Electric aircraft variable pitch structure and electric aircraft

Abstract

The utility model provides a kind of electric aircraft variable pitch structure and electric aircraft, it is related to electric aircraft's technical field.Electric aircraft variable pitch structure includes hub, rotor blade and variable pitch component;The root of rotor blade is rotatably inserted in blade mounting hole;The inside of hub is fixedly provided with the blade support corresponding with blade mounting hole, the first side of blade support is rotatably connected with rotor blade;Variable pitch component includes pitch adjusting part and pitch transmission part;The second side of blade support is slidably connected with pitch adjusting part;Pitch transmission part is relatively fixed with rotor blade;Pitch adjusting part can be connected lifting drive part, and can be driven to move up and down along blade support under the driving of lifting drive part, to drive pitch transmission part rotation in turn, finally drive rotor blade rotation around its axis.The electric aircraft of the technical effect that outside rotor electron 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 variable pitch structure for electric aircraft 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 utility model is to provide a variable pitch structure for electric aircraft and an electric aircraft, so as to alleviate the technical problem of difficulty in variable pitch of the rotor of electric aircraft using external rotor electronics in the prior art.

[0006] In a first aspect, the present invention provides a variable pitch structure for an electric aircraft, including a rotor hub, rotor blades, and a variable pitch assembly; The rotor hub has blade mounting holes on its circumferential sidewalls, and the root of the rotor blade is rotatably inserted into the blade mounting holes. The rotor hub is fixedly provided with a rotor blade support corresponding to the rotor blade mounting hole, and the first side of the rotor blade support is rotatably connected to the rotor blade. The pitch control assembly includes a pitch adjustment component and a pitch transmission component; The second side of the blade support is slidably connected to the pitch adjustment member, so that the pitch adjustment member can move up and down along the longitudinal direction of the blade support member. 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 a possible implementation of the first aspect, wherein the first side of the blade support member is provided with a first bearing fixing seat for mounting the rotor blade; The rotor blades are fitted with a first bearing, which is located in a first bearing mounting seat.

[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, and the connecting fork and the offset rocker arm are integral structures; The connecting fork is fixedly connected to the rotor blade; 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.

[0011] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein an assembly groove is provided at the root of the rotor blade, and the connecting fork is inserted into the assembly groove so that the rotor blade can rotate synchronously when the connecting fork rotates.

[0012] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein the end of the connecting fork away from the bias rocker arm is provided with a connecting hole, and the connecting fork is fixed to the assembly groove by connecting bolts passing through the connecting holes on its two side walls.

[0013] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein a second bearing is sleeved on the rotor blade, and a second bearing fixing seat for installing the second bearing is provided in the blade mounting hole.

[0014] In conjunction with the first aspect, this utility model embodiment 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 second bearing, and the second bearing is located between the bearing limiting member and the blade support member.

[0015] 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 the rotor blade, and the third bearing is located between the rotor hub and the pitch transmission member.

[0016] 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. 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.

[0017] 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 pitch control 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 tie 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 rod is threaded with a clamping ring, which can press the inner ring of the fourth bearing.

[0018] In conjunction with the first aspect, this utility model embodiment provides a possible implementation of the first aspect, wherein a reinforcing rib is provided between each two adjacent blade support members.

[0019] Secondly, this utility model embodiment provides an electric aircraft, including the electric aircraft pitch-changing structure.

[0020] Beneficial effects: This utility model embodiment provides a variable pitch structure for an electric aircraft, including a rotor hub, rotor blades, and a variable pitch assembly. A blade mounting hole is provided on the circumferential sidewall of the rotor hub, and the root of the rotor blade is rotatably inserted into the blade mounting hole. A blade support corresponding to the blade mounting hole is fixedly installed inside the rotor hub, and the first side of the blade support is rotatably connected to the rotor blade. The variable pitch assembly includes a pitch adjustment component and a pitch transmission component. The second side of the blade support is slidably connected to the pitch adjustment component, allowing the pitch adjustment component to move vertically along the longitudinal direction of the blade support. 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, and ultimately causing the rotor blade to rotate around its axis.

[0021] 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 starts working and can drive the pitch adjustment component to move up and down. During the up and down movement of the pitch adjustment component, it can drive the pitch transmission component to swing. The swing of the pitch transmission component can drive the rotor blades to rotate synchronously, so that the rotor blades rotate on the blade mounting holes and blade support components, thereby realizing the pitch change function.

[0022] This utility model provides an electric aircraft, including a variable pitch structure. The electric aircraft has the advantages described above compared to the prior art, which will not be elaborated further here. Attached Figure Description

[0023] 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.

[0024] Figure 1 A schematic diagram of the variable pitch structure of the electric aircraft provided in the embodiments of this utility model; Figure 2 for Figure 1 Sectional view of AA; Figure 3 A schematic diagram of the variable pitch structure of the electric aircraft provided in this embodiment of the utility model; Figure 4 A schematic diagram of the internal structure of the variable pitch structure of the electric aircraft provided in the embodiment of this utility model; Figure 5 A schematic diagram of the rotor hub in the variable pitch structure of the electric aircraft provided in this embodiment of the utility model; Figure 6 A schematic diagram showing the connection between the pitch control assembly and the rotor blades in the pitch control structure of the electric aircraft provided in this embodiment of the utility model. Figure 7 A schematic diagram showing the connection of the pitch adjustment component, the pitch transmission component, and the rotor blades in the variable pitch structure of the electric aircraft provided in this embodiment of the utility model. Figure 8 A schematic diagram showing the connection between the pitch adjustment component and the pitch transmission component in the variable pitch structure of the electric aircraft provided in this embodiment of the utility model. Figure 9 A schematic diagram showing the connection between the pitch transmission component and the rotor blades in the variable pitch structure of the electric aircraft provided in this embodiment of the utility model. Figure 10 A schematic diagram of the connection of the pitch transmission component in the variable pitch structure of the electric aircraft provided in this embodiment of the utility model; Figure 11 A schematic diagram of the rotor blades in the variable-pitch structure of the electric aircraft provided in this embodiment of the utility model; Figure 12 A schematic diagram showing the connection between the rotor blades and multiple bearings in the variable-pitch structure of the electric aircraft provided in this embodiment of the utility model. Figure 13 A schematic diagram of the pitch adjustment component in the variable pitch structure of the electric aircraft provided in this embodiment of the utility model; Figure 14 A cross-sectional view showing the connection between the pitch adjustment component and the pitch control rod in the pitch control structure of the electric aircraft provided in this embodiment of the utility model.

[0025] icon: 10 - External rotor of the motor; 100-Bulb hub; 101-Bolt mounting hole; 110-Blade mounting hole; 111-Second bearing mounting seat; 120-Blade support; 121-First side; 122-First bearing mounting seat; 123-Second side; 124-Guide slide; 125-Reinforcing rib; 200 - Rotor blade; 201 - First bearing; 210 - Assembly slot; 220 - Second bearing; 230 - Bearing retainer; 240 - Third bearing; 300-Pitch assembly; 310-Pitch adjustment component; 311-Guide slider; 312-Pitch control arm; 313-Pitch control pin; 314-Connecting channel; 315-Outer ring support; 320-Pitch transmission component; 321-Connecting fork; 322-Offset rocker arm; 323-Connecting hole; 330-End cap; 400 - Variable pitch tie rod; 410 - Fourth bearing; 420 - Inner ring support seat; 430 - Pressure ring. Detailed Implementation

[0026] 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.

[0027] 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.

[0028] 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.

[0029] 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.

[0030] The present invention will now be described in further detail with reference to specific embodiments and accompanying drawings.

[0031] 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 pitch-changing structure for an electric aircraft, including a rotor hub 100, rotor blades 200, and a pitch-changing assembly 300. A blade mounting hole 110 is provided on the circumferential sidewall of the rotor hub 100, and the root of the rotor blade 200 is rotatably inserted into the blade mounting hole 110. A blade support member 120 corresponding to the blade mounting hole 110 is fixedly disposed inside the rotor hub 100, and the first side 121 of the blade support member 120 is rotatably connected to the rotor blade 200. The pitch-changing assembly 300 includes a pitch adjustment member 310 and a pitch transmission member 32. 0; The second side 123 of the blade support 120 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 120; the pitch transmission member 320 is fixed relative to the rotor blade 200, and the pitch transmission member 320 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 120 under the drive of the lifting drive member, thereby driving the pitch transmission member 320 to rotate, and finally driving the rotor blade 200 to rotate around its axis.

[0032] 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 starts working and can drive the pitch adjustment component 310 to move up and down. During the up and down movement of the pitch adjustment component 310, it can drive the pitch transmission component 320 to swing. The swing of the pitch transmission component 320 can drive the rotor blade 200 to rotate synchronously, so that the rotor blade 200 rotates on the blade mounting hole 110 and the blade support component 120, thereby realizing the pitch change function.

[0033] Among them, the blade support 120 and the blade hub 100 are integral structures. The blade support 120 and the blade hub 100 can be manufactured together by injection molding, which improves production efficiency, reduces production costs, and improves the structural strength of the blade support 120 and the blade hub 100.

[0034] In addition, multiple blade support members 120 correspond one-to-one with multiple blade mounting holes 110, and the root of the rotor blade 200 is inserted into the rotor hub 100 through the blade mounting hole 110.

[0035] It should be noted that multiple bolt mounting holes 101 are provided on the base plate of the rotor hub 100, and the rotor hub 100 is connected to the outer rotor of the motor of the aircraft below by bolts passing through the bolt mounting holes 101.

[0036] It should be noted that a reinforcing rib 125 is provided between every two adjacent blade support members 120. The reinforcing rib 125 enables multiple blade support members 120 to be interconnected, thereby improving the structural strength of the blade support members 120.

[0037] See Figures 1-14 As shown, in an optional embodiment, a first bearing mounting seat 122 for mounting the rotor blade 200 is provided on the first side 121 of the blade support 120; a first bearing 201 is sleeved on the rotor blade 200 and is disposed in the first bearing mounting seat 122.

[0038] The first side 121 of the blade support 120 is rotatably connected to the rotor blade 200, and the second side 123 is slidably connected to the pitch adjustment component 310. The first side 121 and the second side 123 on the blade support 120 are opposite sides.

[0039] Specifically, the root of the rotor blade 200 is mounted on the blade support 120 via the first bearing 201, and a second bearing 220 is provided between the rotor blade 200 and the blade mounting hole 110. This arrangement enables the rotor blade 200 to work smoothly.

[0040] Furthermore, a longitudinal guide slide 124 is provided on the second side 123 of the blade support 120; a guide slider 311 that can be adapted to the guide slide 124 is provided on the circumferential side wall of the pitch adjustment member 310. By providing a longitudinal guide slide 124 on the second side 123 of the blade support 120 and a guide slider 311 that can be adapted to the guide slide 124 on the circumferential side wall of the pitch adjustment member 310, the guide slider 311 on the circumferential side wall of the pitch adjustment member 310 is slidably disposed within the guide slide 124. When the lifting drive member drives the pitch adjustment member 310 to move longitudinally up and down, the guide slider 311 on the circumferential side wall of the pitch adjustment member 310 can slide within the guide slide 124, thereby enabling the pitch adjustment member 310 to move stably longitudinally up and down along the guide slide 124.

[0041] See Figures 1-14 As 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.

[0042] 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.

[0043] See Figures 1-14 As shown, in the optional embodiment, the pitch transmission component 320 includes a connecting fork 321 and an offset rocker arm 322, which are integral structures. 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. When the pitch adjustment component 310 moves up and down, it can drive the offset rocker arm 322 to swing up and down through the variable pitch swing arm 312.

[0044] Specifically, the pitch transmission component 320 has an offset rocker arm 322. Therefore, 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.

[0045] 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.

[0046] See Figures 1-14 As shown, in the optional embodiment, the rotor blade 200 has an assembly groove 210 at its root, 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.

[0047] Specifically, a mounting groove 210 is provided at the root of the rotor blade 200 to fit the connecting fork 321, so that the rotor blade 200 can rotate synchronously when the connecting fork 321 rotates.

[0048] See Figures 1-14 As shown, in an optional embodiment, the end of the connecting fork 321 away from the bias rocker arm 322 is provided with a connecting hole 323, and the connecting fork 321 is fixed to the assembly groove 210 by connecting bolts passing through the connecting holes 323 on both sides of its sidewalls.

[0049] Specifically, a connecting hole 323 is provided at the end of the connecting fork 321 away from the offset rocker arm 322. The connecting bolt passes through the connecting holes 323 on both sides of the connecting fork 321, which can lock the open ends of the connecting fork 321 close to each other, thereby clamping the connecting fork 321 in the mounting groove 210 at the root of the rotor blade 200, so that the connecting fork 321 cannot detach from the rotor blade 200 in the radial direction, and the groove sidewall of the mounting groove 210 can restrict the connecting fork 321 from moving in the axial direction of the rotor blade 200.

[0050] See Figures 1-14 As shown, in an optional embodiment, a second bearing 220 is fitted on the rotor blade 200, and a second bearing mounting seat 111 for mounting the second bearing 220 is provided in the blade mounting hole 110.

[0051] The rotor blade 200 has a bearing limiting member 230 at its root for limiting the second bearing 220, and the second bearing 220 is located between the bearing limiting member 230 and the blade support member 120.

[0052] 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 mounting hole 110 of the rotor hub 100, the bearing limiting member 230 can limit the second bearing 220, so that the second bearing 220 is always located on the second bearing fixing seat 111, and the second bearing 220 is prevented from moving axially along the root of the rotor blade 200.

[0053] See Figures 1-14 As shown, in an optional embodiment, a third bearing 240 is mounted on the rotor blade 200, and the third bearing 240 is located between the rotor hub 100 and the pitch transmission component 320.

[0054] Specifically, a third bearing 240 is fitted at the root of the rotor blade 200. The third bearing 240 is located between the rotor hub 100 and the pitch transmission component 320. By setting the third bearing 240, friction jamming between the pitch transmission component 320 and the side wall of the rotor hub 100 is avoided.

[0055] Specifically, the first bearing 201 and the second bearing 220 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 201, the third bearing 240, and the second bearing 220 according to implementation requirements.

[0056] See Figures 1-14As 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 rod 400, the end of the variable pitch 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 rod 400 and the pitch adjustment component 310.

[0057] In one of the optional embodiments of this invention, the pitch adjustment member 310 has a connecting channel 314 in the middle for connecting with the pitch control 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 pitch control 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 330, which can press the outer ring of the fourth bearing 410. A clamping ring 430 is threaded on the pitch control rod 400, which can press the inner ring of the fourth bearing 410.

[0058] Specifically, the pitch adjustment component 310 is driven by a lifting drive, which is a variable pitch servo, specifically a linear servo. The output end of the lifting drive 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 operating, it drives the variable pitch lever 400 to move up and down. The variable pitch lever 400, in turn, drives the pitch adjustment component 310 to move up and down. This movement causes the variable pitch swing arm 312 to swing, which in turn rotates the pitch transmission component 320. This rotation then drives the rotor blades 200 to rotate, thus achieving the variable pitch function.

[0059] It should be noted that a fourth bearing 410 is provided between the pitch control rod 400 and the pitch adjustment component 310. The pitch adjustment component 310 has a connecting channel 314 in its middle for connecting with the pitch control 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 pitch control rod 400 has an inner ring support 420 for supporting the inner ring of the fourth bearing 410. An end cap 330 is threaded into the connecting channel 314, and the end cap 330 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.

[0060] 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.

[0061] This embodiment provides an electric aircraft, including an electric aircraft pitch control structure.

[0062] Specifically, the electric aircraft provided in this embodiment has the advantages of the aforementioned variable pitch structure of electric aircraft compared with the prior art, which will not be elaborated here.

[0063] 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 structure for an electric aircraft, characterized in that, include: The rotor hub (100), rotor blades (200), and pitch control assembly (300); The rotor hub (100) has a blade mounting hole (110) on its circumferential sidewall, and the root of the rotor blade (200) is rotatably inserted into the blade mounting hole (110). The rotor hub (100) is fixedly provided with a rotor blade support (120) corresponding to the rotor blade mounting hole (110), and the first side (121) of the rotor blade support (120) is rotatably connected to the rotor blade (200). The pitch control assembly (300) includes a pitch adjustment component (310) and a pitch transmission component (320). The second side (123) of the blade support (120) 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 member (120); The pitch transmission component (320) is fixed relative to the rotor blade (200), and the pitch transmission component (320) 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 blade support component (120) under the drive of the lifting drive component, 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 structure for an electric aircraft according to claim 1, characterized in that, The first side (121) of the blade support (120) is provided with a first bearing mounting seat (122) for mounting the rotor blade (200). The rotor blade (200) is fitted with a first bearing (201), which is located inside the first bearing mounting seat (122).

3. The variable pitch structure for electric aircraft according to claim 2, characterized in that, The blade support (120) has a longitudinal guide slide (124) on its second side (123). The circumferential sidewall of the pitch adjustment member (310) is provided with a guide slider (311) that can be adapted to the guide slide (124).

4. The variable pitch structure for an electric aircraft 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 structure for an electric aircraft according to claim 4, characterized in that, The pitch transmission component (320) includes a connecting fork (321) and an offset rocker arm (322), which are integral components. 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), and the pitch adjustment component (310) drives the offset rocker arm (322) to swing up and down through the variable pitch swing arm (312).

6. The variable pitch structure for an electric aircraft according to claim 5, characterized in that, The rotor blade (200) has an assembly groove (210) at its root, 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.

7. The variable pitch structure for an electric aircraft according to claim 6, characterized in that, The connecting fork (321) is provided with a connecting hole (323) at one end away from the offset rocker arm (322), and the connecting fork (321) is fixed to the mounting groove (210) by connecting bolts passing through the connecting holes (323) on its two side walls.

8. The variable pitch structure for an electric aircraft according to claim 1, characterized in that, A second bearing (220) is fitted on the rotor blade (200), and a second bearing mounting seat (111) for mounting the second bearing (220) is provided in the blade mounting hole (110).

9. The variable pitch structure for an electric aircraft according to claim 8, characterized in that, The root of the rotor blade (200) is provided with a bearing limiting member (230) for limiting the second bearing (220), and the second bearing (220) is located between the bearing limiting member (230) and the blade support member (120).

10. The variable pitch structure for an electric aircraft according to claim 8, 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 (320).

11. The variable pitch structure for an electric aircraft according to any one of claims 1-10, 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).

12. The variable pitch structure for an electric aircraft according to claim 11, characterized in that, The pitch adjustment component (310) has a connecting channel (314) in the middle for connecting with the pitch control 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 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 (314) is threaded with an end cap (330), 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).

13. The variable pitch structure for an electric aircraft according to any one of claims 1-10, characterized in that, A reinforcing rib (125) is provided between each two adjacent blade support members (120).

14. An electric aircraft, characterized in that, Includes the electric aircraft pitch-changing structure as described in any one of claims 1-13.

Images