Aircraft and servo buffer mechanism thereof

Abstract

A servo buffer mechanism, comprising: a servo (1), wherein a driving end of the servo (1) is provided with a rocker arm (11), and the servo (1) is used for driving the rocker arm (11) to swing; a control surface (2), wherein the control surface (2) is provided with a support arm (21), and the support arm (21) and the rocker arm (11) are spaced apart in a first direction; and a buffer link (3), wherein the buffer link (3) comprises a first shaft rod (31), a first bent rod (32), a connecting cross rod (33), a second bent rod (34) and a second shaft rod (35); and the rocker arm (11) can drive the rotation of the control surface (2) by means of the buffer link (3). The double-bent link structure can effectively reduce axial stiffness, thereby reducing the impact load of the control surface on the servo, and prolonging the service life of the servo.

Description

Aircraft and its servo buffer mechanism Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to an aircraft and its servo buffer mechanism. Background Technology

[0002] As a crucial component of aircraft, the servo motor drives all the aircraft's tilting and turning attitudes; therefore, its proper functioning is vital for the aircraft. The servo linkage is the mechanical structure connecting the servo motor to the aircraft's control surfaces, transmitting the servo motor's control force and torque to the control surfaces. In current aircraft control systems, the control surface rocker arm is connected to the servo motor via a linkage. However, because the connection between the linkage and the rocker arm is rigid (usually a straight rod connection), when the control surface is subjected to airflow disturbances during flight, an impulse is applied to the linkage, causing the control surface to oscillate around its axis. The oscillation load on the aerodynamic control surface is then transmitted to the servo motor through the straight rod. This oscillation load is an irregular alternating load that can cause fatigue damage or even destruction to the servo motor structure. Furthermore, the teeth of the servo motor's transmission gears have poor fatigue resistance, and in production practice, tooth damage and breakage frequently occur, seriously impacting the aircraft's flight safety. Summary of the Invention

[0003] The purpose of this application is to provide a servo motor buffer mechanism. The double-bending connecting rod structure of this application can effectively reduce axial stiffness, thereby reducing the impact load of the servo surface on the servo motor and extending the service life of the servo motor.

[0004] To address the aforementioned technical problems, this application provides a servo motor buffer mechanism, comprising: a servo motor, the drive end of which is provided with a rocker arm, the servo motor being used to drive the rocker arm to swing; a control surface, the control surface being provided with a support arm, the support arm being spaced apart from the rocker arm along a first direction; and a buffer link, the buffer link comprising a first shaft, a first bent rod, a connecting crossbar, a second bent rod, and a second shaft; the two ends of the connecting crossbar are respectively connected to the first bent rod and the second bent rod; the first shaft is rotatably mounted on the rocker arm, and the second shaft is rotatably mounted on the support arm; the rocker arm is capable of driving the control surface to rotate via the buffer link.

[0005] This application also provides an aircraft including the aforementioned servo buffer mechanism. The aircraft also includes a fuselage, the servo is disposed on the fuselage, and one end of the control surface is rotatably connected to the fuselage.

[0006] Optionally, the first shaft and the second shaft are axially collinear along the first direction.

[0007] Optionally, the connecting crossbar is arranged axially parallel to the first shaft and the second shaft.

[0008] Optionally, both the first and second bending rods are helical bending rods.

[0009] Optionally, both the first and second bent rods are located on the same side of the connecting crossbar.

[0010] Optionally, the end of the first shaft is provided with a first connecting part, and the first shaft is rotatably connected to the rocker arm through the first connecting part; the second shaft is provided with a second connecting part, and the second shaft is rotatably connected to the rudder surface through the second connecting part.

[0011] Optionally, the second shaft is rotatably connected to the support arm of the rudder surface via a second connecting portion.

[0012] Optionally, the first shaft, the first bending rod, the connecting crossbar, the second bending rod, and the second shaft are integrally formed.

[0013] Optionally, the rocker arm is provided with a plurality of through holes spaced apart in the length direction, and the first connecting part can pass through the through holes to form a rotatable connection with the rocker arm.

[0014] The double-bending connecting rod structure of this application can appropriately reduce the axial stiffness, thereby effectively reducing the impact load on the rudder surface of the servo motor and extending the service life of the servo motor. Attached Figure Description

[0015] Figure 1 shows a structural schematic diagram of the aircraft fuselage and its buffer mechanism according to an embodiment of this application;

[0016] Figure 2 shows a magnified view of part A in Figure 1;

[0017] Figure 3 shows a schematic diagram of the structure of the buffer link in an embodiment of this application;

[0018] Figure 4 shows a structural schematic diagram of the buffer link from another perspective in an embodiment of this application. Detailed Implementation

[0019] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and application systems without departing from the spirit of this application. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other.

[0020] The embodiments of this application will now be described in detail with reference to the accompanying drawings, so that those skilled in the art can easily implement the application. This application may be embodied in many different forms and is not limited to the embodiments described herein.

[0021] For the purpose of clearly describing this application, devices that are not relevant to the description are omitted, and the same or similar components throughout the specification are given the same reference numerals.

[0022] Throughout this specification, when it is said that a device is "connected" to another device, this includes not only "direct connection" but also "indirect connection" by placing other components in between. Furthermore, when it is said that a device "comprises" a certain constituent element, unless otherwise stated otherwise, this does not exclude other constituent elements, but rather implies that other constituent elements may be included.

[0023] When we say that a device is "above" another device, this can mean that it is directly above the other device, or it can mean that other devices are present in between. Conversely, when we say that a device is "directly" "above" another device, there are no other devices present in between.

[0024] Although the terms first, second, etc., are used in some instances herein to describe various elements, these elements should not be limited by these terms. These terms are used only to distinguish one element from another. For example, descriptions such as first interface and second interface, etc. Furthermore, as used herein, the singular forms “a,” “an,” and “the” are intended to also include the plural forms unless the context indicates otherwise. It should be further understood that the terms “comprising,” “including,” indicate the presence of the stated feature, step, operation, element, component, item, kind, and / or group, but do not exclude the presence, occurrence, or addition of one or more other features, steps, operations, elements, components, items, kinds, and / or groups. The terms “or” and “and / or” as used herein are interpreted as inclusive, or mean any one or any combination thereof. Thus, “A, B, or C” or “A, B, and / or C” means “any one of: A; B; C; A and B; A and C; B and C; A, B, and C.” Exceptions to this definition occur only when combinations of elements, functions, steps, or operations are inherently mutually exclusive in some way.

[0025] The technical terms used herein are for reference only to specific embodiments and are not intended to limit the scope of this application. The singular form used herein includes the plural form unless the statement explicitly indicates otherwise. The word "comprising" as used in the specification means to specify a particular characteristic, region, integer, step, operation, element, and / or component, and does not exclude the presence or addition of other characteristics, regions, integers, steps, operations, elements, and / or components.

[0026] Terms such as "below" and "above" indicating relative space are used to more easily explain the relationship of one device relative to another in the accompanying drawings. These terms refer not only to their meaning as shown in the drawings but also to other meanings or operations of the device in use. For example, if the device in the drawings is flipped, a device previously described as "below" another device may now be described as "above" another device. Therefore, the exemplary term "below" encompasses both above and below. The device may be rotated 90° or other angles, and the terms representing relative space are interpreted accordingly.

[0027] Although not explicitly defined, all terms, including technical and scientific terms used herein, shall have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains. Terms defined in commonly used dictionaries shall be further interpreted as having a meaning consistent with the relevant technical literature and the content of this present application, and shall not be over-interpreted as having an ideal or overly formulaic meaning unless otherwise defined.

[0028] 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.

[0029] The embodiments of this application are described below with reference to the accompanying drawings. As shown in Figures 1 and 2, the servo buffer mechanism of this application includes: a servo motor 1, a control surface 2, and a buffer link 3. The drive end of the servo motor 1 is provided with a rocker arm 11, which is used to drive the rocker arm 11 to swing. The control surface 2 is provided with a support arm 21, which is spaced apart from the rocker arm 11 along a first direction. The buffer link 3 connects the support arm 21 and the rocker arm 11. The buffer link 3 includes a first shaft 31, a first bent rod 32, a connecting crossbar 33, a second bent rod 34, and a second shaft 35. The two ends of the connecting crossbar 33 are respectively connected to the first bent rod 32 and the second bent rod 34. The first shaft 31 is rotatably mounted on the rocker arm 11, and the second shaft 35 is rotatably mounted on the support arm 21. The rocker arm 11 can drive the control surface 2 to rotate through the buffer link 3.

[0030] The first shaft 31 has a first connecting part 310 at its end, and the first shaft 31 is rotatably connected to the rocker arm 11 through the first connecting part 310. The second shaft 35 has a second connecting part 350 at its end, and the second shaft 35 is rotatably connected to the rudder surface 2 through the second connecting part 350. Specifically, the second shaft 35 is rotatably connected to the support arm 21 of the rudder surface 3 through the second connecting part 350.

[0031] In one embodiment, the first connecting portion 310 is configured as a spherical bearing. In one embodiment, the second connecting portion 350 is configured as a spherical bearing. In one embodiment, both the first connecting portion 310 and the second connecting portion 350 are configured as spherical bearings. The spherical bearing is rigidly connected to the servo rocker arm 11 or the servo surface support arm 21, which can form a certain degree of rotational freedom, thereby preventing possible displacement of the connecting rod from damaging the servo shaft through the rocker arm.

[0032] When the control surface of an aircraft is disturbed by airflow, oscillation will occur. The double-bending linkage structure of this application can appropriately reduce the axial stiffness, thereby effectively reducing the impact load of the control surface on the servo motor, avoiding the wear of the internal gear of the servo motor caused by the linkage acting directly on the servo motor, and extending the service life of the servo motor.

[0033] In one embodiment, as shown in Figures 3 and 4, the first shaft 31 and the second shaft 35 are arranged axially collinearly along a first direction. Being axially collinear along one direction is more conducive to force transmission and improves force transmission efficiency.

[0034] In one embodiment, the connecting crossbar 33 is axially parallel to the first shaft 31 and the second shaft 35, thus maintaining the direction of force transmission and reducing the stiffness of the straight bar without reducing the magnitude of the force. Preferably, both the first bending bar 32 and the second bending bar 34 are helical bending bars. Helical bending bars can effectively reduce the impact load acting on them and extend the service life of the connecting bar. Of course, the first bending bar 32 and the second bending bar 34 can also be other forms of bending.

[0035] Preferably, the first bending rod 32 and the second bending rod 34 are both located on the same side of the connecting crossbar 33. After reducing the axial stiffness by the first bending rod 32, the second bending rod 34 further reduces the axial stiffness, which can further effectively reduce the impact load of the rudder surface on the servo motor. Moreover, since the first bending rod 32 and the second bending rod 34 are both located on the same side of the connecting crossbar 33, the force can be placed on the same axis, thus greatly reducing the probability of deformation.

[0036] In one embodiment, the buffer link 3 is integrally formed, that is, the first shaft 31, the first bending rod 32, the connecting crossbar 33, the second bending rod 34, and the second shaft 35 are integrally formed and connected. The integrally formed buffer link 3 has a stable structure, is easy to manufacture, has strong buffering capacity, and avoids the risk of loosening that may occur with separate connections.

[0037] Optionally, as shown in Figure 2, the rocker arm 11 is provided with a plurality of through holes 100 spaced apart along its length. The first connecting part 310 can pass through the through holes 100 to form a rotatable connection with the rocker arm 11, thereby allowing the position of the first connecting part 310 on the rocker arm 11 to be adjusted to meet the usage requirements of the drive device. It is worth noting that the different through holes 100 can accommodate buffer connecting rods 3 of different lengths. When the buffer connecting rod 3 is too short or too long, different positions on the rocker arm 11 can be selected for adjustment.

[0038] In one embodiment, the buffer link 3 is a stainless steel link, which has a certain degree of elasticity and can be used for buffering. Furthermore, the stainless steel link has strong corrosion resistance, which can further improve the service life of the buffer link 3. Of course, the buffer link 3 can also be made of other materials; this embodiment does not impose specific limitations.

[0039] This application embodiment also provides an aircraft including the aforementioned servo buffer mechanism. The aircraft includes the servo buffer mechanism and a fuselage 4. The servo buffer mechanism includes a servo 1, a control surface 2, and a buffer link 3. The servo 1 is mounted on the fuselage 4, and one end of the control surface 2 is rotatably connected to the fuselage 4. The drive end of the servo 1 is provided with a rocker arm 11, which is used to drive the rocker arm 11 to swing. The control surface 2 is provided with a support arm 21, which is spaced apart from the rocker arm 11 along a first direction. The buffer link 3 connects the support arm 21 and the rocker arm 11. The buffer link 3 includes a first shaft 31, a first bent rod 32, a connecting crossbar 33, a second bent rod 34, and a second shaft 35. The two ends of the connecting crossbar 33 are respectively connected to the first bent rod 32 and the second bent rod 34. The first shaft 31 is rotatably mounted on the rocker arm 11, and the second shaft 35 is rotatably mounted on the support arm 21. The rocker arm 11 can drive the control surface 2 to rotate via the buffer link 3.

[0040] The double-bending linkage structure of the aircraft in this application can appropriately reduce the axial stiffness, thereby effectively reducing the impact load on the servo surface and the servo motor, avoiding wear of the internal gears of the servo motor caused by the linkage acting directly on the servo motor, and extending the service life of the servo motor.

[0041] 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 servo motor buffer mechanism, characterized in that, include: Servo (1), the drive end of the servo (1) is provided with a rocker arm (11), the servo (1) is used to drive the rocker arm (11) to swing; A rudder surface (2) is provided with a support arm (21), and the support arm (21) and the rocker arm (11) are spaced apart along a first direction; The buffer link (3) includes a first shaft (31), a first curved rod (32), a connecting crossbar (33), a second curved rod (34), and a second shaft (35); the two ends of the connecting crossbar (33) are respectively connected to the first curved rod (32) and the second curved rod (34); the first shaft (31) is rotatably mounted on the rocker arm (11), and the second shaft (35) is rotatably mounted on the support arm (21); the rocker arm (11) can drive the rudder surface (2) to rotate through the buffer link (3).

2. The servo motor buffer mechanism according to claim 1, characterized in that, The first shaft (31) and the second shaft (35) are axially collinear along the first direction.

3. The servo motor buffer mechanism according to claim 1, characterized in that, The connecting crossbar (33) is arranged axially parallel to the first shaft (31) and the second shaft (35).

4. The servo motor buffer mechanism according to claim 1, characterized in that, Both the first bending rod (32) and the second bending rod (34) are helical bending rods.

5. The servo motor buffer mechanism according to claim 1, characterized in that, The first bent rod (32) and the second bent rod (34) are both located on the same side of the connecting crossbar (33).

6. The servo motor buffer mechanism according to claim 1, characterized in that, The first shaft (31) has a first connecting part (310) at its end, and the first shaft (31) is rotatably connected to the rocker arm (11) through the first connecting part (310). The second shaft (35) has a second connecting part (350), and the second shaft (35) is rotatably connected to the rudder surface (2) through the second connecting part (350).

7. The servo motor buffer mechanism according to claim 1, characterized in that, The second shaft (35) is rotatably connected to the support arm (21) of the rudder surface (3) via the second connecting part (350).

8. The servo motor buffer mechanism according to claim 1, characterized in that, The first shaft (31), the first bending rod (32), the connecting crossbar (33), the second bending rod (34), and the second shaft (35) are integrally formed.

9. The servo motor buffer mechanism according to claim 6, characterized in that, The rocker arm (11) is provided with a plurality of through holes (100) spaced apart in the length direction, and the first connecting part (310) can pass through the through holes (100) respectively to form a rotatable connection with the rocker arm (11).

10. An aircraft, characterized in that, The aircraft includes a servo buffer mechanism as described in any one of claims 1-9, and further includes a fuselage (4), wherein the servo (1) is disposed on the fuselage (4), and one end of the control surface (2) is rotatably connected to the fuselage (4).

Images