Rotor bearing arrangement

Abstract

A rotor support device is provided. The rotor support device (18) has a support member (24, 24b, 24c) that supports a rotor (20) and has a coupling portion (56, 58) that protrudes outward, a connecting member (26b) that forms a protruding portion (64) by forming a notch (62) at an end portion that is coupled to the coupling portion, the protruding portion overlapping an outer peripheral surface of the coupling portion in a first direction that is orthogonal to a protruding direction of the coupling portion and being detachably coupled to the coupling portion, and a reinforcing member (60) that overlaps the outer peripheral surface of the coupling portion in a second direction that is opposite to the first direction and the connecting member and is detachably coupled to the coupling portion and the connecting member. Accordingly, regarding the structure of the rotor support device, assembly and disassembly are facilitated and maintenance is facilitated.

Description

Technical Field

[0001] The present invention relates to a rotor support device for supporting a rotor that generates vertical thrust. Background Technology

[0002] U.S. Patent Application Publication No. 2020 / 0385130 discloses a vertical takeoff and landing (VTOL) aircraft that generates vertical thrust through multiple rotors. VTOL aircraft are commonly referred to as VTOL aircraft. The VTOL aircraft in U.S. Patent Application Publication No. 2020 / 0385130 has two rotors on each side of the fuselage. The first rotor is mounted on a first support member extending forward of the canard. The second rotor is mounted on a second support member extending from the canard to the aft wing. Summary of the Invention

[0003] The structure supporting the rotor is preferably easy to assemble and disassemble and easy to maintain.

[0004] The purpose of this invention is to solve the above-mentioned technical problems.

[0005] The first invention provides a rotor support device installed in an aircraft for supporting a rotor that generates vertical thrust. The rotor support device includes a mount, a connecting member, and a reinforcing member. The mount supports the rotor and has an outwardly protruding joint. The connecting member extends along the protruding direction of the joint and is detachably connected to the joint. The reinforcing member is detachably connected to the joint and the connecting member to strengthen the connection between them. The connecting member forms a protrusion by forming a notch at its end connected to the joint. The protrusion overlaps with the outer peripheral surface of the joint in a first direction and is detachably connected to the joint, wherein the first direction is orthogonal to the protruding direction of the joint. The reinforcing member overlaps with the outer peripheral surface of the joint and the connecting member in a second direction and is detachably connected to the joint and the connecting member, wherein the second direction is opposite to the first direction.

[0006] The second invention provides a rotor support device installed in an aircraft for supporting a rotor that generates vertical thrust. The rotor support device includes a support member, a connecting member, and a reinforcing member. The support member supports the rotor and has an outwardly protruding connecting portion. The connecting member extends along the protruding direction of the connecting portion and is detachably connected to the connecting portion. The reinforcing member is detachably connected to the connecting portion and the connecting member to strengthen the connection between them. The connecting member forms a protrusion by forming a notch at the end connected to the connecting portion. The protrusion overlaps with the connecting portion from a first direction and is detachably connected to the connecting portion, wherein the first direction is orthogonal to the protruding direction of the connecting portion. The reinforcing member overlaps with the connecting portion and the connecting member from a second direction and is detachably connected to the connecting portion and the connecting member, wherein the second direction is opposite to the first direction.

[0007] According to the present invention, the structure supporting the rotor is easy to assemble and disassemble and easy to maintain.

[0008] The above-described objectives, features, and advantages should be readily understood from the following description of the embodiments with reference to the accompanying drawings. Attached Figure Description

[0009] Figure 1 This is an exterior view of the VTOL aircraft.

[0010] Figure 2 This is the left view of the cantilever.

[0011] Figure 3 This is a top view of the cantilever.

[0012] Figure 4 yes Figure 2 Enlarged view of the first support member, VTOL rotor and its surrounding structure shown.

[0013] Figure 5 This is an exploded perspective view of the connection between the first support member and the intermediate tube. Detailed Implementation

[0014] [Structure of 1VTOL Aircraft 10] Figure 1 This is an external view of the VTOL aircraft 10. The VTOL aircraft 10 is, for example, an electric vertical takeoff and landing aircraft, also known as an eVTOL aircraft. The VTOL aircraft 10 has a fuselage 12, a canard 14, a rear wing 16, two booms 18, eight VTOL rotors 20 and two cruise rotors 22.

[0015] The canard 14 is connected to the front of the fuselage 12. The canard 14 has a left wing 14L and a right wing 14R. The rear wing 16 is connected to the rear of the fuselage 12. The rear wing 16 has a left wing 16L and a right wing 16R. The canard 14 and rear wing 16 generate lift as the VTOL aircraft 10 moves forward.

[0016] The two cantilever arms 18 are rotor support devices that support the four VTOL rotors 20. Cantilever arm 18R is located on the right side of the fuselage 12. Cantilever arm 18L is located on the left side of the fuselage 12. Each cantilever arm 18 extends in the fore-and-aft direction.

[0017] Four VTOL rotors 20 are arranged sequentially from front to back on cantilever 18L. Similarly, four VTOL rotors 20 are arranged sequentially from front to back on cantilever 18R. Each VTOL rotor 20 generates thrust in the vertical direction.

[0018] Two cruise rotors 22 are arranged side to side on the rear wing 16. Each cruise rotor 22 generates horizontal thrust.

[0019] [Structure of 2 cantilever 18 (rotor support device)] Figure 2 This is the left view of the 18L cantilever. Figure 3 This is a top view of the 18L cantilever. Furthermore, the above description refers to... Figure 1 This indicates the cantilever 18L with the fairing installed. On the other hand, Figure 2 and Figure 3 This indicates the cantilever 18L with the fairing removed. Additionally, Figure 2 and Figure 3 This indicates the cantilever 18L with four VTOL rotors 20 installed. Furthermore, the structure of cantilever 18R is identical to that of cantilever 18L, except that it is reversed left to right. Therefore, this specification will describe cantilever 18L, omitting the description of cantilever 18R.

[0020] The cantilever 18L has four support members 24 and three connecting pipes 26 (connecting components). The four support members 24 include a front support member 24a, a first support member 24b, a second support member 24c, and a rear support member 24d. The three connecting pipes 26 include a front pipe 26a, a middle pipe 26b, and a rear pipe 26c. They are connected from front to back in the following order: front support member 24a, front pipe 26a, first support member 24b, middle pipe 26b, second support member 24c, rear pipe 26c, and rear support member 24d.

[0021] like Figure 3As shown, viewed from above, the front tube 26a extends in a direction rotated clockwise by a predetermined angle relative to the front-rear direction. The front tube 26a is connected to the front support member 24a and the first support member 24b. The front end of the front tube 26a is permanently connected to the front support member 24a. The rear end of the front tube 26a is permanently connected to the first support member 24b. Additionally, a left wing 14L (see reference) of the front wing 14 is connected to the front tube 26a. Figure 1 ).

[0022] The intermediate tube 26b extends in the front-to-back direction. The intermediate tube 26b is connected to the first support member 24b and the second support member 24c. The front end of the intermediate tube 26b is detachably connected to the first support member 24b. The rear end of the intermediate tube 26b is detachably connected to the second support member 24c. The connection structure between the support members 24 (the first support member 24b and the second support member 24c) and the intermediate tube 26b will be described later.

[0023] like Figure 3 As shown, viewed from above, the rear tube 26c extends in a direction rotated counterclockwise by a predetermined angle relative to the longitudinal direction. The rear tube 26c is connected to the second support member 24c and the rear support member 24d. The front end of the rear tube 26c is permanently connected to the second support member 24c. The rear end of the rear tube 26c is permanently connected to the rear support member 24d. Additionally, the left wing 16L of the rear wing 16 (see reference) is connected to the rear tube 26c. Figure 1 ).

[0024] As described above, the four support members 24 and the three connecting pipes 26 are alternately connected from front to rear. Furthermore, the front pipe 26a is supported by the left wing 14L of the front wing 14, and the rear pipe 26c is supported by the left wing 16L of the rear wing 16. Accordingly, the cantilever 18L is fixed to the left side of the fuselage 12.

[0025] [3 Connection structure between the first support member 24b and the intermediate tube 26b] Figure 4 yes Figure 2 The diagram shows an enlarged view of the first support member 24b, the VTOL rotor 20, and their surrounding structure. The first support member 24b supports the VTOL rotor 20. The VTOL rotor 20 includes a motor 30, a heat sink 32, a gearbox 34, a shaft 36, a propeller 38, a variable pitch mechanism 40, a first actuator 44a, and a second actuator 44b. The heat sink 32 is mounted on the outer periphery of the motor 30. The gearbox 34 is mounted on the upper end of the motor 30. The shaft 36 extends upward from the gearbox 34. The propeller 38 is mounted on the upper end of the shaft 36.

[0026] The variable pitch mechanism 40 adjusts the pitch angle of the blades 42 of the propeller 38. The variable pitch mechanism 40 has a moving part 46. The moving part 46 is capable of moving up and down along the shaft 36. The moving part 46 is connected to a linkage mechanism (not shown). The linkage mechanism responds to the movement of the moving part 46 by changing the pitch angle of each blade 42. Figure 4 As shown, the moving part 46 extends along the extension direction of the cantilever 18L with the shaft 36 as the center. A first actuator 44a is connected to the front end of the moving part 46. A second actuator 44b is connected to the rear end of the moving part 46.

[0027] A receiving hole 50, a first gap 52, and a second gap 54 are formed in the first support member 24b. Furthermore, a front connecting portion 56 is formed at the front end of the first support member 24b, and a rear connecting portion 58 is formed at the rear end of the first support member 24b. The receiving hole 50, the first gap 52, and the second gap 54 extend through each other in the vertical direction.

[0028] The receiving hole 50 is located approximately at the center of the first support member 24b in the front-rear direction. The VTOL rotor 20 is housed within the receiving hole 50. A first gap 52 is located between the receiving hole 50 and the front connecting portion 56. A first actuator support portion 48a for supporting the first actuator 44a is formed inside the first gap 52. A second gap 54 is located between the receiving hole 50 and the rear connecting portion 58. A second actuator support portion 48b for supporting the second actuator 44b is formed inside the second gap 54.

[0029] The front connecting portion 56 protrudes towards the front tube 26a located at the front. The front connecting portion 56 extends in a direction that has been rotated clockwise by a predetermined angle relative to the front-rear direction. The front connecting portion 56 is inserted into the rear end of the front tube 26a. The front connecting portion 56 is permanently connected to the rear end of the front tube 26a.

[0030] The rear joint 58 protrudes towards the rear of the intermediate tube 26b. The rear joint 58 extends in the front-to-back direction. The rear joint 58 connects to the front end of the intermediate tube 26b and the reinforcing member 60. The upper part of the rear joint 58 is rounded (e.g., elliptical) when viewed from the rear. The lower part of the rear joint 58 is a rounded rectangle when viewed from the rear.

[0031] Figure 5This is an exploded perspective view of the connection between the first support member 24b and the intermediate tube 26b. The cross-sectional shape of the intermediate tube 26b is the same as that of the rear joint 58. That is, the upper part of the intermediate tube 26b is a rounded shape (e.g., an ellipse) when viewed from the front. The lower part of the intermediate tube 26b is a rounded rectangle when viewed from the front. A notch 62 is formed at the lower part of the front end of the intermediate tube 26b. Accordingly, a protrusion 64 is formed at the upper part of the front end of the intermediate tube 26b.

[0032] The protrusion 64 protrudes towards the rear engagement portion 58 of the first support member 24b. That is, the protrusion 64 protrudes forward. The inner circumferential shape of the protrusion 64 is the same as the outer circumferential shape of the upper part of the rear engagement portion 58. The maximum width (left-right width) of the protrusion 64 is less than the width (left-right width) of the notch 62. The length (front-back length) of the protrusion 64 is less than the length (protrusion direction length) of the rear engagement portion 58.

[0033] like Figure 5 As indicated by arrow A, the protrusion 64 of the intermediate tube 26b overlaps with the rear connecting portion 58 from above (in the first direction). Accordingly, the protrusion 64 abuts against the upper outer peripheral surface of the rear connecting portion 58. The protrusion 64 and the rear connecting portion 58 are fastened together by multiple fastening components such as bolts. Thus, the protrusion 64 is detachably connected to the rear connecting portion 58. With the protrusion 64 connected to the rear connecting portion 58, the lower part of the rear connecting portion 58 is positioned at the notch 62.

[0034] The reinforcing member 60 is a curved plate member. The cross-sectional shape of the reinforcing member 60 is the same as the cross-sectional shape of the lower part of the rear joint 58 and the lower part of the intermediate tube 26b. However, the reinforcing member 60 is slightly larger than the lower part of the rear joint 58 and the lower part of the intermediate tube 26b. That is, the width (left-right width) of the reinforcing member 60 is slightly wider than the width (left-right width) of the rear joint 58 and the intermediate tube 26b. The length (front-back length) of the reinforcing member 60 is, for example, about twice the length (protrusion direction length) of the protrusion 64. However, the length of the reinforcing member 60 is not limited to this length. The length of the reinforcing member 60 is only required to overlap the lower part of the rear joint 58 and the lower part of the intermediate tube 26b located at the notch 62 when the rear joint 58 and the protrusion 64 of the intermediate tube 26b are fastened.

[0035] like Figure 5As indicated by arrow B, the reinforcing member 60 overlaps with the rear joint 58 and the intermediate tube 26b from below (in the second direction). Accordingly, the reinforcing member 60 abuts against the lower outer peripheral surface of the rear joint 58 and the lower outer peripheral surface of the intermediate tube 26b. The reinforcing member 60 and the rear joint 58 are fastened together by multiple fastening components such as bolts. Furthermore, the reinforcing member 60 and the intermediate tube 26b are fastened together by multiple fastening components such as bolts. Thus, the reinforcing member 60 is detachably connected to the rear joint 58 and the intermediate tube 26b.

[0036] As described above, the front end of the intermediate tube 26b is connected to the rear joint 58 of the first support member 24b. On the other hand, except for the reversal of front and back, the structure of the rear end of the intermediate tube 26b is the same as the structure of the front end of the intermediate tube 26b. Furthermore, except for the reversal of front and back, the structure of the second support member 24c is the same as the structure of the first support member 24b. Therefore, the rear end of the intermediate tube 26b and the front joint (not shown) of the second support member 24c are connected in the same manner as the front end of the intermediate tube 26b and the rear joint 58 of the first support member 24b.

[0037] [Assembly and maintenance of 4-cantilever 18L] The assembly process of the cantilever 18L is performed, for example, in the following order. First, the front tube 26a, which is connected to the front support member 24a and the first support member 24b, is connected to the front wing 14. Additionally, the rear tube 26c, which is connected to the second support member 24c and the rear support member 24d, is connected to the rear wing 16. Thus, the front tube 26a and the rear tube 26c are pre-connected to the fuselage. Therefore, the first support member 24b and the second support member 24c are positioned respectively.

[0038] In this state, the protrusion 64 at the front end of the intermediate tube 26b overlaps from above with the rear joint 58 of the first support member 24b. The intermediate tube 26b and the first support member 24b are fastened by multiple fastening members. Next, the reinforcing member 60 overlaps from below with the rear joint 58 of the first support member 24b and the intermediate tube 26b. The reinforcing member 60 and the first support member 24b are fastened by multiple fastening members. Additionally, the reinforcing member 60 and the intermediate tube 26b are fastened by multiple fastening members. Accordingly, the intermediate tube 26b is connected to the first support member 24b. Similarly, the intermediate tube 26b is also connected to the second support member 24c. Thus, the basic portion of the cantilever 18L is completed.

[0039] During maintenance of the cantilever 18L, the cantilever 18L is disassembled. The disassembly process of the cantilever 18L is performed in the reverse order of the assembly process.

[0040] [5 Other methods] The protrusion 64 of the intermediate tube 26b can also overlap with the rear joint 58 from a direction other than above (e.g., to the left). Similarly, the reinforcing member 60 can also overlap with the rear joint 58 and the intermediate tube 26b from a direction other than below (e.g., to the right). However, for the following reasons, the protrusion 64 of the intermediate tube 26b preferably overlaps with the rear joint 58 from above. That is, during the assembly and disassembly of the reinforcing member 60, the intermediate tube 26b is supported by the first support member 24b and the second support member 24c. Therefore, according to the above structure, during the assembly and disassembly of the reinforcing member 60, no device for supporting the intermediate tube 26b is required.

[0041] The number of support members 24 may not be four. Similarly, the number of connecting pipes 26 may not be three. For example, the number of support members 24 may be five, and the number of connecting pipes 26 may be four. Furthermore, the shape of the cantilever 18 may not be a shape extending from the front end to the rear end. For example, the shape of the cantilever 18 may be annular. In any embodiment, the connecting pipes 26 not fixed to the fuselage may be detached from the support members 24.

[0042] [Effects of the 6 Implementation Methods] Suppose that to connect the first support member 24b and the second support member 24c using a conventional pipe, it would be necessary to push the first support member 24b and the second support member 24c apart to insert the pipe. However, the first support member 24b and the second support member 24c are fixed to the machine body respectively. Therefore, it is impossible to push the first support member 24b and the second support member 24c apart.

[0043] In this embodiment, the intermediate tube 26b overlaps with the first support member 24b from above, and the reinforcing member 60 overlaps with both the first support member 24b and the intermediate tube 26b from below, thereby connecting the intermediate tube 26b to the first support member 24b. The intermediate tube 26b and the second support member 24c are also connected in the same way. Furthermore, the intermediate tube 26b can be detached from and assembled with respect to the first support member 24b and the second support member 24c. Additionally, one reinforcing member 60 can be detached from and assembled with respect to the first support member 24b and the intermediate tube 26b. The other reinforcing member 60 can be detached from and assembled with respect to the second support member 24c and the intermediate tube 26b. In this embodiment, it is not necessary to push the first support member 24b and the second support member 24c apart. Therefore, according to this embodiment, the rotor support structure is easy to assemble and disassemble and easy to maintain.

[0044] Furthermore, there are also models capable of pushing the first support member 24b and the second support member 24c apart. In the case of such a model, the connection between the first support member 24b and the intermediate tube 26b can also be performed, for example, according to the following steps.

[0045] Viewed from above, the intermediate tube 26b is positioned in the direction extending from the rear joint portion 58 of the first support member 24b. Furthermore, when viewed from the left, the notch 62 at the front end of the intermediate tube 26b overlaps with the upper part of the first support member 24b. In this state, the intermediate tube 26b moves towards the first support member 24b. Thus, the notch 62 at the front end of the intermediate tube 26b abuts against the upper part of the first support member 24b. Next, the intermediate tube 26b moves downward. Accordingly, the protrusion 64 at the front end of the intermediate tube 26b overlaps with the rear joint portion 58 of the first support member 24b from above. Subsequent steps are the same as described above. Through these steps, the alignment (positioning) of the intermediate tube 26b relative to the first support member 24b becomes easy.

[0046] [7. Inventions obtainable according to the embodiments] The invention described below is an invention that can be mastered based on the above-described embodiments.

[0047] The technical solution of the first invention is a rotor support device (18, 18L, 18R), which is installed on an aircraft (10) to support a rotor (20) that generates vertical thrust. The rotor support device (18, 18L, 18R) has: a support member (24, 24b, 24c) that supports the rotor and has an outwardly protruding connecting portion (56, 58); a connecting member (26, 26b) that extends along the protruding direction of the connecting portion and is detachably connected to the connecting portion; and a reinforcing member (60) that is detachably connected to the connecting portion and the connecting member. To strengthen the connection between the joint and the connecting member, the connecting member forms a protrusion (64) by forming a notch (62) at the end connected to the joint. The protrusion overlaps with the outer peripheral surface of the joint in a first direction and is detachably connected to the joint, wherein the first direction is orthogonal to the protrusion direction of the joint. The strengthening member overlaps with the outer peripheral surface of the joint in a second direction and the connecting member, and is detachably connected to the joint and the connecting member, wherein the second direction is opposite to the first direction.

[0048] Based on the above structure, the structure supporting the rotor is easy to assemble and disassemble, and easy to maintain.

[0049] In the above technical solution, the protrusion may overlap with the outer peripheral surface of the upper connecting part and be detachably connected to the connecting part; the reinforcing member may overlap with the outer peripheral surface of the lower connecting part and the connecting member and be detachably connected to the connecting part and the connecting member.

[0050] Based on the above structure, no device for supporting the connecting components is needed during the assembly and disassembly process of the reinforcing components.

[0051] In the above technical solution, the connecting component can also be a pipe.

[0052] In the above technical solution, the rotor support device may also have a first support member (24b) and a second support member (24c) serving as the support members, and a first reinforcing member and a second reinforcing member serving as the reinforcing member. The first support member supports the first rotor serving as the rotor, and the second support member supports the second rotor serving as the rotor. The connecting member has the notch and the protrusion formed at the first end and the second end, respectively. The first end of the connecting member and the first reinforcing member are fastened to the joint of the first support member, and the second end of the connecting member and the second reinforcing member are fastened to the joint of the second support member.

[0053] In the above technical solution, the rotor support device may also have a second connecting component (26a, 26c) that is permanently connected to the support member and connected to the wing (14, 16) of the aircraft.

[0054] In the above technical solution, the rotor support device may also have fixed support members (24a, 24d), which support rotors different from the rotors and are permanently connected to the second connecting component.

[0055] In the above technical solution, the support member may also have a through gap (52, 54) running vertically.

[0056] In the above technical solution, the rotor support device may also include: actuators (44a, 44b) that change the pitch angle of each blade (42) of the rotor; and actuator support portions (48a, 48b) that support the actuators and are disposed inside the gap.

[0057] The technical solution of the second invention is a rotor support device (18, 18L, 18R) installed on an aircraft (10) to support a rotor (20) that generates vertical thrust. The rotor support device (18, 18L, 18R) includes: support members (24, 24b, 24c) that support the rotor and have outwardly protruding connecting portions (56, 58); connecting members (26, 26b) that extend along the protruding direction of the connecting portions and are detachably connected to the connecting portions; and reinforcing members (60) that are detachably connected to the connecting portions. The connecting member is connected to strengthen the connection between the joint and the connecting member. The connecting member forms a protrusion (64) by forming a notch (62) at the end connected to the joint. The protrusion overlaps with the joint from a first direction and is detachably connected to the joint. The first direction is orthogonal to the protrusion direction of the joint. The reinforcing member overlaps with the joint and the connecting member from a second direction and is detachably connected to the joint and the connecting member. The second direction is opposite to the first direction.

[0058] Furthermore, the present invention is not limited to the above disclosure, and various structures can be adopted without departing from the spirit of the present invention.

Claims

1. A rotor support device (18) disposed in an aircraft (10) for supporting a rotor (20) that generates vertical thrust, characterized in that, It has a support member (24), a connecting member (26), and a reinforcing member (60), wherein, The support member supports the rotor and has outwardly protruding joints (56, 58). The connecting component extends along the protruding direction of the joint and is detachably connected to the joint. The reinforcing component is detachably connected to the joint and the connecting component to strengthen the connection between the joint and the connecting component. The connecting component forms a protrusion (64) by forming a notch (62) at the end that connects to the joint. The protrusion overlaps with the outer peripheral surface of the connecting portion located in the first direction and is detachably connected to the connecting portion, wherein the first direction is orthogonal to the protruding direction of the connecting portion. The reinforcing member overlaps with the outer peripheral surface of the joint located in the second direction and the connecting member and is detachably connected to the joint and the connecting member, wherein the second direction is the opposite direction to the first direction.

2. The rotor support device according to claim 1, characterized in that, The protrusion overlaps with the outer peripheral surface of the upper connecting portion and is detachably connected to the connecting portion. The reinforcing member overlaps with the outer peripheral surface of the lower joint and the connecting member and is detachably connected to the joint and the connecting member.

3. The rotor support device according to claim 1 or 2, characterized in that, The connecting component is a pipe.

4. The rotor support device according to claim 3, characterized in that, have: The first support member (24b) and the second support member (24c) serve as the support members; and The first and second reinforcing components serve as the reinforcing members. The first support member supports the first rotor, which serves as the rotor blade. The second support member supports the second rotor, which serves as the rotor blade. The connecting member has the notch and the protrusion formed at the first end and the second end, respectively. The first end of the connecting member and the first reinforcing member are fastened to the joint of the first support member. The second end of the connecting member and the second reinforcing member are fastened to the joint of the second support member.

5. The rotor support device according to claim 1 or 2, characterized in that, It has a second connecting component (26a, 26c) that is permanently coupled to the support and connected to the wing (14, 16) of the aircraft.

6. The rotor support device according to claim 5, characterized in that, It has fixed support members (24a, 24d) that support a rotor that is different from the rotor and are permanently connected to the second connecting member.

7. The rotor support device according to claim 1 or 2, characterized in that, The support member has a through gap (52, 54) running vertically.

8. A rotor support device, disposed in an aircraft, for supporting a rotor that generates vertical thrust, characterized in that, It has support components, connecting components, and reinforcing components, among which, The support member supports the rotor and has a joint that protrudes outward; The connecting component extends along the protruding direction of the joint and is detachably connected to the joint. The reinforcing component is detachably connected to the joint and the connecting component to strengthen the connection between the joint and the connecting component. The connecting component forms a protrusion by forming a notch at the end that connects to the joint. The protrusion overlaps with the connecting portion from a first direction and is detachably connected to the connecting portion, wherein the first direction is orthogonal to the protruding direction of the connecting portion. The reinforcing member overlaps with the joint and the connecting member from a second direction and is detachably connected to the joint and the connecting member, wherein the second direction is the opposite direction to the first direction.

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