Tiltrotor system and vertical take-off and landing aircraft

Abstract

The application relates to a tilt-rotor system and a vertical take-off and landing aircraft. The tilt-rotor system comprises a cabin body, a tilt-rotor shaft assembly and a tilt motor, the tilt-rotor shaft assembly and the tilt motor are both installed on the cabin body, the tilt-rotor shaft assembly comprises a tilt-rotor shaft, the tilt-rotor shaft is fixedly connected with a fuselage, the tilt motor is located outside the cabin body, the tilt motor comprises an extension shaft, the extension shaft is rotationally connected with the tilt-rotor shaft, and the tilt motor is configured to drive the cabin body to tilt relative to the tilt-rotor shaft when the extension shaft of the tilt motor is extended or retracted. The tilt-rotor system and the vertical take-off and landing aircraft provided by the application can realize lightweight.

Description

Technical Field

[0001] This application relates to the field of aviation technology, specifically to a tiltrotor system and a vertical takeoff and landing aircraft. Background Technology

[0002] In recent years, vertical takeoff and landing (VTOL) aircraft, as the core carrier of urban air transportation, have become a research hotspot in the aviation field. Compared with traditional fixed-wing aircraft or helicopters, VTOL aircraft can take off and land flexibly in limited spaces through efficient switching between vertical takeoff and landing modes and cruise modes, thus improving ease of use.

[0003] Vertical takeoff and landing (VTOL) aircraft include a tiltrotor system, which is the core power and lift system of the VTOL aircraft. The tiltrotor system provides lift in VTOL mode and converts to horizontal thrust in cruise mode.

[0004] Existing tiltrotor systems are relatively heavy and have shortcomings in weight control. Utility Model Content

[0005] Therefore, it is necessary to provide a lightweight tiltrotor system and vertical takeoff and landing aircraft to address the above problems.

[0006] A tiltrotor system includes a cabin, a tilt axis assembly, and a tilt motor. The tilt axis assembly and the tilt motor are both mounted on the cabin. The tilt axis assembly includes a tilt axis, which is fixedly connected to the fuselage. The tilt motor is located outside the cabin and includes a telescopic shaft, which is rotatably connected to the tilt axis. The tilt motor is configured to drive the cabin to tilt relative to the tilt axis when its telescopic shaft extends or retracts.

[0007] In some embodiments, the cabin extends along a first direction, the tilting shaft assembly is mounted at one end of the cabin along the first direction, and the tilting shaft passes through the cabin along a second direction intersecting the first direction, and the tilting motor is disposed on one side of the cabin along the second direction; The cabin has a first sidewall and a second sidewall disposed opposite to each other along the second direction, the first sidewall being disposed toward the tilt motor; at least part of the first sidewall is recessed inward along the direction toward the second sidewall to form an accommodating space, and the tilt shaft passes through the accommodating space.

[0008] In some embodiments, the first sidewall includes a first sub-surface, a second sub-surface, and a third sub-surface that are sequentially connected along the first direction. The first sub-surface is away from the tilt axis relative to the second sub-surface and the third sub-surface. The tilt motor is mounted on the first sub-surface. The second sub-surface and the third sub-surface are both recessed relative to the first sub-surface in a direction toward the second sidewall and define an accommodating space with the plane where the first sub-surface is located.

[0009] In some embodiments, the tilt rotor system further includes a rotary motor, which is disposed along the first direction at one end of the cabin away from the tilt axis, and the central axis of the rotary motor is spaced apart from the central axis of the tilt axis in a third direction; The third direction is perpendicular to the second direction and intersects with the first direction.

[0010] In some embodiments, the tilt rotor system further includes a plurality of first supports, all of which surround to form a first mounting space, with the end of the cabin away from the tilt axis and the rotary motor inserted into the first mounting space, and the first supports being fixedly connected to the cabin and the rotary motor.

[0011] In some embodiments, the cabin body has a cavity, and one end of the cabin body extending into the first installation space has a first opening communicating with the cavity; The tiltrotor system also includes a second support, which is inserted into the cavity through the first opening. The second support includes a main body and a plurality of connecting parts arranged circumferentially along the main body. All the connecting parts are fixedly connected to the cabin.

[0012] In some embodiments, the main body is provided with a hollowed-out portion, and all the connecting portions surround to form a second installation space; The tilt rotor system also includes a fan and a radiator. The fan is located between the rotary motor and the cabin, and the radiator is located in the second installation space. Both the fan and the radiator are aligned with the hollow portion. The cabin has a second opening on the end face away from the first opening along the first direction or on at least one side wall of the cabin along the second direction. The cavity communicates with the second opening to form a heat dissipation channel.

[0013] In some embodiments, the cabin is a carbon fiber component, and / or the wall thickness of the cabin is H, where 3mm ≤ H ≤ 5mm.

[0014] In some embodiments, the cabin extends along a first direction, and the sidewall of the cabin along a second direction intersecting the first direction is provided with mounting holes; The tilting shaft assembly also includes a rocker arm and a bearing unit. The bearing unit includes a bearing and a bearing housing. The bearing housing is disposed in the mounting hole and fixedly connected to the cabin body. The bearing is located in the bearing housing and sleeved on the tilting shaft. The rocker arm and the tilting motor are located on the same side of the cabin body, and one end of the rocker arm is fixedly connected to the tilting shaft, while the other end of the rocker arm is rotatably connected to the telescopic shaft.

[0015] A vertical takeoff and landing aircraft, comprising: fuselage; and As described in any of the above embodiments, in the tilt rotor system, the tilt motor and the fuselage are located on the same side of the cabin, and the tilt shaft is fixedly connected to the fuselage.

[0016] Compared with the prior art, this application has the following beneficial effects: The aforementioned tiltrotor system and vertical takeoff and landing (VTOL) aircraft, through the design of the cabin, tilt axis assembly, and tilt motor, and the cooperation of the tilt axis assembly and tilt motor, can achieve adjustment of the tilt angle of the tiltrotor system, enabling the aircraft to switch between cruise mode and VTOL mode. Furthermore, placing the tilt motor outside the cabin, compared to placing it inside, reduces the volume and size of the cabin, thereby contributing to a reduction in the weight of the tiltrotor system and achieving a lightweight design. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the tilt rotor system in one embodiment of this application; Figure 2 for Figure 1 The diagram shows a front view of the tiltrotor system. Figure 3 for Figure 1 A top view of the tiltrotor system shown; Figure 4 for Figure 1 The diagram shows the structural schematic of the tilt shaft assembly in the tilt rotor system. Figure 5 for Figure 1 The diagram shows the structural arrangement of the cabin with the first and second supports in the tiltrotor system. Figure 6 for Figure 1 The diagram shows a cross-sectional view of the rotating motor, fan, radiator, first support, second support, and cabin assembly in the tiltrotor system. Figure 7 for Figure 1 The diagram shows a structural schematic of the tilt rotor system in which all the first supports enclose the first installation space. Figure 8 for Figure 1 The diagram shows the structure of the second support in the tilt rotor system.

[0018] Icon labels: 10. Tiltrotor system; 11. Rotary motor; 12. Fan; 13. Radiator; 14. First support frame; 15. Second support frame; 16. Cabin; 17. Tilting motor; 18. Tilting shaft assembly; 141. First installation space; 151. Main body; 1511. Hollowed-out part; 152. Connecting part; 1521. Second mounting space; 161. First sidewall; 1611. First sub-surface; 1612. Second sub-surface; 1613. Third sub-surface; 1614. Accommodation space; 162. Second sidewall; 163. First segment; 164. Second segment; 165. First opening; 166. Cavity; 167. Second opening; 171. Motor body; 172. Telescopic shaft; 181. Tilting shaft; 182. Rocker arm; 183. Bearing unit; X1, First direction; Y1, Second direction; Z1, Third direction; L1, Central axis of the rotating motor; L2, Central axis of the tilting shaft; L3, Central axis of the second segment. Detailed Implementation

[0019] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0020] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are 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, and therefore should not be construed as a limitation of this application.

[0021] 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.

[0022] In this application, unless otherwise expressly 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, 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.

[0023] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0024] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0025] Please see Figures 1 to 4To address the shortcomings in weight control of the tiltrotor system 10, the applicant, after in-depth research, designed a tiltrotor system 10. The tiltrotor system 10 includes a cabin 16, a tilt shaft assembly 18, and a tilt motor 17. Both the tilt shaft assembly 18 and the tilt motor 17 are mounted on the cabin 16. The tilt shaft assembly 18 includes a tilt shaft 181, which is fixedly connected to the fuselage. The tilt motor 17 is located outside the cabin 16 and includes a telescopic shaft 172, which is rotatably connected to the tilt shaft 181. The tilt motor 17 is configured to drive the cabin 16 to tilt relative to the tilt shaft 181 when its telescopic shaft 172 extends or retracts.

[0026] The hull 16 primarily serves to provide an installation reference and concentrate load transfer, and it integrates other components of the tiltrotor system 10 into a single unit. Optionally, the hull 16 may be made of aluminum, steel, or other materials.

[0027] Preferably, the cabin 16 is a carbon fiber component, which is manufactured and molded from carbon fiber. This ensures strength and rigidity while reducing the weight of the cabin 16, meeting the requirements of airworthiness regulations for lightweighting and reliability, and improving the thrust-to-weight ratio and range of the aircraft.

[0028] As an example, the wall thickness of the cabin 16 is H, where 3mm ≤ H ≤ 5mm. It can be understood that the wall thickness of the cabin 16 refers to the thickness of the plates that enclose and form the cabin 16. H can be, but is not limited to, 3mm, 3.5mm, 4mm, 5mm, etc. By designing the wall thickness H of the cabin 16 to be within the range of 3mm to 5mm, a thin-walled cabin 16 can be formed, thereby further achieving the lightweighting of the cabin 16 and improving the thrust-to-weight ratio and range of the aircraft.

[0029] The tilt shaft 181 is used to connect the tilt rotor system 10 and the fuselage to enable the installation of the tilt rotor system 10.

[0030] The tilt motor 17 can be, but is not limited to, a servo motor. The tilt motor 17 includes a motor body 171 and a telescopic shaft 172. The motor body 171 is mounted on and fixedly connected to the cabin 16, and the telescopic shaft 172 is rotatably connected to the tilt shaft 181. When the tilt motor 17 is operating, the telescopic shaft 172 extends and retracts relative to the motor body 171. Since the tilt shaft 181 is fixed to the fuselage, its relative position to the fuselage remains unchanged. In this situation, the linear extension and retraction of the telescopic shaft 172 is converted into the tilting of the tilt motor 17 and the cabin 16, thereby adjusting the tilt angle of the tilt rotor system 10, enabling the aircraft to switch between vertical takeoff and landing mode and cruise mode.

[0031] In this application, tilting can be understood as the adjustment of the angle relative to the Z-axis direction (the direction perpendicular to the ground). When the tilt rotor system 10 is in vertical take-off and landing mode, the tilt angle is 0°, and when the tilt rotor system 10 is in cruise mode, the tilt angle is between 90° and 90°.

[0032] As an example, the cabin 16 extends along a first direction X1, and the side wall of the cabin 16 along a second direction Y1 intersecting the first direction X1 is provided with mounting holes; the tilting shaft assembly 18 also includes a rocker arm 182 and a bearing unit 183. The bearing unit 183 includes a bearing and a bearing seat. The bearing seat is disposed in the mounting hole and is fixedly connected to the cabin 16. The bearing is located in the bearing seat and is sleeved on the tilting shaft 181. The rocker arm 182 and the tilting motor 17 are located on the same side of the cabin 16, and one end of the rocker arm 182 is fixedly connected to the tilting shaft 181, and the other end of the rocker arm 182 is rotatably connected to the telescopic shaft 172.

[0033] The first direction X1 can be a straight extension or a zigzag extension, depending on the actual shape of the cabin 16. The second direction Y1 can be the width or height of the cabin 16, depending on the actual installation requirements of the tilt axis 181 and the fuselage. For ease of explanation, the following embodiments will use the second direction Y1 as the width of the cabin 16 as an example.

[0034] As an example, the cabin 16 has a first sidewall 161 and a second sidewall 162 arranged opposite each other along the second direction Y1. Both the first sidewall 161 and the second sidewall 162 have mounting holes. There are two bearing units 183, each corresponding to one of the two mounting holes. The bearing units 183 are installed in the corresponding mounting holes. This design improves the stability of the tilt shaft 181 installation. Of course, in some other embodiments, there may be only one bearing unit 183, which is disposed in the mounting hole of either the first sidewall 161 or the second sidewall 162.

[0035] In actual operation, when the telescopic shaft 172 of the tilt motor 17 extends or retracts, both the tilt shaft 181 and the rocker arm 182 are fixed relative to the fuselage. The telescopic shaft 172 tilts relative to the rocker arm 182, thereby causing the cabin 16 to tilt. During this process, the cabin 16 tilts relative to the tilt shaft 181 via bearings.

[0036] The rocker arm 182 and bearing unit 183 work together to improve the stability of the tilt rotor system 10 during the tilting process.

[0037] In this application, by designing the cabin 16, tilt axis assembly 18, and tilt motor 17, the tilt angle of the tilt rotor system 10 can be adjusted through the cooperation of the tilt axis assembly 18 and the tilt motor 17, enabling the aircraft to switch between cruise mode and vertical takeoff and landing mode. Furthermore, placing the tilt motor 17 outside the cabin 16, compared to placing it inside, reduces the volume and size of the cabin 16, thereby helping to reduce the weight of the tilt rotor system 10 and achieving a lightweight design for the tilt rotor system 10.

[0038] In some embodiments, the tilt shaft assembly 18 is mounted at one end of the cabin 16 along a first direction X1, and the tilt shaft 181 passes through the cabin 16 along a second direction Y1 intersecting the first direction X1. The tilt motor 171 is disposed on one side of the cabin 16 along the second direction Y1. The cabin 16 has a first sidewall 161 and a second sidewall 162 disposed opposite to each other along the second direction Y1. The first sidewall 161 is disposed toward the tilt motor 17. The first sidewall 161 is at least partially recessed inward along the direction toward the second sidewall 162 to form a receiving space 1614, and the tilt shaft 181 passes through the receiving space 1614.

[0039] The housing space 1614 can be used to accommodate the wiring harness, bearing unit 183, rocker arm 182, etc. required for the tilt motor 17.

[0040] by Figure 3 Taking the tilt rotor system 10 shown as an example, the accommodating space 1614 is used to accommodate the bearing unit 183, and the rocker arm 182 is located outside the accommodating space 1614. For ease of explanation, the following embodiments will be described with the accommodating space 1614 accommodating the bearing unit 183 and the rocker arm 182 located outside the accommodating space 1614 as an example.

[0041] By forming a receiving space 1614 on the side where the tilt rotor system 10 is located to accommodate some components of the tilt rotor system 10, the size occupied by the tilt rotor system 10 in the second direction Y1 is reduced. In this case, the structure of the tilt rotor system 10 in the second direction Y1 is more compact.

[0042] In some embodiments, the first sidewall 161 includes a first sub-surface 1611, a second sub-surface 1612, and a third sub-surface 1613 connected sequentially along a first direction X1. The first sub-surface 1611 is away from the tilt axis 181 relative to the second sub-surface 1612 and the third sub-surface 1613. The tilt motor 17 is mounted on the first sub-surface 1611. The second sub-surface 1612 and the third sub-surface 1613 are both recessed relative to the first sub-surface 1611 in a direction toward the second sidewall 162, and define an accommodating space 1614 with the plane where the first sub-surface 1611 is located.

[0043] Specifically, in the extending direction of the cabin 16, the first sub-surface 1611, the second sub-surface 1612 and the third sub-surface 1613 gradually move away from the rotary motor 11.

[0044] The inward form of the second sub-surface 1612 and the third sub-surface 1613 can include various forms. For example, the second sub-surface 1612 and the third sub-surface 1613 can be surfaces with opposite inclinations in the extension direction of the cabin 16, and the first sub-surface 1611 and the second sub-surface 1612 form a V-shape. Alternatively, the first sub-surface 1611 and the third sub-surface 1613 can be straight surfaces arranged in parallel, and the second sub-surface 1612 can be an inclined surface that is inclined relative to the first sub-surface 1611 and the third sub-surface 1613. The specific form can be set according to the requirements.

[0045] The second sub-surface 1612 and the third sub-surface 1613 are both concave relative to the first sub-surface 1611 in the direction toward the second sidewall 162. The concave surfaces and the plane containing the first sub-surface 1611 define a receiving space 1614, through which the tilting shaft 181 passes. This receiving space 1614 can be used to accommodate the wiring harness, bearing unit 183, and rocker arm 182 required for the tilting motor 17, thereby improving the compactness of the tilting rotor system 10 structure.

[0046] Please see Figures 1 to 3 In some embodiments, the tilt rotor system 10 further includes a rotary motor 11, which is disposed along a first direction X1 at one end of the cabin 16 away from the tilt axis 181, and the central axis L1 of the rotary motor 11 and the central axis L2 of the tilt axis 181 are spaced apart on a third direction Z1; wherein, the third direction Z1 is perpendicular to the second direction Y1 and intersects the first direction X1.

[0047] The tiltrotor system 10 also includes a rotor, which is connected to a rotary motor 11 and rotates under the drive of the rotary motor 11. In vertical takeoff and landing mode, the rotor rotation provides lift to the aircraft, and in cruise mode, the rotor rotation provides horizontal thrust to the aircraft.

[0048] When the second direction Y1 is the width direction of the cabin 16, the third direction Z1 is the height direction of the cabin 16; when the second direction Y1 is the height direction of the cabin 16, the third direction Z1 is the width direction of the cabin 16. The specific values ​​can be set according to requirements. For ease of explanation, the following embodiments will use the second direction Y1 as the width direction of the cabin 16 and the third direction Z1 as the height direction of the cabin 16 as examples.

[0049] Depending on the orientation of the tilt rotor system 10, the second direction Y1 or the third direction Z1 is the Z-axis direction, or both the second direction Y1 and the third direction Z1 intersect the Z-axis direction.

[0050] The central axis L1 of the rotary motor 11 and the central axis L2 of the tilting shaft 181 are spaced apart in the third direction Z1. That is, the central axis L1 of the rotary motor 11 and the central axis L2 of the tilting shaft 181 are offset in the third direction Z1. This offset design can effectively reduce the load on the tilting motor 17, improve the sensitivity of the tilting motor 17's action response, and extend the service life of the tilting motor 17.

[0051] In some embodiments, the cabin 16 includes a first segment 163 and a second segment 164 that are interconnected and intersect each other. The central axis of the first segment 163 and the central axis L3 of the second segment 164 intersect at a first point. The rotary motor 11 and the tilting shaft 181 are respectively disposed at two ends of the first segment 163 and the second segment 164 that are far apart from each other. The central axis of the first segment 163 coincides with the central axis L1 of the rotary motor 11, and the central axis L3 of the second segment 164 intersects with the central axis L2 of the tilting shaft 181 at a second point, which is different from the first point.

[0052] The first segment 163 is a segment of the hull 16 with a first sub-surface 1611, and the second segment 164 is a segment of the hull 16 with a second sub-surface 1612 and a third sub-surface 1613.

[0053] In this embodiment, the design of the cabin 16 facilitates the installation of the rotary motor 11 and the tilting shaft 181 on the cabin 16, resulting in the central axis L1 of the rotary motor 11 and the central axis L2 of the tilting shaft 181 being spaced apart in the third direction Z1. This reduces the load on the tilting motor 17, improves the sensitivity of the tilting motor 17's action response, and extends the service life of the tilting motor 17.

[0054] Please see Figure 1 , Figures 5 to 8 In some embodiments, the tiltrotor system 10 further includes a plurality of first supports 14, all of which surround to form a first mounting space 141. The end of the cabin 16 away from the tilt axis 181 and the rotary motor 11 are inserted into the first mounting space 141. The first supports 14 are fixedly connected to both the cabin 16 and the rotary motor 11. By providing a plurality of first supports 14, the connection between the rotary motor 11 and the cabin 16 can be achieved.

[0055] Furthermore, the cabin 16 has a cavity 166, and one end of the cabin 16 extending into the first installation space 141 has a first opening 165 communicating with the cavity 166; the tilt rotor system 10 also includes a second bracket 15, which is installed into the cavity 166 through the first opening 165, and the second bracket 15 includes a main body 151 and a plurality of connecting parts 152 arranged circumferentially along the main body 151, all of which are fixedly connected to the cabin 16.

[0056] By setting a second bracket 15, all connecting parts 152 of the second bracket 15 cooperate with all first brackets 14 to fix the cabin 16 and the rotary motor 11, so as to achieve high-precision connection and stable cooperation between the cabin 16 and the rotary motor 11.

[0057] In some embodiments, the main body 151 is provided with a hollow portion 1511, and all connecting portions 152 surround to form a second installation space 1521; the tilt rotor system 10 also includes a fan 12 and a radiator 13, the fan 12 is located between the rotary motor 11 and the cabin 16, the radiator 13 is located in the second installation space 1521, and both the fan 12 and the radiator 13 are aligned with the hollow portion 1511. The end face of the cabin 16 away from the first opening 165 along the first direction X1 or at least one side wall of the cabin 16 along the second direction Y1 is provided with a second opening 167, and the cavity 166 communicates with the second opening 167 to form a heat dissipation channel.

[0058] Preferably, the end face of the cabin 16 away from the first opening 165 along the first direction X1, the first side wall 161 and the second side wall 162 are all provided with second openings 167, so that three heat dissipation channels are formed inside the cabin 16.

[0059] In actual operation, the rotary motor 11, fan 12, and radiator 13 all operate. The fan 12 drives airflow to flow sequentially through the rotary motor 11 and radiator 13, and after heat exchange at the radiator 13, the airflow is output to the outside of the tilt rotor system 10 through various heat dissipation channels. Under this design, a directional cooling airflow is formed within the cabin 16 during the aircraft's flight and tilting processes to cool the rotary motor 11, thereby preventing the rotary motor 11 from overheating during operation.

[0060] This application also provides a vertical takeoff and landing aircraft, which includes a fuselage and a tiltrotor system 10 as described in any of the above embodiments, wherein the tilt motor 17 is located on the same side of the fuselage 16 and the tilt shaft 181 is fixedly connected to the fuselage.

[0061] The vertical takeoff and landing aircraft in this application has the effects of any of the above embodiments, so it will not be described again here.

[0062] The aforementioned tiltrotor system 10 and vertical takeoff and landing (VTOL) aircraft, through the design of the cabin 16, tilt shaft assembly 18, and tilt motor 17, with the tilt shaft assembly 18 and tilt motor 17 working together, can adjust the tilt angle of the tiltrotor system 10, enabling the aircraft to switch between cruise mode and VTOL mode. Furthermore, placing the tilt motor 17 outside the cabin 16, compared to placing it inside, reduces the volume and size of the cabin 16, thereby helping to reduce the weight of the tiltrotor system 10 and achieving a lightweight design.

[0063] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0064] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A tiltrotor system, characterized in that, The tiltrotor system includes a cabin, a tilt axis assembly, and a tilt motor. The tilt axis assembly and the tilt motor are both mounted on the cabin. The tilt axis assembly includes a tilt axis, which is fixedly connected to the fuselage. The tilt motor is located outside the cabin and includes a telescopic shaft, which is rotatably connected to the tilt axis. The tilt motor is configured to drive the cabin to tilt relative to the tilt axis when its telescopic shaft extends or retracts.

2. The tiltrotor system according to claim 1, characterized in that, The cabin extends along a first direction, the tilting shaft assembly is installed at one end of the cabin along the first direction, and the tilting shaft passes through the cabin along a second direction intersecting the first direction, and the tilting motor is disposed on one side of the cabin along the second direction; The cabin has a first sidewall and a second sidewall disposed opposite to each other along the second direction, the first sidewall being disposed toward the tilt motor; at least part of the first sidewall is recessed inward along the direction toward the second sidewall to form an accommodating space, and the tilt shaft passes through the accommodating space.

3. The tiltrotor system according to claim 2, characterized in that, The first sidewall includes a first sub-surface, a second sub-surface, and a third sub-surface connected sequentially along the first direction. The first sub-surface is away from the tilt axis relative to the second sub-surface and the third sub-surface. The tilt motor is mounted on the first sub-surface. The second sub-surface and the third sub-surface are both recessed inward relative to the first sub-surface in the direction toward the second sidewall, and define an accommodating space with the plane where the first sub-surface is located.

4. The tiltrotor system according to claim 2, characterized in that, The tilt rotor system also includes a rotary motor, which is disposed along the first direction at the end of the cabin away from the tilt axis, and the central axis of the rotary motor and the central axis of the tilt axis are spaced apart in a third direction. The third direction is perpendicular to the second direction and intersects with the first direction.

5. The tiltrotor system according to claim 4, characterized in that, The tilt rotor system also includes a plurality of first supports, all of which surround to form a first installation space. The end of the cabin away from the tilt axis and the rotary motor are inserted into the first installation space. The first supports are fixedly connected to the cabin and the rotary motor.

6. The tiltrotor system according to claim 5, characterized in that, The cabin has a cavity, and one end of the cabin that extends into the first installation space has a first opening that communicates with the cavity. The tiltrotor system also includes a second support, which is inserted into the cavity through the first opening. The second support includes a main body and a plurality of connecting parts arranged circumferentially along the main body. All the connecting parts are fixedly connected to the cabin.

7. The tiltrotor system according to claim 6, characterized in that, The main body is provided with a hollowed-out section, and all the connecting parts are arranged to form a second installation space; The tilt rotor system also includes a fan and a radiator. The fan is located between the rotary motor and the cabin, and the radiator is located in the second installation space. Both the fan and the radiator are aligned with the hollow portion. The cabin has a second opening on the end face away from the first opening along the first direction or on at least one side wall of the cabin along the second direction. The cavity communicates with the second opening to form a heat dissipation channel.

8. The tiltrotor system according to claim 1, characterized in that, The cabin is made of carbon fiber components, and / or the wall thickness of the cabin is H, 3mm≤H≤5mm.

9. The tiltrotor system according to claim 1, characterized in that, The cabin extends along a first direction, and mounting holes are provided on the side wall of the cabin along a second direction that intersects with the first direction; The tilting shaft assembly also includes a rocker arm and a bearing unit. The bearing unit includes a bearing and a bearing housing. The bearing housing is disposed in the mounting hole and fixedly connected to the cabin body. The bearing is located in the bearing housing and sleeved on the tilting shaft. The rocker arm and the tilting motor are located on the same side of the cabin body, and one end of the rocker arm is fixedly connected to the tilting shaft, while the other end of the rocker arm is rotatably connected to the telescopic shaft.

10. A vertical takeoff and landing aircraft, characterized in that, include: body; as well as As described in any one of claims 1 to 9, in the tilt rotor system, the tilt motor and the fuselage are located on the same side of the cabin, and the tilt shaft is fixedly connected to the fuselage.

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