Modular actuator mounting method and aircraft

Abstract

The application relates to the field of aircraft technology and discloses a modular rudder installation method applied to an aircraft, which comprises the following steps: S1, providing a motor module, the motor module having a rotating shaft; S2, providing a controller module, the controller module being installed on the shell of the motor module and being connected with the motor module through a lead wire; S3, providing a speed reducer module, the motor module being connected with the speed reducer module through the rotating shaft so as to drive the speed reducer module to move; and the motor module, the controller module and the speed reducer module are combined into a modular rudder, and the modular rudder is installed on the aircraft.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to a modular servo mounting method and an aircraft. Background Technology

[0002] Existing servo motors are complex to manufacture, have low precision, lack modular design and installation methods, and are difficult to disassemble due to their complex overall structure. They require complete disassembly and replacement during testing and maintenance, which is troublesome and inconvenient to use. Summary of the Invention

[0003] This application provides a modular servo mounting method for aircraft, including:

[0004] S1: A motor module is provided, the motor module having a rotating shaft;

[0005] S2: A controller module is provided, which is mounted on the housing of the motor module and connected to the motor module via leads;

[0006] S3: A speed reducer module is provided, wherein the motor module is connected to the speed reducer module through the rotating shaft, thereby driving the speed reducer module to move;

[0007] S4: Combine the motor module, the controller module, and the reducer module into a modular servo, and install the modular servo on the aircraft.

[0008] Optionally, S1 specifically includes: mounting the motor module on the output shaft, the reducer module transmitting the speed and torque output by the motor module to the output shaft, and the output shaft passing through the motor module and the controller module.

[0009] Optionally, S1 further includes placing a small magnet and a magnetic encoder sensor at the end of the output shaft to detect the position and angle of the motor module.

[0010] Optionally, S2 specifically includes providing a limiting component 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.

[0011] Optionally, S4 specifically includes: assembling the motor module, the controller module, and the reducer module into a modular servo using 6 M3 screws.

[0012] This application also provides an aircraft, including:

[0013] Wings;

[0014] Rudder surface;

[0015] And a modular servo installed using the modular servo mounting method described above, wherein after S4, the following is also included:

[0016] S5: Install the modular servo between the wing and the control surface to connect the wing and the control surface;

[0017] The modular servo has a drive shaft, and when the drive shaft rotates, it causes the control surface to rotate around the drive shaft.

[0018] Optionally, the wing surface is aligned with the control surface, and S5 further includes: mounting the modular servo at a position not exceeding the wing surface and the control surface.

[0019] Optionally, the modular servo is directly connected to and drives the control surface, and S5 specifically includes: connecting the modular servo to the wing via a servo mounting bracket.

[0020] Optionally, it also includes a quick-connect mechanism seat, wherein the modular servo 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.

[0021] 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

[0022] Figure 1 The diagram shown is a structural schematic of the modular servo motor of this application.

[0023] Figure 2 The diagram shown is a structural schematic of the control surfaces and wings of this application.

[0024] Figure 3 The diagram shown is a structural schematic of the quick-connect mechanism seat and the rudder surface support of this application.

[0025] Figure 4 The diagram shown is a structural schematic of the servo motor mounting base of this application.

[0026] Figure 5 The flowchart shown is a process for installing the modular servo motor according to this application. Detailed Implementation

[0027] 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.

[0028] 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.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] 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.

[0033] Embodiments of this application are described below with reference to the accompanying drawings, such as Figure 1 As shown, a modular servo motor mounting method according to an embodiment of this application, applied to an aircraft, includes:

[0034] S1: Provide a motor module 2;

[0035] S2: Provides a controller module 6;

[0036] S3: Provides a speed reducer module 1;

[0037] S4: Combine motor module 2, controller module 6 and reducer module 1 into a modular servo, and install the modular servo on the aircraft.

[0038] 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.

[0039] The modular servo mounting method in this application, S1 specifically includes: mounting the motor module 2 on the output shaft 4, and the reducer module 1 transmitting the speed and torque output by the motor module 2 to the output shaft 4, with the output shaft 4 passing through the motor module 2 and the controller module 6.

[0040] It is worth noting that in this application, motor module 2 is the power source of the servo. The rotation 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, 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 modular servo. 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.

[0041] Furthermore, in this application, S1 specifically includes: placing a small magnet 7 and a magnetic encoding sensor 9 at the end of the output shaft 4, thereby realizing the detection of the position and angle of the motor module 2.

[0042] It is worth noting that in this embodiment, S2 further includes: setting the limiting component 5 at one end of the output shaft 4 near the controller module 6, and the limiting component 5 can be used to limit the axial displacement of the output shaft 4.

[0043] Furthermore, in this embodiment, S4 specifically includes: assembling the motor module 2, controller module 6, and reducer module 1 into the modular servo motor of this application using six M3 screws. The modular design of this servo motor enables rapid location of damaged modules for precise repair, while also 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 motor.

[0044] The second embodiment of this application provides an aircraft including a wing 10 and a control surface 11, and a modular servo installed using the modular servo installation method described in the first embodiment. S4 is followed by S5: the modular servo is installed between the wing 10 and the control surface 11 to connect the wing 10 and the control surface 11.

[0045] 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 rotates.

[0046] 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, and the control surface 11 is not directly connected to the wing 10. The modular servo is directly connected to the control surface 11. When the modular servo rotates, the control surface 11 rotates around the drive shaft X of the modular servo, and the rotation angle of the control surface 11 is the same as the rotation angle of the drive shaft X of the modular servo.

[0047] The modular servo motor 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 a rocker arm or connecting rod. This eliminates the traditional linkage transmission structure, simplifies the transmission path, and ensures zero backlash or misalignment between the modular servo motor and the control surface 11, thereby improving the control precision and response speed of the control surface 11.

[0048] In addition, compared with the traditional linkage transmission structure, its maximum deflection angle is more limited, and the modular servo direct drive can be designed with a larger maximum deflection angle.

[0049] In one embodiment, the surface of wing 10 is aligned with the surface of control surface 11. S5 further includes: installing the modular servo at a position not exceeding the surfaces of wing 10 and control surface 11. The modular servo does not damage the smooth curved surfaces of wing 10 and control surface 11, thus not disrupting the streamlined surface of the aircraft, effectively avoiding wind resistance, and resulting in a simpler design.

[0050] Furthermore, in this embodiment, the modular servo is directly connected to and drives the control surface 11. S5 specifically includes connecting the modular servo to the wing 10 via the servo mounting base 12. If the modular servo is used as a standard component, using servo mounting bases 12 of different heights can increase the height of the modular servo to varying degrees, thereby adjusting the position of the modular servo to adapt to different installation scenarios, increasing installation compatibility and reducing production costs.

[0051] It is worth noting that in this embodiment, the aircraft also includes a quick-connect mechanism seat 13, a modular servo motor is directly connected to and drives the quick-connect mechanism seat 13 to rotate, and the quick-connect mechanism seat 13 is directly connected to the control surface 11.

[0052] 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, so that the rudder surface 11 is fixed on the quick-connect mechanism seat 13.

[0053] 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 motor mounting method, applied to an aircraft, characterized in that, include: S1: A motor module is provided, the motor module having a rotating shaft; S2: A controller module is provided, which is mounted on the housing of the motor module and connected to the motor module via leads; S3: A speed reducer module is provided, wherein the motor module is connected to the speed reducer module through the rotating shaft, thereby driving the speed reducer module to move; S4: Combine the motor module, the controller module, and the reducer module into a modular servo, and install the modular servo on the aircraft.

2. The modular servo motor installation method according to claim 1, characterized in that, S1 specifically includes: mounting the motor module on the output shaft, the reducer module transmitting the speed and torque output by the motor module to the output shaft, and the output shaft passing through the motor module and the controller module.

3. The modular servo motor installation method according to claim 2, characterized in that, S1 further includes placing a small magnet and a magnetic encoder sensor at the end of the output shaft to detect the position and angle of the motor module.

4. The modular servo motor installation method according to claim 3, characterized in that, S2 specifically includes setting a limiting component 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.

5. The modular servo motor installation method according to claim 4, characterized in that, Specifically, S4 includes assembling the motor module, the controller module, and the reducer module into a modular servo using 6 M3 screws.

6. An aircraft, characterized in that, include: Wings; Rudder surface; And a modular servo installed using the modular servo mounting method as described in any one of claims 1-5, wherein after step S4, the method further includes: S5: Install the modular servo between the wing and the control surface to connect the wing and the control surface; The modular servo has a drive shaft, and when the drive shaft rotates, it causes 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 S5 further includes: mounting the modular servo at a position not exceeding the wing surface and the control surface.

8. The aircraft according to claim 7, characterized in that, The modular servo is directly connected to and drives the control surface. S5 further includes connecting the modular servo to the wing via a servo mounting bracket.

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