Steering engine structure and aircraft

Abstract

The invention provides a steering engine structure and an aircraft, and relates to the technical field of aircraft control systems, the steering engine structure is used for being arranged in a driving cabin of the aircraft, and the steering engine structure comprises a supporting assembly; the driving motor is arranged on the supporting assembly; the shaft body is rotationally connected to the supporting assembly, the shaft body is connected with a rotor of the driving motor through a first transmission assembly, the shaft body is used for being connected with a control surface of the aircraft, and the control surface can swing when the shaft body rotates; the feedback assembly is arranged on the driving motor and connected with the rotor, and the feedback assembly is used for monitoring the implementation position of the rotor; and the control terminal is in signal connection with the driving motor and the feedback assembly, and has the characteristics of simple structure, small size, light weight and capability of realizing multi-circle rotation action, is easy to mount and dismount, and is suitable for the control requirements of various aircrafts.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft control systems, and more specifically, relates to a steering gear structure and an aircraft. Background Art

[0002] With the continuous development of aviation technology, the performance requirements of aircraft are increasing day by day, and higher requirements are also placed on the design of small-torque, multi-turn rotary servos.

[0003] The main function of the servo is to receive instructions and execute corresponding commands according to the operator's intention, so as to maintain or change the heading of the aircraft. The servo is an actuator used to control the rotation of the aircraft's control surfaces to ensure flight stability and directional control.

[0004] Traditional small-torque, multi-turn rotary servos have complex structures and bulky sizes, which not only increase the weight and manufacturing cost of the aircraft, but also make installation and maintenance in a small space difficult. Therefore, it is of great significance to develop a new type of aircraft small-torque, multi-turn rotary servo structure with simple structure, small size, light weight and easy maintenance. Summary of the invention

[0005] The purpose of the present invention is to provide a servo structure and an aircraft in view of the deficiencies in the existing technology, so as to solve the problems mentioned in the above background technology that the existing servo structure is complex and bulky, which not only increases the weight and manufacturing cost of the aircraft, but also makes installation and maintenance in a small space difficult.

[0006] In order to achieve the above object, the present invention provides a steering gear structure for being arranged in a driving cabin of an aircraft, the steering gear structure comprising:

[0007] Support components;

[0008] A driving motor, wherein the driving motor is arranged on the supporting assembly;

[0009] A shaft body, the shaft body is rotatably connected to the support assembly, the shaft body is connected to the rotor of the drive motor via a first transmission assembly, the shaft body is used to be connected to the control surface of the aircraft, and the control surface can swing when the shaft body rotates;

[0010] A feedback component, the feedback component is arranged on the driving motor and connected to the rotor, and the feedback component is used to monitor the real-time position of the rotor;

[0011] A control terminal is connected to the drive motor and the feedback component by signal, the control terminal can receive a monitoring signal fed back by the feedback component, and the control terminal can control the operation of the drive motor according to the monitoring signal.

[0012] Preferably, the servo structure further includes a brake assembly, which is arranged on the drive motor and connected to the rotor, and the control terminal is signal-connected to the brake assembly, and the control terminal can send instructions to the brake assembly to lock the rotor or release the rotor.

[0013] Preferably, the steering gear structure further includes:

[0014] A lead screw linear module, wherein the lead screw linear module is arranged on the support assembly, and the lead screw of the lead screw linear module is connected to the shaft body through a second transmission assembly;

[0015] Two in-position switches are arranged on the lead screw linear module and on both sides of the moving part of the lead screw linear module. The control terminal is connected to the two in-position switch signals. When the moving part of the lead screw linear module touches one of the two in-position switches, the control terminal can receive the in-position signal sent by the in-position switch, and the control terminal can send an instruction to lock the rotor to the brake assembly according to the in-position signal.

[0016] Preferably, the servo structure also includes a controller, which is arranged on the lead screw linear module, and is electrically connected to the drive motor, the feedback component, the brake component, the lead screw linear module and the in-position switch, and the control terminal is signal-connected to the controller.

[0017] Preferably, the support assembly includes two brackets, the two brackets are arranged at an interval, the shaft and the screw linear module are arranged on the two brackets, the drive motor is arranged on one of the brackets, and the feedback assembly and the screw linear module are arranged on the other bracket.

[0018] Preferably, the first transmission assembly and the second transmission assembly are both gear sets.

[0019] Preferably, the feedback component is a potentiometer or an encoder.

[0020] Preferably, the steering gear structure further comprises a housing, wherein the housing is arranged on the supporting assembly, and the first transmission assembly and the second transmission assembly are both arranged in the housing.

[0021] An aircraft includes a steering gear structure.

[0022] The present invention provides a steering gear structure and an aircraft, which have the following beneficial effects: the steering gear structure is optimized in design compared with the original steering gear structure, the driving motor and the shaft of the steering gear structure are directly arranged on a supporting assembly and connected through a first transmission assembly, compared with the original shell design, it is convenient for maintenance and protection, and is also beneficial for heat dissipation, the control terminal can receive a monitoring signal fed back by a feedback assembly, and the control terminal can control the operation of the driving motor according to the monitoring signal to achieve control surface angle adjustment, has the characteristics of simple structure, small size, light weight, and can achieve multi-turn rotation, is easy to install and disassemble, is suitable for the control requirements of various aircraft, improves the installation convenience and work efficiency of the steering gear in a small space, and reduces the manufacturing and maintenance costs.

[0023] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0025] Figure 1 A schematic diagram of a three-dimensional structure of a steering gear structure according to an embodiment of the present invention is shown. Figure 1 ;

[0026] Figure 2 A schematic diagram of a three-dimensional structure of a steering gear structure according to an embodiment of the present invention is shown. Figure 2 ;

[0027] Description of reference numerals:

[0028] 1. Support assembly; 2. Drive motor; 3. Shaft; 4. Feedback assembly; 5. Brake assembly; 6. Screw linear module; 7. In-position switch; 8. Bracket; 9. Controller; 10. Cable. DETAILED DESCRIPTION

[0029] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0030] like Figure 1 and Figure 2 As shown, the present invention provides a steering gear structure for being arranged in a driving cabin of an aircraft, and the steering gear structure comprises:

[0031] Support assembly 1;

[0032] A driving motor 2, wherein the driving motor 2 is arranged on the supporting assembly 1;

[0033] A shaft body 3, the shaft body 3 is rotatably connected to the support assembly 1, the shaft body 3 is connected to the rotor of the drive motor 2 through a first transmission assembly, the shaft body 3 is used to connect to the control surface of the aircraft, and the control surface can swing when the shaft body 3 rotates;

[0034] A feedback component 4, which is disposed on the driving motor 2 and connected to the rotor, and is used to monitor the real-time position of the rotor;

[0035] The control terminal is connected to the drive motor 2 and the feedback component 4 by signals. The control terminal can receive the monitoring signal fed back by the feedback component 4, and the control terminal can control the operation of the drive motor 2 according to the monitoring signal.

[0036] Specifically, in order to solve the problem that the existing servo engine has a complex structure and a large size, which not only increases the weight and manufacturing cost of the aircraft, but also is difficult to install and maintain in a small space, the present invention provides a servo engine structure, which is optimized in design compared with the original servo engine structure. The drive motor 2 and the shaft body 3 of the servo engine structure are arranged on the support component 1 and are connected through the first transmission component. The control terminal can receive the monitoring signal fed back by the feedback component 4. The control terminal can send an instruction to the drive motor 2 to adjust the rotation stroke of the rotor according to the monitoring signal to achieve the control surface angle adjustment. It has the characteristics of simple structure, small size, light weight, and can realize multi-turn rotation action. It is easy to install and disassemble, suitable for the control requirements of various aircraft, improves the installation convenience and work efficiency of the servo engine in a small space, and reduces the manufacturing and maintenance costs.

[0037] Preferably, the servo structure further includes a brake assembly 5, which is arranged on the drive motor 2 and connected to the rotor. The control terminal is signal-connected to the brake assembly 5, and the control terminal can send instructions to the brake assembly 5 to lock the rotor or release the rotor.

[0038] Specifically, when the rudder reaches the specified position, the brake assembly 5 can be used to lock the rotor of the drive motor 2 to lock the current position. At this time, the drive motor 2 is in a non-power-generating state to reduce energy consumption. When the rotor of the drive motor 2 rotates to the adjusted position, the control terminal can also automatically control the brake assembly 5 to lock the rotor.

[0039] Preferably, the steering gear structure further comprises:

[0040] The lead screw linear module 6 is arranged on the support assembly 1, and the lead screw linear module 6 is connected to the shaft body 3 through a second transmission assembly;

[0041] Two in-position switches 7 are arranged on the lead screw linear module 6 and on both sides of the moving part of the lead screw linear module 6. The control terminal is connected with the signals of the two in-position switches 7. When the moving part of the lead screw linear module 6 touches one of the two in-position switches 7, the control terminal can receive the in-position signal sent by the in-position switch 7. The control terminal can send an instruction to lock the rotor to the brake assembly 5 according to the in-position signal to prevent the rotor from exceeding the set safe rotation stroke.

[0042] Specifically, the second transmission component can convert the rotational motion of the shaft 3 into the linear motion of the moving part of the screw linear module 6. By using the in-position switch 7 on the screw linear module 6, when the moving part of the screw linear module 6 touches one of the two in-position switches 7, the kinetic power of the rotor of the drive motor 2 can be cut off through the brake component 5. The function of the screw linear module 6 and the in-position switch 7 is to mechanically limit the servo structure to ensure that the rotor of the servo structure will not rotate and will not exceed the set safe rotation stroke when an electrical failure occurs, thereby avoiding uncontrolled rotation of the rotor.

[0043] Preferably, the servo structure also includes a controller 9, which is arranged on the screw linear module 6, and the controller 6 is electrically connected to the drive motor 2, the feedback component 4, the brake component 5, the screw linear module 6 and the in-position switch 7, and the control terminal and the controller 6 are signal connected.

[0044] Specifically, the controller 6 is electrically connected to the flight control of the aircraft through a cable 10, and the flight control is connected to the control terminal signal. A control chip is provided in the controller 6, which is the control part of the servo structure and is used for signal acquisition, processing, and budget method solution to accurately control the movement of the servo structure.

[0045] Preferably, the support assembly includes two brackets 8, the two brackets 8 are arranged at an interval, the shaft 3 and the screw linear module 6 are arranged on the two brackets 8, the drive motor 2 is arranged on one of the brackets 8, and the feedback assembly 4 and the screw linear module 6 are arranged on the other bracket 8.

[0046] Specifically, the two brackets 8 are arranged at intervals to ensure the relative position stability between the components and prevent loosening or damage due to vibration. At the same time, the components are exposed to the air, which is convenient for maintenance and protection and is beneficial for heat dissipation.

[0047] Preferably, the first transmission assembly and the second transmission assembly are both gear sets.

[0048] Specifically, the gear set of the first transmission component is a two-stage gear set, which can realize the function of reducing speed and increasing torque, so that the drive motor 3 can output sufficient torque to drive the rudder surface to move. The gear set of the second transmission component is a one-stage gear set. The first transmission component and the second transmission component can also be a wheel output mechanism, a turbine worm mechanism or a harmonic transmission mechanism.

[0049] Preferably, the feedback component 4 is a potentiometer or an encoder.

[0050] Specifically, the feedback component 1 uses a high-precision potentiometer or encoder to monitor the rotation stroke of the rotor in real time. By transmitting the monitored data to the controller 9, accurate control of the rudder position can be achieved, where the rotation stroke is the number of turns and angle of the rotor.

[0051] Specifically, the nut block of the screw linear module is the moving part of the screw linear module 6.

[0052] Preferably, the steering gear structure further comprises a housing, which is disposed on the supporting assembly 1, and the first transmission assembly and the second transmission assembly are both disposed in the housing.

[0053] Specifically, the design of the shell takes into account the requirements of lightness and strength, and is made of high-strength aluminum alloy material to protect the first transmission assembly and the second transmission assembly.

[0054] An aircraft includes a steering gear structure.

[0055] Specifically, the servo structure of the present invention is a small-torque, multi-turn rotary servo mechanism, which is suitable for controlling an aircraft.

[0056] In summary, when the servo structure provided by the present invention is implemented on an aircraft, the feedback component 4 can monitor the rotation stroke of the rotor, the control terminal can receive the monitoring signal fed back by the feedback component 4, and the control terminal can send an instruction to adjust the rotation stroke of the rotor to the drive motor 2 according to the monitoring signal. The drive motor 2 will drive the shaft body 3 to rotate through the first transmission component, and the rudder surface will swing and adjust when the shaft body 3 rotates. When the rudder surface reaches the specified position, the rotor of the drive motor 2 can be locked by the brake component 5 to lock the current position. When the servo structure or other components of the aircraft send an electrical fault, causing the rotation of the rotor to be out of control, The in-position switch 7 on the screw linear module can be utilized. When the nut block of the screw linear module touches one of the two in-position switches 7, the kinetic power of the rotor of the drive motor 2 can be cut off through the brake assembly 5 to ensure that the rotor of the servo structure will not rotate and will not exceed the set safe rotation stroke when an electrical failure occurs, thereby avoiding the rotor from rotating out of control. The servo structure has the characteristics of simple structure, small size, light weight, mechanical limit, and multi-turn rotation output. It is easy to install and disassemble, suitable for the control requirements of various aircraft, and improves the installation convenience and work efficiency of the servo in a small space, while reducing the manufacturing and maintenance costs.

[0057] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A steering gear structure, used for being arranged in a driving cabin of an aircraft, characterized in that: The steering gear structure includes: Support components; A driving motor, wherein the driving motor is arranged on the supporting assembly; A shaft body, the shaft body is rotatably connected to the support assembly, the shaft body is connected to the rotor of the drive motor via a first transmission assembly, the shaft body is used to be connected to the control surface of the aircraft, and the control surface can swing when the shaft body rotates; A feedback component, the feedback component is arranged on the driving motor and connected to the rotor, and the feedback component is used to monitor the real-time position of the rotor; A control terminal is connected to the drive motor and the feedback component by signal, the control terminal can receive a monitoring signal fed back by the feedback component, and the control terminal can control the operation of the drive motor according to the monitoring signal.

2. A steering gear structure according to claim 1, characterized in that: The servo structure also includes a brake assembly, which is arranged on the drive motor and connected to the rotor. The control terminal is signal-connected to the brake assembly, and the control terminal can send an instruction to lock the rotor or release the rotor to the brake assembly.

3. A steering gear structure according to claim 3, characterized in that: The steering gear structure also includes: A lead screw linear module, wherein the lead screw linear module is arranged on the support assembly, and the lead screw of the lead screw linear module is connected to the shaft body through a second transmission assembly; Two in-position switches are arranged on the lead screw linear module and on both sides of the moving part of the lead screw linear module. The control terminal is connected to the two in-position switch signals. When the moving part of the lead screw linear module touches one of the two in-position switches, the control terminal can receive the in-position signal sent by the in-position switch, and the control terminal can send an instruction to lock the rotor to the brake assembly according to the in-position signal.

4. A steering gear structure according to claim 3, characterized in that: The servo structure also includes a controller, which is arranged on the lead screw linear module, and is electrically connected to the drive motor, the feedback component, the brake component, the lead screw linear module and the in-position switch, and the control terminal is signal-connected to the controller.

5. The steering gear structure according to claim 3, characterized in that: The support assembly includes two brackets, the two brackets are arranged at an interval, the shaft and the screw linear module are arranged on the two brackets, the drive motor is arranged on one of the brackets, and the feedback assembly and the screw linear module are arranged on the other bracket.

6. A steering gear structure according to claim 3, characterized in that: The first transmission assembly and the second transmission assembly are both gear sets.

7. The steering gear structure according to claim 1, characterized in that: The feedback component is a potentiometer or an encoder.

8. The steering gear structure according to claim 6, characterized in that: The steering gear structure further comprises a housing, wherein the housing is arranged on the supporting assembly, and the first transmission assembly and the second transmission assembly are both arranged in the housing.

9. An aircraft, characterized in that: include: A steering gear structure according to any one of claims 1 to 8.

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