Fixed hinge type flap actuator mounting structure

Abstract

The invention relates to the technical field of aircraft design, in particular to a fixed hinge type flap actuator mounting structure which comprises a swing device, one end of the swing device is connected with a wing back rest, the other end of the swing device is connected with a flap control surface, and the swing device is used for retracting and releasing the flap control surface; the method has the effect of solving the problem that the flexibility and lightweight design of the system are limited.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft design, and in particular to a fixed hinged flap actuator installation structure. Background Art

[0002] With the development of the aviation industry and technological progress, the field of aircraft design has increasingly focused on improving the overall performance of aircraft, especially in the development of high-lift control systems. In order to cope with the growing market demand, various new types of high-lift devices have been widely used in various types of aircraft. Especially for general aviation, efficient high-lift systems have become one of the key factors in measuring aircraft take-off and landing performance, which not only helps to improve the safety of aircraft, but also can significantly reduce operating costs.

[0003] Most existing flap control systems use a rigid torque tube transmission mechanism to achieve torque transmission. Due to the characteristics of transmitting low-speed and high torque, this mechanism results in large parts and heavy weight, requiring a large installation space and support structure. In addition, the slide rails are usually designed with linear slide rails, which require complex rod systems to control the flap's attitude during the flap's backward movement. The installation and disassembly process is cumbersome, and the width of a single flap rudder is large, the overall processing cost is high, and the difficulty of system maintenance also increases accordingly.

[0004] With regard to the above-mentioned related technologies, the above-mentioned rigid torque tube transmission and slide rail motion mechanism have solved the basic needs of aircraft flap control to a certain extent, but in actual application, there are problems such as bulky structure, high cost and inconvenient maintenance, especially in disassembly and assembly and daily maintenance, which takes a long time. The large installation space and structural support required also limit the flexibility and lightweight design of the system, thereby increasing the cost. Summary of the invention

[0005] In order to solve the problem of limiting the flexibility and lightweight design of the system, the present application provides a fixed hinged flap actuator mounting structure.

[0006] The present application provides a fixed hinge flap actuator installation structure adopts the following technical solution: A fixed hinged flap actuator installation structure comprises a swing device, one end of which is connected to a wing rear beam, and the other end is connected to a flap rudder surface, and the swing device is used to retract and extend the flap rudder surface.

[0007] By adopting the above technical solution, the fixed hinged flap actuator installation structure can realize efficient retraction and extension of the flap, and transmit power to the flap control surface through the swing device, making the flap more stable and reliable during the retraction and extension process.

[0008] In a specific possible implementation scheme, the swing device includes a mounting assembly, a connecting assembly and a driving assembly, the mounting assembly includes a mounting part, the mounting part includes two flap arms, one end of the two flap arms are fixed to the wing rear beam, the two flap arms are spaced apart along the length direction of the wing rear beam, the flap arm is an L-shaped structure, the connecting assembly includes a rocker arm, the end of the flap arm away from the wing rear beam is connected to a suspension seat, the rocker arm is inclined upward from the flap arm toward the side away from the flap arm, the lower end of the rocker arm is hinged to the suspension seat and can rotate around the hinge axis, and the higher end of the rocker arm is fixed to the bottom of the flap rudder surface; The driving assembly comprises a flap actuator, one end of which is fixed to the flap support arm and the other end is connected to the rocker arm. The flap actuator is used to drive the rocker arm to rotate.

[0009] By adopting the above technical solution, the fixed hinged flap actuator installation structure can realize the effective retraction and extension operation of the flap in a smaller space, thereby improving the compactness and ease of operation of the system. Specifically, the solution effectively realizes the coordinated work between the components by dividing the swing device into three parts: the installation component, the connection component and the drive component. Among them, the L-shaped flap support arm not only reduces the required installation space, but also enhances the structural stability; the articulation method of the suspension seat and the rocker arm ensures that the rocker arm can smoothly rotate around the articulation axis, thereby improving the response speed and smoothness of the entire system; and the linkage mechanism between the flap actuator and the rocker arm enables the driving force to be efficiently and accurately transmitted to the flap control surface under the action of the drive component, thereby simplifying the complexity of the entire control system, while also ensuring high reliability and maintenance convenience.

[0010] In a specific possible implementation scheme, the connecting assembly also includes a fork ear and a double-ear joint, the fork ear structure is an open double-hole form, the fork ear is precisely docked with the flap actuator, the double-ear joint is fixed to the fork ear, and the double-ear joint is connected to the flap rudder surface.

[0011] By adopting the above technical solution, the double-ear joint is fixed to the fork ear, and the double-ear joint is connected to the flap rudder surface, so that the precise docking between the fork ear and the flap actuator is achieved, the stability and reliability of the connection are enhanced, and the open double-hole fork ear design improves the flexibility of the overall structure, simplifies the assembly process, and further improves the convenience of maintenance.

[0012] In a specific embodiment, the surface of the fork ear is anodized or coated to prevent corrosion.

[0013] By adopting the above technical solution, the surface of the fork ear is anodized or coated, which enhances the corrosion resistance and increases the service life.

[0014] In a specific feasible implementation scheme, the mounting member also includes a plurality of mounting seats, one flap support arm corresponds to two mounting seats, both mounting seats are fixed to one end of the flap support arm, one mounting seat is located on the side wall of the wing rear beam, and the other mounting seat is located on the bottom wall of the wing rear beam, and the wing rear beam is provided with a plurality of joints corresponding to the mounting seats.

[0015] By adopting the above technical solution, the flap support arm can be fixed in multiple directions, and the stability and reliability of the overall structure can be enhanced. The multiple joints on the wing rear beam correspond to the mounting seat, which further ensures the tight connection between the mounting part and the wing rear beam, and improves the bearing capacity of the system.

[0016] In a specific possible implementation scheme, the mounting assembly also includes a plurality of fasteners, each of which corresponds to the mounting seat one by one. The fasteners are bolts, which are sequentially passed through the mounting seat and the joint, and the fasteners are used to fix the mounting seat and the joint.

[0017] By adopting the above technical solution, multiple fasteners correspond to the mounting seats one by one. The fasteners are bolts, which are sequentially passed through the mounting seat and the joint, thereby achieving a stable fixed connection between the mounting seat and the joint, and enhancing the stability and reliability of the overall structure.

[0018] In a specific possible implementation scheme, the drive assembly also includes a spoiler, which is located above the flap control surface, the spoiler is in contact with the top of the flap control surface, the spoiler is rotatably connected to the flap control surface, the spoiler moves toward or away from the side of the flap control surface, and the flap actuator is connected to the spoiler to drive the spoiler to move.

[0019] By adopting the above technical solution, the spoiler is located above the flap control surface and contacts with the top of the flap control surface. The spoiler and the flap control surface are connected in a rotating manner, which can optimize the airflow when the spoiler is deployed, improve the aircraft's maneuverability and lift-enhancing effect, and the spoiler is consistent with the upper surface of the wing structure when it is in the retracted state to form a smooth surface, reduce flight resistance, and the addition of the spoiler makes the flap movement mechanism simpler, reduces weight and has good reliability.

[0020] In a specific possible implementation manner, it further comprises a protection device, wherein the protection device comprises a fairing, wherein the fairing is connected to the rear arm of the wing, and the fairing is used to cover the swing device and related mechanical connections.

[0021] By adopting the above technical solution, the fairing is connected to the rear beam of the wing, covering the swing device and related mechanical connections, ensuring that these components are protected during flight while maintaining the aerodynamic smoothness of the aircraft. The fairing is made of lightweight materials, which reduces weight and improves the efficiency of the aircraft, further optimizing the overall performance of the aircraft.

[0022] In a specific possible implementation scheme, the swing device also includes a hinge assembly, which includes a hinge, a support and an adjustment member, and the hinge includes a first connecting rod, a first hinge seat, a second connecting rod and a third connecting rod, one end of the first connecting rod is hinged to the wing rear beam, and the other end is hinged to the first hinge seat, the first hinge seat is fixed to the wing rear beam, one end of the second connecting rod is hinged to the hinge of the first hinge seat and the first connecting rod, one end of the third connecting rod is hinged to the wing rear beam, and the other end is hinged to the end of the second connecting rod away from the first hinge seat; The support member is respectively connected to the wing rear beam, the flap rudder surface and the connection between the third connecting rod and the second connecting rod. One end of the adjusting member is connected to the wing rear beam, and the other end is connected to the bottom of the flap rudder surface.

[0023] By adopting the above technical solution, the introduction of the hinge assembly makes the retraction and extension of the flap more stable and reliable. The first connecting rod, the first hinge seat, the second connecting rod and the third connecting rod of the hinge work together to achieve effective control of the flap, which can reduce the size of the flap fairing, thereby greatly reducing the windward area of ​​the fairing, thereby reducing the resistance of the cruise aircraft and increasing the lift of the aircraft. The support parts enhance the overall rigidity of the structure to ensure smooth operation under various flight conditions. At the same time, the adjustment parts further improve the response speed and accuracy of the system, simplify the complexity of the flap movement mechanism, reduce the weight, and improve reliability.

[0024] In a specific possible implementation scheme, the support member includes a flap arm beam, a main driving rocker arm, a pivot connecting rod and a second articulated seat, the flap arm beam is fixed to the bottom of the flap, one end of the main driving rocker arm is articulated with the first articulated seat, and the other end is articulated with the second articulated seat, the second articulated seat is articulated with the wing rear beam, the flap arm beam is articulated with the second articulated seat, the pivot connecting rod is located at the bottom of the flap arm beam, one end of the pivot connecting rod is articulated with the connection between the second connecting rod and the third connecting rod, and the other end is articulated with the bottom of the flap arm beam; The adjusting member comprises a rear flap drive, one end of the rear flap drive is hinged to the second hinge seat, and the other end is hinged to the flap support arm beam.

[0025] By adopting the above technical solution, the supporting parts include flap support arm beam, main drive rocker arm and pivot link, so that the flap can move stably and smoothly during the retraction and extension process, thereby improving the reliability and service life of the system; the adjusting part realizes precise control of the flap through the rear flap drive, further optimizes the stability of the flap movement, and improves the control performance of the aircraft.

[0026] In summary, the present application includes at least one of the following beneficial technical effects: 1. The designed fixed hinged flap actuator installation structure enables the fixed hinged flap actuator installation structure to realize the effective retraction and extension operation of the flap in a smaller space, improving the compactness and ease of operation of the system. Specifically, the scheme effectively realizes the coordinated work between the components by dividing the swing device into three parts: the installation component, the connection component and the drive component; and the linkage mechanism between the flap actuator and the rocker arm enables the driving force to be efficiently and accurately transmitted to the flap control surface under the action of the drive component, thereby simplifying the complexity of the entire control system, while also ensuring high reliability and maintenance convenience.

[0027] 2. The fixed hinged flap actuator installation structure is designed, and the spoiler and the flap control surface are connected in a rotating manner, which can optimize the airflow when the spoiler is deployed, improve the aircraft's maneuverability and lift effect, and the spoiler is consistent with the upper surface of the wing structure when it is folded, forming a smooth surface and reducing flight resistance. The addition of the spoiler makes the flap movement mechanism simpler, lighter and has good reliability.

[0028] 3. The fixed hinged flap actuator installation structure is designed. The introduction of the hinged assembly makes the retraction and extension of the flap more stable and reliable. The first connecting rod, the first hinge seat, the second connecting rod and the third connecting rod of the hinge work together to achieve effective control of the flap, which can reduce the size of the flap fairing, thus greatly reducing the windward area of ​​the fairing, thereby reducing the resistance of the cruise aircraft and increasing the lift of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic diagram of the overall structure in Example 1.

[0030] Figure 2 It is a structural schematic diagram of the swing device in Example 1.

[0031] Figure 3 It is a schematic diagram of the overall structure in Example 2.

[0032] Figure 4 It is a schematic diagram of the overall structure in Example 3.

[0033] Figure 5 It is a schematic diagram of the structure of the hinge assembly in Example 3.

[0034] Description of reference numerals: 1, swing device; 11, mounting assembly; 111, mounting member; 1111, flap arm; 1112, mounting seat; 1113, suspension seat; 112, fastener; 12, connecting assembly; 121, rocker arm; 122, fork ear; 123, double ear joint; 13, driving assembly; 131, flap actuator; 132, driving member; 133, spoiler; 14, hinge assembly; 141, hinge member; 14 11. First connecting rod; 1412. First articulated seat; 1413. Second connecting rod; 1414. Third connecting rod; 142. Support member; 1421. Flap support arm beam; 1422. Main drive rocker arm; 1423. Pivot connecting rod; 1424. Second articulated seat; 143. Adjusting member; 1431. Rear flap drive; 2. Protective device; 21. Fairing; 3. Wing rear beam; 31. Joint; 4. Flap control surface; 41. Connecting seat. DETAILED DESCRIPTION

[0035] The following is combined with Figure 1-5 This application is described in further detail.

[0036] An embodiment of the present application discloses a fixed hinged flap actuator installation structure.

[0037] Example 1 Reference Figure 1 and Figure 2 A fixed hinged flap actuator installation structure includes a swing device 1 and a protective device 2. The swing device 1 includes a mounting component 11, a connecting component 12 and a driving component 13. The connecting component 12 is arranged on the mounting component 11, and the driving component 13 is arranged on the connecting component 12.

[0038] Reference Figure 1 and Figure 2The mounting assembly 11 includes a mounting member 111 and a plurality of fasteners 112. The mounting member 111 includes two flap arms 1111, a plurality of mounting seats 1112 and two suspension seats 1113. The two flap arms 1111 are both close to the wing rear beam 3. The two flap arms 1111 are spaced apart along the length direction of the wing rear beam 3. The material selection of the flap arms 1111 tends to be high-strength alloy materials, such as aluminum alloy or special stainless steel, to take into account both weight and durability. In this embodiment, the flap arms 1111 are L-shaped. The L-shaped structural design helps to disperse stress concentration and improve the stability of the entire system. One flap arm 1111 corresponds to two mounting seats 1112. The two mounting seats 1112 are both located at one end of the flap arm 1111. The two mounting seats 1112 are fixedly connected to the flap arm 1111 by screws, wherein one mounting seat 1112 is located at the wing rear beam. 3 side wall, another mounting seat 1112 is located on the bottom wall of the wing rear beam 3, and a plurality of joints 31 corresponding to the mounting seats 1112 are provided on the wing rear beam 3. The joints 31, as key connecting components, bear the important mission of transmitting loads. The joints 31 can be made of high-quality steel or composite materials, and suitable size specifications can be customized according to actual needs. The joints 31 are tightly combined with the wing rear beam 3 mainly through welding or riveting, etc., to ensure sufficient strength and sealing. In order to adapt to the changing conditions of various flight environments, the joints 31 are built with multiple buffer washers and anti-loosening devices to prevent loosening caused by long-term vibration. The fasteners 112 correspond to the mounting seats 1112 one by one. In this embodiment, the fasteners 112 are bolts, which are sequentially penetrated through the mounting seats 1112 and the joints 31, and the bolts are threadedly connected to the mounting seats 1112 and the joints 31 in turn, and the mounting seats 1112 and the joints 31 are fixedly connected by bolts.

[0039] Reference Figure 2, a flap support arm 1111 corresponds to a suspension seat 1113, and the suspension seat 1113 is fixedly connected to the end of the flap support arm 1111 away from the mounting seat 1112 by screws, so as to establish a firm and reliable contact relationship with the connecting component 12. The connection adopts a ball joint or the like, allowing free rotation within a certain range to adjust the posture, so as to better match the dynamic requirements under different working conditions; the connecting component 12 includes a rocker arm 121, a fork ear 122 and a double-ear joint 123. The rocker arm 121 is the core part of the connecting component 12 and plays a role in transmitting power. The rocker arm 121 is tilted. The rocker arm 121 is tilted upward from the flap support arm 1111 to the side away from the flap support arm 1111. The lower end of 121 is hinged to the suspension seat 1113 and can rotate around the hinge axis. A plurality of connecting seats 41 are provided at the bottom of the flap rudder surface 4. The connecting seat 41 is fixedly connected to the flap rudder surface 4 by welding. The higher end of the rocker arm 121 is fixedly connected to one of the connecting seats 41 by screws. The rocker arm 121 can be made of pipe or solid bar material, and is provided with reinforcing ribs inside to improve the strength. For the purpose of weight reduction, certain areas can be locally punched or hollowed out without affecting the strength. Wear-resistant bushings or copper sleeves are used at the connection between the rocker arm 121 and the suspension seat 1113 to reduce the probability of wear, so as to achieve the advantages of simple deployment mechanism, light weight, good reliability and maintainability, etc.

[0040] Reference Figure 2 The fork ear 122 is made of high-strength alloy material, such as aluminum alloy or titanium alloy. The fork ear 122 is designed as an open double-hole structure, and is precisely connected to the flap actuator 131 through a keyway or a positioning pin. The fork ear 122 is fixedly connected to the double-ear joint 123 by welding. The surface of the fork ear 122 is anodized or coated to prevent corrosion, thereby increasing the service life. The double-ear joint 123 is used to be fixedly connected to the connecting seat 41. As one of the main supporting components of the entire drive assembly 13, the double-ear joint 123 is located on the side of the rocker arm 121 close to the flap support arm 1111. The double-ear joint 123 can be made of high-strength alloy material. For example, common aluminum alloy grades are 7075-T6 or more advanced Ti-6Al-4V titanium alloy to improve its rigidity and fatigue resistance. The design of the double-ear joint 123 adopts a reinforcing rib structure to enhance its shear resistance, and is formed by precision casting or forging and then CNC processed to ensure geometric accuracy. The double-ear joint 123 can be quickly disassembled and assembled with the connecting seat 41 through bolts or pins, which is convenient for maintenance; the connecting assembly 12 consists of a rocker arm 121, a double-ear joint 123 and a fork ear 122. Compared with the integral machined hollow parts, it has a simple structure, reduces manufacturing costs, and effectively improves the maintainability and interchangeability of the flap rocker arm 121 assembly.

[0041] Reference Figure 2The driving assembly 13 includes a flap actuator 131 and a driving member 132. The flap actuator 131 is located on a side of the flap support arm 1111 close to the rocker arm 121. One end of the flap actuator 131 is fixedly connected to the flap support arm 1111 by a screw. The driving member 132 is a connecting rod. The other end of the flap actuator 131 is hinged to one end of the connecting rod. The end of the connecting rod away from the flap actuator 131 is hinged to the double-ear joint 123. By driving the flap actuator 131 to move, the power output by the flap actuator 131 is transmitted to the flap control surface 4 through the double-ear joint 123 and the rocker arm 121, thereby completing the retraction and extension action of the flap, wherein the power drives the rocker arm 121 through the flap actuator 131 to make the flap control surface 4 perform a circular motion around the fixed hinge point.

[0042] Reference Figure 3 The protective device 2 includes a fairing 21, which is detachably connected to the wing rear beam 3 by tension bolts, and can be used to cover the actuator and related mechanical connections to ensure that these components are protected during flight while maintaining the aerodynamic smoothness of the aircraft. The fairing 21 is usually made of lightweight materials, such as composite materials or aluminum alloys, to reduce weight and improve the efficiency of the aircraft.

[0043] The implementation principle of Example 1 is as follows: when the flaps need to be retracted, the personnel drives the flap actuator 131, and the flap actuator 131 transmits the output power to the rocker arm 121, so that the rocker arm 121 can make a circular motion around the flap support arm 1111. At this time, the rocker arm 121 moves around the flap support arm 1111 toward the side close to the flap support arm 1111, and then transmits the power to the flap control surface 4 through the double-ear joint 123 and the rocker arm 121, thereby completing the retraction of the flaps.

[0044] When the flap needs to be deployed, the personnel drives the flap actuator 131, and the flap actuator 131 transmits the output power to the rocker arm 121, which can make the rocker arm 121 move in an arc around the flap support arm 1111. At this time, the rocker arm 121 moves around the flap support arm 1111 toward the side away from the flap support arm 1111, and then transmits the power to the flap control surface 4 through the double-ear joint 123 and the rocker arm 121, completing the deployment of the flap.

[0045] Example 2 Reference Figure 3The difference between this embodiment and embodiment 1 is that the drive assembly 13 also includes a spoiler 133, which is located above the flap control surface 4, and the spoiler 133 is in contact with the top of the flap control surface 4, the spoiler 133 is rotatably connected to the flap control surface 4, and the spoiler 133 moves toward or away from the flap control surface 4. The spoiler 133 is fixedly connected to the flap actuator 131, which is used to drive the spoiler 133 to rotate. When the spoiler 133 is deployed, the free movement of the articulated top flap can optimize the airflow, improve the aircraft's maneuverability and lift-enhancing effect, and in the retracted configuration, the upper surface of the articulated top flap is consistent with the upper surface of the wing structure to form a smooth surface, thereby reducing flight resistance.

[0046] The implementation principle of Example 2 is as follows: when the spoiler 133 is in the retracted configuration, the hinged top flap is consistent with the upper surface of the wing structure to form a smooth surface; when the spoiler 133 is deployed, the hinged top flap can move freely to optimize the airflow, improve the lift and maneuverability of the aircraft, and significantly increase the lift coefficient when the flap moves. Therefore, this structure will reduce the complexity of the flap movement mechanism, reduce weight and improve reliability.

[0047] Example 3 Reference Figure 4 and Figure 5The present embodiment is different from the embodiment 1 in that the swing device 1 further comprises an articulated assembly 14, the articulated assembly 14 comprises an articulated member 141, a supporting member 142 and an adjusting member 143, the articulated member 141 comprises a first connecting rod 1411, a first articulated seat 1412, a second connecting rod 1413 and a third connecting rod 1414, one end of the first connecting rod 1411 is articulated to the wing rear beam 3, and the other end is articulated to the first articulated seat 1412, the first articulated seat 141 2 is fixedly connected to the wing rear beam 3 by screws, one end of the second link 1413 is hinged to the hinge of the first hinge seat 1412 and the first link 1411, one end of the third link 1414 is hinged to the wing rear beam 3, and the other end is hinged to the end of the second link 1413 away from the first hinge seat 1412; the support member 142 includes a flap support arm 1111 beam, a main drive rocker arm 1422, a pivot link 1423 and a second hinge seat 1424, the flap support arm 11 The 11 beam is located at the bottom of the flap, and the flap arm 1111 beam is fixedly connected to the flap through tension bolts. One end of the main driving rocker arm 1422 is hinged to the first hinge seat 1412, and the other end is hinged to the second hinge seat 1424. The second hinge seat 1424 is hinged to the wing rear beam 3. The flap arm 1111 beam is hinged to the second hinge seat 1424. The pivot link 1423 is located at the bottom of the flap arm 1111 beam. One end of the pivot link 1423 is hinged to the second link 1 413 is hinged at the connection with the third connecting rod 1414, and the other end is hinged to the bottom of the flap support arm 1111 beam; the adjusting member 143 includes a rear flap drive 1431, one end of the rear flap drive 1431 is hinged to the second hinge seat 1424, and the other end is hinged to the flap support arm 1111 beam. By moving the rear flap drive 1431, the power output by the rear flap drive 1431 is transmitted to the flap through the flap support arm 1111 beam, thereby completing the retraction and extension action of the flap.

[0048] Reference Figure 4 and Figure 5 The fairing 21 is detachably connected to the wing rear beam 3 through tension bolts, and the hinge assembly 14 is located inside the fairing 21, which can reduce air resistance during flight and protect internal components from being affected by the external environment.

[0049] The implementation principle of Example 3 is: when the flap needs to be retracted, the personnel moves the rear flap drive 1431, and the rear flap drive 1431 transmits the output power to the flap support arm 1111 beam, which can make the second link 1413 and the third link 1414 rotate toward the side away from the wing rear beam 3 until the flap retraction action is completed.

[0050] When the flap needs to be deployed, the personnel moves the rear flap drive 1431, and the rear flap drive 1431 transmits the output power to the flap support arm 1111 beam, which can rotate the second link 1413 and the third link 1414 toward the side close to the wing rear beam 3 until the flap deployment action is completed.

[0051] It has better Fuller motion and secondly can reduce the size of the flap fairing 21, which greatly reduces the windward area of ​​the fairing 21, thereby reducing the resistance of the cruise aircraft and increasing the lift of the aircraft.

[0052] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. A fixed hinge flap actuator installation structure, characterized in that: The invention comprises a swing device (1), one end of which is connected to a wing rear beam (3), and the other end of which is connected to a flap control surface (4). The swing device (1) is used to retract and extend the flap control surface (4).

2. A fixed hinge flap actuator installation structure according to claim 1, characterized in that: The swing device (1) comprises a mounting assembly (11), a connecting assembly (12) and a driving assembly (13); the mounting assembly (11) comprises a mounting part (111); the mounting part (111) comprises two flap arms (1111); one end of the two flap arms (1111) is fixed to a wing rear beam (3); the two flap arms (1111) are spaced apart along the length direction of the wing rear beam (3); the flap arms (1111) are of an L-shaped structure; The connecting assembly (12) comprises a rocker arm (121), one end of the flap support arm (1111) away from the wing rear beam (3) is connected to a suspension seat (1113), the rocker arm (121) is arranged to be inclined upward from the flap support arm (1111) toward a side away from the flap support arm (1111), the lower end of the rocker arm (121) is hinged to the suspension seat (1113) and can rotate around the hinge axis, and the higher end of the rocker arm (121) is fixed to the bottom of the flap control surface (4); The driving assembly (13) comprises a flap actuator (131), one end of the flap actuator (131) is fixed to the flap support arm (1111), and the other end is connected to the rocker arm (121), and the flap actuator (131) is used to drive the rocker arm (121) to rotate.

3. A fixed hinge flap actuator installation structure according to claim 2, characterized in that: The connecting assembly (12) further comprises a fork ear (122) and a double-ear joint (123); the fork ear (122) is an open double-hole structure; the fork ear (122) is precisely docked with the flap actuator (131); the double-ear joint (123) is fixed to the fork ear (122); and the double-ear joint (123) is connected to the flap control surface (4).

4. A fixed hinge flap actuator installation structure according to claim 3, characterized in that: The surface of the fork ear (122) is anodized or coated to prevent corrosion.

5. The fixed hinge flap actuator installation structure according to claim 2, characterized in that: The mounting member (111) further comprises a plurality of mounting seats (1112), one flap support arm (1111) corresponds to two mounting seats (1112), both mounting seats (1112) are fixed to one end of the flap support arm (1111), one mounting seat (1112) is located on a side wall of the wing rear beam (3), and the other mounting seat (1112) is located on a bottom wall of the wing rear beam (3), and a plurality of joints (31) corresponding to the mounting seats (1112) are provided on the wing rear beam (3).

6. A fixed hinge flap actuator installation structure according to claim 5, characterized in that: The mounting assembly (11) further comprises a plurality of fasteners (112), wherein the fasteners (112) correspond one-to-one to the mounting seat (1112), the fasteners (112) are bolts, and the bolts are sequentially passed through the mounting seat (1112) and the joint (31), and the fasteners (112) are used to fix the mounting seat (1112) and the joint (31).

7. A fixed hinge flap actuator installation structure according to claim 2, characterized in that: The driving assembly (13) further comprises a spoiler (133), wherein the spoiler (133) is located above the flap control surface (4), the spoiler (133) contacts the top of the flap control surface (4), the spoiler (133) is rotatably connected to the flap control surface (4), the spoiler (133) moves toward or away from a side of the flap control surface (4), and the flap actuator (131) is connected to the spoiler (133) to drive the spoiler (133) to move.

8. The fixed hinge flap actuator installation structure according to claim 1, characterized in that: It also comprises a protection device (2), wherein the protection device (2) comprises a fairing (21), wherein the fairing (21) is connected to the rear arm of the wing, and the fairing (21) is used to cover the swing device (1) and related mechanical connections.

9. A fixed hinge flap actuator installation structure according to claim 8, characterized in that: The swing device (1) also includes an articulated assembly (14), the articulated assembly (14) includes an articulated member (141), a supporting member (142) and an adjusting member (143), the articulated member (141) includes a first connecting rod (1411), a first articulated seat (1412), a second connecting rod (1413) and a third connecting rod (1414), one end of the first connecting rod (1411) is articulated to the wing rear beam (3), and the other end is articulated to the first articulated seat (1412), the first articulated seat (1412) is fixed to the wing rear beam (3), one end of the second connecting rod (1413) is articulated to the articulation point between the first articulated seat (1412) and the first connecting rod (1411), one end of the third connecting rod (1414) is articulated to the wing rear beam (3), and the other end is articulated to the end of the second connecting rod (1413) away from the first articulated seat (1412); The support member (142) is respectively connected to the wing rear beam (3), the flap control surface (4) and the connection between the third connecting rod (1414) and the second connecting rod (1413); one end of the adjusting member (143) is connected to the wing rear beam (3), and the other end is connected to the bottom of the flap control surface (4).

10. A fixed hinge flap actuator (131) installation structure according to claim 9, characterized in that: The support member (142) comprises a flap support arm beam (1421), a main driving rocker arm (1422), a pivot connecting rod (1423) and a second hinge seat (1424); the flap support arm beam (1421) is fixed to the bottom of the flap; one end of the main driving rocker arm (1422) is hinged to the first hinge seat (1412), and the other end is hinged to the second hinge seat (1424); the second hinge seat (1424) is hinged to the wing rear beam (3); the flap support arm beam (1421) is hinged to the second hinge seat (1424); the pivot connecting rod (1423) is located at the bottom of the flap support arm beam (1421); one end of the pivot connecting rod (1423) is hinged to the connection between the second connecting rod (1413) and the third connecting rod (1414), and the other end is hinged to the bottom of the flap support arm beam (1421); The adjusting member (143) comprises a rear flap drive (1431), one end of the rear flap drive (1431) is hinged to the second hinge seat (1424), and the other end is hinged to the flap support arm beam (1421).

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