Control system and aircraft

Abstract

The embodiment of the utility model provides a control system and an airplane, and relates to the technical field of aircrafts. According to the control system and the airplane, the driving piece, the support and the rocker arm are arranged, and the driving piece can automatically control the steering direction and angle of the rudder; compared with the mode of a mechanical transmission mechanism in the prior art, the control system is simple in overall structure, high in reliability and smaller in occupied space, and the position of the driving part can be reasonably arranged according to the specific structure of the aircraft.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and more specifically, to a control system and an aircraft. Background Technology

[0002] Aircraft in the relevant technology have two rudders, left and right. The rudders are usually controlled by mechanical transmission, that is, the control stick directly controls the rudder to deflect through transmission mechanisms such as steel cables and pulleys.

[0003] However, traditional mechanical transmission mechanisms are complex and require additional pulleys, tensioning mechanisms, etc., which not only increases the overall weight of the drone but also occupies a lot of internal space, thus limiting the placement of other equipment, especially affecting small and medium-sized drones. Utility Model Content

[0004] The purpose of this invention is to provide a control system and an aircraft that can automatically control the steering direction and angle of the rudder.

[0005] The embodiments of this utility model can be implemented as follows:

[0006] In the first direction, this utility model provides a control system for controlling a rudder, the rudder being arranged along a third direction and rotatably connected to the aircraft, and the control system being disposed inside the aircraft;

[0007] The control system includes a drive unit, a support, and a rocker arm. The drive unit and the support are disposed inside the aircraft. The rocker arm is disposed along a second direction and is rotatably connected to the support.

[0008] One end of the rocker arm is connected to the output end of the drive unit, and the other end is connected to one side of the rudder. The drive unit is used to drive the rocker arm to rotate around the support so that the rudder rotates.

[0009] The first direction, the second direction, and the third direction are set perpendicular to each other.

[0010] In an optional embodiment, the control system further includes a linkage arranged along the first direction, one end of which is rotatably connected to the other end of the rocker arm, and the other end is rotatably connected to one side of the rudder.

[0011] In an optional embodiment, the rudder has a first side and a second side disposed opposite to each other along the first direction, and the drive member is located opposite to the first side of the rudder;

[0012] The second side of the rudder is provided with a connecting seat, and the other end of the rocker arm is rotatably connected to the connecting seat.

[0013] In an optional embodiment, the output end of the drive member is provided with an output shaft that extends and retracts along the first direction. One end of the output shaft is connected to the output end of the drive member, and the other end is rotatably connected to one end of the rocker arm.

[0014] In an optional embodiment, the aircraft is provided with a mounting base inside, which is rotatably connected to one end of the drive member, so that the mounting base is rotatably disposed about the first direction.

[0015] In an optional embodiment, the aircraft includes at least a mounting plate, a first bulkhead, and a second bulkhead, the first bulkhead and the second bulkhead being spaced apart along the first direction; the second bulkhead includes a bulkhead body and a reinforcing bulkhead arranged along the second direction, the two ends of the reinforcing bulkhead being connected to the bulkhead body respectively;

[0016] One end of the mounting plate is connected to the main body of the partition frame, and the other end is connected to the first partition frame;

[0017] The drive component is mounted on the mounting plate, and the support is mounted on the first partition and located on the side away from the second partition.

[0018] In an optional embodiment, the first partition frame has a first opening and a second opening at both ends of the rocker arm, and the output end of the drive unit passes through the first opening and is connected to one end of the rocker arm for transmission.

[0019] In an optional embodiment, the drive, the support, and the rocker arm are located on the same plane.

[0020] Secondly, the present invention provides an aircraft, including the control system described in any of the foregoing embodiments, wherein the control system is disposed within the aircraft.

[0021] In an optional embodiment, the aircraft includes an airframe, a tail section at the rear of the airframe, a rudder located at the tail of the airframe and rotatably connected to the airframe, and a control system located within the tail section.

[0022] The beneficial effects of the control system and aircraft provided by this utility model embodiment include:

[0023] This application, by setting up a drive component, a support, and a rocker arm, enables the drive component to automatically control the steering direction and angle of the rudder. Compared with the mechanical transmission mechanism in the prior art, the control system proposed in this application has a simple overall structure, high reliability, and occupies less space. Furthermore, the position of the drive component can be reasonably set according to the specific structure of the aircraft. Attached Figure Description

[0024] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of the structure of the control system from a first-person perspective provided in this embodiment;

[0026] Figure 2 This is a schematic diagram of the structure of the control system from a second perspective provided in this embodiment;

[0027] Figure 3 This is a schematic diagram of the control system from a third-person perspective provided in this embodiment;

[0028] Figure 4 This is a top view of the control system provided in this embodiment.

[0029] Icons: 010 - Aircraft; X - First direction; Y - Second direction; Z - Third direction; 100 - Rudder; 110 - Connector; 200 - Airframe; 210 - First bulkhead; 211 - First opening; 212 - Second opening; 220 - Second bulkhead; 221 - Bulkhead body; 222 - Reinforced bulkhead; 230 - Mounting plate; 231 - Mounting seat; 300 - Control system; 310 - Drive component; 311 - Output shaft; 312 - Connector; 320 - Support; 330 - Rocker arm; 340 - Linkage rod. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0031] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0032] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0033] In the description of this utility model, it should be noted that if terms such as "upper," "lower," "inner," or "outer" are used to indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the utility model product is usually placed during use, they are only for the convenience of describing this utility model 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 utility model.

[0034] Furthermore, the terms "first" and "second" are used only to distinguish descriptions and should not be interpreted as indicating or implying relative importance.

[0035] It should be noted that, where there is no conflict, the features in the embodiments of this utility model can be combined with each other.

[0036] The overall structure, working principle, and technical effects of the control system 300 provided by this utility model are described in detail below with reference to the embodiments and accompanying drawings.

[0037] Please refer to Figures 1-4 The control system 300 provided by this utility model is applied to an aircraft 010 and used to control the rudder 100.

[0038] The present invention proposes an aircraft 010, including a control system 300, which is disposed within the aircraft 010.

[0039] Optionally, aircraft 010 can be an unmanned cargo aircraft, a general aviation small aircraft, etc.

[0040] In this embodiment, the aircraft 010 includes a fuselage 200, a tail compartment at the tail of the fuselage 200, a rudder 100 disposed at the tail of the fuselage 200 and rotatably connected to the fuselage 200; and a control system 300 disposed in the tail compartment.

[0041] In this embodiment, please refer to Figures 1-4 The rudder 100 is set along the third direction Z and is rotatably connected to the tail of the fuselage 200 through a rotating shaft; so that the rudder 100 can rotate around the rotating shaft, thereby realizing the steering function of the aircraft 010.

[0042] In this embodiment, the body 200 includes multiple partitions and a skin. The multiple partitions are spaced apart along the extending direction of the body 200, and the skin surrounds the multiple partitions and is riveted to the partitions.

[0043] In this embodiment, please refer to Figures 1-4 If the control system 300 is located in the tail compartment, then the fuselage 200 of the aircraft 010 located in the tail compartment includes a mounting plate 230, a first bulkhead 210 and a second bulkhead 220. The first bulkhead 210 and the second bulkhead 220 are spaced apart along a first direction X. The second bulkhead 220 includes a bulkhead body 221 and a reinforcing bulkhead 222 arranged along a second direction Y. The two ends of the reinforcing bulkhead 222 are respectively connected to the bulkhead body 221. One end of the mounting plate 230 is connected to the bulkhead body 221 and the other end is connected to the first bulkhead 210.

[0044] Please refer to Figures 1-4 The present invention proposes a control system 300, wherein the rudder 100 is arranged along the third direction Z and is rotatably connected to the aircraft 010, and the control system 300 is disposed inside the aircraft 010;

[0045] The control system 300 includes a drive unit 310, a support 320 and a rocker arm 330. The drive unit 310 and the support 320 are disposed inside the aircraft 010. The rocker arm 330 is disposed along the second direction Y and is rotatably connected to the support 320.

[0046] One end of the rocker arm 330 is connected to the output end of the drive unit 310, and the other end is connected to one side of the rudder 100. The drive unit 310 is used to drive the rocker arm 330 to rotate around the support 320 so that the rudder 100 can rotate.

[0047] Among them, the first direction X, the second direction Y, and the third direction Z are set perpendicular to each other.

[0048] It is understood that when the drive member 310 drives the rocker arm 330 to rotate clockwise around the support 320, the other end of the rocker arm 330 drives the rudder 100 to rotate counterclockwise; conversely, when the drive member 310 drives the rocker arm 330 to rotate counterclockwise around the support 320, the other end of the rocker arm 330 drives the rudder 100 to rotate clockwise. Therefore, compared to the mechanical transmission mechanism in the prior art, the control system 300 in this application, by setting up the drive member 310, the support 320, and the rocker arm 330, allows the drive member 310 to automatically control the steering direction and angle of the rudder 100. Furthermore, the control system 300 has a simple overall structure, high reliability, and occupies less space. The position of the drive member 310 can also be reasonably set according to the specific structure of the aircraft 010.

[0049] In this embodiment, the control system 300 includes a drive unit 310.

[0050] The drive unit 310 is used to drive the rocker arm 330 to rotate around the support 320 so that the rudder 100 rotates.

[0051] In this embodiment, please refer to Figures 2-4 The output end of the drive member 310 is provided with an output shaft 311 that extends and retracts along the first direction. One end of the output shaft 311 is connected to the output end of the drive member 310, and the other end is rotatably connected to one end of the rocker arm 330.

[0052] Optionally, the other end of the output shaft 311 is provided with a first hinge portion, the first hinge portion is provided with a first groove, one end of the rocker arm 330 is located in the first groove, and the first hinge portion provided at the other end of the output shaft 311 is hinged to one end of the rocker arm 330 through a first hinge shaft.

[0053] Optionally, the drive unit 310 can be a servo motor.

[0054] It is understandable that by setting up the drive unit 310, which is connected to the external flight control system, the drive unit 310 can automatically control the steering direction and angle of the rudder 100 by operating on the external flight control system.

[0055] In this embodiment, please refer to Figures 2-4 The aircraft 010 has an internal mounting plate 230, and a mounting base 231 is fixed on the mounting plate 230. The mounting base 231 is rotatably connected to one end of the drive component 310 so that the mounting base 231 can be rotatably set around the first direction X.

[0056] The drive member 310 has a connecting part 312 extending from its housing. The mounting base 231 has a second hinge part with a second groove. The connecting part 312 is located in the second groove. The connecting part 312 of the drive member 310 and the second hinge part of the mounting base 231 are hinged together by a second hinge shaft.

[0057] Understandably, the drive component 310 is rotatably connected to the mounting assembly, enabling the drive component 310 to adapt to multi-degree-of-freedom motion and avoiding motion interference caused by rigid connections, which is especially suitable for scenarios requiring complex angle adjustments; it also eliminates the need for high-precision installation and positioning of the hinge, reducing the difficulty of processing and assembly; at the same time, during the change of direction of the control system 300, the hinge structure can buffer instantaneous torque changes, reduce the oscillation of the control system 300, and improve the control accuracy of the drive component 310.

[0058] In this embodiment, the control system 300 includes a support 320 and a rocker arm 330.

[0059] In this embodiment, please refer to Figures 2-4 The support 320 is disposed on the first partition 210 and located on the side away from the second partition 220. The rocker arm 330 is disposed along the second direction Y and is rotatably connected to the support 320.

[0060] Optionally, the support 320 is hinged to the midpoint of the rocker arm 330. The support 320 is provided with a third groove along the second direction Y, the rocker arm 330 passes through the third groove, and the midpoint of the rocker arm 330 is hinged to the support 320 through a third hinge axis.

[0061] In this embodiment, the first partition 210 has a first opening 211 and a second opening 212 at both ends relative to the rocker arm 330. The output shaft 311 of the output end of the drive member 310 passes through the first opening 211 and is connected to one end of the rocker arm 330 for transmission.

[0062] Understandably, this configuration of the control system 300 allows it to be integrated with the overall structure of the fuselage, enabling the drive unit 310 to be designed in a reasonable position and making good use of the space in the tail section.

[0063] In this embodiment, the control system 300 includes a linkage 340.

[0064] The connecting rod 340 is used to connect the rudder 100 and the other end of the rocker arm 330.

[0065] In this embodiment, please refer to Figures 1-4 The rudder 100 has a first side and a second side that are arranged opposite to each other along the first direction X. The drive member 310 is located opposite to the first side of the rudder 100. The second side of the rudder 100 is provided with a connecting seat 110, and the other end of the rocker arm 330 is rotatably connected to the connecting seat 110.

[0066] In this embodiment, the control system 300 further includes a link 340 arranged along the first direction X. One end of the link 340 is rotatably connected to the other end of the rocker arm 330, and the other end is rotatably connected to one side of the rudder 100.

[0067] Furthermore, the connecting rod 340 has a fourth hinge portion at both ends, and a fourth groove is provided in the fourth hinge portion; the other end of the rocker arm 330 is located in the fourth groove, and one end of the connecting rod 340 is hinged to the other end of the rocker arm 330 through the fourth hinge shaft; the connecting seat 110 on the rudder 100 is located in the fourth groove, and the other end of the connecting rod 340 is hinged to the connecting seat 110 of the rudder 100 through the fourth hinge shaft.

[0068] It is worth mentioning that the length of the connecting rod 340 is adjustable, and the drive component 310 can be designed in a reasonable position according to the length of the connecting rod 340.

[0069] In this embodiment, please refer to Figure 1 The drive component 310, support 320, rocker arm 330 and connecting rod 340 are located on the same plane.

[0070] Optionally, the drive member 310, support 320, rocker arm 330, and connecting rod 340 may be located on a horizontal plane inclined relative to the first direction X. Of course, the drive member 310, support 320, rocker arm 330, and connecting rod 340 may be located on a horizontal plane arranged along the first direction X.

[0071] Understandably, by making the drive unit 310, support 320, rocker arm 330 and connecting rod 340 of the control system 300 coplanar, the three-dimensional mechanical transmission mechanism of the prior art can be eliminated, reducing manufacturing and maintenance costs. At the same time, the control system 300 has a simple structure and reduces the steering components of the prior art, thereby improving the reliability of the control system 300 in controlling the rudder 100.

[0072] The working principle and process of the control system 300 provided in this embodiment of the utility model are as follows:

[0073] When the output shaft 311 of the drive unit 310 retracts, and the output shaft 311 drives the rocker arm 330 to rotate clockwise around the support 320, the other end of the rocker arm 330 pulls the rudder 100 to rotate counterclockwise through the connecting rod 340.

[0074] When the output shaft 311 of the drive unit 310 extends out and drives the rocker arm 330 to rotate counterclockwise around the support 320, the other end of the rocker arm 330 pushes the rudder 100 to rotate clockwise through the connecting rod 340.

[0075] In summary, the control system 300 and aircraft 010 provided in this embodiment of the present invention, by setting up a drive component 310, a support 320 and a rocker arm 330, enable the drive component 310 to automatically control the steering direction and angle of the rudder 100. Compared with the mechanical transmission mechanism in the prior art, the control system 300 proposed in this application has a simple overall structure, high reliability, and occupies less space. Furthermore, the position of the drive component 310 can be reasonably set according to the specific structure of the aircraft 010.

[0076] The above are merely specific embodiments of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model.

Claims

1. A control system, characterized in that, The control system is used to operate the rudder, which is arranged along a third direction and rotatably connected to the aircraft; the control system is located inside the aircraft. The control system includes a drive unit, a support, and a rocker arm. The drive unit and the support are disposed inside the aircraft. The rocker arm is disposed along a second direction and is rotatably connected to the support. One end of the rocker arm is connected to the output end of the drive unit, and the other end is connected to one side of the rudder. The drive unit is used to drive the rocker arm to rotate around the support so that the rudder rotates. The first direction, the second direction, and the third direction are set perpendicular to each other.

2. The operating system according to claim 1, characterized in that, The control system also includes a linkage arranged along the first direction, one end of which is rotatably connected to the other end of the rocker arm, and the other end is rotatably connected to one side of the rudder.

3. The operating system according to claim 1, characterized in that, The rudder has a first side and a second side that are disposed opposite to each other along the first direction, and the drive member is located opposite to the first side of the rudder. The second side of the rudder is provided with a connecting seat, and the other end of the rocker arm is rotatably connected to the connecting seat.

4. The control system according to claim 1, characterized in that, The output end of the drive component is provided with an output shaft that extends and retracts along the first direction. One end of the output shaft is connected to the output end of the drive component, and the other end is rotatably connected to one end of the rocker arm.

5. The operating system according to claim 1, characterized in that, The aircraft is equipped with a mounting base inside, which is rotatably connected to one end of the drive component, so that the mounting base can be rotatably arranged around the first direction.

6. The operating system according to claim 1, characterized in that, The aircraft includes at least a mounting plate, a first bulkhead, and a second bulkhead, the first bulkhead and the second bulkhead being spaced apart along a first direction; the second bulkhead includes a bulkhead body and a reinforcing bulkhead arranged along a second direction, the two ends of the reinforcing bulkhead being connected to the bulkhead body respectively; One end of the mounting plate is connected to the main body of the partition frame, and the other end is connected to the first partition frame; The drive component is mounted on the mounting plate, and the support is mounted on the first partition and located on the side away from the second partition.

7. The operating system according to claim 6, characterized in that, The first partition frame has a first opening and a second opening at both ends of the rocker arm, and the output end of the drive unit passes through the first opening and is connected to one end of the rocker arm for transmission.

8. The operating system according to claim 1, characterized in that, The drive unit, the support, and the rocker arm are located on the same plane.

9. An aircraft, characterized in that, The system includes the control system according to any one of claims 1-8, wherein the control system is disposed within the aircraft.

10. The aircraft according to claim 9, characterized in that, The aircraft includes an airframe, a tail section at the rear of the airframe, a rudder located at the tail of the airframe and rotatably connected to the airframe, and a control system located within the tail section.

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