Rotor pitch structure and electrically powered aircraft

Abstract

The utility model provides a kind of rotor variable pitch structure and electric aircraft, it is related to the technical field of electric aircraft.Rotor variable pitch structure includes hub, rotor blade and variable pitch component;Hub includes hub base and hub upper cover, and hub upper cover is detachably installed on hub base, and the root of rotor blade is rotatably inserted in paddle mounting hole;Variable pitch component includes pitch adjusting piece, blade support and pitch transmission part;Blade support is arranged on hub base, and the first side of blade support is rotatably connected with rotor blade, and the second side is slidably connected with pitch adjusting piece, so that pitch adjusting piece can move up and down along blade support vertically;Pitch adjusting piece moves up and down along blade support vertically, and then drives pitch transmission part to rotate, finally drives rotor blade to rotate around its axis.The technical effect that electric aircraft using outer rotor electronic can realize rotor variable pitch is achieved.

Description

Technical Field

[0001] This utility model relates to the field of electric aircraft technology, and more specifically, to a rotor variable pitch structure and an electric aircraft. Background Technology

[0002] Electric vertical takeoff and landing (EVTOL) aircraft are capable of vertical takeoff and landing, using electric motors to drive rotors for power and lift. These motors include internal rotor motors and external rotor motors, with the rotor of the external rotor motor located on the outside of the motor. Aircraft rotors include fixed-pitch rotors and variable-pitch rotors. Fixed-pitch rotors maintain a constant pitch angle during flight, resulting in higher efficiency under certain operating conditions. However, because of the constant pitch angle, rotors cannot adapt to a wide range of incoming airflow velocities. In some conditions, extensive airflow separation occurs on the rotor surface, leading to reduced rotor efficiency. Variable-pitch rotors, on the other hand, can adjust the pitch according to changes in incoming airflow velocity, thus ensuring high efficiency under various flight conditions.

[0003] Traditional variable-pitch rotors are mounted on aircraft engines, which are connected to the rotor via a central drive shaft. The pitch control mechanism uses a constant-speed governor to control the pitch, matching the pitch angle with the engine speed. Similarly, the variable-pitch rotor of a traditional engine uses a constant-speed governor to control the pitch, matching the pitch angle with the engine speed. However, the flight control of electric vertical takeoff and landing (EVTOL) aircraft is far more complex than that of traditional fixed-wing aircraft, requiring real-time and precise pitch control to provide a suitable flight attitude. Traditional constant-speed governor pitch control methods cannot meet the needs of electric aircraft.

[0004] Traditional rotor structures use an engine that outputs power through a central drive shaft to rotate the rotor, with pitch control achieved via a rocker arm. However, for external rotor motors in electric aircraft, the motor connects to the rotor hub via an external rotor, and the rotation of the external rotor drives the rotor to generate lift. Traditional rotor structures are not compatible with the mounting structure of external rotor motors. Utility Model Content

[0005] The purpose of this invention is to provide a rotor pitch control structure and an electric aircraft to alleviate the technical problem of difficult rotor pitch control in existing electric aircraft using external rotor electronics.

[0006] In a first aspect, the present invention provides a rotor pitch-changing structure, including a rotor hub, rotor blades, and a pitch-changing assembly; The rotor hub includes a rotor hub base and a rotor hub cover. The rotor hub cover is detachably mounted on the rotor hub base. The rotor hub base and the rotor hub cover are provided with opposing mounting slots. The opposing mounting slots are connected to form a rotor blade mounting hole. The root of the rotor blade is rotatably inserted into the rotor blade mounting hole. The pitch control assembly includes a pitch adjustment component, a blade support component, and a pitch transmission component. The blade support is mounted on the rotor hub base. The first side of the blade support is rotatably connected to the rotor blade, and the second side is slidably connected to the pitch adjustment component, so that the pitch adjustment component can move up and down along the longitudinal direction of the blade support. The pitch transmission component is fixed relative to the rotor blade, and the pitch transmission component is rotatably connected to the pitch adjustment component. The pitch adjustment component can be connected to the lifting drive component and can move up and down along the longitudinal direction of the blade support component under the drive of the lifting drive component, thereby driving the pitch transmission component to rotate, and finally driving the rotor blade to rotate around its axis.

[0007] In conjunction with the first aspect, this utility model embodiment provides one possible implementation of the first aspect, wherein a longitudinal guide slide is provided on the second side of the aforementioned blade support member; The circumferential sidewall of the pitch adjustment component is provided with a guide slider that can be adapted to the guide slide.

[0008] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein the circumferential sidewall of the above-mentioned pitch adjustment member is rotatably provided with a pitch-changing swing arm that can be pivotally connected to the pitch transmission member. The pitch adjustment component has a connecting pin hole on its circumferential sidewall for mounting the pitch control arm, and the pitch control arm is mounted on the pitch adjustment component via a pitch control pin.

[0009] In conjunction with the first aspect, this utility model embodiment provides one possible implementation of the first aspect, wherein the aforementioned pitch transmission member has an offset rocker arm; The offset rocker arm is pivotally connected to the variable pitch swing arm, and when the pitch adjustment component moves up and down, it can drive the offset rocker arm to swing up and down through the variable pitch swing arm.

[0010] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein a first bearing is sleeved on the rotor blade, and a first bearing fixing seat for installing the first bearing is provided in the blade mounting hole.

[0011] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein the number of the first bearings is two, and the first bearing fixing seats are provided at both ends of the blade mounting hole; The root of the rotor blade is provided with a bearing limiting member for limiting the first bearing, and the two first bearings are located between the two bearing limiting members.

[0012] In conjunction with the first aspect, this utility model embodiment provides one possible implementation of the first aspect, wherein the first bearing is a split bearing.

[0013] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein a metal connector is pre-embedded at the root of the rotor blade, and the metal connector is provided with a first threaded hole. The pitch transmission component has a connection hole that matches the first threaded hole, and the metal connector is connected to the pitch transmission component by bolts.

[0014] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein the first side of the blade support is provided with a second bearing fixing seat for mounting the blade pitch transmission component; The pitch transmission component is fitted with a second bearing, which is located inside the second bearing mounting seat.

[0015] In conjunction with the first aspect, this utility model embodiment provides one possible implementation of the first aspect, wherein the above-mentioned lifting drive component is a variable pitch servo motor; The output end of the lifting drive component is provided with a pitch control rod, and the end of the pitch control rod away from the lifting drive component is connected to the pitch adjustment component. A fourth bearing is provided between the pitch control rod and the pitch adjustment component.

[0016] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein the pitch adjustment member has a connecting channel in the middle for connecting with the variable pitch drive rod, and the interior of the connecting channel has an outer ring support seat for supporting the outer ring of the fourth bearing; The outer wall of the variable pitch drive rod is provided with an inner ring support seat for supporting the inner ring of the fourth bearing; The top of the connecting channel is threaded with an end cap, which can press the outer ring of the fourth bearing. The variable pitch drive rod is threaded with a clamping ring, which can press the inner ring of the fourth bearing.

[0017] Secondly, this utility model embodiment provides an electric aircraft, including the rotor pitch structure. Beneficial effects: This utility model embodiment provides a rotor pitch-changing structure, including a rotor hub, rotor blades, and a pitch-changing assembly. The rotor hub includes a hub base and a hub cover, with the hub cover detachably mounted on the hub base. Both the hub base and hub cover have opposing mounting slots, which connect to form blade mounting holes. The root of the rotor blade is rotatably inserted into the blade mounting hole. The pitch-changing assembly includes a pitch adjustment component, a blade support component, and a pitch transmission component. The blade support component is mounted on the hub base, with a first side rotatably connected to the rotor blade and a second side slidably connected to the pitch adjustment component, allowing the pitch adjustment component to move vertically along the longitudinal direction of the blade support component. The pitch transmission component is fixed relative to the rotor blade and rotatably connected to the pitch adjustment component. The pitch adjustment component can be connected to a lifting drive component and can move vertically along the longitudinal direction of the blade support component under the drive of the lifting drive component, thereby driving the pitch transmission component to rotate, ultimately causing the rotor blade to rotate around its axis.

[0018] Specifically, when pitch adjustment is needed, the control center of the electric aircraft sends a command to the lift drive. Upon receiving the command, the lift drive moves the pitch adjustment component up and down. As the pitch adjustment component slides up and down, its guide slider slides within the guide rails on the blade support. This up-and-down movement of the pitch adjustment component then causes the pitch control arm to swing, which in turn causes the pitch transmission component to swing and rotate. The pitch transmission component then drives the rotor blades to rotate, thus achieving the pitch adjustment function. Furthermore, the hub base and hub cover facilitate assembly by workers and allow for easy maintenance by users during later use.

[0019] This utility model provides an electric aircraft, including a rotor pitch-changing structure. The electric aircraft has the advantages described above compared to the prior art, which will not be elaborated further here. Attached Figure Description

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

[0021] Figure 1 A schematic diagram of the rotor pitch-changing structure provided in an embodiment of this utility model; Figure 2 for Figure 1 Sectional view of AA; Figure 3 A schematic diagram of the rotor pitch-changing structure provided in the embodiment of this utility model; Figure 4This is a schematic diagram of the internal structure of the rotor pitch-changing structure provided in an embodiment of the present utility model; Figure 5 This is an internal schematic diagram of the rotor pitch-changing structure provided in an embodiment of the present utility model; Figure 6 A schematic diagram of the rotor hub in the variable pitch structure provided in this embodiment of the utility model; Figure 7 A schematic diagram of the rotor hub base in the rotor pitch structure provided in this embodiment of the utility model; Figure 8 A schematic diagram showing the connection between the rotor blades and the pitch transmission component in the rotor variable pitch structure provided in this embodiment of the utility model. Figure 9 A schematic diagram of the rotor blades in the variable pitch structure provided in this embodiment of the utility model; Figure 10 A schematic diagram of the rotor blades and the first bearing in the rotor variable pitch structure provided in this embodiment of the utility model; Figure 11 A schematic diagram of the pitch transmission component in the rotor variable pitch structure provided in this embodiment of the utility model; Figure 12 A schematic diagram of the pitch adjustment component and pitch drive rod in the rotor pitch control structure provided in this embodiment of the utility model; Figure 13 A cross-sectional view of the pitch adjustment component and the pitch drive rod in the rotor pitch control structure provided in this embodiment of the utility model.

[0022] icon: 10 - External rotor of the motor; 100-Propeller hub; 101-Propeller hub base; 102-Propeller hub cover; 110-Propeller blade mounting hole; 120-First bearing mounting seat; 130-First bolt mounting hole; 140-Bolt connection hole; 200 - Rotor blade; 210 - First threaded hole; 220 - First bearing; 230 - Bearing retainer; 300-Pitch adjustment assembly; 310-Pitch adjustment component; 311-Guide slider; 312-Pitch control arm; 313-Pitch control pin; 314-Connecting channel; 315-Outer ring support; 320-Blade support; 321-Guide slide; 322-Second bearing mounting seat; 323-First side; 324-Second side; 325-Second bolt mounting hole; 330-Pitch transmission component; 331-Connecting hole; 332-Offset rocker arm; 333-Second bearing; 334-Boss; 340-End cap; 400 - Pitch control rod; 410 - Fourth bearing; 420 - Inner ring support; 430 - Pressure ring. Detailed Implementation

[0023] The technical solution of this utility model will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0024] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0025] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0026] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0027] The present invention will now be described in further detail with reference to specific embodiments and accompanying drawings.

[0028] See Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 , Figure 9 , Figure 10 , Figure 11 , Figure 12 and Figure 13 As shown, this embodiment provides a rotor pitch-changing structure, including a rotor hub 100, rotor blades 200, and a pitch-changing assembly 300. The rotor hub 100 includes a hub base 101 and a hub cover 102. The hub cover 102 is detachably mounted on the hub base 101. Both the hub base 101 and the hub cover 102 have opposing mounting slots, which connect to form a blade mounting hole 110. The root of the rotor blade 200 is rotatably inserted into the blade mounting hole 110. The pitch-changing assembly 300 includes a pitch adjustment component 310, a blade support component 320, and a pitch transmission component 330. The blade support component 320 is provided with… On the rotor hub base 101, the first side 323 of the blade support 320 is rotatably connected to the rotor blade 200, and the second side 324 is slidably connected to the pitch adjustment member 310, so that the pitch adjustment member 310 can move up and down along the longitudinal direction of the blade support 320; the pitch transmission member 330 is fixed relative to the rotor blade 200, and the pitch transmission member 330 is rotatably connected to the pitch adjustment member 310; the pitch adjustment member 310 can be connected to the lifting drive member, and can move up and down along the longitudinal direction of the blade support 320 under the drive of the lifting drive member, thereby driving the pitch transmission member 330 to rotate, and finally driving the rotor blade 200 to rotate around its axis.

[0029] Specifically, when pitch adjustment is required, the control center of the electric aircraft sends a command to the lift drive. After receiving the pitch adjustment command, the lift drive can drive the pitch adjustment component 310 to move up and down. When the pitch adjustment component 310 slides up and down, its guide slider 311 slides within the guide rail 321 on the blade support component 320. Then, the up and down movement of the pitch adjustment component 310 can drive the pitch adjustment arm 312 to swing, thereby driving the pitch transmission component 330 to swing and rotate. The pitch transmission component 330 can drive the rotor blade 200 to rotate, thus realizing the pitch adjustment function. In addition, the design of the hub base 101 and the hub cover 102 facilitates assembly by workers and makes it easier for users to maintain during later use.

[0030] It should be noted that the propeller hub 100 includes a propeller hub base 101 and a propeller hub cover 102. The propeller hub cover 102 is detachably mounted on the propeller hub base 101. Specifically, bolt connection holes 140 are provided on the propeller hub base 101 and the propeller hub cover 102. The propeller hub base 101 and the propeller hub cover 102 are connected by bolts. This design allows staff and users to easily remove the propeller hub cover 102 to inspect the internal condition of the equipment, thereby improving maintenance efficiency.

[0031] The rotor hub 100 has multiple first bolt mounting holes 130 on its inner bottom plate. The rotor hub 100 is connected to the outer rotor 10 of the aircraft's motor below via bolts passing through these holes. Furthermore, the blade support 320 has multiple second bolt mounting holes 325 on its bottom. The positions of these second bolt mounting holes 325 correspond to the positions of the first bolt mounting holes 130, allowing the blade support 320, rotor hub 100, and outer rotor 10 to be connected and secured with bolts. Each blade support 320 corresponds one-to-one with a blade mounting hole 110. A pitch transmission component 330 is fixedly connected to the end of the rotor blade 200. The pitch transmission component 330 is rotatably mounted on the blade support 320 and is connected to the pitch adjustment component 310 via a pitch-adjusting arm 312.

[0032] The first side 323 of the blade support 320 is rotatably connected to the rotor blade 200, and the second side 324 is slidably connected to the pitch adjustment member 310. The first side 323 and the second side 324 on the blade support 320 are opposite sides.

[0033] See Figures 1-13 As shown, in the optional embodiment, the second side 324 of the blade support 320 is provided with a longitudinal guide slide 321; the circumferential sidewall of the pitch adjustment member 310 is provided with a guide slider 311 that can be adapted to the guide slide 321.

[0034] Specifically, the guide slider 311 on the circumferential sidewall of the pitch adjustment component 310 is slidably disposed in the guide slide 321. When the lifting drive component drives the pitch adjustment component 310 to move vertically up and down, the guide slider 311 on the circumferential sidewall of the pitch adjustment component 310 can slide in the guide slide 321, thereby enabling the pitch adjustment component 310 to move vertically up and down stably along the guide slide 321.

[0035] See Figures 1-13 As shown, in an optional embodiment, the circumferential sidewall of the pitch adjustment member 310 is rotatably provided with a pitch control arm 312 that can be pivotally connected to the pitch transmission member 330; the circumferential sidewall of the pitch adjustment member 310 is provided with a connecting pin hole for mounting the pitch control arm 312, and the pitch control arm 312 is mounted on the pitch adjustment member 310 through a pitch control pin 313.

[0036] Specifically, when the pitch adjustment component 310 moves vertically up and down, it can drive the pitch pin 313 to move vertically up and down synchronously. When the pitch pin 313 moves vertically up and down, it can drive the pitch swing arm 312 to move vertically up and down. The pitch swing arm 312 can drive the pitch transmission component 330 to rotate, thereby causing the rotor blade 200 to rotate.

[0037] See Figures 1-13As shown, in the optional embodiment, the pitch transmission component 330 has an offset rocker arm 332; the offset rocker arm 332 is pivotally connected to the variable pitch swing arm 312, and when the pitch adjustment component 310 moves up and down, the offset rocker arm 332 can be driven to swing up and down through the variable pitch swing arm 312.

[0038] Specifically, the pitch transmission component 330 has an offset rocker arm 332. Therefore, when the variable pitch rocker arm 312 swings up and down, it can drive the offset rocker arm 332 to swing up and down. At this time, the swinging of the offset rocker arm 332 can drive the pitch transmission component 330 to rotate. The rotation of the pitch transmission component 330 can drive the rotor blade 200 to rotate, thereby realizing the variable pitch function.

[0039] It should be noted that the pitch adjustment component 310 can adopt a disc-shaped structure, and the pitch adjustment component 310 is provided with a first pin hole for connecting with the guide slider 311 and a second pin hole for connecting with the variable pitch pin 313.

[0040] See Figures 1-13 As shown, in an optional embodiment, a first bearing 220 is fitted onto the rotor blade 200, and a first bearing mounting seat 120 for mounting the first bearing 220 is provided in the blade mounting hole 110.

[0041] Specifically, the rotor blade 200 is inserted into the blade mounting hole 110 of the rotor hub 100, and the first bearing 220 on the rotor blade 200 is mounted on the first bearing fixing seat 120 in the blade mounting hole 110, so that the rotor blade 200 can rotate relative to the rotor hub 100.

[0042] See Figures 1-13 As shown, in the optional scheme of this embodiment, there are two first bearings 220, and first bearing fixing seats 120 are provided at both ends of the blade mounting hole 110; a bearing limiting member 230 for limiting the first bearings 220 is provided at the root of the rotor blade 200, and the two first bearings 220 are located between the two bearing limiting members 230.

[0043] Specifically, two first bearings 220 are provided at the root of the rotor blade 200, and first bearing mounting seats 120 are provided at both ends of the blade mounting hole 110. With this arrangement, the two first bearings 220 at the root of the rotor blade 200 can be installed in the first bearing mounting seats 120 respectively.

[0044] Furthermore, a bearing limiting member 230 is provided at the root of the rotor blade 200, and two first bearings 220 are located between the two bearing limiting members 230. When the rotor blade 200 is installed in the blade mounting hole 110 of the rotor hub 100, the bearing limiting member 230 can limit the first bearing 220, so that the first bearing 220 is always located on the first bearing fixing seat 120, and the first bearing 220 is prevented from moving axially along the root of the rotor blade 200.

[0045] Among them, the bearing limiting component 230 can be a limiting convex ring.

[0046] See Figures 1-13 As shown, in the optional scheme of this embodiment, the first bearing 220 is a split bearing.

[0047] Specifically, the first bearing 220 is a split bearing. When maintenance and repair of the electric aircraft are required, the staff can remove the hub cover 102 and then remove the split bearing. With this setting, the first bearing 220 can be maintained without disassembling the rotor blades 200.

[0048] See Figures 1-13 As shown, in the optional scheme of this embodiment, a metal connector is pre-embedded at the root of the rotor blade 200, and a first threaded hole 210 is provided on the metal connector; a connecting hole 331 adapted to the first threaded hole 210 is provided on the pitch transmission component 330, and the metal connector is connected to the pitch transmission component 330 by bolts.

[0049] Specifically, during the production of rotor blade 200, a metal connector is pre-embedded at its root. The metal connector has a first threaded hole 210, and the pitch transmission component 330 has a connecting hole 331. The bolt passes through the connecting hole 331 and is tightened into the first threaded hole 210, thereby fixing the rotor blade 200 and the pitch transmission component 330 together.

[0050] See Figures 1-13 As shown, in an optional embodiment, the first side 323 of the blade support 320 is provided with a second bearing mounting seat 322 for mounting the pitch transmission component 330; the end of the pitch transmission component 330 away from the rotor blade 200 has a boss 334, and a second bearing 333 is sleeved on the boss 334. The second bearing 333 is sleeved on the pitch transmission component 330 and is disposed in the second bearing mounting seat 322.

[0051] Specifically, the second bearing mounting seat 322 on the blade support 320 and the first bearing mounting seat 120 in the blade mounting hole 110 work together to support the rotor blade 200, reduce the friction between the rotor blade 200 and the rotor hub 100, and ensure that the rotor blade 200 can work normally for a long time.

[0052] The first bearing 220 and the second bearing 333 can be radial bearings, which are used to bear the radial load of the blades. In addition, those skilled in the art can choose the type of the first bearing 220 and the second bearing 333 according to the implementation requirements.

[0053] See Figures 1-13 As shown, in the optional scheme of this embodiment, the lifting drive is a variable pitch servo; the output end of the lifting drive is provided with a variable pitch drive rod 400, the end of the variable pitch drive rod 400 away from the lifting drive is connected to the pitch adjustment component 310, and a fourth bearing 410 is provided between the variable pitch drive rod 400 and the pitch adjustment component 310.

[0054] Specifically, the pitch adjustment component 310 is driven by the lifting drive component, which is a variable pitch servo, specifically a linear servo. The output end of the lifting drive component is equipped with a variable pitch drive rod 400. The end of the variable pitch drive rod 400 away from the linear servo is connected to the pitch adjustment component 310. When the linear servo is working, it can drive the variable pitch drive rod 400 to move up and down. The variable pitch drive rod 400 can drive the pitch adjustment component 310 to move up and down. The up and down movement of the pitch adjustment component 310 can drive the variable pitch swing arm 312 on it to swing. The swing of the variable pitch swing arm 312 can drive the pitch transmission component 330 to rotate. The rotation of the pitch transmission component 330 can drive the rotor blade 200 to rotate, thereby realizing the variable pitch function.

[0055] See Figures 1-13 As shown, in an optional embodiment, the pitch adjustment member 310 has a connecting channel 314 in the middle for connecting with the variable pitch drive rod 400. The interior of the connecting channel 314 has an outer ring support 315 for supporting the outer ring of the fourth bearing 410. The outer wall of the variable pitch drive rod 400 is provided with an inner ring support 420 for supporting the inner ring of the fourth bearing 410. The top of the connecting channel 314 is threaded with an end cap 340, which can press the outer ring of the fourth bearing 410. A clamping ring 430 is threaded on the variable pitch drive rod 400, which can press the inner ring of the fourth bearing 410.

[0056] Specifically, the pitch adjustment component 310 has a connecting channel 314 in its middle for connecting with the pitch drive rod 100. The connecting channel 314 has an outer ring support 315 for supporting the outer ring of the fourth bearing 410. The outer wall of the pitch drive rod 400 has an inner ring support 420 for supporting the inner ring of the fourth bearing 410. An end cap 340 is threaded into the connecting channel 314, and the end cap 340 can press against the outer ring of the fourth bearing 410. A clamping ring 430 is threaded onto the pitch drive rod 400, and the clamping ring 430 can press against the inner ring of the fourth bearing 410. This arrangement connects the pitch adjustment component 310 and the pitch drive rod 400 together.

[0057] In addition, the fourth bearing 410 can be a tapered roller bearing. The pitch drive rod 400 and the pitch adjustment component 310 are connected by the tapered roller bearing. The tapered roller bearing is used to transmit the up and down movement of the pitch drive rod 400 to the pitch adjustment component 310. By setting the bearing, the pitch drive rod 400 on the drive assembly can rotate relative to the pitch adjustment component 310. Thus, the pitch adjustment component 310 and the drive assembly can be installed on the outer rotor 10 and inner stator of the aircraft power motor, respectively. There is no need to set the pitch adjustment component 310 outside the aircraft power motor, which reduces space occupation and improves the integration of the overall equipment.

[0058] This embodiment provides an electric aircraft, including a rotor pitch control structure.

[0059] Specifically, the electric aircraft provided in this embodiment has the advantages of the aforementioned rotor pitch structure compared to the prior art, which will not be elaborated here.

[0060] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model.

Claims

1. A rotor variable pitch structure, characterized in that, include: The rotor hub (100), rotor blades (200), and pitch control assembly (300); The rotor hub (100) includes a rotor hub base (101) and a rotor hub cover (102). The rotor hub cover (102) is detachably mounted on the rotor hub base (101). The rotor hub base (101) and the rotor hub cover (102) are provided with opposing mounting slots. The opposing mounting slots are connected to form a blade mounting hole (110). The root of the rotor blade (200) is rotatably inserted into the blade mounting hole (110). The pitch control assembly (300) includes a pitch adjustment component (310), a blade support component (320), and a pitch transmission component (330). The blade support (320) is disposed on the hub base (101). The first side (323) of the blade support (320) is rotatably connected to the rotor blade (200), and the second side (324) is slidably connected to the pitch adjustment member (310) so that the pitch adjustment member (310) can move up and down along the longitudinal direction of the blade support (320). The pitch transmission component (330) is fixed relative to the rotor blade (200), and the pitch transmission component (330) is rotatably connected to the pitch adjustment component (310); The pitch adjustment component (310) can be connected to the lifting drive component and can move up and down along the longitudinal direction of the blade support component (320) under the drive of the lifting drive component, thereby driving the pitch transmission component (330) to rotate, and finally driving the rotor blade (200) to rotate around its axis.

2. The rotor variable pitch structure according to claim 1, characterized in that, The blade support (320) has a longitudinal guide slide (321) on its second side (324). The circumferential sidewall of the pitch adjustment member (310) is provided with a guide slider (311) that can be adapted to the guide slide (321).

3. The rotor pitch-changing structure according to claim 2, characterized in that, The pitch adjustment member (310) is rotatably provided with a pitch control arm (312) that can be pivotally connected to the pitch transmission member (330). The pitch adjustment component (310) has a connecting pin hole on its circumferential sidewall for mounting the pitch control arm (312), and the pitch control arm (312) is mounted on the pitch adjustment component (310) via a pitch control pin (313).

4. The rotor pitch-changing structure according to claim 3, characterized in that, The pitch transmission component (330) has an offset rocker arm (332); The offset rocker arm (332) is pivotally connected to the variable pitch swing arm (312). When the pitch adjustment member (310) moves up and down, it can drive the offset rocker arm (332) to swing up and down through the variable pitch swing arm (312).

5. The rotor pitch-changing structure according to claim 1, characterized in that, A first bearing (220) is fitted on the rotor blade (200), and a first bearing mounting seat (120) for mounting the first bearing (220) is provided in the blade mounting hole (110).

6. The rotor pitch-changing structure according to claim 5, characterized in that, There are two first bearings (220), and the first bearing fixing seats (120) are provided at both ends of the blade mounting hole (110). The root of the rotor blade (200) is provided with a bearing limiting member (230) for limiting the first bearing (220), and the two first bearings (220) are located between the two bearing limiting members (230).

7. The rotor pitch-changing structure according to claim 5, characterized in that, The first bearing (220) is a split bearing.

8. The rotor pitch-changing structure according to claim 1, characterized in that, A metal connector is pre-embedded at the root of the rotor blade (200), and a first threaded hole (210) is provided on the metal connector. The pitch transmission component (330) has a connection hole (331) that is adapted to the first threaded hole (210), and the metal connector is connected to the pitch transmission component (330) by bolts.

9. The rotor pitch-changing structure according to claim 8, characterized in that, The first side (323) of the blade support (320) is provided with a second bearing fixing seat (322) for mounting the pitch transmission component (330); The pitch transmission component (330) is fitted with a second bearing (333), which is located inside the second bearing mounting base (322).

10. The rotor pitch-changing structure according to any one of claims 1-9, characterized in that, The lifting drive component is a variable pitch servo motor; The output end of the lifting drive component is provided with a pitch drive rod (400). The end of the pitch drive rod (400) away from the lifting drive component is connected to the pitch adjustment component (310). A fourth bearing (410) is provided between the pitch drive rod (400) and the pitch adjustment component (310).

11. The rotor pitch-changing structure according to claim 10, characterized in that, The pitch adjustment component (310) has a connecting channel (314) in the middle for connecting with the variable pitch drive rod (400), and the interior of the connecting channel (314) has an outer ring support seat (315) for supporting the outer ring of the fourth bearing (410). The outer wall of the variable pitch drive rod (400) is provided with an inner ring support seat (420) for supporting the inner ring of the fourth bearing (410). The top of the connecting channel (314) is threaded with an end cap (340), which can press the outer ring of the fourth bearing (410). The variable pitch drive rod (400) is threaded with a clamping ring (430), which can press the inner ring of the fourth bearing (410).

12. An electric aircraft, characterized in that, Includes the rotor pitch structure as described in any one of claims 1-11.

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