Modular rudder mechanism and aircraft comprising same

Abstract

The application relates to the field of aircraft technology and discloses a modular steering engine mechanism applied to an aircraft, which comprises a motor module, a controller module and a speed reducer module. The motor module has a rotating shaft, the controller module is installed on the shell of the motor module and is connected with the motor module through a lead wire, and the motor module is connected with the speed reducer module through the rotating shaft so as to drive the speed reducer module to move.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more particularly to a modular servo mechanism and an aircraft comprising the same. Background Technology

[0002] Existing servo motors suffer from complex manufacturing processes, low precision, and a lack of modular design. Their complex overall structure makes them difficult to disassemble, requiring complete disassembly and replacement during testing and maintenance, which is cumbersome and inconvenient. To address these issues, a split-type servo motor was designed that is lightweight, offers high torque, high precision, long lifespan, high transmission efficiency, and high stability, while also being easy to disassemble, replace, and maintain. Summary of the Invention

[0003] This application provides a modular servo mechanism for use in aircraft, including:

[0004] Motor module, the motor module having a rotating shaft;

[0005] A controller module is mounted on the housing of the motor module and connected to the motor module via leads;

[0006] The motor module is connected to the reducer module via the rotating shaft, thereby driving the reducer module to move.

[0007] Optionally, it also includes an output shaft, through which the reducer module transmits the speed and torque output by the motor module to the output shaft, and the output shaft passes through the motor module and the controller module.

[0008] Optionally, the end of the output shaft is provided with a small magnet and a magnetic encoder sensor to detect the position and angle of the motor module.

[0009] Optionally, a limiting component is provided at one end of the output shaft near the controller module, the limiting component being used to limit the axial displacement of the output shaft.

[0010] Optionally, the motor module, the controller module, and the reducer module are assembled into the modular servo mechanism using screws.

[0011] This application also provides an aircraft, including:

[0012] Wings;

[0013] Rudder surface;

[0014] The modular servo mechanism described in the above scheme is installed between the wing and the control surface to connect the wing and the control surface; the servo mechanism has a drive shaft, and when the drive shaft of the servo mechanism rotates, it drives the control surface to rotate around the drive shaft.

[0015] Optionally, the wing surface is aligned with the control surface, and the servo mechanism does not extend beyond the wing surface and the control surface.

[0016] Optionally, the servo mechanism is directly connected to and drives the control surface, and the servo mechanism is connected to the wing via a servo mounting bracket.

[0017] Optionally, it also includes a quick-connect mechanism seat, the servo mechanism being directly connected to and driving the quick-connect mechanism seat to rotate, and the quick-connect mechanism seat being directly connected to the servo surface.

[0018] Optionally, the rudder surface is provided with a rudder surface bracket, which is connected to the quick-connect mechanism seat without gaps, thereby fixing the rudder surface on the quick-connect mechanism seat. Attached Figure Description

[0019] Figure 1 The diagram shown is a structural schematic of the modular servo mechanism of this application.

[0020] Figure 2 The diagram shown is a structural schematic of the control surfaces and wings of this application.

[0021] Figure 3 The diagram shown is a structural schematic of the quick-connect mechanism seat and the rudder surface support of this application.

[0022] Figure 4 The diagram shown is a structural schematic of the servo mounting base of this application. Detailed Implementation

[0023] The following embodiments further illustrate the technical solutions of this application. It should be understood that the specific embodiments described herein are merely for explaining this application. Furthermore, it should be noted that, for ease of description, only the parts relevant to this application are shown in the accompanying drawings, not all of them.

[0024] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections or detachable connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal connections between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0025] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0026] The term "aircraft" is defined as an air transport system of any size having at least one lift propeller as its propulsion source. The term "aircraft" can include both "manned" and "unmanned" air transport systems. A manned aircraft can mean an air transport system carrying one or more human passengers, none of whom have control over the aircraft. A manned aircraft can also mean an air transport system carrying one or more human passengers, some of whom, or one of whom, has partial or full control over the aircraft. An unmanned aircraft can mean an air transport system that does not carry any human passengers and flies autonomously or is remotely controlled by someone at a distance.

[0027] The term "control surface" is defined as a movable aerodynamic surface on an aircraft that generates control force through deflection to adjust flight attitude. The term "stabilizer," as a general term, includes the vertical tail, wings, canards, and horizontal stabilizer. The function of the stabilizer is to provide the aircraft with appropriate static stability. When an aircraft flies in near-uniform straight-line motion, it is often affected by various updrafts or crosswinds. This causes changes in the aircraft's attitude, resulting in yaw, pitch, and roll around its center of gravity. If the aircraft is statically unstable, it cannot automatically return to its original flight attitude. That is, if the aircraft is disturbed by wind and pitches up, it will remain pitched up, and even after the disturbing airflow disappears, the aircraft will retain this pitched attitude and will not be able to return to its original attitude.

[0028] In this specification, aircraft include manned aircraft and any unmanned vehicles, such as unmanned aerial vehicles (UAVs), unmanned aircraft, remote-controlled aircraft, unmanned aircraft systems, any aircraft covered under cycle 328AN / 190 as classified by the International Civil Aviation Organization, etc.

[0029] Embodiments of this application are described below with reference to the accompanying drawings, such as Figure 1 As shown in the figure, a modular servo mechanism according to an embodiment of this application is applied to an aircraft and includes: a motor module 2, a controller module 6, and a reducer module 1.

[0030] The motor module 2 has a rotating shaft 3. The controller module 6 is installed on the housing of the motor module 2 and is connected to the motor module 2 through a lead wire. The motor module 2 is connected to the reducer module 1 through the rotating shaft 3, thereby driving the reducer module 1 to move.

[0031] The modular servo mechanism in this application also includes an output shaft 4, and the reducer module 1 transmits the speed and torque output by the motor module 2 to the output shaft 4, which passes through the motor module 2 and the controller module 6.

[0032] It is worth noting that in this application, motor module 2 is the power source of the servo mechanism. The rotating shaft 3 of motor module 2 is connected to reducer module 1, thereby driving the reducer module 1 to move. Controller module 6, consisting of a control board mounted on the housing of motor module 2 and connected to the leads of drive motor module 2, is the core of the servo mechanism for precise, safe, and efficient operation, achieving closed-loop feedback and high-precision positioning. Reducer module 1 is the output end of the servo mechanism, converting the high speed and low torque output of motor module 2 into low speed and high torque. The three modules are connected by screws to form a complete servo mechanism. This design fully utilizes the structural strength, support, and heat conduction of the components themselves, achieving low weight and high strength, effectively saving materials, reducing weight, simplifying the installation structure and space, and improving the reliability of the servo.

[0033] Furthermore, in this application, the end of the output shaft 4 is provided with a small magnet 7 and a magnetic encoder sensor 9, thereby realizing the detection of the position and angle of the motor module 2.

[0034] It is worth noting that in this embodiment, a limiting component 5 is provided at one end of the output shaft 4 near the controller module 6. The limiting component 5 can be used to limit the axial displacement of the output shaft 4.

[0035] Furthermore, in this embodiment, the motor module 2, controller module 6, and reducer module 1 are assembled using screws to form the modular servo mechanism of this application. This modular design of the servo mechanism enables rapid location of damaged modules, facilitating precise repair and improving the efficiency of maintenance personnel. Simultaneously, this design fully utilizes the structural strength, support, and heat conduction capabilities of the components themselves, achieving low weight and high strength, effectively saving materials, reducing weight, simplifying the installation structure and space, and improving the reliability of the servo.

[0036] The second embodiment of this application provides an aircraft including a wing 10 and a control surface 11, as well as a modular servo mechanism described in the first embodiment, which is installed between the wing 10 and the control surface 11 for connecting the wing 10 and the control surface 11.

[0037] Furthermore, the modular servo mechanism has a drive shaft X, which can drive the rudder surface 11 to rotate around the drive shaft X when the drive shaft X of the modular servo mechanism rotates.

[0038] In this embodiment, the wing 10 is generally referred to as the stabilizer. The control surface 11 is indirectly connected to the wing 10 via a modular servo mechanism, and the control surface 11 is not directly connected to the wing 10. The modular servo mechanism is directly connected to the control surface 11. When the modular servo mechanism rotates, the control surface 11 rotates around the drive shaft X of the modular servo mechanism, and the rotation angle of the control surface 11 is consistent with the rotation angle of the drive shaft X of the modular servo mechanism.

[0039] The modular servo mechanism is directly connected to the control surface 11, allowing it to directly drive the control surface 11 to rotate without the need for a multi-part transmission chain, such as rocker arms or connecting rods. This eliminates the traditional linkage transmission structure, simplifies the transmission path, and ensures zero backlash or misalignment between the modular servo mechanism and the control surface 11, thereby improving the control precision and response speed of the control surface 11.

[0040] Furthermore, compared to traditional linkage transmission structures, which have a more limited maximum deflection angle, modular servo mechanisms with direct drive can be designed to have a larger maximum deflection angle.

[0041] In one embodiment, the surface of wing 10 is aligned with the surface of control surface 11, and the modular servo mechanism does not extend beyond the surfaces of wing 10 and control surface 11. The modular servo mechanism does not disrupt the smooth curved surfaces of wing 10 and control surface 11, thus avoiding disruption to the streamlined surface of the aircraft, effectively preventing wind resistance, and resulting in a simpler design.

[0042] Furthermore, in this embodiment, the modular servo mechanism is directly connected to and drives the control surface 11, and is connected to the wing 10 via the servo mounting base 12. If the modular servo mechanism is used as a standard component, using servo mounting bases 12 of different heights can increase the height of the modular servo mechanism to varying degrees. This allows for adjustment of the position of the modular servo mechanism, adapting to different installation scenarios, increasing installation compatibility, and reducing production costs.

[0043] It is worth noting that in this embodiment, the aircraft also includes a quick-connect mechanism seat 13, and a modular servo mechanism is directly connected to and drives the quick-connect mechanism seat 13 to rotate. The quick-connect mechanism seat 13 is directly connected to the control surface 11.

[0044] Furthermore, in this embodiment, the rudder surface 11 is provided with a rudder surface bracket 14, which is connected to the quick-connect mechanism seat 13 without gap, thereby fixing the rudder surface 11 on the quick-connect mechanism seat 13.

[0045] The above embodiments are merely illustrative of the principles and effects of this application. Any person skilled in the art can modify or alter the above embodiments without departing from the purpose of this application. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the purpose disclosed in this application should still be covered by the claims of this application.

Claims

1. A modular servo mechanism, applied to an aircraft, characterized in that, include: Motor module, the motor module having a rotating shaft; A controller module is mounted on the housing of the motor module and connected to the motor module via leads; The motor module is connected to the reducer module via the rotating shaft, thereby driving the reducer module to move.

2. The modular servo mechanism according to claim 1, characterized in that, It also includes an output shaft, through which the reducer module transmits the speed and torque output by the motor module to the output shaft, and the output shaft passes through the motor module and the controller module.

3. The modular servo mechanism according to claim 2, characterized in that, The output shaft is equipped with a small magnet and a magnetic encoder sensor at its end to detect the position and angle of the motor module.

4. The modular servo mechanism according to claim 3, characterized in that, A limiting component is provided at one end of the output shaft near the controller module, and the limiting component is used to limit the axial displacement of the output shaft.

5. The modular servo mechanism according to claim 4, characterized in that, The motor module, the controller module, and the reducer module are assembled into the modular servo mechanism using screws.

6. An aircraft, characterized in that, include: Wings; Rudder surface; And includes a modular servo mechanism as described in any one of claims 1-5, the servo mechanism being mounted between the wing and the control surface for connecting the wing and the control surface; the servo mechanism having a drive shaft, wherein when the drive shaft of the servo mechanism rotates, it drives the control surface to rotate around the drive shaft.

7. The aircraft according to claim 6, characterized in that, The wing surface is aligned with the control surface, and the servo mechanism does not extend beyond the wing surface and the control surface.

8. The aircraft according to claim 7, characterized in that, The servo mechanism is directly connected to and drives the control surface, and the servo mechanism is connected to the wing via a servo mounting base.

9. The aircraft according to claim 8, characterized in that, It also includes a quick-connect mechanism seat, the servo mechanism is directly connected to and drives the quick-connect mechanism seat to rotate, and the quick-connect mechanism seat is directly connected to the servo surface.

10. The aircraft according to claim 9, characterized in that, The rudder surface is provided with a rudder surface bracket, which is connected to the quick-connect mechanism seat without gaps, thereby fixing the rudder surface on the quick-connect mechanism seat.

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