 13. In some other embodiments, rotor mount assembly 10 may not need to include a shaft, and resilient member 12 may abut directly between base 111 and the mounting portion of the rotor blade assembly without being supported or constrained by the shaft.

[0056] A rotor mounting assembly according to the present disclosure may be used to mount a rotor blade assembly to form a propulsion device that may be used on an aircraft. Figure 3 1 to 3 are perspective views of an exemplary propulsion device 300 according to the present disclosure. The propulsion device 300 includes a rotor mounting assembly 310 and a rotor blade assembly 320 mounted at the rotor mounting assembly 310. The rotor mounting assembly 310 may be any rotor mounting assembly according to the present disclosure, such as the rotor mounting assembly 320 described above in conjunction with FIGS. Figure 1C and Figure 2 An exemplary rotor mount assembly 10 is described.

[0057] like Figure 3 As shown, the rotor mounting assembly 310 includes a rotor seat 311 and an elastic member (in Figure 3 The rotor mount 311 includes a base 3111 and two locking structures 3112 arranged at the base 3111. The two locking structures 3112 can cooperate with the elastic member to lock the rotor blade assembly 320 to the rotor mounting assembly 310. Figure 3 In the example shown, rotor mounting assembly 310 includes two locking structures 3112. Two locking structures 3112 may also be referred to as a first locking structure and a second locking structure, respectively. Two locking structures 3112 may be arranged axially symmetrically with respect to the rotation axis of rotor mounting assembly 310. In some other embodiments, rotor mounting assembly 310 may include one locking structure 3112 or may include three or more locking structures 3112.

[0058] In some embodiments, Figure 3 As shown, each of the two locking structures 3112 includes a cantilever structure. Each cantilever structure includes a support member 3113 extending from the base 3111 and an extension 3114 connected to the support member 3113. Each extension 3114 includes a recess 31141. For example, each recess 31141 may include a groove extending laterally across the corresponding extension 3114. Both recesses 31141 are open toward the base 3111. The construction of each locking structure 3112 can be combined with the above Figures 1A to 1C and Figure 2 The locking structure 112 is identical or similar in structure, so a detailed description thereof is omitted.

[0059] Similar to the above combination Figures 1A to 1C and Figure 2In the rotor mounting assembly 100, the rotor mounting assembly 310 further includes an opening 3115 formed between the two locking structures 3112, for example, the opening 3115 is located between the two extensions 3114. In some embodiments, the opening 3115 may extend in a direction parallel to the extension direction of the extension 3114. For example, Figure 3 As shown, both the opening 3115 and the extension portion 3114 may extend along the X direction in the figure. In some other embodiments, the extension direction of the opening 3115 and the extension direction of the extension portion 3114 may form an angle greater than 0° and less than 90°.

[0060] The rotor blade assembly 320 includes two blades 321 and a mounting portion 322 connecting the two blades 321. The mounting portion 322 can be configured to engage the rotor mounting assembly 310 to allow the rotor blade assembly 320 to be mounted and fixed to the rotor mounting assembly 310. In some embodiments, the mounting portion 322 may include a central portion of the rotor blade assembly 320. In some embodiments, the rotor blade assembly 320 may include a foldable blade assembly, wherein the two blades 321 are connected to each other via a hub and can rotate relative to each other. In these embodiments, when the foldable blade assembly is in an expanded state, the two blades 321 can extend in opposite directions, and when the foldable blade assembly is in a folded state, the two blades 321 can extend in substantially the same direction. In addition, the mounting portion 322 can be a hub of the foldable blade assembly.

[0061] like Figure 3 As shown, the recess 31141 of the first locking structure 3112 in the locking structure 3112 is configured to receive the first portion of the mounting portion 322, and the recess 31141 of the second locking structure 3112 in the locking structure 3112 is configured to receive the second portion of the mounting portion 322. In some embodiments, the first portion of the mounting portion 322 may include or be close to the first end of the mounting portion 322, and the second portion of the mounting portion 322 may include or be close to the second end of the mounting portion 322 opposite to the first end.

[0062] When rotor blade assembly 320 is held by recess 31141, the elastic member may provide elastic force to mounting portion 322 of rotor blade assembly 320 to push mounting portion 322 against bottom surface 31142 of each recess 31141 so as to constrain mounting portion 322 in recess 31141. Figure 3 As shown, rotor blade assembly 320 may be mounted and secured to rotor mounting assembly 310 .

[0063] In order to keep the mounting portion 322 in the recess 31141, the width of each recess 31141 may be greater than the width of the mounting portion 322. In some embodiments, the width of each recess 31141 may be approximately equal to or slightly greater than the width of the mounting portion 322. In some embodiments, the widths of the two recesses 31141 may be approximately equal to each other. In addition, the depth of each recess 31141 may be greater than the thickness of the mounting portion 322. In some embodiments, the depth of each recess 31141 may be approximately equal to or slightly greater than the thickness of the mounting portion 322. In some embodiments, the depths of the two recesses 31141 may be approximately equal to each other.

[0064] In some embodiments, the width of opening 3115 may be greater than the width of mounting portion 322 of rotor blade assembly 320 to allow mounting portion 322 to pass through the opening. In some embodiments, the width of opening 3115 may be substantially equal to or slightly greater than the width of mounting portion 322.

[0065] In some embodiments, Figure 3 As shown, rotor mounting assembly 310 further includes shaft 313. Shaft 313 may be arranged at the center of base 3111 and substantially perpendicular to the rotation plane of rotor mounting assembly 310. Accordingly, rotor blade assembly 320 further includes shaft hole 323 at mounting portion 322. Shaft hole 323 is configured to receive shaft 313. In some embodiments, the elastic member of rotor mounting assembly 310 may include a coil spring sleeved on shaft 313.

[0066] As mentioned above, in Figure 3 Some features and characteristics of rotor mounting assembly 310 are shown in FIG. In some embodiments, rotor mounting assembly 310 may have a configuration similar to that described above. Figures 1A to 1C and Figure 2 The same or similar features and / or characteristics as those of the rotor mounting assembly 10. Therefore, for details of the rotor mounting assembly 310, such as the construction of its various components and their functions, reference may be made to the above description of the rotor mounting assembly 10. A detailed description of the rotor mounting assembly 310 is omitted.

[0067] FIG. 4A to FIG. 4C The process of installing the rotor blade assembly 320 to the rotor mounting assembly 310 is schematically shown. Figure 4A As shown, rotor blade assembly 320 is placed on rotor mounting assembly 310, wherein mounting portion 322 of rotor blade assembly 320 is at least partially received in opening 3115. At this stage, the elastic member of rotor mounting assembly 310 may be in a natural state or in a slightly compressed state to hold mounting portion 322 in opening 3115. Then, as shown in FIG. Figure 4BAs shown, an external force can be applied to rotor blade assembly 320 to push rotor blade assembly 320 downward, thereby allowing mounting portion 322 to exceed the bottom of extension 3114, for example, to exceed the top of recess 31141 of extension 3114. At this stage, the elastic member of rotor mounting assembly 310 is further compressed. In some embodiments, rotor blade assembly 320 can be pushed downward until mounting portion 322 contacts base 3111. Thereafter, rotor blade assembly 320 can be rotated to allow mounting portion 322 to pass through the opening between the top of recess 31141 and base 3111. When mounting portion 322 reaches the extreme position, for example, when mounting portion 322 contacts one or both support members 3113, the external force can be removed, and the elastic force applied to mounting portion 322 by the elastic member of rotor mounting portion 322 can push rotor blade assembly 320 upward until mounting portion 322 contacts bottom surface 31142 of recess 31141. In this way, as shown in FIG. Figure 4C As shown, the mounting portion 322 can be constrained in the recess 31141.

[0068] According to the propulsion device disclosed in the present invention, for example, Figure 3 The propulsion device 300 may be used in an aircraft such as an unmanned aerial vehicle (UAV) to provide lift for the aircraft. Figure 5 An exemplary aircraft 500 according to the present disclosure is schematically shown. The aircraft 500 includes a fuselage frame 510 and a propulsion system 520, which is coupled to the fuselage frame 510 and is configured to provide lift to the aircraft 500. The fuselage frame 510 includes a fuselage 511 and a plurality of arms 512 extending from the fuselage 511. The fuselage 511 can be configured to accommodate various components of the aircraft 500, such as a flight controller, electronic circuits, and / or one or more sensors. In some embodiments, a gimbal for carrying a payload (e.g., a camera) can be coupled to the fuselage 511, for example, arranged below the fuselage 511.

[0069] The propulsion system 520 includes a plurality of propulsion devices 530, each of which is arranged at or near an end of one of the plurality of arm-shaped portions 512 away from the fuselage 511. Each propulsion device 530 can be combined with the above Figure 3The propulsion device 300 is the same or similar, and each propulsion device 530 may have the same or similar components as the propulsion device 300. For example, each propulsion device 530 may include a rotor mounting assembly and a rotor blade assembly mounted thereon, and the rotor mounting assembly may include a rotor seat and an elastic member. The rotor seat may include a base and a plurality of locking structures, such as two locking structures, each locking structure including a recess opening toward the base, the recess being configured to accommodate a portion of the mounting portion of the rotor blade assembly. The elastic member is configured to provide an elastic force to the mounting portion to constrain the mounting portion in the corresponding recess. A detailed description of the structure, construction, and function of the various components of each propulsion device 530 is omitted herein.

[0070] exist Figure 5 In the example shown, the aircraft 500 is a quadrotor aircraft, which includes four arms 512 and four propulsion devices 530, each of which is arranged at or near one end of one of the four arms 512 away from the fuselage 511. In some other embodiments, the aircraft 500 may be a two-rotor aircraft including two propulsion devices 530, a three-rotor aircraft including three propulsion devices 530, a six-rotor aircraft including six propulsion devices 530, or an eight-rotor aircraft including eight propulsion devices 530. In some embodiments, the plurality of propulsion devices 530 may be arranged evenly spaced from each other. In some embodiments, the plurality of propulsion devices 530 may be divided into two groups, and the two groups of propulsion devices 530 may be arranged symmetrically with respect to the middle plane of the aircraft 500.

[0071] In order for the aircraft 500 to function properly, for example, to balance the angular momentum generated by the rotors of the plurality of propulsion devices 530 during rotation, the plurality of propulsion devices 530 should be configured to rotate in different directions while being able to generate upward thrust. Figure 5 For the aircraft 500 shown in , the two propulsion devices marked as 530A may need to rotate in a first direction (e.g., counterclockwise (as viewed from above)), and the two propulsion devices marked as 530B may need to rotate in a second direction different from the first direction (e.g., clockwise (as viewed from above)). The two propulsion devices 530A are also referred to as "first direction propulsion devices", and can provide lift when the two propulsion devices 530A rotate in the first direction. The base of each first direction propulsion device may include a first direction motor that can rotate in the first direction when in operation. The two propulsion devices 530B are also referred to as "second direction propulsion devices", and can provide lift when the two propulsion devices 530B rotate in the second direction. The base of each second direction propulsion device may include a second direction motor that can rotate in the second direction when in operation.

[0072] In some embodiments, Figure 5As shown, four propulsion devices 530 are arranged around the fuselage 511 in the following order: first direction propulsion device 530A, second direction propulsion device 530B, first direction propulsion device 530A, and second direction propulsion device 530B. In some embodiments, the propulsion system 520 of the aircraft 500 may include two propulsion devices, one is a first direction propulsion device, and the other is a second direction propulsion device.

[0073] In order to allow the first direction propulsion device 530A and the second direction propulsion device 530B to provide upward thrust while rotating in different directions, the rotor blade assembly of the first direction propulsion device 530A (also referred to as the "first direction rotor blade assembly") and the rotor blade assembly of the second direction propulsion device 530B (also referred to as the "second direction rotor blade assembly") can have different structures. For example, the blades of the first direction rotor blade assembly and the blades of the second direction rotor blade assembly can be tilted in different directions. If the first direction rotor blade assembly is used in the second direction propulsion device, or vice versa, downward thrust may be generated instead of the expected upward thrust. This will cause the aircraft 500 to malfunction and may cause damage to the aircraft 500.

[0074] In order to avoid using incorrect rotor blade assemblies in the propulsion device, the present disclosure also provides certain fool-proof designs of the propulsion device 530 that can be applied to the propulsion system 520. In some embodiments, the rotor mounting assembly of the first direction propulsion device 530A (also referred to as the "first direction rotor mounting assembly") may be configured to not allow the second direction rotor blade assembly to be assembled or installed to the first direction rotor mounting assembly. In some embodiments, the rotor mounting assembly of the second direction propulsion device 530B (also referred to as the "second direction rotor mounting assembly") may be configured to not allow the first direction rotor blade assembly to be assembled or installed to the second direction rotor mounting assembly. In some embodiments, both the first direction rotor mounting assembly and the second direction rotor mounting assembly may be configured to not allow other types of rotor blade assemblies to be assembled or installed thereon. The following is in conjunction with Figure 6 9 describe various fool-proof designs according to the present disclosure in more detail.

[0075] Figure 6 An exemplary propulsion system 600 having an exemplary fool-proof design according to the present disclosure is schematically shown. The propulsion system 600 includes a first propulsion device 610A and a second propulsion device 610B. The first propulsion device 610A may be one of the first direction propulsion device and the second direction propulsion device, and the second propulsion device 610B may be the other of the second direction propulsion device and the second direction propulsion device. Figure 6 Includes a top view of a first propulsion device 610A and a second propulsion device 610B.

[0076] Each of the first propulsion device 610A and the second propulsion device 610B can be combined with the above Figure 3 The propulsion device 300 is the same as or similar to the above, or is combined with Figure 5 The propulsion device 530 is the same or similar to the one described above, and detailed description of the same or similar components, features and functions is omitted. Figure 6 As shown, first propulsion device 610A is in a state where mounting portion 611A of the rotor blade assembly of first propulsion device 610A is received in opening 612A formed between two locking structures 613A of the rotor mounting assembly of first propulsion device 610A. Similarly, second propulsion device 610B is in a state where mounting portion 611B of the rotor blade assembly of second propulsion device 610B is received in opening 612B formed between two locking structures 613B of the rotor mounting assembly of second propulsion device 610B.

[0077] exist Figure 6 In the example shown, the width W1 of the opening 612A is smaller than the width W2 of the mounting portion 611 B. With this foolproof design, since the mounting portion 611B cannot be inserted and therefore cannot pass through the opening 612A, the possibility of incorrectly mounting the rotor blade assembly of the second propulsion device 610B to the rotor mounting assembly of the first propulsion device 610A can be eliminated or at least greatly reduced.

[0078] Figure 7 Another exemplary propulsion system 700 having another exemplary fool-proof design according to the present disclosure is schematically shown. The propulsion system 700 includes a first propulsion device 710A and a second propulsion device 710B. The first propulsion device 710A may be one of the first direction propulsion device and the second direction propulsion device, and the second propulsion device 710B may be the other of the second direction propulsion device and the second direction propulsion device. Figure 7 Includes a top view of a first propulsion device 710A and a second propulsion device 710B.

[0079] Each of the first propulsion device 710A and the second propulsion device 710B can be combined with the above Figure 3 The propulsion device 300 is the same as or similar to the above, or is combined with Figure 5 The propulsion device 530 is the same or similar to the one described above, and detailed description of the same or similar components, features and functions is omitted. Figure 7As shown, first propulsion device 710A is in a state where mounting portion 711A of the rotor blade assembly of first propulsion device 710A is received in opening 712A formed between two locking structures 713A of the rotor mounting assembly of first propulsion device 710A. Similarly, second propulsion device 710B is in a state where mounting portion 711B of the rotor blade assembly of second propulsion device 710B is received in opening 712B formed between two locking structures 713B of the rotor mounting assembly of second propulsion device 710B.

[0080] In addition, the rotor mounting assembly of the first propulsion unit 710A includes a shaft 714A, which is configured to be inserted into a shaft hole 715A of the rotor blade assembly of the first propulsion unit 710A. The rotor mounting assembly of the second propulsion unit 710B includes a shaft 714B, which is configured to be inserted into a shaft hole 715B of the rotor blade assembly of the second propulsion unit 710B.

[0081] exist Figure 7 In the example shown, shaft 714A (e.g., the free end (mounting end) of shaft 714A) and shaft hole 715A have a circular shape, and shaft 714B (e.g., the free end (mounting end) of shaft 714B) and shaft hole 715B have a rectangular shape. Shaft hole 715A is configured to not allow shaft 714B to pass therethrough. Similarly, shaft hole 715B is configured to not allow shaft 714A to pass therethrough. In some embodiments, the dimensions of the circular shape and the rectangular shape may be configured such that shaft 715A cannot allow shaft 714B to pass therethrough, but shaft hole 715B allows shaft 714A to pass therethrough, and vice versa.

[0082] Figure 7 The configurations of shaft 714A, shaft 714B and shaft hole 715A, shaft hole 715B shown in and as described above are merely examples for illustrative purposes. In some other embodiments, shaft 714A, shaft 714B and shaft hole 715A, shaft hole 715B may have other shapes, as long as at least one of shaft hole 715A and shaft hole 715B does not allow a shaft belonging to another propulsion device to pass therethrough. The different shapes of shaft 714A and shaft hole 715A and shaft 714B and shaft hole 715B may be selected from a variety of shapes, such as elliptical, triangular, pentagonal, hexagonal, and octagonal.

[0083] Figure 8Another exemplary propulsion system 800 having another exemplary fool-proof design according to the present disclosure is schematically shown. The propulsion system 800 includes a first propulsion device 810A and a second propulsion device 810B. The first propulsion device 810A may be one of the first direction propulsion device and the second direction propulsion device, and the second propulsion device 810B may be the other of the second direction propulsion device and the second direction propulsion device. Figure 8 Includes a top view of a first propulsion device 810A and a second propulsion device 810B.

[0084] Each of the first propulsion device 810A and the second propulsion device 810B can be combined with the above Figure 3 The propulsion device 300 is the same as or similar to the above, or is combined with Figure 5 The propulsion device 530 is the same or similar to the one described above, and detailed description of the same or similar components, features and functions is omitted. Figure 8 As shown, the first propulsion device 810A is in a state where the mounting portion 811A of the rotor blade assembly of the first propulsion device 810A is received in an opening 812A formed between two locking structures 813A of the rotor mounting assembly of the first propulsion device 810A. Similarly, the second propulsion device 810B is in a state where the mounting portion 811B of the rotor blade assembly of the second propulsion device 810B is received in an opening 812B formed between two locking structures 813B of the rotor mounting assembly of the second propulsion device 810B.

[0085] In addition, similar to Figure 7 , the rotor mounting assembly of the first propulsion device 810A includes a shaft 814A configured to be inserted into a shaft hole 815A of the rotor blade assembly of the first propulsion device 810A. Figure 7 In the second propulsion device 710B shown in FIG. 8 , the rotor mounting assembly of the second propulsion device 810B includes a shaft 814B that is configured to be inserted into a shaft hole 815B of the rotor blade assembly of the second propulsion device 810B.

[0086] and Figure 7 Unlike the propulsion system 700 shown in Figure 8 In the exemplary propulsion system 800 shown in FIG. 8 , the shaft 814A (e.g., the free end (mounting end) of the shaft 814A), the shaft hole 815A, the shaft 814B (e.g., the free end (mounting end) of the shaft 814B), and the shaft hole 815B have the same shape, for example, Figure 8 The circular shape shown. However, the diameter d1 of the shaft hole 815A is smaller than the diameter d2 of the shaft 814B. Thus, the shaft hole 815A will not allow the shaft 814B to pass therethrough.

[0087] Figure 8 The configurations of shaft 814A, shaft 814B and shaft hole 815A, shaft hole 815B shown in and as described above are merely examples for illustrative purposes. In some other embodiments, shaft 814A, shaft 814B and shaft hole 815A, shaft hole 815B may have other shapes, as long as the size of at least one of shaft hole 815A and shaft hole 815B does not allow shafts belonging to other propulsion devices to pass therethrough. The shape may be selected from a variety of shapes, such as elliptical, triangular, rectangular, pentagonal, hexagonal, and octagonal shapes. For example, shaft 814A, shaft 814B and shaft hole 815A, shaft hole 815B may all have a triangular, rectangular, pentagonal, hexagonal, or octagonal shape, and the length of the side of one of shaft hole 815A and shaft hole 815B is less than the length of the corresponding side of the shaft belonging to the other propulsion device.

[0088] Fig. 9A and Fig. 9B Another exemplary propulsion system 900 having another exemplary fool-proof design according to the present disclosure is schematically shown. The propulsion system 900 includes a first propulsion device 910A and a second propulsion device 910B. The first propulsion device 910A may be one of the first direction propulsion device and the second direction propulsion device, and the second propulsion device 910B may be the other of the second direction propulsion device and the second direction propulsion device. Fig. 9A Includes a top view of a first propulsion device 910A and a second propulsion device 910B. Fig. 9B Included is a cross-sectional view of the first propulsion device 910A taken along line II and a cross-sectional view of the second propulsion device 910B taken along line II-II.

[0089] Each of the first propulsion device 910A and the second propulsion device 910B can be combined with Figure 3 The propulsion device 300 is the same as or similar to the above, or is combined with Figure 5 The propulsion device 530 is the same or similar to the one described above, and detailed description of the same or similar components, features and functions is omitted. Fig. 9A and 9B As shown, first propulsion device 910A is in a state where mounting portion 911A of the rotor blade assembly of first propulsion device 910A is received and restrained in recess 914A of the locking structure of the rotor mounting assembly of first propulsion device 910A. Similarly, second propulsion device 910B is in a state where mounting portion 911B of the rotor blade assembly of second propulsion device 910B is received in recess 914B of the locking structure of the rotor mounting assembly of second propulsion device 910B.

[0090] exist Fig. 9A and Fig. 9BIn the example shown in , the width W3 of the recess 914A is smaller than the width W4 of the mounting portion 911 B. With this foolproof design, since the mounting portion 911B cannot be inserted and cannot be constrained in the recess 914A, the possibility of incorrectly mounting the rotor blade assembly of the second propulsion device 910B to the rotor mounting assembly of the first propulsion device 910A can be eliminated or at least greatly reduced.

[0091] In some embodiments, the above combination Figure 6 , Figure 7 , Figure 8 , Fig. 9A and Fig. 9B The foolproof designs described can be combined in any suitable manner. Two or more such foolproof designs can be used in the same propulsion system according to the present disclosure.

[0092] The processes shown in the figures associated with the method embodiments may be performed or implemented in any suitable order or sequence, which is not limited to the order and sequence shown in the figures and described above. For example, depending on the functions involved, two consecutive processes may be performed substantially simultaneously or in parallel where appropriate to reduce waiting time and processing time, or in the reverse order as shown in the figures.

[0093] Furthermore, as desired, components associated with the device embodiments in the figures may be coupled in a manner different from that shown in the figures. Certain components may be omitted, and other components may be added.

[0094] Other embodiments of the present disclosure will be apparent to those skilled in the art through consideration of the specification and practice of the embodiments disclosed herein. It is intended that the specification and examples be considered exemplary only and not limiting the scope of the present disclosure, the true scope and spirit of the present invention being indicated by the appended claims.

Claims

1. A propulsion device, comprising: Rotor blade assembly; as well as Rotor mounting assembly, comprising: Rotor mount, including: Base; A first locking structure comprising a first support member protruding from the base; and a first extension portion extending from an end of the first support member, wherein an extension direction of the first extension portion is different from an extension direction of the first support member; and a second locking structure, comprising a second supporting member protruding from the base and a second extending portion extending from an end of the second supporting member, wherein an extending direction of the second extending portion is different from an extending direction of the second supporting member; Wherein, the first extension portion and the second extension portion are arranged at intervals, and a first opening is formed between the first extension portion and the second extension portion; the rotor blade assembly can be in a first state and a second state, in the first state, the entire rotor blade assembly can move along the direction of the rotation axis corresponding to the rotor blade assembly, so that the entire rotor blade assembly passes through the first opening; in the second state, the outer surface of the rotor blade assembly cooperates with the first extension portion and the second extension portion, so that the rotor blade assembly is fixed to the rotor seat; An elastic member is configured to provide an elastic force to the rotor blade assembly to lock the rotor blade assembly to the rotor mounting assembly.

2. The propulsion device according to claim 1, wherein: The bottom of the first extension portion forms a first recess opening toward the base, and the first recess is used to cooperate with the outer surface of the rotor blade assembly; The bottom of the second extension portion forms a second recess opening toward the base; the second recess is used to cooperate with the outer surface of the rotor blade assembly.

3. The propulsion device according to claim 1, wherein: The first support member and the second support member are generally perpendicular to a plane of rotation of the rotor mount assembly.

4. The propulsion device according to claim 1, wherein: The first extension and the second extension are generally parallel to a plane of rotation of the rotor mount assembly.

5. The propulsion device according to claim 1, wherein: The first end of the first extension portion is coupled to the base through the first supporting member, and the second end of the first extension portion is opposite to the first end of the first extension portion and is spaced apart from the base; The first end of the second extension portion is coupled to the base through the second supporting member, and the second end of the second extension portion is opposite to the first end of the second extension portion and is spaced apart from the base.

6. The propulsion device according to claim 2, wherein: Any one of the first recess and the second recess comprises a bottom surface and two side surfaces extending from the bottom surface toward the top surface of the base; The bottom surface is substantially parallel to the plane of rotation of the rotor mounting assembly; and The two side surfaces are substantially parallel to each other.

7. The propulsion device according to claim 6, wherein: The two side surfaces are generally perpendicular to the plane of rotation of the rotor mounting assembly.

8. The propulsion device according to claim 6, wherein: A first side of the two sides extends to the base, and a second side of the two sides is spaced apart from the base; as well as A second opening is formed between the second side surface and the base, and the second opening is configured to allow a portion of the rotor blade assembly to pass therethrough to be received in the first recess and the second recess.

9. The propulsion device according to claim 2, wherein: The first locking structure comprises a first inclined surface extending from an outer side surface of the first locking structure toward a top of the first recess, the first inclined surface being inclined at an angle greater than 0° and less than 90° relative to a rotation plane of the rotor mounting assembly; The second locking structure includes a second inclined surface extending from an outer side surface of the second locking structure toward a top of the second recess, and the second inclined surface is inclined at an angle greater than 0° and less than 90° relative to a rotation plane of the rotor mounting assembly.

10. The propulsion device according to claim 1, wherein: The elastic member is made of elastic material.

11. The propulsion device according to claim 10, wherein: The elastic material includes at least one of an elastomer or a metal.

12. The propulsion device according to claim 1, wherein: The elastic member includes a spring structure.

13. The propulsion device according to claim 12, wherein: The spring structure includes at least one of a leaf spring or a coil spring.

14. The propulsion device according to claim 1, wherein: The rotor mounting assembly also includes: an axis disposed at the center of the base; Wherein, the elastic component is sleeved on the shaft.

15. The propulsion device according to claim 14, wherein: The shaft includes a step portion at a free end of the shaft; and The elastic member is configured to abut between the step portion and a portion of the rotor blade assembly.

16. The propulsion device according to claim 15, wherein: The shaft is configured to be inserted into a shaft hole in a portion of the rotor blade assembly.

17. The propulsion device according to claim 16, wherein: The shaft is configured to be positioned in the shaft hole.

18. The propulsion device according to claim 16, wherein: The shaft is configured to rotate into the shaft hole.

19. The propulsion device according to claim 1, wherein: The base includes a motor.

20. The propulsion device according to claim 19, wherein: The electric motor is an outer rotor electric motor.

21. The propulsion device of claim 19, wherein the rotor mounting assembly further comprises: A shaft is disposed at the center of the base and is configured to rotate with the motor.

22. The propulsion device according to claim 1, wherein: The elastic member is disposed at a top surface of the base and is configured to abut a portion of the rotor blade assembly.

23. The propulsion device according to claim 1, wherein: The first locking structure and the second locking structure are substantially symmetrical to each other relative to an axis of rotation of the rotor mounting assembly.

24. The propulsion device according to claim 2, wherein: The first recess and the second recess are substantially parallel to each other.

25. The propulsion device according to claim 2, wherein: The first recess and the second recess are substantially symmetrical to each other relative to an axis of rotation of the rotor mount assembly.

26. The propulsion device of claim 25, the first recess being configured to receive a first portion of a portion of the rotor blade assembly, and the second recess being configured to receive a second portion of a portion of the rotor blade assembly.

27. The propulsion device of claim 1, wherein: The first extension portion and the second extension portion extend in substantially opposite directions.

28. The propulsion device according to claim 2, wherein: The first recess and the second recess extend along a first direction; and The first opening extends along a second direction that is not parallel to the first direction.

29. The propulsion device according to claim 28, wherein: The first direction is substantially perpendicular to the second direction.

30. The propulsion device of claim 1, wherein: The first support member and the second support member are substantially parallel to each other; and The first extending portion and the second extending portion are substantially parallel to each other.

31. The propulsion device according to claim 2, wherein: The elastic member is configured to urge the rotor blade assembly to abut against a bottom surface of the first recess and a bottom surface of the second recess when the rotor blade assembly is held in the first recess and the second recess.

32. The propulsion device of claim 2, wherein: A width of the first recess, a width of the second recess, and a width of a portion of the rotor blade assembly are substantially equal to one another.

33. The propulsion device of claim 32, wherein: A first depth of the first recess is substantially equal to a second depth of the second recess; and The first depth and the second depth are both greater than a thickness of a portion of the rotor blade assembly.

34. The propulsion device of claim 1, wherein: The rotor mounting assembly also includes a shaft disposed at the center of the base; and The rotor blade assembly includes a shaft bore at a portion of the rotor blade assembly, the shaft bore being configured to receive the shaft.

35. The propulsion device of claim 34, wherein: The elastic member includes a coil spring sleeved on the shaft.

36. The propulsion device of claim 1, wherein: The rotor blade assembly includes a foldable blade assembly.

37. A propulsion device according to claim 36, wherein: A portion of the rotor blade assembly includes a hub of the foldable blade assembly; The foldable paddle assembly includes two paddles connected by the hub; and The two paddles are configured to extend in opposite directions when the foldable paddle assembly is in the deployed state, and to extend in substantially the same direction when the foldable paddle assembly is in the folded state.

38. A propulsion system comprising: The first propulsion device comprises: A first rotor blade assembly includes a first portion; and The first rotor mounting assembly comprises: The first rotor seat comprises: First base; A first locking structure comprising a first support member protruding from the base; and a first extension portion extending from an end of the first support member, wherein an extension direction of the first extension portion is different from an extension direction of the first support member; and a second locking structure, comprising a second supporting member protruding from the base and a second extending portion extending from an end of the second supporting member, wherein an extending direction of the second extending portion is different from an extending direction of the second supporting member; Wherein, the first extension portion and the second extension portion are arranged at an interval, and an opening is formed between the first extension portion and the second extension portion; the rotor blade assembly can be in a first state and a second state, in the first state, the entire rotor blade assembly can move along the direction of the rotation axis corresponding to the rotor blade assembly, so that the entire rotor blade assembly passes through the opening; in the second state, the outer surface of the rotor blade assembly cooperates with the first extension portion and the second extension portion, so that the first rotor blade assembly is fixed to the first rotor seat; a first elastic member configured to provide an elastic force to the first rotor blade assembly to lock the first rotor blade assembly to the first rotor mounting assembly; The second propulsion device comprises: A second rotor blade assembly includes a second portion; and The second rotor mounting assembly comprises: The second rotor mount comprises: Second base; a third locking structure comprising a third support member protruding from the base; and a third extension portion extending from an end of the third support member, wherein an extension direction of the third extension portion is different from an extension direction of the third support member; and a fourth locking structure, comprising a fourth supporting member protruding from the base and a fourth extending portion extending from an end of the fourth supporting member, wherein an extending direction of the fourth extending portion is different from an extending direction of the fourth supporting member; The third extension portion is spaced from the fourth extension portion, and an opening is formed between the third extension portion and the fourth extension portion; the rotor blade assembly can be in a first state and a second state, in the first state, the entire rotor blade assembly can move along the direction of the rotation axis corresponding to the rotor blade assembly, so that the entire rotor blade assembly passes through the opening; in the second state, the outer surface of the rotor blade assembly cooperates with the third extension portion and the fourth extension portion, so that the second rotor blade assembly is fixed to the second rotor seat; a second elastic member configured to provide an elastic force to the second rotor blade assembly to lock the second rotor blade assembly to the second rotor mounting assembly; The mounting portion of the second rotor blade assembly is configured to be connected to a blade of the second rotor blade assembly; wherein the first rotor mounting assembly is configured to not allow the second rotor blade assembly to be assembled to the first rotor mounting assembly.

39. The propulsion system of claim 38, wherein: The second rotor mount assembly is configured to not allow the first rotor blade assembly to be assembled to the second rotor mount assembly.

40. The propulsion system of claim 38, wherein: The first rotor blade assembly is configured to provide lift when rotated in a first direction; and The second rotor blade assembly is configured to provide lift when rotated in a second direction opposite the first direction.

41. The propulsion system of claim 38, wherein: The bottom of the first extension portion forms a first recess opening toward the base, and the first recess is used to cooperate with the outer surface of the rotor blade assembly; The bottom of the second extension portion forms a second recess opening toward the base; the second recess is used to cooperate with the outer surface of the rotor blade assembly.

42. The propulsion system of claim 41, wherein: A width of the first recess and a width of the second recess are both smaller than a width of the second portion.

43. The propulsion system of claim 41, wherein: The width of the opening is smaller than the width of the second portion.

44. The propulsion system of claim 38, wherein: The first rotor mounting assembly further includes a shaft disposed at a center of the first base; The second rotor blade assembly includes an axial hole at the second portion; and At least one of a size or a shape of the shaft hole is configured to not allow the shaft to pass through the shaft hole.

45. The propulsion system of claim 44, wherein: The shaft and the shaft hole both have a circular shape, and a diameter of the shaft is larger than a diameter of the shaft hole.

46. ​​The propulsion system of claim 38, wherein: The first base includes a first motor; and The second base includes a second motor.

47. An aircraft, comprising: Fuselage frame; as well as A propulsion system according to claim 38 coupled to said fuselage frame.

48. The flying machine of claim 47, wherein: The fuselage frame comprises: fuselage; and at least two arms extending from the body; and Each of the first propulsion device and the second propulsion device is arranged at an end of one of the at least two arm-shaped portions away from the fuselage.

49. The flying machine of claim 48, wherein: The at least two arms include four arms extending from the body; The propulsion system further comprises: a third propulsion device, the first propulsion device and the third propulsion device having substantially the same structure and configured to rotate in a first direction; and a fourth propulsion device, the second propulsion device and the fourth propulsion device having substantially the same structure and configured to rotate in a second direction opposite to the first direction; Each of the first propulsion device, the second propulsion device, the third propulsion device and the fourth propulsion device is arranged at an end of one of the four arm-shaped parts away from the fuselage; and The first propulsion device, the second propulsion device, the third propulsion device and the fourth propulsion device are sequentially arranged around the fuselage.

50. The flying machine of claim 49, wherein: The first propulsion device, the second propulsion device, the third propulsion device and the fourth propulsion device are arranged evenly spaced from each other.

51. A rotor mounting assembly for use in a propulsion device according to any one of claims 1 to 37, comprising: Base; as well as A plurality of cantilever structures are arranged on the base, each of the plurality of cantilever structures comprises an arm-shaped portion and is configured to cooperate with an outer surface of a rotor blade assembly of a drone to fix the rotor blade assembly.

52. The rotor mounting assembly of claim 51, wherein: The arm includes a recess configured to receive a portion of the rotor blade assembly.

53. The rotor mounting assembly of claim 51, wherein: The plurality of cantilever structures are arranged axisymmetrically with respect to an axis of rotation of the rotor mount assembly.

54. The rotor mounting assembly of claim 51, wherein: The plurality of cantilever structures are arranged along a peripheral portion of the base.

55. The rotor mounting assembly of claim 51, wherein: The arm portion includes a beam.

56. The rotor mounting assembly of claim 51, wherein: The arm portion is curved.

57. The rotor mounting assembly of claim 51, wherein: The arm is rigid.

58. The rotor mounting assembly of claim 51, wherein: The arm portion is elastic.

59. The rotor mounting assembly of claim 51, wherein: Each cantilever structure further includes a support member extending generally vertically from the base; and The arm portion of the cantilever structure extends generally laterally from the support member of the cantilever structure.

60. The rotor mounting assembly of claim 51, wherein: Each cantilevered structure is configured to wrap around a portion of the rotor blade assembly.

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