Variable-pitch rotor system and electric aircraft

Abstract

The invention provides a variable-pitch rotor system and an electric aircraft, and relates to the technical field of electric aircrafts. Comprising a propeller hub, rotor blades and a variable pitch assembly. The roots of the rotor blades penetrate through the side wall of the propeller hub and are rotatably connected with the propeller hub; the variable pitch assembly comprises a propeller pitch adjusting piece, a propeller blade supporting piece and a propeller pitch transmission piece. The first side of the blade supporting piece is rotatably connected with the rotor blade, and the second side of the blade supporting piece is slidably connected with the propeller pitch adjusting piece, so that the propeller pitch adjusting piece can longitudinally move up and down along the blade supporting piece; the propeller pitch transmission part and the rotor blade are relatively fixed, and the propeller pitch transmission part and the propeller pitch adjusting part are rotatably connected; the propeller pitch adjusting piece can be connected with the lifting driving piece and can be driven by the lifting driving piece to move up and down in the longitudinal direction of the propeller blade supporting piece, then the propeller pitch transmission piece is driven to rotate, and finally the rotor wing propeller blades are driven to rotate around the axes of the rotor wing propeller blades. The technical effect that the electric aircraft adopting the outer rotor electron can achieve the variable pitch of the rotor wing is achieved.

Description

Technical Field

[0001] This invention relates to the field of electric aircraft technology, and more specifically, to variable pitch rotor systems and 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. The motors include internal rotor motors and external rotor motors, with the rotor of the external rotor motor located on the outside of the motor. The aircraft's rotors include fixed-pitch rotors and variable-pitch rotors. Fixed-pitch rotors maintain a constant pitch angle during flight, resulting in high efficiency under certain operating conditions. However, because of the constant pitch angle, rotors with constant pitch angles cannot adapt to a wide range of incoming flow velocities. In some operating conditions, large-scale 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 flow 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. Summary of the Invention

[0005] The purpose of this invention is to provide a variable-pitch rotor system and an electric aircraft to alleviate the technical problem of difficulty in variable-pitch rotors of electric aircraft using external rotor electronics in the prior art.

[0006] In a first aspect, embodiments of the present invention provide a variable-pitch rotor system, including a rotor hub, rotor blades, and a variable-pitch assembly; The root of the rotor blade passes through the side wall of the hub and is rotatably connected to the hub. The pitch control assembly includes a pitch adjustment component, a blade support component, and a pitch transmission component. The blade support is disposed on the rotor hub. 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, the present invention provides one possible implementation of the first aspect, wherein a longitudinal guide slide is provided on the second side of the 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, the present invention provides a possible implementation of the first aspect, wherein the circumferential sidewall of the 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, the present invention 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, the present invention provides a possible implementation of the first aspect, wherein a blade fixing hole is provided on the circumferential sidewall of the aforementioned propeller hub; A first bearing is fitted onto the rotor blade, and a first bearing mounting seat for installing the first bearing is provided in the blade fixing hole.

[0011] In conjunction with the first aspect, the present invention provides a possible implementation of the first aspect, wherein the root of the rotor blade is provided with a bearing limiting member for limiting the first bearing, the bearing limiting member being located between the first bearing and the rotor blade.

[0012] In conjunction with the first aspect, the present invention 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 first connecting hole that matches the first threaded hole, and the metal connector is connected to the pitch transmission component by bolts.

[0013] In conjunction with the first aspect, the present invention provides a possible implementation of the first aspect, wherein a second bearing mounting seat for mounting the pitch transmission component is provided on the first side of the blade support member. The pitch transmission component is fitted with a second bearing, which is located inside the second bearing mounting seat.

[0014] In conjunction with the first aspect, the present invention provides a possible implementation of the first aspect, wherein a third bearing is sleeved on the rotor blade, and the third bearing is located between the rotor hub and the pitch transmission member.

[0015] In conjunction with the first aspect, the present invention provides one possible implementation of the first aspect, wherein the above-mentioned lifting drive is a variable pitch servo motor; The output end of the lifting drive is provided with a pitch control rod, and the end of the pitch control rod away from the lifting drive 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, the present invention provides a possible implementation of the first aspect, wherein the pitch adjustment member has a connecting channel in the middle for connecting with the pitch control rod, and the interior of the connecting channel has an outer ring support for supporting the outer ring of the fourth bearing. The outer wall of the variable pitch tie rod is provided with an inner ring support seat for supporting the inner ring of the fourth bearing; An end cap is threaded into the connecting channel, and the end cap can press the outer ring of the fourth bearing. A clamping ring is threaded into the variable pitch rod, and the clamping ring can press the inner ring of the fourth bearing.

[0017] Secondly, embodiments of the present invention provide an electric aircraft, including the variable-pitch rotor system.

[0018] Beneficial effects: This invention provides a variable-pitch rotor system, including a rotor hub, rotor blades, and a variable-pitch assembly. The root of the rotor blades passes through the sidewall of the rotor hub and is rotatably connected to the rotor hub. The variable-pitch assembly includes a pitch adjustment component, a blade support component, and a pitch transmission component. The blade support component is disposed on the rotor hub, with a first side rotatably connected to the rotor blades and a second side slidably connected to the pitch adjustment component, so that the pitch adjustment component can move up and down longitudinally along the blade support component. The pitch transmission component is fixed relative to the rotor blades and is rotatably connected to the pitch adjustment component. The pitch adjustment component can be connected to a lifting drive component and can move up and down longitudinally along the blade support component under the drive of the lifting drive component, thereby driving the pitch transmission component to rotate, and ultimately driving the rotor blades to rotate around their axis.

[0019] Specifically, when pitch change is required, the control center of the electric aircraft sends a command to the lift drive. After receiving the pitch change command, the lift drive can drive the pitch adjustment component to move up and down relative to the blade support component. When the pitch adjustment component slides up and down, it can drive the pitch transmission component connected to it to swing. The swing of the pitch transmission component can drive the rotor blade to rotate, thereby realizing the pitch change function.

[0020] This invention provides an electric aircraft, including a variable-pitch rotor system. The electric aircraft has the advantages described above compared to existing technologies, which will not be elaborated further here. Attached Figure Description

[0021] To more clearly illustrate the specific embodiments of the present invention 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 the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the structure of the variable-pitch rotor system provided in an embodiment of the present invention; Figure 2 This is an internal schematic diagram of a variable-pitch rotor system provided in an embodiment of the present invention; Figure 3 This is a cross-sectional view of a variable-pitch rotor system provided in an embodiment of the present invention; Figure 4 This is a schematic diagram of the rotor hub in a variable-pitch rotor system provided in an embodiment of the present invention; Figure 5 This is a schematic diagram of the rotor blade structure in a variable-pitch rotor system provided in an embodiment of the present invention; Figure 6 This is a schematic diagram of the pitch transmission component and the pitch control arm in the variable pitch rotor system provided in an embodiment of the present invention; Figure 7 This is a schematic diagram of the pitch transmission component in a variable-pitch rotor system provided in an embodiment of the present invention; Figure 8 A schematic diagram of the rotor blades and pitch transmission components of a variable-pitch rotor system provided in an embodiment of the present invention; Figure 9 This is a schematic diagram of the pitch adjustment component in the variable-pitch rotor system provided in an embodiment of the present invention; Figure 10 This is a schematic diagram of the blade support component in a variable-pitch rotor system provided in an embodiment of the present invention; Figure 11 This is a partial structural schematic diagram of the variable-pitch rotor system provided in an embodiment of the present invention; Figure 12 This is a schematic diagram of the pitch control component in a pitch control rotor system provided in an embodiment of the present invention; Figure 13 This is a schematic diagram of the pitch adjustment component and the pitch control rod in the variable-pitch rotor system provided in an embodiment of the present invention; Figure 14 This is a cross-sectional view of the pitch adjustment component and the pitch control rod in the variable pitch rotor system provided in an embodiment of the present invention.

[0023] icon: 10 - External rotor of the motor; 100 - Propeller hub; 101 - First bolt mounting hole; 110 - Propeller blade fixing hole; 120 - First bearing mounting seat; 200 - Rotor blade; 210 - First threaded hole; 220 - First bearing; 230 - Bearing retainer; 240 - Third bearing; 300-Pitch adjustment assembly; 310-Pitch adjustment component; 311-Guide slider; 312-Pitch control arm; 313-Pitch pin; 314-First pin hole; 315-Second pin hole; 316-Connecting channel; 317-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-First connecting hole; 332-Offset rocker arm; 333-Second bearing; 334-Boss; 340-End cap; 400 - Variable pitch tie rod; 410 - Fourth bearing; 420 - Inner ring support seat; 430 - Pressure ring. Detailed Implementation

[0024] The technical solution of the present invention 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 the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0026] 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 invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0027] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," 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 invention according to the specific circumstances.

[0028] The present invention will now be described in further detail with reference to specific embodiments and accompanying drawings.

[0029] 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 , Figure 13 and Figure 14 As shown, this embodiment provides a variable-pitch rotor system, including a rotor hub 100, rotor blades 200, and a variable-pitch assembly 300; the root of the rotor blade 200 passes through the sidewall of the rotor hub 100 and is rotatably connected to the rotor hub 100; the variable-pitch 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 disposed on the rotor hub 100, and the first side 323 of the blade support component 320 is rotatably connected to the rotor blade 200, and the second side 324... The pitch adjustment component 310 is slidably connected to the blade support component 320 so that the blade support component 310 can move up and down along the longitudinal direction of the blade support component 320; the pitch transmission component 330 is fixed relative to the rotor blade 200 and is rotatably connected to the blade 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 blade transmission component 330 to rotate, and finally driving the rotor blade 200 to rotate around its axis.

[0030] Specifically, when pitch change is required, the control center of the electric aircraft will send a command to the lift drive. After receiving the pitch change command, the lift drive can drive the pitch adjustment component 310 to move up and down relative to the blade support component 320. When the pitch adjustment component 310 slides up and down, it can drive the pitch transmission component 330 connected to it to swing. The swing of the pitch transmission component 330 can drive the rotor blade 200 to rotate, thereby realizing the pitch change function.

[0031] The rotor hub 100 has multiple first bolt mounting holes 101 on its inner bottom plate. The rotor hub 100 is connected to the outer rotor 10 of the aircraft's motor below by bolts passing through these first bolt mounting holes 101. 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 101, 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 fixing 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] The blade support 320 has a longitudinal guide rail 321 on its second side 324; the pitch adjustment member 310 has a guide slider 311 on its circumferential sidewall that is compatible with the guide rail 321. The guide slider 311 on the circumferential sidewall of the pitch adjustment member 310 is slidably disposed within the guide rail 321. When the lifting drive member drives the pitch adjustment member 310 to move longitudinally up and down, the guide slider 311 on the circumferential sidewall of the pitch adjustment member 310 can slide within the guide rail 321, thereby enabling the pitch adjustment member 310 to move stably longitudinally up and down along the guide rail 321.

[0034] It should be noted that 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 lever 400, the end of which is furthest from the linear servo and connected to the pitch adjustment component 310. When the linear servo is working, it can drive the variable pitch lever 400 to move up and down. The variable pitch lever 400 can then drive the pitch adjustment component 310 to move up and down. The up and down movement of the pitch adjustment component 310 can then cause the variable pitch swing arm 312 on it to swing. The swinging of the variable pitch swing arm 312 can then cause the pitch transmission component 330 to rotate. The rotation of the pitch transmission component 330 can then cause the rotor blades 200 to rotate, thus achieving the variable pitch function.

[0035] It should be noted that a fourth bearing 410 is provided between the pitch control rod 400 and the pitch adjustment component 310. A connecting channel 316 for connecting with the pitch control rod 400 is provided in the middle of the pitch adjustment component 310. The interior of the connecting channel 316 has an outer ring support 317 for supporting the outer ring of the fourth bearing 410. An inner ring support 420 for supporting the inner ring of the fourth bearing 410 is provided on the outer wall of the pitch control rod 400. An end cap 340 is threaded into the connecting channel 316, 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 control 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 control rod 400 together.

[0036] In addition, the fourth bearing 410 can be a tapered roller bearing. The pitch control 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 control rod 400 to the pitch adjustment component 310. By setting the bearing, the pitch control 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.

[0037] See Figures 1-14As 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.

[0038] 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.

[0039] See Figures 1-14 As shown, in an optional embodiment, the pitch transmission member 330 has an offset rocker arm 332, which can drive the pitch transmission member 330 to rotate; the offset rocker arm 332 is pivotally connected to the variable pitch swing arm 312, and can drive the offset rocker arm 332 to swing up and down through the variable pitch swing arm 312 when the pitch adjustment member 310 moves up and down.

[0040] 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.

[0041] 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 314 for connecting with the guide slider 311 and a second pin hole 315 for connecting with the variable pitch pin 313.

[0042] See Figures 1-14 As shown, in the optional embodiment, a blade fixing hole 110 is provided on the circumferential sidewall of the rotor hub 100; a first bearing 220 is sleeved on the rotor blade 200, and a first bearing fixing seat 120 for installing the first bearing 220 is provided in the blade fixing hole 110.

[0043] Specifically, the rotor blade 200 is inserted into the blade fixing 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 fixing hole 110, so that the rotor blade 200 can rotate relative to the rotor hub 100.

[0044] See Figures 1-14As shown, in an optional embodiment, the root of the rotor blade 200 is provided with a bearing limiting member 230 for limiting the first bearing 220, and the bearing limiting member 230 is located between the first bearing 220 and the blade of the rotor blade 200.

[0045] Specifically, a bearing limiting member 230 is provided at the root of the rotor blade 200. After the rotor blade 200 is installed in the blade fixing 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 prevents the first bearing 220 from moving axially along the root of the rotor blade 200.

[0046] See Figures 1-14 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 first 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.

[0047] 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 first connecting hole 331. The bolt passes through the first connecting hole 331 and is tightened into the first threaded hole 210, thereby firmly fixing the rotor blade 200 and the pitch transmission component 330 together.

[0048] See Figures 1-14 As shown, in an optional embodiment, 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 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 disposed in the second bearing fixing seat 322.

[0049] 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.

[0050] In addition, a third bearing 240 is fitted on the rotor blade 200, and the third bearing 240 is located between the rotor hub 100 and the pitch transmission component 330. The installation of the third bearing 240 prevents friction and jamming between the pitch transmission component 330 and the side wall of the rotor hub 100.

[0051] It should be noted that the rotor blade 200 passes through the blade fixing hole 110, and a first bearing 220 is sleeved on the rotor blade 200. The first bearing 220 is completely installed in the first bearing fixing seat 120 on the rotor hub 100, and a bearing limiting member 230 is provided at the root of the rotor blade 200. When the rotor blade 200 is inserted into the blade fixing hole 110, the bearing limiting member 230 can press the first bearing 220 tightly into the first bearing fixing seat 120, and the rotor blade The root of rotor blade 200 is fixedly connected to the pitch transmission component 330. A third bearing 240 is sleeved on rotor blade 200. The third bearing 240 is located between rotor hub 100 and pitch transmission component 330. It is fixedly connected to the root of rotor blade 200 and pitch transmission component 330. Pitch transmission component 330 is set on blade support component 320 through second bearing 333, thereby ensuring the stability of rotor blade 200 and reducing the friction between pitch transmission component 330 and blade support component 320.

[0052] Specifically, the first bearing 220 and the second bearing 333 can be radial bearings, which are used to bear the radial load of the blades, and the third bearing 240 can be a thrust bearing, which is used to bear the centrifugal force of the blades. Furthermore, those skilled in the art can choose the types of the first bearing 220, the third bearing 240, and the second bearing 333 according to implementation requirements.

[0053] This embodiment provides an electric aircraft, including a variable-pitch rotor system.

[0054] The electric aircraft provided in this embodiment has the advantages of the aforementioned variable-pitch rotor system compared to the prior art, which will not be elaborated here.

[0055] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit them. Although the present invention 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 the present invention.

Claims

1. A variable-pitch rotor system, characterized in that, include: The rotor hub (100), rotor blades (200), and pitch control assembly (300); The root of the rotor blade (200) passes through the side wall of the hub (100) and is rotatably connected to the hub (100); 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 rotor hub (100). 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 variable-pitch rotor system 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 variable-pitch rotor system 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 variable-pitch rotor system 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 variable-pitch rotor system according to claim 1, characterized in that, The blade fixing hole (110) is provided on the circumferential side wall of the rotor hub (100). A first bearing (220) is fitted on the rotor blade (200), and a first bearing mounting seat (120) for installing the first bearing (220) is provided in the blade fixing hole (110).

6. The variable-pitch rotor system according to claim 5, characterized in that, The root of the rotor blade (200) is provided with a bearing limiting member (230) for limiting the first bearing (220), and the bearing limiting member (230) is located between the first bearing (220) and the blade of the rotor blade (200).

7. The variable-pitch rotor system 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 first connecting 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.

8. The variable-pitch rotor system according to claim 7, characterized in that, The first side (323) of the blade support (320) is provided with a second bearing fixing seat (322) for mounting the blade 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).

9. The variable-pitch rotor system according to claim 7, characterized in that, A third bearing (240) is fitted on the rotor blade (200), and the third bearing (240) is located between the rotor hub (100) and the pitch transmission component (330).

10. The variable-pitch rotor system 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 is provided with a pitch control rod (400). The end of the pitch control rod (400) away from the lifting drive is connected to the pitch adjustment component (310). A fourth bearing (410) is provided between the pitch control rod (400) and the pitch adjustment component (310).

11. The variable-pitch rotor system according to claim 10, characterized in that, The pitch adjustment component (310) has a connecting channel (316) in the middle for connecting with the pitch control rod (400), and the interior of the connecting channel (316) has an outer ring support seat (317) for supporting the outer ring of the fourth bearing (410). The outer wall of the variable pitch tie 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 (316) is threaded with an end cap (340), which can press the outer ring of the fourth bearing (410). The variable pitch 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 variable pitch rotor system as described in any one of claims 1-11.

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