Transmission mechanism of aircraft aileron

Abstract

The invention discloses a transmission mechanism of an aircraft aileron, which comprises a wing, an aileron, a bevel gear transmission mechanism and a driving transmission mechanism, and the driving transmission mechanism is a main motion control and power output component and is fixed at the root of the wing. And the driving transmission mechanism drives the aileron to perform fixed-axis rotation through the bevel gear transmission mechanism, so that the attitude adjustment of the aircraft is realized. According to the transmission mechanism of the aircraft aileron, the longitudinal layout mode along the wing root is adopted, and straight tooth bevel gears are used for transmission. Therefore, the whole transmission mechanism has the characteristics of compact structure, high transmission efficiency and the like.

Description

Technical Field

[0001] The invention belongs to the technical field of mechanical design, and in particular relates to a transmission mechanism of an aircraft aileron. Background Art

[0002] Ailerons are important components of fixed-wing aircraft and are key components for aircraft attitude adjustment. At present, research on aircraft ailerons mainly focuses on performance research, including vibration performance, flight control, composite materials, wind tunnel testing, manufacturing, and testing. For example, for multi-wall ailerons, a resin rotary wing molding process (RTM) is used to study the feasibility of aileron integral molding, in order to reduce the manufacturing cost of ailerons. Among them, some research works use composite material integral molding technology to achieve large swept wing design and verification. Focusing on the cabin noise during flight, the influence of gaps on the acoustic and vibroacoustic characteristics of aileron cabins was studied, and the finite element method was used to analyze the noise characteristics and their sources. In order to accurately obtain aerodynamic parameters, the dynamic excitation method is used to excite the modal parameters of the longitudinal and lateral heading of the aircraft, thereby completing the aircraft maneuverability analysis. Since it is difficult to identify the parameters of spoiler and aileron control efficiency, related studies have proposed a method for using flight measurements to identify aileron control derivatives, thereby achieving precise control of the aircraft. With the diversification of flight missions, there are more and more large maneuvers of aircraft, and faults are occurring more and more frequently. Focusing on the interference crack failure, the docking activity of the lower leading edge of the flaperon root and the tail beam bulkhead skin was studied, the source of the relevant interference failure was determined, and relevant prevention methods were proposed. In general, the main research work at present is mostly concentrated on relevant theories and experiments. In addition, in order to verify the strength and stiffness of the aileron control system of the light aircraft and its fuselage connection structure, the problem of too small rudder angle in the operation test was studied, and the displacement of the rocker arm at the key position was measured by applying static load step by step, and the main influence of the fuselage mechanism was determined. In comparison, there is little progress in the research on aileron structure design. Generally, the aircraft wing control methods include mechanical, pneumatic, hydraulic and electric transmission. Among them, electric transmission is the main transmission control method at present. The existing wing transmission mechanism has poor load-bearing capacity, narrow application range, complex structure and low transmission efficiency, and the cost of later maintenance and repair is high. Summary of the invention

[0003] The purpose of the present invention is to solve the above problems and provide a transmission mechanism for an aircraft aileron having a higher load-bearing capacity, strong applicability, compact structure and high transmission efficiency.

[0004] In order to solve the above technical problems, the technical solution of the present invention is: a transmission mechanism of an aircraft aileron, comprising a wing, an aileron, a bevel gear transmission mechanism and an active transmission mechanism, wherein the active transmission mechanism is a main motion control and power output component and is fixed at the root of the wing; the active transmission mechanism drives the aileron to rotate on a fixed axis through the bevel gear transmission mechanism to achieve aircraft attitude adjustment.

[0005] Preferably, the wing includes a wing body, a wing root module and a wingtip module fixed together, and the wing root module and the wingtip module are respectively located at both ends of the wing body; the wing root module includes an aileron front fixing hole, a front fixing plate, a rear fixing plate and a motor connecting plate. In order to achieve a fixed connection, the end face of the aileron front fixing hole is designed with 8 internal threaded holes, and the end faces of the front fixing plate, the rear fixing plate and the motor fixing plate are each provided with 4 light holes; in order to facilitate the installation of the aileron, the wingtip module is provided with an aileron end fixing platform, and 6 aileron end fixing platform holes are provided on the end face of the aileron end fixing platform, and the aileron end fixing platform hole is an internal threaded hole, and the installation and connection of the aileron can be achieved through the aileron front fixing hole and the aileron end fixing platform.

[0006] Preferably, the aileron includes an aileron body, on which an aileron rear end fixing sleeve and an aileron front end fixing sleeve are provided, the aileron rear end fixing sleeve is connected to the aileron end fixing platform on the wing by connecting screws; the aileron front end fixing sleeve is connected to the aileron front fixing hole on the wing, and the aileron is reliably fixed by screw connection.

[0007] Preferably, the front and rear ends of the aileron body are respectively designed with an aileron rear transmission shaft and an aileron front transmission shaft, which are respectively connected to the aileron rear end fixing sleeve and the aileron front end fixing sleeve; the aileron front transmission shaft is provided with a connecting key, which is used to connect the aileron and the aileron front end fixing sleeve.

[0008] Preferably, the aileron front end fixing sleeve includes an aileron front fixing sleeve, a connecting screw, a front end bearing retaining ring, a front end fixing nut of a transmission shaft, a driven bevel gear and a driven bevel gear fixing nut. The aileron front fixing sleeve, the front end bearing retaining ring, the front end fixing nut of a transmission shaft and the driven bevel gear are sequentially sleeved on the aileron front transmission shaft, and the driven bevel gear is connected to the aileron front transmission shaft through a connecting key; the connecting screw passes through the aileron front end fixing sleeve and cooperates with the internal threaded hole.

[0009] Preferably, a sliding bearing is placed inside each of the front and rear ends of the aileron front fixing sleeve, namely a front end bearing and a rear end bearing, to ensure the free rotation of the aileron.

[0010] Preferably, the active transmission mechanism includes a motor, a motor connecting plate, a connecting flange, a rear connecting plate, a front connecting plate and a driving bevel gear, the motor is connected to the motor connecting plate, the rotating shaft end of the motor is connected to the driving bevel gear through the connecting flange, the rear connecting plate and the front connecting plate are respectively sleeved on the driving bevel gear; the front connecting plate, the rear connecting plate and the motor connecting plate respectively cooperate with the front fixing plate, the rear fixing plate and the motor connecting plate of the wing, and are fixed by bolts or screws; the driving bevel gear and the driven bevel gear are meshed.

[0011] Preferably, the rear connecting plate and the front connecting plate are both provided with bearing devices, the bearing devices include bearings and bearing retaining rings, the two bearing retaining rings are respectively bolted to the rear connecting plate and the front connecting plate, and the inner ring of the bearing forms an interference fit with the active bevel gear to achieve transmission.

[0012] The beneficial effects of the present invention are:

[0013] 1. The transmission mechanism of an aircraft aileron provided by the present invention adopts a longitudinal layout along the wing root and uses a spur bevel gear transmission. Therefore, the entire transmission mechanism has the characteristics of compact structure and high transmission efficiency.

[0014] 2. The present invention takes the wing of a fixed-wing aircraft as the research object and proposes a transmission mechanism for an aircraft aileron, in order to achieve rapid maintenance (for example, installation, disassembly) and reliable transmission and control between the aircraft aileron and the wing.

[0015] 3. The transmission mechanism of the aircraft aileron proposed in the present invention has the following three main characteristics: First, it adopts a bevel gear transmission method, which has a high load-bearing capacity and can be used for aileron control of light, medium and heavy-loaded aircraft. It has the characteristics of strong applicability and high load-bearing capacity. Second, the entire bevel gear transmission structure is arranged on the internal rib plate of the wing root, which not only does not occupy the space in the fuselage cabin, but also shortens the transmission route distance of the aileron, reduces the size of the transmission mechanism, and has the characteristics of compact structure and high transmission efficiency. Third, the connection method between the aileron and the wing adopts a differentiated design of "front shaft sleeve and rear fixing plate", which is convenient for the rapid installation and replacement of the aileron, is conducive to aircraft maintenance and repair, and has high maintainability. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of a transmission mechanism of an aircraft aileron of the present invention;

[0017] Figure 2 It is a schematic diagram of the wing root module structure of the wing of the present invention;

[0018] Figure 3 It is a schematic diagram of the wingtip module structure of the wing of the present invention;

[0019] Figure 4It is a structural schematic diagram of the aileron of the present invention;

[0020] Figure 5 It is a structural schematic diagram of the aileron body of the present invention;

[0021] Figure 6 It is a schematic structural diagram of the aileron front end fixing sleeve of the present invention;

[0022] Figure 7 It is a schematic cross-sectional structural diagram of the aileron front fixing sleeve of the present invention;

[0023] Figure 8 It is a structural schematic diagram of the active transmission mechanism of the present invention.

[0024] Description of reference numerals: 1, wing; 2, aileron; 3, bevel gear transmission mechanism; 4, active transmission mechanism; 10, wing body; 11, wing root module; 12, wing tip module; 20, aileron body; 21, aileron rear end fixing sleeve; 22, aileron front end fixing sleeve; 41, motor; 42, motor connecting plate; 43, connecting flange; 44, rear connecting plate; 45, front connecting plate; 46, active bevel gear; 47, bearing; 48, bearing retaining ring; 110, aileron front fixing hole; 111, front fixing plate; 11 2. Rear fixing plate; 113. Motor connecting plate; 114. Internal threaded hole; 115. Light hole; 121. Aileron end fixing platform; 122. Aileron end fixing platform hole; 201. Aileron rear transmission shaft; 202. Aileron front transmission shaft; 203. Connecting key; 220. Aileron front fixing sleeve; 221. Connecting screw; 222. Front end bearing retaining ring; 223. Front end fixing nut of transmission shaft; 224. Driven bevel gear; 225. Driven bevel gear fixing nut; 226. Front end bearing; 227. Rear end bearing. DETAILED DESCRIPTION

[0025] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments:

[0026] like Figures 1 to 8 As shown, the present invention provides a transmission mechanism for an aircraft aileron, comprising a wing 1, an aileron 2, a bevel gear transmission mechanism 3 and an active transmission mechanism 4, wherein the active transmission mechanism 4 is a main motion control and power output component and is fixed at the root of the wing 1. The active transmission mechanism 4 drives the aileron 2 to rotate along a fixed axis through the bevel gear transmission mechanism 3 to achieve aircraft attitude adjustment.

[0027] like Figure 2 and Figure 3As shown, the wing 1 includes a wing body 10, a wing root module 11 and a wing tip module 12 which are fixed together. The wing root module 11 and the wing tip module 12 are respectively located at the two ends of the wing body 10. The wing root module 11 includes an aileron front fixing hole 110, a front fixing plate 111, a rear fixing plate 112 and a motor connecting plate 113. In order to achieve fixed connection, the end surface of the aileron front fixing hole 110 is designed with 8 internal thread holes 114, and the end surfaces of the front fixing plate 111, the rear fixing plate 112 and the motor fixing plate 113 are each provided with 4 light holes 115. In order to facilitate the installation of the aileron 2, the wing tip module 12 is provided with an aileron end fixing platform 121, and the end surface of the aileron end fixing platform 121 is provided with 6 aileron end fixing platform holes 122, and the aileron end fixing platform holes 122 are internal thread holes. Through the aileron front fixing hole 110 and the aileron end fixing platform 121, the installation and connection of the aileron 2 can be achieved.

[0028] In this embodiment, the internal threaded holes 114 are distributed in a circumferential shape on the end surface of the aileron front fixing hole 110. The light holes 115 in the front fixing plate 111, the rear fixing plate 112 and the motor fixing plate 113 are all distributed symmetrically. The aileron end fixing platform holes 122 are distributed in an arc shape on the aileron end fixing platform 121.

[0029] like Figure 4 As shown, the aileron 2 includes an aileron body 20, and an aileron rear end fixing sleeve 21 and an aileron front end fixing sleeve 22 are provided on the aileron body 20. The aileron rear end fixing sleeve 21 is connected to the aileron end fixing platform 121 on the wing 1 through connecting screws. The aileron front end fixing sleeve 22 is connected to the aileron front fixing hole 110 on the wing 1, and the aileron 2 is reliably fixed by screw connection.

[0030] The front and rear ends of the aileron body 20 are respectively designed with an aileron rear transmission shaft 201 and an aileron front transmission shaft 202, which are respectively connected to the aileron rear end fixing sleeve 21 and the aileron front end fixing sleeve 22. The aileron front transmission shaft 202 is provided with a connecting key 203, which is used to connect the aileron 2 with the aileron front end fixing sleeve 22.

[0031] The cross section of the aileron rear end fixing sleeve 21 is a fan-shaped structure, and a through hole is provided in the middle of the aileron rear end fixing sleeve 21 for passing the aileron rear transmission shaft 201. An aileron rear end fixing sleeve connection hole is provided on the edge of the aileron rear end fixing sleeve 21, and a screw passes through the aileron rear end fixing sleeve connection hole and matches with the aileron end fixing platform hole 122. The aileron rear end fixing sleeve 21 plays a guiding role in the rotation of the aileron body 20.

[0032] The aileron front end fixing sleeve 22 comprises an aileron front fixing sleeve 220, a connecting screw 221, a front end bearing retaining ring 222, a front end fixing nut 223 of a transmission shaft, a driven bevel gear 224 and a driven bevel gear fixing nut 225. The aileron front end fixing sleeve 220, the front end bearing retaining ring 222, the front end fixing nut 223 of a transmission shaft and the driven bevel gear 224 are sequentially sleeved on the aileron front transmission shaft 202, and the driven bevel gear 224 is connected to the aileron front transmission shaft 202 via a connecting key 203. The connecting screw 221 passes through the aileron front end fixing sleeve 22 and matches with the internal threaded hole 114.

[0033] A sliding bearing is placed inside each of the front and rear ends of the aileron front fixing sleeve 22 , namely a front end bearing 226 and a rear end bearing 227 , to ensure the free rotation of the aileron 2 .

[0034] The aileron front fixing sleeve 220 is located in the aileron front fixing hole 110. The cross section of the aileron front fixing sleeve 220 is a "convex" shaped structure. The connecting screw 221 is inserted into the end face of the aileron front fixing sleeve 220. The front end bearing retaining ring 222 is connected to the end face of the aileron front fixing sleeve 220 by bolts. The aileron front transmission shaft 202 is provided with an external thread structure, and the front end fixing nut 223 of the transmission shaft is sleeved on the external thread structure and meshed. The end of the aileron front transmission shaft 202 is a threaded structure. After the driven bevel gear 224 is installed first, the driven bevel gear fixing nut 225 is sleeved.

[0035] The active transmission mechanism 4 includes a motor 41, a motor connecting plate 42, a connecting flange 43, a rear connecting plate 44, a front connecting plate 45 and an active bevel gear 46. The motor 41 is connected to the motor connecting plate 42, and the rotating shaft end of the motor 41 is connected to the active bevel gear 46 through the connecting flange 43. The rear connecting plate 44 and the front connecting plate 45 are respectively sleeved on the active bevel gear 46. The front connecting plate 45, the rear connecting plate 44 and the motor connecting plate 42 are respectively matched with the front fixing plate 111, the rear fixing plate 112 and the motor connecting plate 113 of the wing 1, and are fixed by bolts or screws, and the active bevel gear 46 is meshed with the driven bevel gear 224.

[0036] The driving bevel gear 46 includes a bevel gear top and a driving bevel gear connecting rod, which are fixedly connected to form an integral structure. The bevel gear top is a circular bevel gear structure that meshes with the driven bevel gear 224. The driving bevel gear connecting rod passes through the front connecting plate 45 and the rear connecting plate 44 in sequence and is connected to the connecting flange 43. The rear connecting plate 44 and the front connecting plate 45 are both circular ring structures.

[0037] The rear connecting plate 44 and the front connecting plate 45 are both provided with bearing devices, and the bearing devices include bearings 47 and bearing retaining rings 48. The two bearing retaining rings 48 are bolted to the rear connecting plate 44 and the front connecting plate 45 respectively, and the inner ring of the bearing 47 forms an interference fit with the active bevel gear 46 to realize transmission.

[0038] In this embodiment, the two sides of the wing body 10 are wing surfaces, and the two sides of the aileron body 20 are aileron surfaces. During operation, the motor 41 drives the active bevel gear 46 to rotate through the connecting flange 43, thereby moving the driven bevel gear 224 and finally moving the aileron body 20.

[0039] Those skilled in the art will appreciate that the embodiments described herein are intended to help readers understand the principles of the present invention, and should be understood that the protection scope of the present invention is not limited to such specific statements and embodiments. Those skilled in the art can make various other specific variations and combinations that do not deviate from the essence of the present invention based on the technical revelations disclosed by the present invention, and these variations and combinations are still within the protection scope of the present invention.

Claims

1. A transmission mechanism for an aircraft aileron, characterized in that: The invention comprises a wing (1), an aileron (2), a bevel gear transmission mechanism (3) and an active transmission mechanism (4); the active transmission mechanism (4) is a main motion control and power output component and is fixed at the root of the wing (1); the active transmission mechanism (4) drives the aileron (2) to rotate on a fixed axis through the bevel gear transmission mechanism (3) to achieve aircraft attitude adjustment.

2. The transmission mechanism of an aircraft aileron according to claim 1, characterized in that: The wing (1) comprises a wing body (10), a wing root module (11) and a wing tip module (12) which are fixed together, wherein the wing root module (11) and the wing tip module (12) are respectively located at two ends of the wing body (10); the wing root module (11) comprises an aileron front fixing hole (110), a front fixing plate (111), a rear fixing plate (112) and a motor connecting plate (113); in order to achieve fixed connection, the end surface of the aileron front fixing hole (110) is designed with 8 internal thread holes (114); the front fixing plate (111), the rear fixing plate (112) and the motor connecting plate (113) are connected to the aileron front fixing hole (110) and the motor connecting plate (113). The end surfaces of the fixing plate (112) and the motor fixing plate (113) are both provided with four light holes (115); in order to facilitate the installation of the aileron (2), the wingtip module (12) is provided with an aileron end fixing platform (121); the end surface of the aileron end fixing platform (121) is provided with six aileron end fixing platform holes (122); the aileron end fixing platform holes (122) are internal threaded holes; the aileron (2) can be installed and connected through the aileron front fixing hole (110) and the aileron end fixing platform (121).

3. The transmission mechanism of an aircraft aileron according to claim 1, characterized in that: The aileron (2) comprises an aileron body (20), and an aileron rear end fixing sleeve (21) and an aileron front end fixing sleeve (22) are provided on the aileron body (20); the aileron rear end fixing sleeve (21) is connected to an aileron end fixing platform (121) on the wing (1) via connecting screws; the aileron front end fixing sleeve (22) is connected to an aileron front fixing hole (110) on the wing (1), and the aileron (2) is reliably fixed via the screw connection.

4. The transmission mechanism of an aircraft aileron according to claim 3, characterized in that: The front and rear ends of the aileron body (20) are respectively designed with an aileron rear transmission shaft (201) and an aileron front transmission shaft (202), which are respectively connected to the aileron rear end fixing sleeve (21) and the aileron front end fixing sleeve (22); the aileron front transmission shaft (202) is provided with a connecting key (203), and the connecting key (203) is used to connect the aileron (2) with the aileron front end fixing sleeve (22).

5. The transmission mechanism of an aircraft aileron according to claim 1, characterized in that: The aileron front end fixing sleeve (22) comprises an aileron front end fixing sleeve (220), a connecting screw (221), a front end bearing retaining ring (222), a transmission shaft front end fixing nut (223), a driven bevel gear (224) and a driven bevel gear fixing nut (225); the aileron front end fixing sleeve (220), the front end bearing retaining ring (222), the transmission shaft front end fixing nut (223) and the driven bevel gear (224) are sequentially sleeved on the aileron front transmission shaft (202); the driven bevel gear (224) and the aileron front transmission shaft (202) are connected via a connecting key (203); and the connecting screw (221) passes through the aileron front end fixing sleeve (22) and then matches with the internal threaded hole (114).

6. The transmission mechanism of an aircraft aileron according to claim 1, characterized in that: A sliding bearing is placed inside each of the front and rear ends of the aileron front fixing sleeve (22), namely a front end bearing (226) and a rear end bearing (227), for ensuring the free rotation of the aileron (2).

7. The transmission mechanism of an aircraft aileron according to claim 1, characterized in that: The active transmission mechanism (4) comprises a motor (41), a motor connecting plate (42), a connecting flange (43), a rear connecting plate (44), a front connecting plate (45) and an active bevel gear (46); the motor (41) is connected to the motor connecting plate (42); the rotating shaft end of the motor (41) is connected to the active bevel gear (46) through the connecting flange (43); the rear connecting plate (44) and the front connecting plate (45) are respectively sleeved on the active bevel gear (46); the front connecting plate (45), the rear connecting plate (44) and the motor connecting plate (42) are respectively matched with the front fixing plate (111), the rear fixing plate (112) and the motor connecting plate (113) of the wing (1) and fixed by bolts or screws; the active bevel gear (46) is meshed with the driven bevel gear (224).

8. The transmission mechanism of an aircraft aileron according to claim 1, characterized in that: The rear connecting plate (44) and the front connecting plate (45) are both provided with bearing devices, the bearing devices comprising bearings (47) and bearing retaining rings (48), the two bearing retaining rings (48) are respectively bolted to the rear connecting plate (44) and the front connecting plate (45), and the inner ring of the bearing (47) forms an interference fit with the active bevel gear (46) to achieve transmission.

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