Model airplane single slide rail flap structure

Abstract

The utility model belongs to the technical field of airplane model flaps, and relates to an airplane model single-slide-rail flap structure which comprises an installation block, a connecting hole is formed in the top of the outer side of the installation block, a fixing rod is installed in the connecting hole, a rotating assembly is installed on the outer side of the fixing rod, and a sliding assembly is installed at the end of the installation block. A flap body is arranged on the outer side of the mounting block and used in cooperation with a sliding assembly and a rotating assembly, through the use of the rotating assembly and the sliding assembly, angle adjustment of the flap body is more flexible, meanwhile, the number of parts is reduced, the structure simplification rate is high, the structure is simple, and the structure is more compact. And compared with a traditional flap, the assembly process is simpler, the complexity of the assembly process is remarkably reduced, the maintenance time is shortened, and the maintenance cost is reduced.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft model flap technology, and relates to a single-rail flap structure for aircraft models. Background Technology

[0002] Flaps are movable wing surfaces installed on the trailing or leading edge of an aircraft wing. They adjust lift and drag by changing the wing's curvature and area. They are one of the core components of flight control and have functions such as improving stall characteristics and reducing takeoff and landing distances. Based on their characteristics, they are divided into types such as trailing edge flaps and leading edge flaps.

[0003] When using the above technology, the following technical problems were found in the existing technology: In the traditional model aircraft field, multi-hinge linkage flaps are usually used. The typical structure is a multi-rail parallel mechanism, which is usually controlled by multiple parallel rails to deflect and adjust the flap angle. This has the disadvantages of a large number of parts, high assembly complexity, and high maintenance cost. Utility Model Content

[0004] The technical problem to be solved by this utility model is that in the traditional model aircraft field, multi-hinge linkage flaps are usually used. The typical structure is a multi-rail parallel mechanism, which usually uses multiple parallel rails to control the flap angle for deflection and adjustment. This has the disadvantages of a large number of parts, high assembly complexity, and high maintenance cost.

[0005] The present invention discloses a single-rail flap structure for a model aircraft, comprising a mounting block, a connecting hole on the top outer side of the mounting block, a fixing rod installed inside the connecting hole, a rotating component installed on the outer side of the fixing rod, a sliding component installed at the end of the mounting block, and a flap body provided on the outer side of the mounting block. The flap body is used in conjunction with the sliding component and the rotating component.

[0006] The rotating assembly includes a connecting rod, and a rotating shaft is installed at the end of the connecting rod away from the fixed rod. The connecting rod is rotatably connected to the outside of the fixed rod. A first rotating hole is opened at the bottom of the flap body, and the first rotating hole is rotatably connected to the outside of the rotating shaft.

[0007] The sliding component includes a second rotating hole located at the bottom outer side of the flap body. A sliding groove is provided on the outer side of the mounting block, and a sliding groove is slidably connected inside the sliding groove. The sliding groove rotates inside the second rotating hole.

[0008] The flap body is equipped with a flap keel inside.

[0009] The connecting rod is made of polyethylene.

[0010] Compared with the prior art, the beneficial effects of this utility model are: the use of rotating and sliding components makes it more flexible to adjust the angle of the flap body, while reducing the number of parts, resulting in a higher structural simplification rate. The assembly process is also simpler than that of traditional flaps, significantly reducing the complexity of the assembly process, reducing maintenance time, and lowering maintenance costs.

[0011] By using the flap keel inside the flap body, the weight of the device is reduced by 70% compared to a solid structure. At the same time, it has better fatigue resistance and impact resistance, achieving weight reduction while increasing the strength of the flap body. Attached Figure Description

[0012] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0013] Figure 1 This is a schematic diagram of the structure of the mounting block of this utility model.

[0014] Figure 2 This is a schematic diagram of the structure of the mounting block of this utility model.

[0015] Figure 3 This is a schematic diagram of the flap body of this utility model.

[0016] Figure 4 This is a schematic diagram of the connecting rod of this utility model.

[0017] Figure 5 This is a schematic diagram of the structure of the flap keel of this utility model.

[0018] In the diagram: 1. Mounting block; 11. Flap body; 12. Connecting hole; 13. Fixing rod; 2. Connecting rod; 21. Rotating shaft; 22. First rotating hole; 3. Second rotating hole; 31. Connecting rod; 32. Sliding groove; 4. Flap keel. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.

[0020] To enable those skilled in the art to better understand the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings.

[0021] It should be noted that, unless otherwise specified, the embodiments and features and technical solutions in the present invention can be combined with each other.

[0022] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0023] Example 1

[0024] like Figures 1-5 As shown, a single-rail flap structure for a model aircraft includes a mounting block 1. The mounting block 1 is made of carbon fiber, which has the characteristics of high strength and light weight, and can reduce the load on the model aircraft. A connecting hole 12 is provided on the top of the outer side of the mounting block 1. A fixing rod 13 is installed inside the connecting hole 12. A rotating component is installed on the outer side of the fixing rod 13. A sliding component is installed at the end of the mounting block 1. A flap body 11 is provided on the outer side of the mounting block 1. The flap body 11 is used in conjunction with the sliding component and the rotating component. The rotating component includes a connecting rod 2, which is rotatably connected to the outside of the fixing rod 13. A rotating shaft 21 is installed at the end of the connecting rod 2 away from the fixing rod 13. A first rotating hole 22 is provided at the bottom of the flap body 11. The first rotating hole 22 is located outside the rotating shaft 21 and is rotatably connected. The sliding component includes a second rotating hole 3, which is located at the bottom of the outer side of the flap body 11. A sliding groove 32 is provided on the outer side of the mounting block 1. A sliding groove 32 is slidably connected inside the sliding groove 32 and rotates inside the second rotating hole 3.

[0025] During operation, the two sets of mounting blocks 1 are first connected by the fixing rod 13. Then, the connecting rod 31 passes through the second rotating hole 3 at the bottom of the flap body 11 and the sliding groove 32 on the outside of the mounting block 1, so that the connecting rod 31 can slide inside the sliding groove 32 and rotate inside the second rotating hole 3. Then, the first rotating hole 22 at the bottom of the flap body 11 is connected to the connecting rod 2 through the rotating shaft 21, so that when the connecting rod 2 is pushed, the connecting rod 31 can slide arbitrarily inside the sliding groove 32. When the connecting rod 31 is at one end of the sliding groove 32, the flap body 11 can still be rotated around the connecting rod 31 by adjusting the angle of the connecting rod 2, which increases the flexibility of the angle of the flap body 11. The use of the rotating component and the sliding component makes the angle adjustment of the flap body 11 more flexible, while reducing the number of parts, resulting in a high structural simplification rate. The assembly process is also simpler than that of traditional flaps, significantly reducing the complexity of the assembly process, reducing maintenance time, and reducing maintenance costs.

[0026] Example 2

[0027] like Figure 3 - Figure 5 As shown, the flap body 11 is provided with flap keel 4 inside, and the connecting rod 31 is made of polyethylene. Polyethylene has the characteristics of being easy to mold, recyclable and having high strength, which helps to reduce the production cost of the device.

[0028] The work involves using the flap keel 4 inside the flap body 11 to reduce the weight of the device by 70% compared to a solid structure, while also providing better fatigue resistance and impact resistance, thus increasing the strength of the flap body 11 while reducing weight.

[0029] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the present utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the present utility model, thereby enabling those skilled in the art to better understand and utilize it. The present utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A model aircraft single-slat flap configuration, characterized by: The utility model provides a kind of wing flap, including installation block (1), the connecting hole (12) is opened in the outside top of installation block (1), the fixed rod (13) is installed in the inside of connecting hole (12), the rotating assembly is installed in the outside of fixed rod (13), the sliding assembly is installed in the end of installation block (1), the wing flap body (11) is provided in the outside of installation block (1), and the wing flap body (11) is used with sliding assembly, rotating assembly cooperation.

2. A model aircraft single-slider flap construction according to claim 1, characterized in that: The rotating assembly includes connecting rod (2), the rotating shaft (21) is installed in the end away from fixed rod (13) of connecting rod (2), and connecting rod (2) is rotatably connected outside fixed rod (13), the first rotating hole (22) is opened in the bottom of wing flap body (11), and the first rotating hole (22) is rotatably connected outside rotating shaft (21).

3. A single-slider flap configuration for a model aircraft as defined in Claim 1 wherein: The sliding assembly includes second rotating hole (3), and the second rotating hole (3) is located in the bottom outside wing flap body (11), the sliding groove (32) is provided in the outside of installation block (1), the connecting rod (31) is slidably connected in the inside of sliding groove (32), and the sliding groove (32) is rotated in the inside of second rotating hole (3).

4. A model aircraft single-slider flap construction according to claim 1, characterized in that: The wing flap body (11) is provided with wing flap keel (4) inside.

5. A single-slider flap configuration for a model aircraft as defined in claim 3, wherein: The connecting rod (31) is made of polyethylene.

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