A high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism

Abstract

The present invention provides a high-rigidity and high-reliability variable connection eVTOL tilt-wing tilt mechanism, which relates to the field of aircraft technology, and specifically includes a group of servos, a tilt shaft and an electromagnetic clutch, wherein the tilt shaft includes an inner tilt shaft and an outer tilt shaft, wherein the inner tilt shaft passes through the servo and is connected to the electromagnetic clutch, and the other end is connected to the outer tilt shaft, and the other end of the outer tilt shaft is connected to the tilt wing; the servo is symmetrically arranged about the electromagnetic clutch, and the electromagnetic clutch can control the separation and connection of the left and right tilt shafts. While realizing the free switching connection and disconnection of the left and right wings, high rigidity, high reliability and light weight are achieved. The structure is simple, easy to produce, and easy to integrate and arrange, which is very suitable for the intelligent flight control system of the tilt-wing eVTOL.

Description

Technical Field

[0001] The present invention relates to the field of aircraft technology, and in particular to a variable connection eVTOL tilt-wing tilt mechanism with high rigidity and high reliability. Background Art

[0002] With the progress of urbanization, land space is becoming increasingly saturated and traffic congestion is becoming increasingly serious. It is urgent to develop available space in the air in cities and develop vertical transportation. The development of eVTOL (Electric Vertical Takeoff and Landing) electric vertical take-off and landing aircraft has attracted widespread attention from aerospace companies, the automotive industry, the transportation industry, the government, the military, and academia. The potential future applications of eVTOL involve a variety of scenarios such as urban passenger transportation, regional passenger transportation, freight, personal aircraft, and emergency medical services. Tilt-wing eVTOL has received more and more attention due to its excellent performance, and a reliable and stable tilt mechanism is one of the most critical mechanisms of tilt-wing eVTOL.

[0003] For eVTOL with a tilt-rotor configuration, each rotor requires an independent tilt mechanism. The main feature of the tilt-wing configuration is its high structural complexity. The current mainstream approach is to adopt an overall tilt design based on a mechanical structure. The structure is reliable but heavy, and it is impossible to freely switch between the left and right axes.

[0004] Therefore, it is necessary to design a high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism to solve the above technical problems. Summary of the invention

[0005] In view of the above problems existing in the prior art, the present invention provides a high-rigidity and high-reliability variable connection eVTOL tilt-wing tilt mechanism, which realizes the free switching connection and disconnection of the left and right wings, and achieves high rigidity, high reliability and light weight. It has a simple structure, is easy to produce, and is easy to integrate and arrange, and is very suitable for the intelligent flight control system of the tilt-wing eVTOL.

[0006] Technical solution: In order to achieve the above-mentioned purpose, the present invention provides a high-rigidity and high-reliability variable connection eVTOL tilt-wing tilt mechanism, comprising a set of servos, a tilt shaft and an electromagnetic clutch, wherein the tilt shaft comprises an inner tilt shaft and an outer tilt shaft, wherein the inner tilt shaft passes through the servo and is connected to the electromagnetic clutch, and the other end is connected to the outer tilt shaft, and the other end of the outer tilt shaft is connected to the tilt-wing; The steering gear is symmetrically arranged about the electromagnetic clutch, and the electromagnetic clutch can control the separation and connection of the tilt shafts on the left and right sides.

[0007] Furthermore, the outer camber shaft passes through the outer bearing assembly to connect with the tilt wing, and the inner camber shaft passes through the inner bearing assembly to connect with the electromagnetic clutch. By controlling the disconnection and connection of the electromagnetic clutch, the separation and connection of the left and right tilt shafts can be achieved.

[0008] Furthermore, the outer bearing assembly includes an outer bearing support and an outer bearing, the outer bearing support is fixedly connected to the fuselage by bolts, the outer bearing is a sliding bushing with a flanged edge embedded in the outer bearing support, and the camber shaft passes through the outer bearing and is connected to the tilt wing. Not only does it achieve rolling connection and force with the camber shaft, but it also limits the sliding and force of the tilt shaft into the fuselage.

[0009] Furthermore, the inner bearing assembly includes an inner bearing support and an inner bearing, the inner bearing support is fixedly connected to the fuselage, the inner bearing is a sliding bushing with a flanged edge embedded in the inner bearing support, and the inner tilt shaft passes through the inner bearing and is connected to the electromagnetic clutch. This not only realizes the rolling connection and force with the inner tilt shaft, but also limits the sliding and force of the tilt shaft to the outside of the fuselage.

[0010] Furthermore, bearing retaining rings are provided inside the outer bearing support and the inner bearing support.

[0011] Furthermore, it also includes a steering gear support, which is fixedly connected to the fuselage, the inner bearing support is arranged on the steering gear support, a flange is provided on the inner side of the steering gear support, and the steering gear is arranged inside the steering gear support through the flange.

[0012] Furthermore, a shaft-rudder connecting flange is provided on the side of the steering gear support, the inward tilt shaft is connected to the outward tilt shaft in the shaft-rudder connecting flange, and the inward tilt shaft is inserted into the outward tilt shaft, and the outward tilt shaft is rotatably arranged in the shaft-rudder connecting flange.

[0013] Furthermore, the servo support is an integrated box-shaped structure with an opening at the top, and a power cable through hole is provided on the shaft-rudder connecting flange, and the power cable passes through the power cable through hole from the tilt shaft and is connected to the interior of the fuselage.

[0014] Furthermore, the inwardly tilted shaft is fixedly connected to the electromagnetic clutch via a connecting flange.

[0015] Compared with the prior art, the variable connection eVTOL tilt-wing tilt mechanism with high rigidity and high reliability provided by the present invention has the following beneficial effects: The invention provides a high-rigidity and high-reliability variable connection eVTOL tilt-wing tilt mechanism, which realizes the free switching connection and disconnection of the left and right wings, and achieves high rigidity, high reliability and light weight. It has a simple structure, is easy to produce, and is easy to integrate and arrange, and is very suitable for the intelligent flight control system of the tilt-wing eVTOL. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of a high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism according to the present invention; Figure 2 This is a cross-sectional view of a high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism described in the present invention (tilt-wing omitted).

[0017] In the figure: 1-servo, 2-electromagnetic clutch, 3-inward tilt shaft, 4-outward tilt shaft, 5-tilt wing, 6-outer bearing assembly, 61-outer bearing support, 62-outer bearing, 7-inner bearing assembly, 71-inner bearing support, 72-inner bearing, 8-servo support, 81-axis rudder connecting flange, 82-power cable through hole. DETAILED DESCRIPTION

[0018] The preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making a clearer and more specific definition of the protection scope of the present invention. The embodiments of the present invention include the following parts: Embodiment 1: like Figure 1 As shown, a high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism includes a group of servos 1, a tilt shaft and an electromagnetic clutch 2, wherein the tilt shaft includes an inner tilt shaft 3 and an outer tilt shaft 4, wherein the inner tilt shaft 3 passes through the servo 1 and is connected to the electromagnetic clutch 2, and the other end is connected to the outer camber shaft 4, and the other end of the outer camber shaft 4 is connected to the tilt-wing 5; in this embodiment, the servo 1 adopts an intelligent frameless motor system, which is connected to the tilt-wing through the tilt shaft to achieve high-precision, high-response, and high-torque power transmission, and is connected to the flight control system through a CAN signal line to achieve rapid wing tilting.

[0019] The steering gear 1 is symmetrically arranged with respect to the electromagnetic clutch 2, and the electromagnetic clutch 2 can control the separation and connection of the left and right tilt axes. The flight control software controls the disconnection and connection of the electromagnetic clutch 2, thereby realizing the separation and connection of the left and right tilt axes.

[0020] like Figure 2 As shown, the camber shaft 4 is connected to the tilt wing 5 through the outer bearing assembly 6 , and the inner camber shaft 3 is connected to the electromagnetic clutch 2 through the inner bearing assembly 7 .

[0021] The outer bearing assembly 6 includes an outer bearing support 61 and an outer bearing 62. The outer bearing support 61 is fixedly connected to the fuselage by bolts. The outer bearing 62 is a sliding bushing with a flange and is embedded in the outer bearing support 61. The camber shaft 4 passes through the outer bearing 62 and is connected to the tilt wing 5. In this embodiment, the outer bearing 62 is embedded in the bearing support 61 with a sliding bushing with a flange, which not only realizes the rolling connection and force with the camber shaft 4, but also limits the sliding and force of the tilt shaft toward the inside of the fuselage.

[0022] The inner bearing assembly 7 includes an inner bearing support 71 and an inner bearing 72. The inner bearing support 71 is fixedly connected to the fuselage. The inner bearing 72 is a sliding bushing with a flange and is embedded in the inner bearing support 71. The inner tilt shaft 3 passes through the inner bearing 72 and is connected to the electromagnetic clutch 2. The inner bearing 72 in this embodiment is embedded in the bearing support 71 with a sliding bushing with a flange, which not only realizes the rolling connection and force with the inner tilt shaft 3, but also limits the sliding and force of the tilt shaft to the outside of the fuselage.

[0023] The outer bearing support 61 and the inner bearing support 71 are both provided with bearing retaining rings, so as to further improve the stability of rolling connection and force, and enhance the reliability of the overall structure.

[0024] Embodiment 2: Based on the embodiment 1, the present embodiment further includes a steering gear support 8, please refer to Figure 1 The steering gear support 8 is fixedly connected to the fuselage, the inner bearing support 71 is arranged on the steering gear support 8, a flange is provided on the inner side of the steering gear support 8, and the steering gear 1 is arranged inside the steering gear support 8 through the flange.

[0025] Among them, a shaft-rudder connecting flange 81 is set on the side of the steering gear support 8, the inclination shaft 3 is connected to the camber shaft 4 in the shaft-rudder connecting flange 81, and the inclination shaft 3 is inserted into the camber shaft 4, and the camber shaft 4 is rotatably set in the shaft-rudder connecting flange 81.

[0026] The servo support 8 is an integrated box-shaped structure with an upper opening. The shaft-rudder connecting flange 81 is provided with a power cable through hole 82. The power cable passes through the power cable through hole 82 from the tilt shaft and is connected to the interior of the fuselage.

[0027] The flange on the inner side of the steering gear support 8 is formed by integrated turning and milling. The steering gear support 8 adopts an aluminum alloy integrated casting process and is in an open box shape as a whole to ensure sufficient rigidity and strength. It is fixed to the fuselage by bolts.

[0028] The inner tilt shaft 3 is fixedly connected to the electromagnetic clutch 2 via a connecting flange.

[0029] The working principle of a high-rigidity and high-reliability variable connection eVTOL tilt-wing tilt mechanism disclosed in the present invention is as follows: During the take-off and landing phase of the aircraft, the tilt-wing 5 rotates as a whole to a vertical state of about 90°. When transitioning to the cruise phase, the flight control system sends a command to the servo 1 through the CAN signal bus. The servo 1 starts to drive the tilt-wing 5 through the tilt shaft according to the flight control command. The tilt-wing 5 starts to rotate under the limit of the inner bearing 72 and the outer bearing 62, and finally rotates to a horizontal state of about 0°.

[0030] The above description is only a preferred embodiment of the present invention. It should be pointed out that a person skilled in the art can make several improvements without departing from the principle of the present invention, and these improvements should also be regarded as within the protection scope of the present invention.

Claims

1. A high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism, characterized in that: The invention comprises a set of steering gears (1), a tilt shaft and an electromagnetic clutch (2), wherein the tilt shaft comprises an inner tilt shaft (3) and an outer tilt shaft (4), wherein the inner tilt shaft (3) passes through the steering gear (1) and is connected to the electromagnetic clutch (2), and the other end is connected to the outer tilt shaft (4), and the other end of the outer tilt shaft (4) is connected to the tilt wing (5); The steering gear (1) is symmetrically arranged with respect to the electromagnetic clutch (2), and the electromagnetic clutch (2) can control the separation and connection of the tilting shafts on the left and right sides.

2. The high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism according to claim 1, characterized in that: The outer camber shaft (4) passes through an outer bearing assembly (6) to be connected to the tilting wing (5), and the inner camber shaft (3) passes through an inner bearing assembly (7) to be connected to the electromagnetic clutch (2).

3. The high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism according to claim 2, characterized in that: The outer bearing assembly (6) comprises an outer bearing support (61) and an outer bearing (62); the outer bearing support (61) is fixedly connected to the fuselage by bolts; the outer bearing (62) is a sliding bushing with a flange and is embedded in the outer bearing support (61); and the outer tilt shaft (4) passes through the outer bearing (62) and is connected to the tilt wing (5).

4. The high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism according to claim 3, characterized in that: The inner bearing assembly (7) comprises an inner bearing support (71) and an inner bearing (72); the inner bearing support (71) is fixedly connected to the fuselage; the inner bearing (72) is a sliding bushing with a flange and is embedded in the inner bearing support (71); and the inner tilt shaft (3) passes through the inner bearing (72) and is connected to the electromagnetic clutch (2).

5. The high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism according to claim 4, characterized in that: The outer bearing support (61) and the inner bearing support (71) are both provided with bearing retaining rings therein.

6. The high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism according to claim 5, characterized in that: It also includes a steering gear support (8), the steering gear support (8) is fixedly connected to the fuselage, the inner bearing support (71) is arranged on the steering gear support (8), a flange is provided on the inner side of the steering gear support (8), and the steering gear (1) is arranged inside the steering gear support (8) through the flange.

7. The high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism according to claim 6, characterized in that: A shaft-rudder connection flange (81) is provided on the side of the steering gear support (8); the inward-curved rotating shaft (3) is connected to the outward-curved rotating shaft (4) in the shaft-rudder connection flange (81); the inward-curved rotating shaft (3) is inserted into the outward-curved rotating shaft (4); and the outward-curved rotating shaft (4) is rotatably disposed in the shaft-rudder connection flange (81).

8. The high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism according to claim 7, characterized in that: The steering gear support (8) is an integrated box-shaped structure with an upper opening, and the shaft-rudder connecting flange (81) is provided with a power cable through hole (82), through which the power cable passes from the tilt shaft into the fuselage.

9. The high-rigidity and high-reliability variable-connection eVTOL tilt-wing tilt mechanism according to claim 1, characterized in that: The inwardly tilted rotating shaft (3) is fixedly connected to the electromagnetic clutch (2) via a connecting flange.

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