A proportional airplane model tail swing structure

Abstract

The utility model relates to a kind of equal proportion aircraft model tail wing rotary swing structures, including fuselage and tail wing, the tail wing includes framework, composite film layer, pivot and buffer seat, the composite film layer is adhered in the outer surface of framework, the pivot is connected below framework, the buffer seat is installed in fuselage, the pivot is through sealing bearing movable and penetrates the fuselage, inserts into buffer seat using composite film layer covers the outer surface of hollow framework, increase the load area to wind, the tail wing can rotate around the junction with fuselage by wind blowing, realize the simulation design of movable tail wing, while buffer seat can when pivot rotates, exert a damping force, so that tail wing can only swing back and forth a certain angle.

Description

Technical Field

[0001] This utility model relates to the field of simulation model technology, and in particular to a tail wing gyratory structure for a scaled-down aircraft model. Background Technology

[0002] A life-size aircraft model is not merely a replica in appearance, but a precise copy strictly adhering to the specified scale. For example, a fighter jet with a real length of 20 meters, when built at a 1:10 scale, would have a model length of 2 meters. Every component, from the canopy to the landing gear, from the rivets to the antenna, is meticulously reproduced to this scale. Currently, most life-size aircraft models have fixed tail fins. When displayed statically outdoors, the tail fins cannot move. In contrast, the tail fins of China's J-20, the US's F-22 Raptor, and Russia's S-57 are all movable. If the tail fin of a life-size model is fixed and cannot sway with the wind, it results in a poor visitor experience during the display. Utility Model Content

[0003] Therefore, it is necessary to provide a tail wing gyratory structure for a scaled-down aircraft model to address the aforementioned issues.

[0004] A tail wing oscillation structure for a scaled-down aircraft model includes a fuselage and a tail wing. The tail wing includes a frame, a composite film layer, a pivot, and a buffer seat. The composite film layer is adhered to the outer surface of the frame. The pivot is connected to the lower part of the frame. The buffer seat is installed inside the fuselage. The pivot movably passes through the fuselage via a sealed bearing and is inserted into the buffer seat. Preferably, the composite film is made of carbon fiber and has a sun-protective coating on its surface.

[0005] Preferably, the buffer seat includes a seat body and a tension spring. The seat body is fixed inside the machine body, and the rotating shaft is movably inserted into the seat body. Two sets of symmetrical hooks are provided on the rotating shaft. The front end of the tension spring is connected to the hooks, and the rear end of the tension spring is connected to the machine body. The two sets of tension springs and hooks are detachably connected in a straight line.

[0006] Preferably, the upper surface of the seat is provided with an annular groove, and a positioning rod is provided on the rotating shaft, the positioning rod being movably inserted into the annular groove.

[0007] Preferably, the positioning rod and the hook are arranged in a cross shape.

[0008] The advantages of this utility model are: by using a composite film layer to cover the outer surface of the hollowed-out frame, the load-bearing area for wind is increased, and the tail fin can rotate around the connection point with the fuselage when the wind blows, realizing the simulation design of a movable tail fin. At the same time, the buffer seat can apply a damping force when the rotating shaft rotates, so that the tail fin can only swing back and forth at a certain angle. Attached Figure Description

[0009] Figure 1 This is a three-dimensional schematic diagram of the tail wing gyroscope structure of a scaled-down aircraft model, as one embodiment. Figure 2 This is a schematic diagram of a tail fin explosion. Detailed Implementation

[0010] To make the above-mentioned objects, features, and advantages of this utility model more apparent and understandable, the specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a full understanding of this utility model. However, this utility model can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this utility model. Therefore, this utility model is not limited to the specific embodiments disclosed below.

[0011] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0012] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0013] like Figures 1-2As shown, a scaled-down aircraft model tail wing oscillation structure includes a fuselage 1 and a tail wing 2. The tail wing 2 includes a frame 21, a composite film layer 22, a pivot 23, and a buffer seat 24. The composite film layer 22 is adhered to the outer surface of the frame 21. The pivot 23 is connected to the lower part of the frame 21. The buffer seat 24 is installed inside the fuselage 1. The pivot 23 movably passes through the fuselage 1 via a sealed bearing and is inserted into the buffer seat 24. Specifically, in this embodiment, the tail wing 2 is installed at the tail of the fuselage 1. The tail wing 2 has an internal aluminum alloy frame 21 to strengthen its structural strength, ensuring its integrity when exposed to wind outdoors. The frame 21 is covered with a composite film layer 22 to protect it from wind and sun exposure, while also enhancing its aesthetics. Meanwhile, the composite membrane layer 22 covers the outer surface of the hollowed-out frame 21, increasing the load-bearing area against the wind. This allows the tail fin 2 to rotate around its connection with the fuselage 1, achieving a simulated design of a movable tail fin. In this design, the rotating shaft 23 is welded to the frame 21 as a whole and inserted into the fuselage 1 through a sealed bearing, allowing the rotating shaft 23 to rotate freely. A buffer seat 24 is set inside the fuselage 1, and the rotating shaft 24 is inserted into the buffer seat 24. The buffer seat 24 acts as a damper when the rotating shaft 23 rotates, so that the tail fin can only sway back and forth at a certain angle. This prevents the tail fin 2 from being affected by strong winds during static outdoor displays, which would cause it to rotate rapidly 360 degrees, which is unsightly and does not conform to the actual rotation angle of a fighter jet's tail fin, thus failing to meet the requirements of model simulation.

[0014] Specifically, the composite membrane layer 22 is made of carbon fiber and coated with a sun-protective coating to enhance the lifespan of the tail wing during long-term static outdoor display.

[0015] like Figure 2 As shown, the buffer seat 24 includes a seat body 241 and a tension spring 242. The seat body 241 is fixed inside the body 1, and the rotating shaft 23 is movably inserted into the seat body 241. The rotating shaft 23 is provided with two symmetrical sets of hooks 231. The front end of the tension spring 242 is connected to the hook 231, and the rear end of the tension spring 242 is connected to the body 1. The two sets of tension springs 242 and hooks 231 are detachably connected in a straight line. Specifically, in this embodiment, the seat body 241 supports the rotating shaft 23. The rotating shaft 23 is provided with hooks 231 for connecting to the tension springs 242. The two tension springs 242 are symmetrical. When the rotating shaft 23 rotates, one side of the tension spring 242 is stretched, while the other side is bent and compressed. The elastic force provided by the stretched side of the tension spring 242 provides damping for the rotating shaft 23, preventing the rotating shaft 23 from rapidly swinging at a large angle.

[0016] like Figure 2As shown, the upper surface of the base 241 is provided with an annular groove 2411, and the rotating shaft 23 is provided with a positioning rod 232, which is movably inserted into the annular groove 2411. Specifically, the annular groove 2411 and the positioning rod 232 cooperate to play a limiting role, restricting the angle of rotation of the rotating shaft 23, and preventing the rotating shaft 23 from rotating too much, which would cause the tension spring 242 to be overstretched and lose its elastic performance.

[0017] like Figure 2 As shown, the positioning rod 232 and the hook 231 are cross-shaped to prevent the positioning rod 232 and the tension spring 242 from scraping when the rotating shaft 23 rotates.

[0018] The embodiments described above are merely illustrative of several implementations of this utility model, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model patent should be determined by the appended claims.

Claims

1. A tail wing yaw structure for a scaled-down airplane model, characterized in that: The device includes a fuselage and a tail fin. The tail fin includes a frame, a composite film layer, a rotating shaft, and a buffer seat. The composite film layer is adhered to the outer surface of the frame. The rotating shaft is connected to the lower part of the frame. The buffer seat is installed inside the fuselage. The rotating shaft moves through the fuselage via a sealed bearing and is inserted into the buffer seat.

2. The tail wing gyratory structure of a scaled-down aircraft model as described in claim 1, characterized in that: The composite membrane is made of carbon fiber and has a sun-protective coating on its surface.

3. The tail wing yaw structure of a proportionally scaled aircraft model as described in claim 1, characterized in that: The buffer seat includes a seat body and a tension spring. The seat body is fixed inside the machine body, and the rotating shaft is movably inserted into the seat body. Two sets of symmetrical hooks are provided on the rotating shaft. The front end of the tension spring is connected to the hooks, and the rear end of the tension spring is connected to the machine body. The two sets of tension springs and hooks are detachably connected in a straight line.

4. The tail wing yaw structure of a scaled-down aircraft model as described in claim 3, characterized in that: The upper surface of the base is provided with an annular groove, and a positioning rod is provided on the rotating shaft, the positioning rod being movably inserted into the annular groove.

5. The tail wing gyratory structure of a scaled-down aircraft model as described in claim 4, characterized in that: The positioning rod and the hook are arranged in a cross shape.

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