Automatic tilting devices and manned aircraft

Abstract

This application relates to the field of aircraft technology, and more particularly to an automatic swashplate and a manned aircraft. The automatic swashplate provided in this application includes a tilting swashplate, a first rotating component, and a second rotating component. During periodic pitch adjustment, the tilting swashplate tilts horizontally, causing the first rotating component to rotate around its own axis. The first rotating component then drives the second rotating component to rotate around its own axis. The transmission ratio between the second and first rotating components is greater than 1, therefore the rotation angle of the second rotating component is greater than that of the first rotating component, increasing the blade angle adjustment range and giving the automatic swashplate a larger angle adjustment range. The manned aircraft provided in this application, due to the inclusion of the aforementioned automatic swashplate, also has a large angle adjustment range, improving the aircraft's maneuverability and enhancing its ability to resist pitch, roll, and roll, thus adapting to the needs of use in harsh weather and complex environments.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more particularly to an automatic tilting device and a manned aircraft. Background Technology

[0002] An automatic swashplate is a specialized device for aircraft to change the tilt direction of the rotor and the tilt angle of the blades. Through the automatic swashplate, the collective pitch and cyclic pitch of the propeller can be adjusted.

[0003] The automatic tilting mechanism specifically includes a non-rotating ring and a rotating ring. The non-rotating ring is fitted around the outer circumference of the spherical sleeve and connected to the pitch control mechanism. The rotating ring is fitted around the outer circumference of the non-rotating ring via a bearing and connected to the blade clamping device. The pitch control mechanism can drive the non-rotating ring and the rotating ring to periodically tilt horizontally relative to the spherical sleeve. The rotating ring causes the blade angle of the blades in the blade clamping device to change periodically, thereby realizing the periodic pitch adjustment of the propeller.

[0004] However, existing automatic swashplates are limited by the structure of the rotating ring and spherical sleeve, which limits the range of blade angle adjustment. This, in turn, restricts the aircraft's ability to counter pitch, roll, and roll, making it unsuitable for use in complex environments. Summary of the Invention

[0005] This application provides an automatic tilting device and a manned aircraft, which can effectively solve the above-mentioned or other potential technical problems.

[0006] The first aspect of this application provides an automatic tilter, including a tilting swashplate, a first rotating member, and a second rotating member; the tilting swashplate is rotatably connected to the outer periphery of a spherical sleeve and is configured to tilt horizontally relative to the spherical sleeve; the first rotating member is rotatably connected to a propeller hub and connected to the tilting swashplate; the second rotating member is rotatably connected to the propeller hub and connected to a blade holder; the second rotating member is rotatably connected to the first rotating member, and the transmission ratio between the second rotating member and the first rotating member is greater than 1.

[0007] In an optional embodiment according to the first aspect, the number of first rotating members and second rotating members is at least two, and each set of first rotating members and second rotating members is connected to a propeller.

[0008] In an optional embodiment according to the first aspect, a cover is provided on the outer side of the first rotating member and the second rotating member, the cover having a cavity for accommodating the first rotating member and the second rotating member, the first rotating member and the second rotating member being encapsulated within the cover, and the cover being connected to the propeller hub.

[0009] In an optional embodiment according to the first aspect, the first rotating member includes a first rotating portion and a first engaging portion, the first rotating portion being connected to a tilting swashplate and rotatably connected to a propeller hub; the second rotating member includes a second rotating portion and a second engaging portion, the second rotating portion being rotatably connected to a propeller hub and connected to a blade clamping member, the second engaging portion engaging with the first engaging portion.

[0010] In an optional embodiment according to the first aspect, the first meshing portion includes a first gear, the second meshing portion includes a second gear, the first gear and the second gear mesh and drive each other, the first gear drives the second gear to rotate; and the transmission ratio between the second gear and the first gear is greater than 1.

[0011] In an optional embodiment according to the first aspect, the first rotating part includes a first rotating shaft rotatably connected to the propeller hub, and the end of the first rotating shaft is connected to a swashplate; a first gear is fitted around the outer periphery of the first rotating shaft so that when the swashplate drives the first rotating shaft to rotate, it can drive the first gear to rotate synchronously; the second rotating part includes a second rotating shaft rotatably connected to the propeller hub, and the end of the second rotating shaft is connected to a blade holder; a second gear is fitted around the outer periphery of the second rotating shaft so that when the swashplate drives the first rotating shaft to rotate, the first gear and the second gear mesh and drive the second rotating shaft to rotate, and the second rotating shaft drives the blade holder to rotate.

[0012] In an alternative embodiment according to the first aspect, the first gear includes sector teeth.

[0013] In an optional embodiment according to the first aspect, the tilting swashplate includes a fixed ring, a moving ring, and at least two rocker arms; the fixed ring is rotatably connected to the outer periphery of a spherical sleeve and connected to a pitch control mechanism of the aircraft, the pitch control mechanism being used to drive the fixed ring to tilt horizontally relative to the spherical sleeve; the moving ring is rotatably connected to the outer periphery of the fixed ring via a bearing; at least two rocker arms are equally spaced on the outer periphery of the moving ring, and one end of each rocker arm is rotatably connected to the moving ring, and the other end is connected to a first rotating shaft.

[0014] In an optional embodiment according to the first aspect, the fixed ring is provided with an insertion hole on the side near the spherical sleeve, and a guide groove is provided at the corresponding position on the spherical sleeve; a positioning pin is provided in the insertion hole, one end of the positioning pin is elastically connected to the insertion hole by a spring, and the other end is slidably connected to the guide groove; when the fixed ring is horizontally inclined relative to the spherical sleeve, the positioning pin can slide along the guide groove.

[0015] In an optional embodiment according to the first aspect, the fixed ring includes a first fixed ring and a second fixed ring, which are fixedly connected along the axial direction; the second fixed ring is connected to a pitch mechanism; the first fixed ring has a first hemispherical groove on the side near the spherical sleeve, and the second fixed ring has a second hemispherical groove on the side near the spherical sleeve; the first fixed ring and the second fixed ring are fastened together so that the first hemispherical groove and the second hemispherical groove form a spherical groove; the shape and size of the spherical groove are adapted to the outer dimensions of the spherical sleeve, and the first fixed ring and the second fixed ring are fitted onto the outer periphery of the spherical sleeve through the formed spherical groove.

[0016] In an optional embodiment according to the first aspect, a first flange is provided on one side of the first fixed ring, and a second flange is provided on the side of the second fixed ring away from the first fixed ring. The moving ring is rotatably fitted onto the outer periphery of the first and second fixed rings via a bearing, and the two ends of the bearing in the axial direction are respectively defined between the first flange and the second flange.

[0017] In an optional embodiment according to the first aspect, an inner flange is further provided above the rotating ring, and the inner flange is thrust-connected to the upper end face of the bearing; a limiting edge is provided below the rotating ring, the limiting edge is folded inward, and the limiting edge is thrust-connected to the lower end face of the bearing, the inner flange and the limiting edge together provide axial positioning for the rotating ring.

[0018] A second aspect of this application also provides a manned aircraft including the aforementioned automatic tilter.

[0019] The automatic tilting device and manned aircraft provided in this application have at least the following technical effects:

[0020] This application provides an automatic swashplate and a manned aircraft. The automatic swashplate includes a tilting swashplate, a first rotating component, and a second rotating component. During periodic pitch adjustment, the tilting swashplate tilts horizontally, causing the first rotating component to rotate around its own axis. The first rotating component then drives the second rotating component to rotate around its own axis. The transmission ratio between the second and first rotating components is greater than 1, therefore the rotation angle of the second rotating component is greater than that of the first rotating component, increasing the blade angle adjustment range and giving the automatic swashplate a larger angle adjustment range. The manned aircraft provided in this application, due to the inclusion of the aforementioned automatic swashplate, also has a large angle adjustment range, improving the aircraft's maneuverability and enhancing its ability to resist pitch, roll, and roll, thus adapting to the needs of use in harsh weather and complex environments.

[0021] Additional advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0022] The above and other objects, features, and advantages of embodiments of this application will become more readily understood through the following detailed description with reference to the accompanying drawings. In the drawings, several embodiments of this application will be described by way of example and non-limitation, wherein:

[0023] Figure 1 This is a schematic diagram of the structure of the automatic tilter and propeller hub provided in the embodiments of this application;

[0024] Figure 2 This is a schematic diagram of the structure of the automatic tilter provided in the embodiments of this application;

[0025] Figure 3 A schematic diagram of the tilting swashplate of the automatic tilter provided in the embodiments of this application;

[0026] Figure 4 for Figure 3 Cross-sectional view of a swashplate;

[0027] Figure 5 This is a schematic diagram of the fixed ring structure of the automatic tilter provided in the embodiments of this application;

[0028] Figure 6 for Figure 5 Cross-sectional view of the central ring;

[0029] Figure 7 This is a schematic diagram of the dynamic ring of the automatic tilter provided in the embodiments of this application.

[0030] Explanation of reference numerals in the attached figures:

[0031] 1. Inclined swashplate;

[0032] 11. Moving ring; 111. Inner flange; 112. Limiting edge;

[0033] 12. Fixed ring; 121. First fixed ring; 122. Second fixed ring; 123. First flange; 124. Second flange; 125. Oil guide groove;

[0034] 13. Rocker arm; 14. Positioning pin;

[0035] 2. First rotating component;

[0036] 21. First rotating part; 22. First meshing part;

[0037] 3. Second rotating component;

[0038] 31. Second rotating part; 32. Second meshing part;

[0039] 4. Propeller hub;

[0040] 5. Spherical sleeve; 51. Guide groove;

[0041] 6. Cover body. Detailed Implementation

[0042] The embodiments of this application are described in detail below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application.

[0043] In the description of this application, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "vertical," "horizontal," "top," "bottom," "inner," "outer," "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 application 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 application.

[0044] 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 at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0045] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," "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; 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, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0046] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0047] The automatic swashplate specifically includes a non-rotating ring and a rotating ring. The non-rotating ring is fitted around the outer circumference of a spherical sleeve and connected to a pitch control mechanism. The rotating ring is fitted around the outer circumference of the non-rotating ring via a bearing and connected to a blade clamping device. The pitch control mechanism can cause the non-rotating ring and the rotating ring to periodically tilt horizontally relative to the spherical sleeve. The rotating ring causes the blade angle of the blades in the blade clamping device to change periodically, thereby achieving periodic pitch adjustment of the propeller. However, existing automatic swashplates are limited by the structure of the rotating ring and the spherical sleeve, resulting in a limited range of blade angle adjustment. This, in turn, limits the aircraft's ability to counteract pitch, roll, and roll, making it unsuitable for use in complex environments.

[0048] In view of this, the automatic swashplate provided in this application includes a swashplate, a first rotating member, and a second rotating member. The swashplate is configured to tilt horizontally relative to a spherical sleeve; the first rotating member is rotatably connected to the rotor hub and to the swashplate; the second rotating member is rotatably connected to the rotor hub and to the blade clamping member; the second rotating member is rotatably connected to the first rotating member, and the transmission ratio between the second and first rotating members is greater than 1. When the automatic swashplate is in periodic pitch adjustment, the swashplate tilts horizontally, causing the first rotating member to rotate around its own axis. The first rotating member then causes the second rotating member to rotate around its own axis. Since the transmission ratio between the second and first rotating members is greater than 1, the rotation angle of the second rotating member is greater than that of the first rotating member, effectively increasing the blade angle adjustment range. This gives the automatic swashplate a larger angle adjustment range, thereby improving the maneuverability of the aircraft using the aforementioned automatic swashplate and enhancing its ability to resist pitch, roll, and roll, making it suitable for use in harsh weather and complex environments.

[0049] Please refer to Figure 1 and Figure 2The automatic tilter provided in this application embodiment includes a tilting swashplate 1, a first rotating member 2, and a second rotating member 3. The tilting swashplate 1 is rotatably connected to the outer periphery of a spherical sleeve 5, and the tilting swashplate 1 is configured to tilt horizontally relative to the spherical sleeve 5. The first rotating member 2 is rotatably connected to a propeller hub 4 and is connected to the tilting swashplate 1. The second rotating member 3 is rotatably connected to the propeller hub 4 and is connected to a blade clamping member. The second rotating member 3 is rotatably connected to the first rotating member 2, and the transmission ratio between the second rotating member 3 and the first rotating member 2 is greater than 1.

[0050] The automatic tilter provided in this embodiment includes a tilting swashplate 1, a first rotating member 2, and a second rotating member 3. The tilting swashplate 1 is configured to tilt horizontally relative to a spherical sleeve 5; the first rotating member 2 is rotatably connected to a propeller hub 4 and connected to the tilting swashplate 1; the second rotating member 3 is rotatably connected to the propeller hub 4 and connected to a blade clamping member; the second rotating member 3 is rotatably connected to the first rotating member 2, and the transmission ratio between the second rotating member 3 and the first rotating member 2 is greater than 1. When the automatic swashplate is in periodic pitch adjustment, the swashplate 1 tilts horizontally, causing the first rotating component 2 to rotate around its own axis. The first rotating component 2 then drives the second rotating component 3 to rotate around its own axis. Since the transmission ratio between the second rotating component 3 and the first rotating component 2 is greater than 1, the rotation angle of the second rotating component 3 is greater than that of the first rotating component 2. This effectively increases the adjustment range of the blade angle, giving the automatic swashplate a larger angle adjustment range. This, in turn, improves the maneuverability of the aircraft using the aforementioned automatic swashplate and enhances the aircraft's ability to resist pitch, roll, and roll, making it suitable for use in harsh weather and complex environments.

[0051] It should be noted that in this embodiment, the swashplate 1 of the automatic swashplate in the related art is directly connected to the blade clamping component. The swashplate 1 moves horizontally and periodically around the spherical sleeve 5, causing the blade clamping component to adjust the blade angle. That is, the rotation angle of its first rotating component 2 is the blade angle of the automatic swashplate in the related art. In this embodiment, by setting the second rotating component 3 to cooperate with the first rotating component 2, and by adapting the second rotating component 3 and the first rotating component 2 to other components of the aircraft, the swashplate 1 moves horizontally and tilts, causing the first rotating component 2 to rotate around its own axis. The first rotating component 2 then causes the second rotating component 3 to rotate around its own axis. Since the transmission ratio between the second rotating component 3 and the first rotating component 2 is greater than 1, the rotation angle of the second rotating component 3 is greater than the rotation angle of the first rotating component 2. Therefore, the automatic swashplate proposed in this embodiment can make the blade angle greater than that in the related art.

[0052] In an optional exemplary embodiment, the number of first rotating members 2 and second rotating members 3 is at least two, and each set of first rotating members 2 and second rotating members 3 is connected to a propeller.

[0053] It should be noted that in this embodiment, the number of the first rotating member 2 and the second rotating member 3 is at least two, and each set of the first rotating member 2 and the second rotating member 3 is connected to a propeller. That is to say, in this application, the specific number of the first rotating member 2 and the second rotating member 3 is not limited, and the specific number can be adaptively set according to the user's needs.

[0054] In an optional exemplary embodiment, a cover 6 is provided on the outer side of the first rotating member 2 and the second rotating member 3. The cover 6 has a cavity for accommodating the first rotating member 2 and the second rotating member 3. The first rotating member 2 and the second rotating member 3 are encapsulated in the cover 6, and the cover 6 is connected to the propeller hub 4.

[0055] It should be noted that, specifically, in this embodiment, a cover 6 is provided on the outside of the first rotating member 2 and the second rotating member 3, and the first rotating member 2 and the second rotating member 3 are encapsulated in the cover 6. This arrangement can effectively protect the first rotating member 2 and the second rotating member 3, prevent sand and dust from entering and causing wear on the first rotating member 2 and the second rotating member 3, thereby extending the service life of the first rotating member 2 and the second rotating member 3. The cover 6 also makes the overall structure of the automatic tilter aesthetically pleasing and neat.

[0056] In an optional exemplary embodiment, the first rotating member 2 includes a first rotating part 21 and a first engaging part 22. The first rotating part 21 is connected to the tilting swashplate 1 and is rotatably connected to the propeller hub 4. The second rotating member 3 includes a second rotating part 31 and a second engaging part 32. The second rotating part 31 is rotatably connected to the propeller hub 4 and is connected to the blade clamping member. The second engaging part 32 engages with the first engaging part 22.

[0057] It should be noted that, specifically, in this embodiment, the first rotating member 2 is configured to include a first rotating part 21 and a first engaging part 22, and the second rotating member 3 is configured to include a second rotating part 31 and a second engaging part 32, with the second engaging part 32 engaging with the first engaging part 22. With this configuration, the first rotating member 2 and the second rotating member 3 are rotatably connected through meshing transmission. At the same time, the meshing transmission has the technical effect of transmission stability, thus effectively ensuring the stability and safety of the automatic tilter operation.

[0058] Specifically, during the operation of the automatic swashplate, when the swashplate 1 tilts horizontally, the swashplate 1 drives the first rotating part 21 to rotate around its own axis. The first rotating part 21 drives the first meshing part 22 to mesh with the second meshing part 32. The second meshing part 32 drives the second rotating part 31 to rotate around its own axis, thereby driving the blade holder connected to it and the blade held in the blade holder to rotate around its own axis to adjust the blade angle of the blade.

[0059] In an optional exemplary embodiment, the first meshing part 22 includes a first gear, the second meshing part 32 includes a second gear, the first gear meshes with the second gear for transmission, the first gear drives the second gear to rotate; and the transmission ratio between the second gear and the first gear is greater than 1.

[0060] It should be noted that, specifically, in this embodiment, the first meshing part 22 is configured to include a first gear, and the second meshing part 32 is configured to include a second gear. The first gear and the second gear mesh and transmit power, with the first gear driving the second gear to rotate. In other words, the first gear is the driving gear, and the second gear is the driven gear. This gear transmission mechanism effectively ensures the smoothness of the transmission, thereby ensuring the stability of the automatic swashplate operation. Furthermore, setting the transmission ratio between the second gear and the first gear to be greater than 1 effectively amplifies the blade angle.

[0061] In an optional exemplary embodiment, the first rotating part 21 includes a first rotating shaft, which is rotatably connected to the propeller hub 4, and the end of the first rotating shaft is connected to the tilting swashplate 1; a first gear is fitted on the outer periphery of the first rotating shaft so that when the tilting swashplate 1 drives the first rotating shaft to rotate, it can drive the first gear to rotate synchronously.

[0062] Specifically, the first gear is fitted onto the outer circumference of the first rotating shaft and fixed by a pin. When the tilting swashplate 1 drives the first rotating shaft to rotate, it drives the first gear to rotate synchronously.

[0063] The second rotating part 31 includes a second rotating shaft, which is rotatably connected to the rotor hub 4. The end of the second rotating shaft is connected to the blade clamping member. A second gear is fitted on the outer circumference of the second rotating shaft so that when the tilting swashplate 1 drives the first rotating shaft to rotate, the first gear and the second gear mesh and drive the second rotating shaft to rotate, and the second rotating shaft drives the blade clamping member to rotate.

[0064] Specifically, the second gear is fitted onto the outer circumference of the second shaft and fixed by a pin. When the tilting swashplate 1 drives the first shaft to rotate, the first gear and the second gear mesh and drive each other. The second gear drives the second shaft to rotate, and the second shaft drives the blade holder to rotate, thereby driving the blades held in the blade holder to adjust the blade angle.

[0065] In an optional exemplary embodiment, the first gear includes sector teeth. The sector tooth structure is configured to reduce the overall weight of the autoslope while maintaining the transmission ratio, thereby reducing the weight of the aircraft including the autoslope, to meet the requirements for lightweight and miniaturized aircraft.

[0066] It should also be noted that the blade clamping component is not a component included in the automatic tilter provided in the embodiments of this application. The blade clamping component is mentioned to illustrate the working principle of the automatic tilter provided in the embodiments of this application. Therefore, this application does not specifically limit the structure of the blade clamping component, as long as the structure of the blade clamping component is compatible with the second rotating shaft.

[0067] Please refer to Figure 3 In an optional exemplary embodiment, the tilting swashplate 1 includes a fixed ring 12, a moving ring 11, and at least two rocker arms 13; the fixed ring 12 is rotatably connected to the outer periphery of the spherical sleeve 5 and connected to the pitch mechanism of the aircraft, the pitch mechanism being used to drive the fixed ring 12 to tilt horizontally relative to the spherical sleeve 5; the moving ring 11 is rotatably connected to the outer periphery of the fixed ring 12 via a bearing; at least two rocker arms 13 are equally spaced on the outer periphery of the moving ring 11, and one end of the rocker arm 13 is rotatably connected to the moving ring 11, and the other end is connected to the first rotating shaft.

[0068] Specifically, when performing periodic pitch adjustment, the pitch mechanism drives the fixed ring 12 to periodically tilt horizontally relative to the spherical sleeve 5. The fixed ring 12 drives the moving ring 11 to synchronously perform periodic horizontal tilting motion. Through the rocker arm 13, the first rotating shaft connected to the rocker arm 13 rotates around its own axis, thereby driving the first gear and the second gear to mesh and transmit power. This drives the blade clamping member and the blade clamped in the blade clamping member to rotate around its own axis, so as to amplify the blade angle.

[0069] Please refer to Figure 5 and Figure 6 In an optional exemplary embodiment, the fixed ring 12 is provided with an insertion hole on the side near the spherical sleeve 5, and a guide groove 51 is provided at the corresponding position on the spherical sleeve 5; a positioning pin 14 is provided in the insertion hole, one end of the positioning pin 14 is elastically connected to the insertion hole by a spring, and the other end is slidably connected to the guide groove 51; when the fixed ring 12 is horizontally inclined relative to the spherical sleeve 5, the positioning pin 14 can slide along the guide groove 51.

[0070] It should be noted that an insertion hole is provided on the fixed ring 12, and a guide groove 51 is provided at a corresponding position on the spherical sleeve 5; and a positioning pin 14 is provided in the insertion hole. One end of the positioning pin 14 is elastically connected to the insertion hole by a spring, and the other end is slidably connected to the guide groove 51. When the fixed ring 12 is horizontally inclined relative to the spherical sleeve 5, the positioning pin 14 can slide along the guide groove 51. This arrangement can effectively prevent the fixed ring 12 from rotating relative to the spherical sleeve 5.

[0071] If the fixed ring 12 rotates relative to the spherical sleeve 5, it will cause the moving ring 11 to rotate relative to it. The moving ring 11 also rotates synchronously with the propeller hub 4. If the rotation direction is opposite, it will cause the rocker arm 13 to be torn and damaged. Therefore, the positioning pin 14 and guide groove 51 provided in this embodiment can prevent the rocker arm 13 from being torn and damaged, thereby extending the service life of the automatic tilter.

[0072] Please refer to Figure 4 and Figure 5 In an optional exemplary embodiment, the fixed ring 12 includes a first fixed ring 121 and a second fixed ring 122, the first fixed ring 121 and the second fixed ring 122 being fixedly connected along the axial direction; the second fixed ring 122 is connected to the pitch mechanism; the first fixed ring 121 is provided with a first hemispherical groove on the side near the spherical sleeve 5, and the second fixed ring 122 is provided with a second hemispherical groove on the side near the spherical sleeve 5, the first fixed ring 121 and the second fixed ring 122 being fastened together so that the first hemispherical groove and the second hemispherical groove constitute a spherical groove; the shape and size of the spherical groove are adapted to the outer dimensions of the spherical sleeve 5, and the first fixed ring 121 and the second fixed ring 122 are fitted onto the outer periphery of the spherical sleeve 5 through the spherical groove formed.

[0073] It should be noted that, specifically, in this embodiment, the fixed ring 12 is configured to include a first fixed ring 121 and a second fixed ring 122, as shown in... Figure 4 In the example shown, the first fixed ring 121 is located above the second fixed ring 122 and is fixedly connected to the second fixed ring 122 by bolts. The second fixed ring 122 is used to connect to the pitch-changing mechanism, and a mounting hole for connecting the pitch-changing mechanism is correspondingly provided on the second fixed ring 122. The first fixed ring 121 has a first hemispherical groove on the side near the spherical sleeve 5, and the second fixed ring 122 has a second hemispherical groove on the side near the spherical sleeve 5. The first fixed ring 121 and the second fixed ring 122 are fastened together to form a spherical groove. The shape and size of the spherical groove are adapted to the outer dimensions of the spherical sleeve 5. The first fixed ring 121 and the second fixed ring 122 are fitted onto the outer periphery of the spherical sleeve 5 through the spherical groove, so that the fixed ring 121 and the spherical sleeve 5 form a spherical pair.

[0074] In an optional exemplary embodiment, an oil guide groove 125 is further provided at the engagement point of the first fixed ring 121 and the second fixed ring 122. The oil guide groove 125 is filled with grease, which is used to lubricate the ball pair composed of the fixed ring 12 and the ball sleeve 5.

[0075] In an optional exemplary embodiment, a first flange 123 is provided on one side of the first fixed ring 121, and a second flange 124 is provided on the side of the second fixed ring 122 away from the first fixed ring 121. The moving ring 11 is rotatably fitted onto the outer periphery of the first fixed ring 121 and the second fixed ring 122 via a bearing, and the two ends of the bearing in the axial direction are respectively defined between the first flange 123 and the second flange 124.

[0076] It should be noted that a first flange 123 is provided on one side of the first fixed ring 121, and a second flange 124 is provided on the side of the second fixed ring 122 away from the first fixed ring 121. Figure 5 In the indicated direction, the first flange 123 is located above and the second flange 124 is located below. The moving ring 11 is rotatably fitted onto the outer periphery of the first fixed ring 121 and the second fixed ring 122 via bearings, thereby limiting the two ends of the bearing in the axial direction between the first flange 123 and the second flange 124, and the first flange 123 and the second flange 124 provide axial positioning for the bearing.

[0077] Please refer to Figure 7 In an optional exemplary embodiment, an inner flange 111 is further provided above the rotating ring 11, and the inner flange 111 is thrust-connected to the upper end face of the bearing; a limiting edge 112 is provided below the rotating ring 11, the limiting edge 112 is folded inward, and the limiting edge 112 is thrust-connected to the lower end face of the bearing, and the inner flange 111 and the limiting edge 112 together provide axial positioning for the rotating ring 11.

[0078] It should be noted that, in the direction shown in the figure, an inner flange 111 is also provided above the rotating ring 11, and the inner flange 111 is thrust-connected to the upper end face of the bearing. A limiting edge 112 is provided below the rotating ring 11. When the bearing is press-fitted, the limiting edge 112 is folded inward (not shown in the figure), and the folded limiting edge 112 is thrust-connected to the lower end face of the bearing to achieve axial positioning of the rotating ring 11.

[0079] It is understandable that the connection between the moving ring 11 and the bearing, and the connection between the bearing and the fixed ring 12, are achieved through the thrust connection between the moving ring 11 and the fixed ring 12. The moving ring 11 can move horizontally in sync with the fixed ring 12, thereby driving the rocker arm 13 connected to the moving ring 11 to move. The rocker arm 13 then drives the first rotating shaft connected to it to rotate around its own axis.

[0080] In an optional exemplary embodiment, the first fixed ring 121 and the second fixed ring 122 are further provided with through-holes for reducing weight. The holes are used to reduce the mass of the fixed ring 12, thereby reducing the overall weight of the automatic tilting device, so that the aircraft using the automatic tilting device can meet the development requirements of lightweighting and miniaturization.

[0081] This application also provides a manned aircraft, including the aforementioned automatic tilter.

[0082] The manned aircraft provided in this application includes the aforementioned automatic swashplate, and therefore also has the aforementioned increased blade angle adjustment range. According to the user's needs, the flight attitude of the manned aircraft can be adjusted by periodic pitch adjustment to improve the manned aircraft's ability to resist pitch, roll and roll, thereby improving the aircraft's maneuverability and making it suitable for flight requirements in strong airflow and complex environments.

[0083] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application 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 application.

[0084] It should also be noted that the various specific technical features described in the above embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, this application will not describe the various possible combinations separately.

Claims

1. An automatic tilting device, characterized in that, Includes a tilting swashplate, a first rotating component, and a second rotating component; The swashplate is rotatably connected to the outer periphery of the spherical sleeve, and the swashplate is configured to move horizontally tilted relative to the spherical sleeve. The first rotating component is rotatably connected to the propeller hub and is connected to the tilting swashplate; The second rotating member is rotatably connected to the blade hub and connected to the blade clamping member; The second rotating member is rotatably connected to the first rotating member, and the transmission ratio between the second rotating member and the first rotating member is greater than 1; The first rotating component includes a first rotating part, the first rotating part includes a first rotating shaft, the first rotating shaft is rotatably connected to the propeller hub, and the end of the first rotating shaft is connected to the tilting swashplate; The tilting swashplate includes a fixed ring, a moving ring, and at least two rocker arms; The fixed ring is rotatably connected to the outer periphery of the spherical sleeve and connected to the pitch mechanism of the aircraft. The pitch mechanism is used to drive the fixed ring to move horizontally relative to the spherical sleeve. The moving ring is rotatably connected to the outer periphery of the fixed ring via a bearing; The at least two rocker arms are equally spaced on the outer periphery of the moving ring, and one end of each rocker arm is rotatably connected to the moving ring, while the other end is connected to the first rotating shaft.

2. The automatic tilter according to claim 1, characterized in that, The number of the first rotating component and the second rotating component is at least two, and each group of the first rotating component and the second rotating component is connected to a propeller.

3. The automatic tilter according to claim 1, characterized in that, The first rotating member and the second rotating member are provided with a cover on their outer sides. The cover has a cavity for accommodating the first rotating member and the second rotating member. The first rotating member and the second rotating member are encapsulated in the cover, and the cover is connected to the propeller hub.

4. The automatic tilter according to claim 1, characterized in that, The first rotating component includes a first engaging portion, which is connected to the tilting swashplate and is rotatably connected to the propeller hub. The second rotating member includes a second rotating part and a second engaging part. The second rotating part is rotatably connected to the blade hub and is connected to the blade clamping member. The second engaging part engages with the first engaging part.

5. The automatic tilter according to claim 4, characterized in that, The first meshing part includes a first gear, and the second meshing part includes a second gear. The first gear meshes with the second gear, and the first gear drives the second gear to rotate. The transmission ratio between the second gear and the first gear is greater than 1.

6. The automatic tilter according to claim 5, characterized in that, The first gear is fitted onto the outer circumference of the first rotating shaft so that when the tilting swashplate drives the first rotating shaft to rotate, it can drive the first gear to rotate synchronously. The second rotating part includes a second rotating shaft, which is rotatably connected to the propeller hub. The end of the second rotating shaft is connected to the blade clamping member. The second gear is fitted around the outer circumference of the second rotating shaft so that when the tilting swashplate drives the first rotating shaft to rotate, the first gear and the second gear mesh and drive the second rotating shaft to rotate, and the second rotating shaft drives the blade clamping member to rotate.

7. The automatic tilter according to claim 5, characterized in that, The first gear includes sector teeth.

8. The automatic tilter according to claim 1, characterized in that, The fixed ring has an insertion hole on the side near the spherical sleeve, and a guide groove is provided on the spherical sleeve at the corresponding position; A positioning pin is provided in the insertion hole. One end of the positioning pin is elastically connected to the insertion hole by a spring, and the other end is slidably connected to the guide groove. When the fixed ring is horizontally inclined relative to the spherical sleeve, the positioning pin can slide along the guide groove.

9. The automatic tilter according to claim 1, characterized in that, The fixed ring includes a first fixed ring and a second fixed ring, the first fixed ring and the second fixed ring being fixedly connected along the axial direction; the second fixed ring is connected to the pitch mechanism. The first fixed ring has a first hemispherical groove on the side near the spherical sleeve, and the second fixed ring has a second hemispherical groove on the side near the spherical sleeve. The first fixed ring and the second fixed ring are fastened together so that the first hemispherical groove and the second hemispherical groove form a spherical groove. The shape and size of the spherical groove are adapted to the outer size of the spherical sleeve. The first fixed ring and the second fixed ring are fitted onto the outer periphery of the spherical sleeve through the spherical groove.

10. The automatic tilter according to claim 9, characterized in that, The first fixed ring has a first flange on one side, and the second fixed ring has a second flange on the side away from the first fixed ring. The moving ring is rotatably fitted onto the outer periphery of the first fixed ring and the second fixed ring via a bearing. The two ends of the bearing are respectively defined between the first flange and the second flange in the axial direction.

11. The automatic tilter according to claim 10, characterized in that, An inner flange is also provided above the moving ring, and the inner flange is thrust-connected to the upper end face of the bearing. A limiting edge is provided below the moving ring. The limiting edge is folded inward and is thrust-connected to the lower end face of the bearing. The inward fold and the limiting edge together position the moving ring axially.

12. A manned aircraft, characterized in that, Includes the automatic tilter according to any one of claims 1 to 11.

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