Variable pitch rotor system with pitch angle measurement and electric aircraft

Abstract

This utility model provides a variable-pitch rotor system with pitch angle measurement and an electric aircraft, relating to the technical field of electric aircraft technology. The variable-pitch rotor system with pitch angle measurement includes a rotor hub, rotor blades, a measuring blade, a pitch control assembly, and a pitch angle measurement assembly. The rotor hub has a blade support component inside, and the root of the measuring blade passes through both the rotor hub and the blade support component, and is driveably connected to the pitch angle measurement assembly. The pitch control assembly includes a pitch adjustment component and a pitch transmission component. A first side of the blade support component is rotatably connected to the rotor blade, and a second side is 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 relatively fixed to the rotor blade and is driveably connected to the pitch adjustment component. The pitch adjustment component can be connected to a lifting drive component. This achieves the technical effect of variable-pitch control and pitch measurement of the propeller during rotation.

Description

Technical Field

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

[0002] Electric vertical takeoff and landing (EVTOL) aircraft can take off and land vertically, using an electric motor to drive a propeller for power and lift. The internal rotor motor is connected to the propeller via an output shaft; the rotation of the output shaft drives the propeller's rotation. Aircraft propellers come in two types: fixed-pitch propellers and variable-pitch propellers. Fixed-pitch propellers maintain a constant pitch angle during flight, resulting in higher efficiency under certain conditions. However, because of the constant pitch angle, they cannot adapt to a wide range of incoming airflow velocities. In some situations, airflow separation occurs over a large area at the propeller surface, leading to reduced propeller efficiency. Variable-pitch propellers, on the other hand, adjust their pitch according to changes in incoming airflow velocity, ensuring high efficiency under various flight conditions.

[0003] Traditional variable-pitch propellers use a constant-speed governor to control 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. It requires real-time, precise control of the propeller pitch to provide a suitable flight attitude. Furthermore, the pitch and motor speed are not matched, necessitating separate pitch control. Traditional constant-speed governor pitch control methods cannot meet the requirements of electric aircraft.

[0004] Existing fixed-pitch propellers cannot achieve pitch control and pitch measurement during propeller rotation. Utility Model Content

[0005] The purpose of this invention is to provide a variable pitch rotor system and an electric aircraft with pitch angle measurement, so as to alleviate the technical problem that the variable pitch control and pitch measurement of the propeller cannot be achieved during the rotation of the propeller in the prior art.

[0006] In a first aspect, this utility model provides a variable pitch rotor system with pitch angle measurement, including a rotor hub, rotor blades, measuring blades, a variable pitch assembly, and a pitch angle measurement assembly. The roots of both the rotor blade and the measuring blade pass through the sidewall of the hub and are rotatably connected to the hub. The rotor hub has a blade support inside, and the pitch angle measuring component is disposed inside the rotor hub. The pitch angle measuring component is located inside the blade support, and the root of the measuring blade passes through both the rotor hub and the blade support and is connected to the pitch angle measuring component in a driving connection. The pitch control assembly includes a pitch adjustment component and a pitch transmission component. 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 component. The pitch transmission component is fixed relative to the rotor blade, and the pitch transmission component is transmissively 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 a possible implementation of the first aspect, wherein the above-mentioned pitch angle measuring component includes a sensor mounting base and an angle sensor; The sensor mounting base is located inside the propeller hub, the angle sensor is mounted on the sensor mounting base, and the angle sensor is provided with a first transmission gear; A second transmission gear is provided at the root of the measuring blade, and the second transmission gear meshes with the first transmission gear.

[0008] 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.

[0009] 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.

[0010] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein the above-mentioned pitch transmission component includes a connecting fork and an offset rocker arm, the connecting fork and the offset rocker arm are integral structures, and the connecting fork is fixedly connected to the rotor blade; The offset rocker arm is pivotally connected to the variable pitch swing arm, so that the pitch adjustment component drives the offset rocker arm to swing up and down through the variable pitch swing arm.

[0011] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein both the rotor blade and the measuring blade have mounting grooves at their roots, and the connecting fork is inserted into the mounting groove so that the rotor blade can rotate synchronously when the connecting fork rotates. The connecting fork and the assembly groove are provided with corresponding connecting holes, and the connecting bolts are inserted into the connecting holes on both the connecting fork and the assembly groove.

[0012] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein a blade fixing hole is provided on the circumferential sidewall of the aforementioned propeller hub. Both the rotor blade and the measuring blade are fitted with a first bearing, and a first bearing mounting seat for installing the first bearing is provided in the blade fixing hole. Both the rotor blade and the measuring blade are provided with bearing limiting members at their roots for limiting the first bearing, and the bearing limiting members are located between the first bearing and the rotor blade. The first side of the blade support is provided with a second bearing mounting seat for mounting the rotor blade and the measuring blade. The rotor blade and the measuring blade are both fitted with a second bearing, which is disposed in the second bearing mounting seat.

[0013] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein a third bearing is sleeved on both the rotor blade and the measuring blade, and the third bearing is located between the rotor hub and the pitch transmission member.

[0014] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein the bottom of the aforementioned propeller hub has a mounting cylinder for connecting to a drive motor, the lifting drive component is installed inside the mounting cylinder, and the lifting drive component is a variable pitch servo. The output end of the lifting drive is connected to a variable pitch screw, the pitch adjustment component is inserted on the variable pitch screw, and the pitch adjustment component has a screw nut connected to the variable pitch screw. The propeller hub is covered with a cover plate, and the two ends of the variable pitch screw are respectively disposed on the propeller hub and the cover plate. A fourth bearing is disposed between the propeller hub and the cover plate and the variable pitch screw.

[0015] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein a slip ring is sleeved on the mounting cylinder, and both the lifting drive component and the pitch angle measuring component are electrically connected to the slip ring.

[0016] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein a flange is sleeved and connected to the bottom of the mounting cylinder, the end of the mounting cylinder is rectangular, a rectangular channel is opened in the middle of the flange, and the flange and the mounting cylinder are connected by bolts. The flange is connected to the drive motor.

[0017] Secondly, this utility model embodiment provides an electric aircraft, including the variable-pitch rotor system with pitch angle measurement.

[0018] Beneficial effects: This utility model provides a variable-pitch rotor system with pitch angle measurement, including a rotor hub, rotor blades, measuring blades, a pitch control assembly, and a pitch angle measurement assembly. The roots of both the rotor blades and the measuring blades pass through the sidewall of the rotor hub and are rotatably connected to it. The rotor hub has a blade support member inside, and the pitch angle measurement assembly is disposed inside the rotor hub, located inside the blade support member. The root of the measuring blade passes through both the rotor hub and the blade support member and is drively connected to the pitch angle measurement assembly. The pitch control assembly... The component includes a pitch adjustment component and a pitch transmission component. The first side of the blade support component 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 component. The pitch transmission component is fixed relative to the rotor blade and can be driven to connect with the pitch adjustment component. The pitch adjustment component can be connected to a 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.

[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. When the pitch adjustment component moves 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 and the measuring blade to rotate, thereby realizing the pitch change function. In addition, during the rotation of the measuring blade, the measuring blade can trigger the pitch angle measurement component, thereby realizing the pitch angle measurement.

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

[0021] 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.

[0022] Figure 1 A schematic diagram of a variable-pitch rotor system with pitch angle measurement provided for an embodiment of this utility model; Figure 2 A top view of a variable-pitch rotor system with pitch angle measurement provided in an embodiment of this utility model; Figure 3 for Figure 2 Sectional view of AA; Figure 4 An internal schematic diagram of a variable-pitch rotor system with pitch angle measurement provided for an embodiment of this utility model; Figure 5 A schematic diagram of the internal structure of a variable-pitch rotor system with pitch angle measurement provided for an embodiment of this utility model; Figure 6 A schematic diagram of the rotor hub in a variable-pitch rotor system with pitch angle measurement provided for an embodiment of this utility model; Figure 7 A schematic diagram of the pitch adjustment component and the pitch transmission component in a variable-pitch rotor system with pitch angle measurement provided for an embodiment of this utility model; Figure 8 A schematic diagram of the pitch transmission component and rotor blades in a variable pitch rotor system with pitch angle measurement provided for an embodiment of this utility model; Figure 9 A schematic diagram of a rotor blade in a variable-pitch rotor system with pitch angle measurement provided for an embodiment of this utility model; Figure 10 A schematic diagram of the measuring blade in a variable-pitch rotor system with pitch angle measurement provided in an embodiment of this utility model; Figure 11 A schematic diagram of the measuring blade in a variable-pitch rotor system with pitch angle measurement provided in an embodiment of this utility model; Figure 12 A schematic diagram of the pitch transmission component, pitch control arm, and pitch control pin in a variable pitch rotor system with pitch angle measurement provided for an embodiment of this utility model; Figure 13 A schematic diagram of the pitch transmission component, pitch control arm, and pitch pin in a pitch angle measurement variable-pitch rotor system provided for an embodiment of this utility model. Figure 14A schematic diagram of the rotor hub, lifting drive and pitch adjustment components in a variable-pitch rotor system with pitch angle measurement provided for an embodiment of this utility model; Figure 15 A schematic diagram of the lifting drive component and the pitch adjustment component in a variable-pitch rotor system with pitch angle measurement provided for an embodiment of this utility model; Figure 16 A schematic diagram of the lifting drive component in a variable-pitch rotor system with pitch angle measurement provided in an embodiment of this utility model; Figure 17 A schematic diagram of the rotor hub and flange in a variable pitch rotor system with pitch angle measurement provided for an embodiment of this utility model.

[0023] icon: 100-Bulb hub; 110-Blade support; 111-First side; 112-Second side; 113-Guide slide; 114-Second bearing mounting seat; 120-Blade mounting hole; 130-First bearing mounting seat; 140-Mounting cylinder; 150-Cover plate; 160-Slip ring; 170-Flange; 171-Rectangular channel; 180-Wire passage hole; 200-Rotor blade; 201-Measuring blade; 202-Second transmission gear; 210-Assembly slot; 211-Connecting hole; 212-Connecting bolt; 220-First bearing; 230-Bearing limiter; 240-Second bearing; 250-Third bearing; 300-Pitch adjustment assembly; 310-Pitch adjustment component; 311-Guide slider; 312-Pitch control arm; 313-Pitch control pin; 320-Pitch transmission component; 321-Connecting fork; 322-Offset rocker arm; 400 - Pitch angle measurement assembly; 410 - Sensor mounting base; 420 - Angle sensor; 421 - First transmission gear; 500 - Lifting drive component; 510 - Variable pitch screw; 520 - Screw nut; 530 - Fourth bearing; 540 - Adapter sleeve; 600 - Drive motor. Detailed Implementation

[0024] 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.

[0025] 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.

[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 utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0027] 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.

[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 , Figure 14 , Figure 15 , Figure 16 and Figure 17As shown, this embodiment provides a variable-pitch rotor system with pitch angle measurement, including a rotor hub 100, rotor blades 200, measuring blades 201, a variable-pitch assembly 300, and a pitch angle measurement assembly 400. The roots of both the rotor blades 200 and the measuring blades 201 pass through the sidewall of the rotor hub 100 and are rotatably connected to the rotor hub 100. The rotor hub 100 has a blade support member 110 inside, and the pitch angle measurement assembly 400 is disposed inside the rotor hub 100, located inside the blade support member 110. The root of the measuring blade 201 passes through both the rotor hub 100 and the blade support member 110 and is drively connected to the pitch angle measurement assembly 400. The component 300 includes a pitch adjustment component 310 and a pitch transmission component 320. The first side 111 of the blade support component 110 is rotatably connected to the rotor blade 200 and slidably connected to the pitch adjustment component 310, so that the pitch adjustment component 310 can move up and down along the longitudinal direction of the blade support component 110. The pitch transmission component 320 is fixed relative to the rotor blade 200 and is driveably connected to the pitch adjustment component 310. The pitch adjustment component 310 can be connected to the lifting drive component 500 and can move up and down along the longitudinal direction of the blade support component 110 under the drive of the lifting drive component 500, thereby driving the pitch transmission component 320 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 sends a command to the lift drive 500. After receiving the pitch change command, the lift drive 500 can drive the pitch adjustment component 310 to move up and down relative to the blade support component 110. When the pitch adjustment component 310 moves up and down, it can drive the pitch transmission component 320 connected to it to swing. The swing of the pitch transmission component 320 can drive the rotor blade 200 and the measuring blade 201 to rotate, thereby realizing the pitch change function. During the rotation of the measuring blade 201, the measuring blade 201 can trigger the pitch angle measurement component 400, thereby realizing the pitch angle measurement.

[0031] The blade support 110 has a longitudinal guide slide 113 on its second side 112; the pitch adjustment member 310 has a guide slider 311 on its circumferential sidewall that can be adapted to the guide slide 113. The guide slider 311 on the circumferential sidewall of the pitch adjustment member 310 is slidably disposed within the guide slide 113. When the lifting drive member 500 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 slide 113, thereby enabling the pitch adjustment member 310 to move stably longitudinally up and down along the guide slide 113.

[0032] The first side 111 of the blade support 110 is rotatably connected to both the rotor blade 200 and the measuring blade 201, and the second side 112 is slidably connected to the pitch adjustment member 310. The first side 111 and the second side 112 on the blade support 110 are opposite sides.

[0033] It should be noted that the blade support 110 is annular and is fixedly installed inside the blade hub 100. The blade support 110 and the blade hub 100 are an integral structure and can be produced by injection molding or integral processing. The first side 111 is the outer ring sidewall of the blade support 110, and the second side 112 is the inner ring sidewall of the blade support 110.

[0034] In addition, the root of the measuring blade 201 can pass through the blade support 110 and be connected to the pitch angle measuring component 400 located inside the blade support 110, so that when the pitch adjustment component 310 drives the measuring blade 201 to change pitch, the pitch angle measuring component 400 can monitor the pitch angle.

[0035] See Figures 1-17 As shown, in an optional embodiment, the pitch angle measuring assembly 400 includes a sensor mounting base 410 and an angle sensor 420. The sensor mounting base 410 is located inside the rotor hub 100, and the angle sensor 420 is mounted on the sensor mounting base 410. A first transmission gear 421 is mounted on the angle sensor 420. A second transmission gear 202 is mounted at the root of the measuring blade 201, and the second transmission gear 202 meshes with the first transmission gear 421.

[0036] Specifically, the second bearing mounting seat 114 at the position corresponding to the measuring blade 201 on the blade support 110 is a through hole, so that the root end of the measuring blade 201 can pass through the second bearing mounting seat 114 and be connected to the pitch angle measuring assembly 400 located inside the blade support 110. Specifically, the second transmission gear 202 at the end of the measuring blade 201 meshes with the first transmission gear 421 on the angle sensor 420, so that the angle sensor 420 can monitor the pitch angle of the measuring blade 201.

[0037] The pitch angle measurement data measured by the angle sensor 420 can be transmitted to the external controller via the slip ring 160.

[0038] It should be noted that the sensor mounting base 410 is fixedly installed inside the propeller hub 100 to improve the stability of the sensor mounting base 410.

[0039] See Figures 1-17As shown, in an optional embodiment, the circumferential sidewall of the pitch adjustment member 310 is rotatably provided with a pitch-changing swing arm 312 that can be pivotally connected to the pitch transmission member 320; the circumferential sidewall of the pitch adjustment member 310 is provided with a connecting pin hole for mounting the pitch-changing swing arm 312, and the pitch-changing swing arm 312 is mounted on the pitch adjustment member 310 through a pitch-changing pin 313.

[0040] 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 320 to rotate, thereby causing the rotor blade 200 to rotate.

[0041] See Figures 1-17 As shown, in the optional embodiment, the pitch transmission component 320 includes a connecting fork 321 and an offset rocker arm 322. The connecting fork 321 and the offset rocker arm 322 are an integral structure. The connecting fork 321 is fixedly connected to the rotor blade 200. The offset rocker arm 322 is pivotally connected to the variable pitch swing arm 312, so that the pitch adjustment component 310 drives the offset rocker arm 322 to swing up and down through the variable pitch swing arm 312.

[0042] Specifically, the pitch transmission component 320 has an offset rocker arm 322. When the variable pitch rocker arm 312 swings up and down, it can drive the offset rocker arm 322 to swing up and down. At this time, the swinging of the offset rocker arm 322 can drive the pitch transmission component 320 to rotate. The rotation of the pitch transmission component 320 can drive the rotor blade 200 to rotate, thereby realizing the variable pitch function.

[0043] 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.

[0044] See Figures 1-17 As shown, in the optional embodiment, both the rotor blade 200 and the measuring blade 201 have an assembly groove 210 at their roots, and the connecting fork 321 is inserted into the assembly groove 210 so that the rotor blade 200 can rotate synchronously when the connecting fork 321 rotates; the connecting fork 321 and the assembly groove 210 have corresponding connecting holes 211, and the connecting bolts 212 pass through the connecting holes 211 on both the connecting fork 321 and the assembly groove 210.

[0045] Specifically, mounting slots 210 that can be adapted to the connecting fork 321 are provided at the root of both the rotor blade 200 and the measuring blade 201, so that the rotor blade 200 can be driven to rotate synchronously when the connecting fork 321 rotates.

[0046] Furthermore, corresponding connecting holes 211 are provided on both the connecting fork 321 and the mounting groove 210. The connecting bolt 212 can be inserted into the connecting holes 211 on both the connecting fork 321 and the mounting groove 210, thereby connecting and locking the connecting fork 321 and the mounting groove 210 together, so that the connecting fork 321 and the mounting groove 210 are relatively fixed, so that the connecting fork 321 drives the rotor blade 200 and the measuring blade 201 to rotate under the drive of the pitch adjustment component 310.

[0047] See Figures 1-17 As shown, in an optional embodiment, a blade fixing hole 120 is provided on the circumferential sidewall of the rotor hub 100; a first bearing 220 is fitted on both the rotor blade 200 and the measuring blade 201, and a first bearing fixing seat 130 for installing the first bearing 220 is provided in the blade fixing hole 120; a bearing limiting member 230 for limiting the first bearing 220 is provided at the root of both the rotor blade 200 and the measuring blade 201, and the bearing limiting member 230 is located between the first bearing 220 and the blade of the rotor blade 200; a second bearing fixing seat 114 for installing the rotor blade 200 and the measuring blade 201 is provided on the first side 111 of the blade support member 110, and a second bearing 240 is fitted on both the rotor blade 200 and the measuring blade 201, and the second bearing 240 is disposed in the second bearing fixing seat 114.

[0048] Specifically, the rotor blade 200 and the measuring blade 201 are inserted into the blade fixing hole 120 of the rotor hub 100, and the first bearing 220 on both the rotor blade 200 and the measuring blade 201 is mounted on the first bearing fixing seat 130 in the blade fixing hole 120, so that the rotor blade 200 and the measuring blade 201 can rotate relative to the rotor hub 100.

[0049] Bearing limiting members 230 are provided at the root of both the rotor blade 200 and the measuring blade 201. After the rotor blade 200 and the measuring blade 201 are respectively installed in the blade fixing hole 120 of the rotor hub 100, the bearing limiting members 230 can limit the first bearing 220, so that the first bearing 220 is always located on the first bearing fixing seat 130, and prevents the first bearing 220 from moving axially along the root of the rotor blade 200 or the measuring blade 201.

[0050] In addition, the second bearing mounting seat 114 on the blade support 110 and the first bearing mounting seat 130 in the blade mounting hole 120 work together to support the rotor blade 200 or the measuring blade 201, reducing the friction between the rotor blade 200 and the measuring blade 201 and the rotor hub 100, and ensuring that the rotor blade 200 can work normally for a long time.

[0051] It should be noted that the second bearing mounting seat 114 on the blade support 110 corresponding to the rotor blade 200 is a blind hole. The second bearing 240 is located inside the second bearing mounting seat 114 and is used to support the end of the blade support 110. The guide slide 113 on the second side 112 of the blade support 110 corresponds to the blind hole type second bearing mounting seat 114 on the first side 111. In addition, the second bearing mounting seat 114 on the blade support 110 corresponding to the measuring blade 201 is a through hole type, and there is no guide slide 113 at the position corresponding to the through hole type second bearing mounting seat 114 on the second side 112 of the blade support 110.

[0052] See Figures 1-17 As shown, in an optional embodiment, a third bearing 250 is fitted on both the rotor blade 200 and the measuring blade 201, and the third bearing 250 is located between the hub 100 and the pitch transmission component 320.

[0053] Specifically, a third bearing 250 is fitted on both the rotor blade 200 and the measuring blade 201, and the third bearing 250 is located between the rotor hub 100 and the pitch transmission component 320. The third bearing 250 is provided to prevent friction and jamming between the pitch transmission component 320 and the side wall of the rotor hub 100.

[0054] Specifically, the first bearing 220 and the second bearing 240 can be radial bearings, which are used to bear the radial load of the blades, and the third bearing 250 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 250, and the second bearing 240 according to implementation requirements.

[0055] See Figures 1-17 As shown, in an optional embodiment, the bottom of the propeller hub 100 has a mounting cylinder 140 for connecting to the drive motor 600. The lifting drive component 500 is installed inside the mounting cylinder 140 and is a variable pitch servo. The output end of the lifting drive component 500 is connected to a variable pitch screw 510. The pitch adjustment component 310 passes through the variable pitch screw 510 and has a screw nut 520 connected to the variable pitch screw 510. A cover plate 150 is provided on the propeller hub 100. The two ends of the variable pitch screw 510 are respectively set on the propeller hub 100 and the cover plate 150. A fourth bearing 530 is provided between the propeller hub 100 and the cover plate 150 and the variable pitch screw 510.

[0056] Specifically, when pitch adjustment is required, the lifting drive 500 drives the pitch-changing screw 510 to rotate. The fourth bearing 530 of the pitch-changing screw 510 rotates stably on both the rotor hub 100 and the cover plate 150. The rotation of the pitch-changing screw 510 can drive the screw nut 520 to move up and down. The screw nut 520 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 pitch swing arm 312 to swing through the pitch pin 313. The swing of the pitch swing arm 312 can drive the pitch transmission component 320 to rotate, thereby driving the rotor blade 200 or the measuring blade 201 to rotate, thus completing the pitch adjustment.

[0057] The lead screw nut 520 has a connecting ring at its top, which is fixed to the bottom of the pitch adjustment component 310 by bolts, thereby causing the lead screw nut 520 to drive the pitch adjustment component 310 to move up and down.

[0058] Among them, the variable pitch servo can be a linear servo.

[0059] It should be noted that the lifting drive component 500 is connected to the variable pitch screw 510 via the adapter sleeve 540.

[0060] See Figures 1-17 As shown, in the optional embodiment, a slip ring 160 is fitted on the mounting cylinder 140, and both the lifting drive component 500 and the pitch angle measuring component 400 are electrically connected to the slip ring 160.

[0061] Specifically, a slip ring 160 is provided on the mounting cylinder 140. The rotating end of the slip ring 160 can rotate synchronously with the mounting cylinder 140, and the fixed end of the slip ring 160 can be fixedly connected to the components of the external unmanned aerial vehicle. A wire hole 180 is opened at the bottom of the rotor hub 100. The angle sensor 420 and the lifting drive component 500 inside the rotor hub 100 can pass through the wire hole 180 and connect to the slip ring 160, thereby controlling and supplying power to the lifting drive component 500 through the slip ring 160, and transmitting the signal measured by the angle sensor 420 to the outside through the slip ring 160.

[0062] See Figures 1-17 As shown, in the optional embodiment, a flange 170 is sleeved and connected to the bottom of the mounting cylinder 140. The end of the mounting cylinder 140 is rectangular, and a rectangular channel 171 is opened in the middle of the flange 170. The flange 170 and the mounting cylinder 140 are connected by bolts. The flange 170 is connected to the drive motor 600.

[0063] Specifically, the flange 170 can be inserted into the bottom of the mounting cylinder 140, and by setting the end of the mounting cylinder 140 into a rectangle, a rectangular channel 171 is opened in the middle of the flange 170 to achieve circumferential restriction between the flange 170 and the mounting cylinder 140.

[0064] In addition, holes are drilled in both the flange 170 and the mounting sleeve 140, and bolts can pass through both the flange 170 and the mounting sleeve 140 to fasten the flange 170 and the mounting sleeve 140 together, ensuring that the flange 170 and the mounting sleeve 140 rotate synchronously. The surface of the flange 170 can be connected to the drive motor 600 of the aircraft.

[0065] This embodiment provides an electric aircraft, including a variable-pitch rotor system with pitch angle measurement.

[0066] Specifically, the electric aircraft provided in this embodiment has the advantages of the aforementioned variable-pitch rotor system with pitch angle measurement compared to the prior art, which will not be elaborated here.

[0067] 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 variable-pitch rotor system with pitch angle measurement, characterized in that, include: The rotor hub (100), rotor blades (200), measuring blades (201), pitch control assembly (300), and pitch angle measurement assembly (400). The roots of both the rotor blade (200) and the measuring blade (201) pass through the sidewall of the hub (100) and are rotatably connected to the hub (100). The rotor hub (100) has a blade support (110) inside, and the pitch angle measuring component (400) is disposed inside the rotor hub (100). The pitch angle measuring component (400) is located inside the blade support (110), and the root of the measuring blade (201) passes through both the rotor hub (100) and the blade support (110) and is connected to the pitch angle measuring component (400) in a driving connection. The pitch control assembly (300) includes a pitch adjustment component (310) and a pitch transmission component (320). The first side (111) of the blade support component (110) is rotatably connected to the rotor blade (200), and the second side (112) is slidably connected to the pitch adjustment component (310), so that the pitch adjustment component (310) can move up and down along the longitudinal direction of the blade support component (110). The pitch transmission component (320) is fixed relative to the rotor blade (200), and the pitch transmission component (320) is transmissionably connected to the pitch adjustment component (310). The pitch adjustment component (310) can be connected to the lifting drive component (500) and can move up and down along the longitudinal direction of the blade support component (110) under the drive of the lifting drive component (500), thereby driving the pitch transmission component (320) to rotate, and finally driving the rotor blade (200) to rotate around its axis.

2. The variable-pitch rotor system with pitch angle measurement according to claim 1, characterized in that, The pitch angle measurement assembly (400) includes a sensor mounting base (410) and an angle sensor (420). The sensor mounting base (410) is located inside the propeller hub (100), the angle sensor (420) is mounted on the sensor mounting base (410), and the angle sensor (420) is provided with a first transmission gear (421). The root of the measuring blade (201) is provided with a second transmission gear (202), which meshes with the first transmission gear (421).

3. The variable-pitch rotor system with pitch angle measurement according to claim 1, characterized in that, The second side (112) of the blade support (110) is provided with a longitudinal guide slide (113). The circumferential sidewall of the pitch adjustment member (310) is provided with a guide slider (311) that can be adapted to the guide slide (113).

4. The variable-pitch rotor system with pitch angle measurement according to claim 3, 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 (320). 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).

5. The variable-pitch rotor system with pitch angle measurement according to claim 4, characterized in that, The pitch transmission component (320) includes a connecting fork (321) and an offset rocker arm (322). The connecting fork (321) and the offset rocker arm (322) are an integral structure. The connecting fork (321) is fixedly connected to the rotor blade (200). The offset rocker arm (322) is pivotally connected to the variable pitch swing arm (312) so that the pitch adjustment member (310) drives the offset rocker arm (322) to swing up and down through the variable pitch swing arm (312).

6. The variable-pitch rotor system with pitch angle measurement according to claim 5, characterized in that, Both the rotor blade (200) and the measuring blade (201) have an assembly groove (210) at their root. The connecting fork (321) is inserted into the assembly groove (210) so that when the connecting fork (321) rotates, it can drive the rotor blade (200) to rotate synchronously. The connecting fork (321) and the mounting groove (210) are provided with corresponding connecting holes (211), and the connecting bolt (212) passes through the connecting holes (211) on both the connecting fork (321) and the mounting groove (210).

7. The variable-pitch rotor system with pitch angle measurement according to claim 1, characterized in that, The blade fixing hole (120) is provided on the circumferential side wall of the rotor hub (100). Both the rotor blade (200) and the measuring blade (201) are fitted with a first bearing (220), and a first bearing fixing seat (130) for installing the first bearing (220) is provided in the blade fixing hole (120). Both the rotor blade (200) and the measuring blade (201) are provided with a bearing limiting member (230) at their root 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). The first side (111) of the blade support (110) is provided with a second bearing mounting seat (114) for mounting the rotor blade (200) and the measuring blade (201). A second bearing (240) is fitted on both the rotor blade (200) and the measuring blade (201), and the second bearing (240) is disposed in the second bearing mounting seat (114).

8. The variable-pitch rotor system with pitch angle measurement according to claim 7, characterized in that, A third bearing (250) is fitted on both the rotor blade (200) and the measuring blade (201), and the third bearing (250) is located between the rotor hub (100) and the pitch transmission component (320).

9. The variable-pitch rotor system with pitch angle measurement according to claim 1, characterized in that, The bottom of the propeller hub (100) has a mounting sleeve (140) for connecting to the drive motor (600), and the lifting drive (500) is installed in the mounting sleeve (140). The lifting drive (500) is a variable pitch servo. The output end of the lifting drive (500) is connected to a variable pitch screw (510), and the pitch adjustment component (310) is mounted on the variable pitch screw (510). The pitch adjustment component (310) has a screw nut (520) connected to the variable pitch screw (510). The rotor hub (100) is covered with a cover plate (150), and the two ends of the variable pitch screw (510) are respectively disposed on the rotor hub (100) and the cover plate (150). A fourth bearing (530) is disposed between the rotor hub (100) and the cover plate (150) and the variable pitch screw (510).

10. The variable-pitch rotor system with pitch angle measurement according to claim 9, characterized in that, A slip ring (160) is fitted on the mounting cylinder (140), and both the lifting drive (500) and the pitch angle measuring component (400) are electrically connected to the slip ring (160).

11. The variable-pitch rotor system with pitch angle measurement according to claim 9, characterized in that, The bottom of the mounting cylinder (140) is fitted with a flange (170). The end of the mounting cylinder (140) is rectangular. A rectangular channel (171) is opened in the middle of the flange (170). The flange (170) and the mounting cylinder (140) are connected by bolts. The flange (170) is connected to the drive motor (600).

12. An electric aircraft, characterized in that, Includes the variable pitch rotor system with pitch angle measurement as described in any one of claims 1-11.

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