Composite material rudder sheet structure for flight device

Abstract

The utility model relates to the technical field of aircrafts, in particular to a composite material rudder sheet structure for a flight device, which comprises a main body and a control surface, a driving part is arranged in the main body, a transmission mechanism is arranged at one end of the driving part close to the control surface, and the transmission mechanism is in transmission connection with a transmission shaft; a mounting seat is mounted on one side of the main body close to the control surface; by adopting the clamping design between the limiting block and the inner insertion hole and combining the two groups of mounting rods sleeved on the surface of the transmission shaft, the stable and flexible rotating connection between the control surface and the main body is realized, so that the control surface can accurately and stably change the included angle between the control surface and the main body under the driving of the driving piece and the transmission mechanism, and the control surface can stably change the included angle between the control surface and the main body; and the stability and durability of the whole rudder sheet structure are improved, the firmness of connection and the smoothness of rotation are further enhanced through the circumferential array distribution of the limiting blocks and the inner insertion holes, and therefore the flight device can keep good control performance and flight stability in the complex environment.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to a composite material rudder structure for flight devices. Background Technology

[0002] In aircraft, control blades are key aerodynamic control components, and their performance plays a crucial role in the flight performance of the aircraft. Traditional metal control blades are mostly made of materials such as aluminum alloy and titanium alloy, which have obvious defects. Their high density makes the overall weight of the control blades relatively high, affecting the endurance and payload of the aircraft. Moreover, metal materials are also susceptible to corrosion and require additional protective treatment. The lightweight, high strength, and corrosion resistance of composite materials enable the control blade structure to achieve lightweight while maintaining sufficient strength and rigidity, which is of great significance for improving the performance and efficiency of aircraft.

[0003] A search revealed that Chinese utility model patent CN219428358U discloses a control surface mechanism and an aircraft. The servo motor drives the first joint to move through the control arm. The first joint is connected to the second joint through the control linkage, thereby driving the linkage lugs and control surfaces to rotate accordingly. The left-hand and right-hand threads, as well as the corresponding left-hand and right-hand nuts, set at both ends of the control linkage ensure a tight connection and stable transmission between the components. The use of joint bearings reduces friction and energy loss during movement, improving the stability and efficiency of the mechanism. The entire mechanism is compact, easy to assemble and disassemble, and can achieve precise control of the control surfaces.

[0004] However, in actual use, the control linkage between the rudder arm and the connecting rod lug is prone to loosening due to the large wind resistance during flight, which leads to a decrease in the safety performance of the aircraft during flight. Utility Model Content

[0005] To address the aforementioned shortcomings of existing technologies, this invention provides a composite material rudder structure for flight devices, which effectively solves the problem that the control linkage between the rudder arm and the connecting rod lug is prone to loosening during flight, leading to a decrease in the safety performance of the aircraft.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] This utility model provides a composite material control plate structure for an aircraft device, including a main body and a control surface. A driving component is provided inside the main body, and a transmission mechanism is provided at one end of the driving component near the control surface. The transmission mechanism is connected to a transmission shaft, and a limit block is provided on the surface of the transmission shaft. A mounting seat is installed on the side of the main body near the control surface, and a bushing is rotatably mounted on the mounting seat. An inner insertion hole is provided on the inner side of the bushing, and the limit block is engaged with the inner insertion hole. Both the limit block and the inner insertion hole are arranged in a circumferential array. Two sets of mounting rods are sleeved on the surface of the transmission shaft, and the ends of the two sets of mounting rods away from the transmission shaft are fixedly mounted on the control surface.

[0008] Furthermore, the transmission mechanism includes a first bevel gear fixedly mounted on the driving component, the first bevel gear meshing with a second bevel gear, the second bevel gear being sleeved on the surface of the connecting rod, and identical transmission components being installed at both ends of the connecting rod.

[0009] Furthermore, the transmission assembly includes a track mounted on a connecting rod, with a drive shaft connected to the end of the track away from the drive member, and the drive member passing through the support member and being rotatably connected to it.

[0010] Furthermore, the main body has symmetrical mounting grooves on the side near the rudder surface, and the drive shaft has a drive groove on the surface of the end near the limiting block.

[0011] Furthermore, the mounting base has multiple sets of screw holes on its surface, and the screw holes are threaded with matching bolts.

[0012] Furthermore, a second magnetic block is provided on the surface of the mounting base away from the screw hole, and a first magnetic block is provided at both ends of the drive shaft, with the second magnetic block and the first magnetic block being magnetically connected.

[0013] Furthermore, the drive shaft is provided with reinforcing blocks at both ends near the first magnetic block, and the bushing surface is provided with reinforcing insertion holes. The reinforcing insertion holes are engaged with the reinforcing blocks, and the reinforcing blocks and reinforcing insertion holes are arranged in a circumferential array.

[0014] Beneficial effects

[0015] The technical solution provided by this utility model has the following advantages compared with the known prior art:

[0016] I. This utility model achieves a stable and flexible rotational connection between the control surface and the main body by adopting a snap-fit ​​design between the limiting block and the inner insertion hole, combined with two sets of mounting rods sleeved on the surface of the transmission shaft. This not only ensures that the control surface can accurately and smoothly change the angle between itself and the main body under the drive of the drive component and the transmission mechanism, but also improves the stability and durability of the entire control plate structure. The circumferential array distribution of the limiting block and the inner insertion hole further enhances the firmness of the connection and the smoothness of the rotation, enabling the flight device to maintain good handling performance and flight stability even in complex environments.

[0017] II. This utility model utilizes the principle of magnetic attraction between the first magnetic block on the mounting base and the second magnetic block on the transmission shaft, as well as the snap-fit ​​between the reinforcing block and the reinforcing socket, to effectively prevent the transmission shaft from shifting during rotation, thereby improving the stability and accuracy of the control surface rotation and significantly enhancing the control performance of the entire flight device.

[0018] Third, by opening the mounting slot, this utility model provides a clear installation path and positioning point for the track, which simplifies the installation process and improves installation efficiency. In addition, by fixing the mounting seat to the main body with bolts, it is convenient to disassemble and replace the mounting seat, which provides convenience for subsequent maintenance work. This design not only reduces maintenance costs, but also improves maintenance efficiency. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of a composite material rudder structure for a flight device proposed in this utility model;

[0021] Figure 2 This is a partial cross-sectional view of the main body of this utility model.

[0022] Figure 3 This is a schematic diagram of the overall appearance structure of the main body of this utility model;

[0023] Figure 4 This is a schematic diagram of the external structure of one end of the drive shaft of this utility model;

[0024] Figure 5 This is a schematic diagram of the overall appearance structure of the mounting base of this utility model.

[0025] Reference numerals: 1. Main body; 2. Control surface; 3. Drive component; 4. Support component; 5. First bevel gear; 6. Second bevel gear; 7. Connecting rod; 8. Track; 9. Mounting groove; 10. Drive shaft; 11. Drive groove; 12. Limiting block; 13. Reinforcing block; 14. First magnetic block; 15. Mounting base; 16. Screw hole; 17. Internal insertion hole; 18. Reinforcing insertion hole; 19. Second magnetic block; 20. Mounting rod; 21. Bushing. Detailed Implementation

[0026] 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, not all, of the embodiments of this utility model. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the scope of protection of this utility model.

[0027] The present invention will be further described below with reference to the embodiments.

[0028] A composite material rudder structure for an aircraft, as shown in the attached figure. Figure 1 - Figure 5 The system includes a main body 1 and a control surface 2. A drive component 3 is installed inside the main body 1. A transmission mechanism is located at one end of the drive component 3 near the control surface 2. The transmission mechanism is connected to a drive shaft 10. Limiting blocks 12 are provided on the surface of the drive shaft 10. A mounting base 15 is installed on the side of the main body 1 near the control surface 2. A bushing 21 is rotatably mounted on the mounting base 15. An inner insertion hole 17 is provided inside the bushing 21. The limiting blocks 12 and the inner insertion hole 17 are engaged. Both the limiting blocks 12 and the inner insertion hole 17 are arranged in a circumferential array. Two... Two sets of mounting rods 20 are fixedly mounted on the rudder surface 2 at the ends away from the drive shaft 10. By controlling the rotation direction of the drive component 3, the drive shaft 10 is driven to rotate through the transmission mechanism. The drive shaft 10 drives the mounting rods 20 to rotate stably on the two sets of symmetrically arranged mounting seats 15. The mounting rods 20 drive the rudder surface 2 to rotate, thereby changing the angle between the rudder surface 2 and the main body 1. By using composite materials, not only is the weight of the rudder plate structure reduced, but the adaptability to complex environments is also improved.

[0029] In the above technical solution, the transmission mechanism includes a first bevel gear 5 fixedly mounted on the driving member 3. The first bevel gear 5 is meshed with a second bevel gear 6. The second bevel gear 6 is sleeved on the surface of the connecting rod 7. The connecting rod 7 has identical transmission components installed at both ends. The transmission components include a track 8 installed on the connecting rod 7. The end of the track 8 away from the driving member 3 is connected to a transmission shaft 10. The driving member 3 passes through the support member 4 and is rotatably connected to it. The rotation of the driving member 3 drives the first bevel gear 5 to rotate. The first bevel gear 5 drives the second bevel gear 6 to rotate through meshing. The rotation of the second bevel gear 6 drives the 10 to rotate through the two sets of tracks 8 at both ends. Throughout the process, the support member 4 always provides stable support for the transmission mechanism, ensuring that the first bevel gear 5 and the second bevel gear 6 always remain in meshing state, thus ensuring the continuity and stability of power transmission.

[0030] The main body 1 has symmetrical mounting grooves 9 on the side near the rudder surface 2, and the drive shaft 10 has a drive groove 11 on the surface of the end near the limit block 12. The mounting grooves 9 provide a clear installation path and positioning point for the track 8, making the installation process faster and more accurate. At the same time, this also facilitates subsequent maintenance work. The two ends of the connecting rod 7 are rotatably mounted on the inner walls of the two sides of the main body 1. The drive groove 11 enables the drive shaft 10 to achieve a more precise transmission connection with the track 8, ensuring the continuity and stability of power transmission, thereby improving the handling performance of the entire rudder structure.

[0031] Furthermore, the mounting base 15 has multiple sets of screw holes 16 on its surface, with matching bolts threaded into each screw hole 16. The mounting base 15 is fixed to the main body 1 using these matching bolts. A second magnet 19 is positioned on the surface of the mounting base 15 away from the screw holes 16. First magnets 14 are positioned at both ends of the drive shaft 10. The second magnet 19 is magnetically connected to the first magnets 14. This magnetic connection prevents the drive shaft 10 from shifting at both ends during rotation, effectively improving the stability of the rudder surface 2's rotation. Reinforcing blocks 13 are provided at both ends near the first magnetic block 14. Reinforcing insertion holes 18 are provided on the surface of the bushing 21. The reinforcing insertion holes 18 and the reinforcing blocks 13 are engaged. The reinforcing blocks 13 and the reinforcing insertion holes 18 are arranged in a circumferential array. During installation, the drive shaft 10 is passed through the bushing 21, and then the reinforcing blocks 13 on the surface of the drive shaft 10 are inserted into the reinforcing insertion holes 18 on the surface of the bushing 21. Then the mounting base 15 is fixed, which ensures that the drive shaft 10 will not deviate when rotating, thereby further improving the control performance of the entire rudder structure and making the flight process safer, more stable and efficient.

[0032] Working principle: When in use, when the drive component 3 rotates, the meshing transmission of the first bevel gear 5 and the second bevel gear 6 drives the track 8 on the connecting rod 7 to move, thereby driving the drive shaft 10 to rotate. The limiting block 12 on the surface of the drive shaft 10 is engaged with the inner insertion hole 21 of the bushing 21 in the mounting base 15, ensuring that the drive shaft 10 rotates stably on the mounting base 15. At the same time, the drive shaft 10 drives the control surface 2 to rotate through the mounting rod 20, and changes the direction of the control surface 2 by controlling the rotation direction of the drive component 3, thereby changing the angle between the control surface 2 and the main body 1 to achieve control. The magnetic attraction between the first magnetic block 14 and the second magnetic block 19, and the engagement of the reinforcing block 13 with the reinforcing insertion hole 18, together prevent the drive shaft from deviating when rotating, improve the stability of the control surface 2 rotation, and make the flight process safer, more stable and efficient.

[0033] The above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions will not cause the essence of the corresponding technical solutions to deviate from the protection scope of the technical solutions of the embodiments of this utility model.

Claims

1. A composite material rudder structure for an aircraft, comprising a main body (1) and a rudder surface (2), characterized in that, The main body (1) is provided with a drive component (3). The drive component (3) is provided with a transmission mechanism at one end near the rudder surface (2). The transmission mechanism is connected to a drive shaft (10). The surface of the drive shaft (10) is provided with a limit block (12). The main body (1) is provided with a mounting seat (15) near the rudder surface (2). The mounting seat (15) is rotatably mounted with a bushing (21). The bushing (21) is provided with an inner insertion hole (17). The limit block (12) is engaged with the inner insertion hole (17). The limit block (12) and the inner insertion hole (17) are both arranged in a circumferential array. The surface of the drive shaft (10) is fitted with two sets of mounting rods (20). The ends of the two sets of mounting rods (20) away from the drive shaft (10) are fixedly mounted on the rudder surface (2).

2. The composite material rudder structure for a flight device according to claim 1, characterized in that, The transmission mechanism includes a first bevel gear (5) fixedly mounted on the drive member (3), the first bevel gear (5) meshing with a second bevel gear (6), the second bevel gear (6) being sleeved on the surface of the connecting rod (7), and the connecting rod (7) having identical transmission components installed at both ends.

3. The composite material rudder structure for a flight device according to claim 2, characterized in that, The transmission assembly includes a track (8) mounted on a connecting rod (7), with a drive shaft (10) connected to the end of the track (8) away from the drive member (3), and the drive member (3) passing through the support member (4) and being rotatably connected to the drive member (3).

4. The composite material rudder structure for an aircraft device according to claim 1, characterized in that, The main body (1) has symmetrical mounting grooves (9) on the side near the rudder surface (2), and the drive shaft (10) has a drive groove (11) on the surface of the end near the limiting block (12).

5. The composite material rudder structure for an aircraft device according to claim 1, characterized in that, The mounting base (15) has multiple sets of screw holes (16) on its surface, and the screw holes (16) are threaded with matching bolts.

6. The composite material rudder structure for a flight device according to claim 1, characterized in that, The mounting base (15) has a second magnetic block (19) on its surface away from the screw hole (16), and the transmission shaft (10) has a first magnetic block (14) on both ends. The second magnetic block (19) and the first magnetic block (14) are magnetically connected.

7. The composite material rudder structure for a flight device according to claim 1, characterized in that, The drive shaft (10) is provided with reinforcing blocks (13) at both ends near the first magnetic block (14). The bushing (21) has reinforcing insertion holes (18) on its surface. The reinforcing insertion holes (18) are engaged with the reinforcing blocks (13). The reinforcing blocks (13) and the reinforcing insertion holes (18) are arranged in a circumferential array.

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