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 frame and a tilt-rotor shaft assembly. The frame comprises a plurality of mounting plates and a plurality of connecting beams. All the mounting plates are arranged at intervals along a first direction, all the connecting beams are arranged at intervals along the circumferential direction of the mounting plates, and the connecting beams are connected with all the mounting plates. Each two adjacent mounting plates and all the connecting beams define a mounting space, and the mounting space comprises a tilt-rotor shaft mounting space. The tilt-rotor shaft assembly is at least partially mounted in the tilt-rotor shaft mounting space. The tilt-rotor shaft assembly comprises a tilt-rotor shaft. The tilt-rotor shaft penetrates the tilt-rotor shaft mounting space along a second direction intersecting the first direction and is fixedly connected with the fuselage. The tilt-rotor system and the vertical take-off and landing aircraft provided by the application can realize light weight.

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 component 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, the tiltrotor system comprising a frame and a tilt shaft assembly; The frame includes multiple mounting plates and multiple connecting beams. All the mounting plates are spaced apart along a first direction, and all the connecting beams are spaced apart along the circumference of the mounting plates. The connecting beams are connected to all the mounting plates. Each pair of adjacent mounting plates and all the connecting beams define an installation space, which includes a tilting shaft installation space. The tilt axis assembly is at least partially installed within the tilt axis mounting space. The tilt axis assembly includes a tilt axis, which passes through the tilt axis mounting space along a second direction intersecting the first direction and is fixedly connected to the fuselage.

[0007] In some embodiments, the installation space further includes a tilt motor installation space, which is disposed on one side of the tilt shaft installation space along the first direction; The tilt rotor system also includes the tilt motor, which is at least partially installed in the tilt motor mounting space, and the tilt motor includes a telescopic shaft that is rotatably connected to the tilt shaft. The tilt motor is configured to drive the frame to tilt relative to the tilt shaft when its telescopic shaft extends or retracts.

[0008] In some embodiments, the tilting shaft assembly includes a rocker arm, a bearing, and a bearing housing. The rocker arm, the bearing, and the bearing housing are all located within the tilting shaft mounting space. One end of the rocker arm is fixedly connected to the tilting shaft, and the other end of the rocker arm is rotatably connected to the telescopic shaft. The bearing is installed in the bearing housing and sleeved on the outside of the tilting shaft. The tilt rotor system also includes a mounting bracket, which is disposed within the tilt shaft mounting space and is used to fix the frame and the bearing housing.

[0009] In some embodiments, the tilt rotor system further includes a rotary motor, a first air guide shell, and a rotor. The installation space also includes a rotary motor installation space, which is located on the side of the tilting shaft installation space away from the tilting motor installation space. The first air guide shell extends along the first direction to define two mounting plates forming the rotary motor installation space. The rotary motor is located inside the first air guide shell and forms a first heat dissipation air duct with the first air guide shell. The rotor is disposed on the side of the rotary motor away from the tilting shaft installation space and is connected to the rotary motor in a transmission manner.

[0010] In some embodiments, the tilt rotor system further includes an exhaust casing; The installation space also includes an air outlet housing installation space, which is located between the rotary motor installation space and the tilting shaft installation space. The mounting plate that forms the air outlet housing installation space and the rotary motor installation space is defined as an air outlet mounting plate. The air outlet mounting plate has a through hole that runs through the first direction. The through hole of the air outlet mounting plate is connected to the first heat dissipation air duct. The air outlet housing has a central hole and multiple air outlet ducts. The through hole, the central hole, and the air outlet ducts of the air outlet mounting plate are sequentially connected to form an air guide duct.

[0011] In some embodiments, the tilt rotor system further includes a reducer and a second air guide shell. Another mounting plate defining the mounting space of the rotary motor is defined as a rotary motor mounting plate. The reducer and the second air guide shell are both located on the side of the rotary motor mounting plate away from the air outlet mounting plate. The reducer is located inside the second air guide shell and forms a second heat dissipation duct with the second air guide shell. The second heat dissipation duct communicates with the first heat dissipation duct. The reducer is driven between the rotary motor and the rotor along the first direction.

[0012] In some embodiments, the tilt rotor system further includes a reducer bracket and a third air guide shell. The third air guide shell is mounted on the rotary motor mounting plate and located between the rotary motor mounting plate and the second air guide shell. The reducer bracket is mounted inside the third air guide shell and is used to connect the rotary motor mounting plate and the reducer. A third heat dissipation duct is defined inside the third air guide shell and is connected between the first heat dissipation duct and the second heat dissipation duct.

[0013] In some embodiments, the mounting plate has a plurality of grooves spaced apart in sequence along its circumference, the grooves penetrating the mounting plate along the first direction, the grooves of the mounting plate corresponding one-to-one with the connecting beams, the connecting beams being at least partially disposed in the corresponding grooves of the mounting plate and detachably connected to the mounting plate.

[0014] In some embodiments, the connecting beam includes a limiting portion and an overlapping portion connected together. The limiting portion is located within the groove, and the overlapping portion is located outside the groove and overlaps the side peripheral surface of the mounting plate. The overlapping portion is detachably connected to the mounting plate.

[0015] A vertical takeoff and landing aircraft, comprising: fuselage; and As described in any of the above embodiments, the tilt rotor system is disposed on one side of the fuselage along the second direction, and the tilt axis 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 aircraft, which use a frame consisting of mounting plates and connecting beams to install the tilt shaft assembly, have a lighter frame weight, which can effectively reduce the weight of the tiltrotor system and achieve a lightweight design for the tiltrotor system. 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 tilt rotor system shown is a side-pitch view. Figure 3 for Figure 1 The diagram shows the structural arrangement of the frame and mounting bracket in the tilt rotor system. Figure 4 for Figure 1 The diagram shows the structural arrangement of the mounting plate, tilt motor, tilt shaft assembly, and motor in the tilt rotor system. Figure 5 for Figure 4 The tilt rotor system shown is a side-pitch view. Figure 6 for Figure 1 The diagram shows the structure of the tilt shaft assembly in the tilt rotor system. Figure 7 for Figure 1 The diagram shows the structural arrangement of the first air guide shell, the rotary motor mounting plate, and the air outlet shell in the tilt rotor system. Figure 8 This is a schematic diagram of the tilt rotor system in another embodiment of this application; Figure 9 for Figure 8 The diagram shows the structural arrangement of the mounting plate in the tilt rotor system with the tilt motor, tilt shaft assembly, motor, reducer bracket and reducer. Figure 10 for Figure 8 The diagram shows the structural arrangement of the frame and the reducer support in the tilt rotor system.

[0018] Icon labels: 10. Tiltrotor system; 11. Frame; 12. Tilting shaft assembly; 13. Tilting motor; 14. Mounting bracket; 15. Rotary motor; 16. First air guide shell; 17. Air outlet shell; 18. Reducer; 19. Second air guide shell; 21. Reducer bracket; 22. Third air guide shell; 111. Mounting plate; 1111. Rotary motor mounting plate; 1112. Air outlet mounting plate; 11121. First through hole; 1113. Third mounting plate; 1114. Fourth mounting plate; 1115. Fifth mounting plate; 1116. Groove; 112. Connecting beam; 1121. Limiting part; 1122. Overlapping part; 113. Mounting space; 1131. Rotary motor mounting space; 1132. Air outlet housing mounting space; 1133. Tilting shaft mounting space; 1134. Tilting motor mounting space; 121. Tilting shaft; 122. Rocker arm; 123. Bearing assembly; 131. Motor body; 132. Telescopic shaft; 161. First heat dissipation air duct; 171. Center hole; 172. Air outlet duct; 191. Second heat dissipation air duct; 221. Third heat dissipation air duct; X, the first direction; Y, the second direction. 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 6 To address the shortcomings in weight control of the tiltrotor system 10, the applicant, after in-depth research, designed a tiltrotor system 10, which includes a frame 11 and a tiltshaft assembly 12. The frame 11 includes multiple mounting plates 111 and multiple connecting beams 112. All mounting plates 111 are spaced apart along a first direction X, and all connecting beams 112 are spaced apart circumferentially along the mounting plates 111. Each pair of adjacent mounting plates 111 and connecting beams 112 defines an installation space 113, which includes a tiltshaft installation space 1133. The tiltshaft assembly 12 is at least partially installed within the tiltshaft installation space 1133. The tiltshaft assembly 12 includes a tiltshaft 121, which passes through the tiltshaft installation space 1133 along a second direction Y intersecting the first direction X and is fixedly connected to the fuselage.

[0026] Specifically, the angle between the first direction X and the second direction Y can be 30°, 50°, 90°, 125°, etc., and can be set according to requirements. In one specific embodiment, the angle between the first direction and the second direction is 90°.

[0027] The frame 11 primarily serves to centralize load transfer and provide an installation reference, integrating other components of the rotor system into a single unit. The number of mounting plates 111 and connecting beams 112 within the frame 11 is determined according to requirements and is not specified here.

[0028] The tilt shaft 121 is used to connect the tilt rotor system 10 and the fuselage. The tilt shaft 121 passes through the tilt shaft mounting space 1133 along the second direction Y, and partially extends out of the tilt shaft mounting space 1133 to facilitate connection with the fuselage. Specifically, each pair of connected beams 112 defines an opening that connects to the tilt shaft mounting space 1133. When the tilt shaft 121 passes through the tilt shaft mounting space 1133, the opposite ends of the tilt shaft 121 pass through two openings that are respectively arranged opposite each other along the second direction Y.

[0029] In this embodiment, the tilt shaft assembly 12 is installed using a frame 11 consisting of a mounting plate 111 and connecting beams 112. The lighter weight of the frame 11 effectively reduces the weight of the tilt rotor system 10, achieving a lightweight design for the tilt rotor system 10. Furthermore, the opening formed between adjacent connecting beams 112 facilitates maintenance of the tilt shaft assembly 12.

[0030] In some embodiments, the mounting space 113 further includes a tilt motor mounting space 1134, which is disposed along a first direction X on one side of the tilt shaft mounting space 1133. The tilt rotor system 10 also includes a tilt motor 13, which is at least partially mounted within the tilt motor mounting space 1134, and the tilt motor 13 includes a telescopic shaft 132 rotatably connected to the tilt shaft 121. The tilt motor 13 is configured to cause the frame 11 to tilt relative to the tilt shaft 121 when its telescopic shaft 132 extends or retracts.

[0031] The tilt motor 13 can be, but is not limited to, a servo motor. The tilt motor 13 includes a motor body 131 and a telescopic shaft 132. The motor body 131 is located within the tilt motor mounting space 1134 and is fixedly connected to the frame 11. The telescopic shaft 132 extends into the tilt shaft mounting space 1133 and is rotatably connected to the tilt shaft 121. When the tilt motor 13 is working, the telescopic shaft 132 extends and retracts relative to the motor body 131. Since the tilt shaft 121 is fixed to the fuselage, the relative position of the tilt shaft 121 and the fuselage remains unchanged. In this case, the linear extension and retraction motion of the telescopic shaft 132 is converted into the tilting of the tilt motor 13 and the frame 11 to adjust the tilt angle of the tilt rotor system 10, enabling the aircraft to switch between vertical takeoff and landing mode and cruise mode.

[0032] In this application, tilting can be understood as an 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 takeoff and landing mode, the tilt angle is 0°; when the tilt rotor system 10 is in cruise mode, the tilt angle is 90°. Please refer to [link to relevant documentation]. Figure 1 , Figure 3 , Figure 5 and Figure 6 In some embodiments, the tilt axis assembly 12 includes a rocker arm 122, a bearing, and a bearing housing. The rocker arm 122, bearing, and bearing housing are all located within the tilt axis mounting space 1133. One end of the rocker arm 122 is fixedly connected to the tilt axis 121, and the other end of the rocker arm 122 is rotatably connected to the telescopic shaft 132. The bearing is installed in the bearing housing and sleeved on the outside of the tilt axis 121. The tilt rotor system 10 also includes a mounting frame 14, which is disposed within the tilt axis mounting space 1133 and is used to fix the frame 11 and the bearing housing.

[0033] Specifically, bearings and bearing housings are matched to form bearing assemblies 123. The number of bearing assemblies 123 and mounting brackets 14 is not limited here. Each mounting bracket 14 corresponds to one bearing assembly 123, and the mounting bracket 14 is connected between the bearing housing of the corresponding bearing assembly 123 and the frame 11. For example, in one specific embodiment, there are two mounting brackets 14, spaced apart along the second direction Y, and both mounting brackets 14 are connected between two mounting plates 111 that define the tilting shaft mounting space 1133. Two bearing assemblies 123 are provided on the tilting shaft 121. The tilting shaft 121 passes through the two mounting brackets 14 and is rotatably connected to the two mounting brackets 14 respectively through the two bearing assemblies 123, thereby improving the stability of the tilting shaft 121 installation.

[0034] In actual operation, when the telescopic shaft 132 of the tilting motor 13 extends or retracts, both the tilting shaft 121 and the rocker arm 122 are fixed relative to the machine body. The telescopic shaft 132 tilts relative to the rocker arm 122, thereby driving the frame 11 and the mounting bracket 14 to tilt. During this process, the mounting bracket 14 tilts relative to the tilting shaft 121 through bearings.

[0035] In this application, the rocker arm 122, bearing, bearing housing and mounting bracket 14 work together to help improve the stability of the tilt rotor system 10 during the tilting process.

[0036] Please see Figure 1 In some embodiments, the tilt rotor system 10 further includes a rotary motor 15, a first air guide shell 16, and a rotor; the mounting space 113 further includes a rotary motor mounting space 1131, which is located on the side of the tilt shaft mounting space 1133 away from the tilt motor mounting space 1134. The first air guide shell 16 extends through the first direction X to define two mounting plates 111 forming the rotary motor mounting space 1131. The rotary motor 15 is located inside the first air guide shell 16 and forms a first heat dissipation duct 161 with the first air guide shell 16. The rotor is disposed on the side of the rotary motor 15 away from the tilt shaft mounting space 1133 and is connected to the rotary motor 15 in a transmission manner.

[0037] The rotary motor 15 is used to drive the rotor to rotate. In the vertical take-off and landing mode, the rotor rotation provides lift for the aircraft, and in the cruise mode, the rotor rotation provides horizontal thrust for the aircraft.

[0038] The two mounting plates 111 that define the rotating motor mounting space 1131 are each provided with through holes along the first direction X. The two opposite ends of the first air guide shell 16 are respectively inserted into the two through holes of the two mounting plates 111. Generally speaking, the rotating motor mounting space 1131 is located in the first or last mounting space 113 of the frame 11 along the first direction X, so as to facilitate the connection between the rotating motor 15 and the rotor located outside the frame 11.

[0039] In actual operation, during the operation of the rotary motor 15, airflow enters from the side of the rotary motor 15 opposite to the tilting shaft mounting space 1133 along the first direction X, flows through the first heat dissipation duct 161, and then flows out. This design allows for heat dissipation and cooling of the rotary motor 15, preventing overheating and potential malfunctions.

[0040] Please see Figure 1 and Figure 7 Furthermore, the tilt rotor system 10 also includes an air outlet shell 17; the installation space 113 also includes an air outlet shell installation space 1132, which is located between the rotary motor installation space 1131 and the tilt shaft installation space 1133. The mounting plate 111 that forms the air outlet shell installation space 1132 and the rotary motor installation space 1131 is defined as the air outlet mounting plate 1112. The air outlet mounting plate 1112 has a through hole that runs through the first direction X. The through hole of the air outlet mounting plate 1112 is connected to the first heat dissipation air duct 161. The air outlet shell 17 has a central hole 171 and multiple air outlet ducts 172. The through hole, central hole 171 and air outlet ducts 172 of the air outlet mounting plate 1112 are connected in sequence to form an air guide duct.

[0041] Specifically, the air outlet housing 17 is mounted on the air outlet mounting plate 1112.

[0042] For ease of explanation and labeling, the through hole on the air outlet mounting plate 1112 is defined as the first through hole 11121.

[0043] In actual operation, the airflow flows sequentially through the first heat dissipation duct 161, the first through hole 11121, the center hole 171 of the air outlet shell 17, and each air outlet duct 172 before being output to the outside of the tilt rotor system 10. By setting the air outlet shell 17, the airflow can be guided to exchange heat with the rotary motor 15 and then be directly output to the outside of the frame 11, so as to avoid the high-temperature airflow from contacting the components located downstream of the air outlet shell 17 in the first direction X, which could lead to the failure of the tilt rotor system 10.

[0044] Specifically, taking five mounting plates 111 spaced apart along the first direction X as an example, the five mounting plates 111 arranged sequentially along the first direction X are a first mounting plate, a second mounting plate, a third mounting plate 1113, a fourth mounting plate 1114, and a fifth mounting plate 1115. The second mounting plate is the air outlet mounting plate 1112. The first mounting plate and the second mounting plate define a first mounting space, which is the rotary motor mounting space 1131. The second mounting plate and the third mounting plate 1113 define a second mounting space, which is the air outlet housing mounting space 1132. The third mounting plate 1113 and the fourth mounting plate 1114 define a third mounting space, which is the tilting shaft mounting space 1133. The fourth mounting plate 1114 and the fifth mounting plate 1115 define a fourth mounting space, which is the tilting motor mounting space 1134. The rotor is mounted on the side of the first mounting plate facing away from the second mounting plate and is connected to the rotary motor 15 for transmission.

[0045] Please see Figure 1 , Figures 8 to 10 In some embodiments, the tilt rotor system 10 further includes a reducer 18 and a second air guide shell 19. Another mounting plate 111 that defines and forms the rotary motor mounting space 1131 is the rotary motor mounting plate 1111 (i.e., the first mounting plate mentioned above). The reducer 18 and the second air guide shell 19 are both located on the side of the rotary motor mounting plate 1111 away from the air outlet mounting plate 1112. The reducer 18 is located inside the second air guide shell 19 and forms a second heat dissipation air duct 191 with the second air guide shell 19. The second heat dissipation air duct 191 is connected to the first heat dissipation air duct 161. The reducer 18 is connected to the rotary motor 15 and the rotor along the first direction X.

[0046] The reducer 18 is used to transmit the required speed and torque of the rotor to ensure that the rotor works properly.

[0047] During actual operation, the airflow sequentially flows through the second heat dissipation duct 191, the first heat dissipation duct 161, the first through hole 11121, the center hole 171 of the air outlet shell 17, and each air outlet duct 172 before being output to the outside of the tiltrotor system 10. With this configuration, the airflow can exchange heat with the reducer 18 and the rotary motor 15 to reduce their temperature, preventing them from overheating and affecting the normal operation of the aircraft.

[0048] In some embodiments, the tilt rotor system 10 further includes a reducer bracket 21 and a third air guide shell 22. The third air guide shell 22 is mounted on the rotary motor mounting plate 1111 and is located between the rotary motor mounting plate 1111 and the second air guide shell 19. The reducer bracket 21 is mounted inside the third air guide shell 22 and is used to connect the rotary motor mounting plate 1111 and the reducer 18. A third heat dissipation duct 221 is defined inside the third air guide shell 22 and is connected between the first heat dissipation duct 161 and the second heat dissipation duct 191.

[0049] In actual operation, the airflow sequentially flows through the second heat dissipation duct 191, the third heat dissipation duct 221, the first heat dissipation duct 161, the first through hole 11121, the center hole 171 of the air outlet shell 17, and each air outlet duct 172 before being output to the outside of the tilt rotor system 10. With this configuration, the airflow can exchange heat with the reducer 18 and the rotary motor 15, further improving heat dissipation efficiency and reducing the operating temperature of the rotary motor 15 and the reducer 18.

[0050] As an example, there may be one or more reducer brackets 21. Preferably, there are multiple reducer brackets 21 and they are arranged at intervals along the circumference of the reducer 18 to improve the installation strength of the reducer 18.

[0051] In some embodiments, the cross-sectional area of ​​the frame 11 gradually decreases in the first direction X. In actual operation, taking the forward movement of the aircraft in cruise mode as an example, the first direction X is the forward direction. By setting the cross-sectional area of ​​the frame 11 to gradually decrease in the first direction X, the drag during the forward movement of the aircraft can be reduced, thereby helping to reduce the energy consumption of the aircraft during flight.

[0052] Please see Figure 3 In some embodiments, the mounting plate 111 has a plurality of grooves 1116 arranged at intervals along its circumference. The grooves 1116 penetrate the mounting plate 111 along a first direction X. Each groove 1116 of the mounting plate 111 corresponds to a connecting beam 112. The connecting beam 112 is at least partially disposed within the corresponding groove 1116 of the mounting plate 111 and is detachably connected to the mounting plate 111. The grooves 1116 are used to position the connecting beam 112, so as to facilitate subsequent fixation of the connecting beam 112 and the mounting plate 111 by a detachable connection.

[0053] By designing the connecting beam 112 to be detachably connected to the mounting plate 111, when a component in the mounting space 113 fails, the connecting beam 112 can be disassembled to facilitate maintenance personnel to repair the component in the mounting space 113.

[0054] In some embodiments, the connecting beam 112 includes a limiting portion 1121 and an overlapping portion 1122 connected together. The limiting portion 1121 is limited within the groove 1116, and the overlapping portion 1122 is located outside the groove 1116 and overlaps the side peripheral surface of the mounting plate 111. The overlapping portion 1122 is detachably connected to the mounting plate 111.

[0055] The lap joint 1122 of the connecting beam 112 can be one or two. If there are two limiting parts 1121, the two limiting parts 1121 are arranged on opposite sides of the lap joint 1122 and are connected to each mounting plate 111, which helps to improve the stability of the connection of the connecting beam 112.

[0056] 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. The tiltrotor system 10 is disposed on one side of the fuselage along a second direction Y, and the tilt shaft 121 is fixedly connected to the fuselage.

[0057] 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.

[0058] The tiltrotor system 10 and vertical takeoff and landing aircraft described above use a frame 11 composed of mounting plate 111 and connecting beam 112 to install the tilt shaft assembly 12. The lighter weight of the frame 11 can effectively reduce the weight of the tiltrotor system 10 and achieve a lightweight design of the tiltrotor system 10.

[0059] 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.

[0060] 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 tilt rotor system includes a frame and a tilt shaft assembly; The frame includes multiple mounting plates and multiple connecting beams. All the mounting plates are spaced apart along a first direction, and all the connecting beams are spaced apart along the circumference of the mounting plates. The connecting beams are connected to all the mounting plates. Each pair of adjacent mounting plates and all the connecting beams define an installation space, which includes a tilting shaft installation space. The tilt axis assembly is at least partially installed within the tilt axis mounting space. The tilt axis assembly includes a tilt axis, which passes through the tilt axis mounting space along a second direction intersecting the first direction and is fixedly connected to the fuselage.

2. The tiltrotor system according to claim 1, characterized in that, The installation space also includes a tilt motor installation space, which is located on one side of the tilt shaft installation space along the first direction; The tilt rotor system also includes the tilt motor, which is at least partially installed in the tilt motor mounting space, and the tilt motor includes a telescopic shaft that is rotatably connected to the tilt shaft. The tilt motor is configured to drive the frame to tilt relative to the tilt shaft when its telescopic shaft extends or retracts.

3. The tiltrotor system according to claim 2, characterized in that, The tilting shaft assembly includes a rocker arm, a bearing, and a bearing housing. The rocker arm, the bearing, and the bearing housing are all located within the tilting shaft mounting space. One end of the rocker arm is fixedly connected to the tilting shaft, and the other end of the rocker arm is rotatably connected to the telescopic shaft. The bearing is installed inside the bearing housing and sleeved outside the tilting shaft. The tilt rotor system also includes a mounting bracket, which is disposed within the tilt shaft mounting space and is used to fix the frame and the bearing housing.

4. The tiltrotor system according to claim 2, characterized in that, The tilt rotor system also includes a rotary motor, a first air guide shell, and rotor blades; The installation space also includes a rotary motor installation space, which is located on the side of the tilting shaft installation space away from the tilting motor installation space. The first air guide shell extends along the first direction to define two mounting plates forming the rotary motor installation space. The rotary motor is located inside the first air guide shell and forms a first heat dissipation air duct with the first air guide shell. The rotor is disposed on the side of the rotary motor away from the tilting shaft installation space and is connected to the rotary motor in a transmission manner.

5. The tiltrotor system according to claim 4, characterized in that, The tilt rotor system also includes an exhaust casing; The installation space also includes an air outlet housing installation space, which is located between the rotary motor installation space and the tilting shaft installation space. The mounting plate that forms the air outlet housing installation space and the rotary motor installation space is defined as an air outlet mounting plate. The air outlet mounting plate has a through hole that runs through the first direction. The through hole of the air outlet mounting plate is connected to the first heat dissipation air duct. The air outlet housing has a central hole and multiple air outlet ducts. The through hole, the central hole, and the air outlet ducts of the air outlet mounting plate are sequentially connected to form an air guide duct.

6. The tiltrotor system according to claim 5, characterized in that, The tilt rotor system also includes a reducer and a second air guide shell. Another mounting plate that defines the mounting space for the rotary motor is defined as the rotary motor mounting plate. The reducer and the second air guide shell are both located on the side of the rotary motor mounting plate away from the air outlet mounting plate. The reducer is located inside the second air guide shell and forms a second heat dissipation duct with the second air guide shell. The second heat dissipation duct is connected to the first heat dissipation duct. The reducer is connected to the rotary motor and the rotor along the first direction.

7. The tiltrotor system according to claim 6, characterized in that, The tilt rotor system also includes a reducer bracket and a third air guide shell. The third air guide shell is mounted on the rotary motor mounting plate and located between the rotary motor mounting plate and the second air guide shell. The reducer bracket is installed inside the third air guide shell and is used to connect the rotary motor mounting plate and the reducer. A third heat dissipation duct is defined inside the third air guide shell and is connected between the first heat dissipation duct and the second heat dissipation duct.

8. The tiltrotor system according to claim 1, characterized in that, The mounting plate has a plurality of grooves arranged at intervals along its circumference. The grooves penetrate the mounting plate along the first direction. Each groove of the mounting plate corresponds to a connecting beam. The connecting beam is at least partially disposed in the corresponding groove of the mounting plate and is detachably connected to the mounting plate.

9. The tiltrotor system according to claim 8, characterized in that, The connecting beam includes a limiting part and an overlapping part connected together. The limiting part is located within the groove, and the overlapping part is located outside the groove and overlaps the side circumferential surface of the mounting plate. The overlapping part is detachably connected to the mounting plate.

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, the tilt rotor system is disposed on one side of the fuselage along the second direction, and the tilt axis is fixedly connected to the fuselage.

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