Model airplane
By designing a combination of pendulum, front tie rod, swing rod, rear tie rod, drive rod and rudder in model aircraft, the existing model aircraft lacks rudder and complex adjustment problems are solved, and the precise positioning and simple structure of the rudder are achieved.
Patent Information
- Application Number
- CN202421736804.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-22
- Publication Date
- 2025-06-17
- Estimated Expiration
- 2034-07-22
AI Technical Summary
Most of the vertical tails of existing model aircraft have no rudders, and the steering action cannot be achieved. Some models with rudders cannot be effectively adjusted or the adjustment mechanism is complicated.
A model aircraft including a pendulum, a front tie rod, a pendulum, a rear tie rod, a driving rod and a rudder was designed. The adjustment of the rudder deviation position is achieved through the coordination of the pendulum and the pendulum to ensure the precise position of the rudder.
The precise positioning of the rudder is achieved, with simple structure, low processing cost and significantly improved adjustment effect.
Smart Images
Figure CN222983708U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of model airplanes, and particularly relates to a model airplane. Background Art
[0002] Most of the existing model airplanes do not have a rudder on the vertical stabilizer. Therefore, turning actions cannot be achieved during flight. For some model airplanes with rudders, the deflection of the rudder often cannot be effectively adjusted, or the mechanism for adjusting the rudder is relatively complex. There is a lack of a rudder adjustment device with simple driving and reasonable structure. Summary of the Utility Model
[0003] Therefore, the utility model provides a model airplane to solve the above problems in the prior art. To achieve the above object, the utility model provides the following technical solutions: According to the first aspect of the utility model, a model airplane includes a frame, wings, a vertical stabilizer, and a horizontal stabilizer. The wings are installed in the middle of the frame, and the vertical stabilizer and the horizontal stabilizer are installed at the front and rear of the tail of the frame. It also includes a pendulum, a front pull rod, a swing rod, a rear pull rod, a driving rod, and a rudder. The front end of the frame is hinged with a pendulum, and a counterweight is arranged at the front end of the pendulum. The frame is hinged with a swing rod in the middle below the wings, and a hook is arranged at the lower end of the swing rod. The pendulum is connected with the swing rod through a front pull rod. The rudder is rotatably arranged on the vertical stabilizer, and a driving rod protrudes from the side of the rudder. The driving rod is connected with the swing rod through a rear pull rod.
[0004] Further, a front limit screw is arranged at the position of the bottom surface of the frame below the counterweight to limit the lower limit position of the counterweight.
[0005] Further, the pendulum is of an arc-shaped bent structure, and the bent part is connected with the upper end of the frame through a return spring.
[0006] Further, a rear limit screw is arranged at the position of the bottom surface of the frame in front of the swing rod to limit the front limit position of the swing rod.
[0007] Further, a front hook and a rear hook are sequentially arranged on the upper edge of the frame from front to back. The wings are located between the front hook and the rear hook. The front end of the rubber band is hung on the front hook, and the rear end is hung on the rear hook, thereby pressing the wings on the frame.
[0008] Further, the horizontal stabilizer is clamped on the tail of the frame through buckle A and buckle B.
[0009] Further, both buckle A and buckle B are of a square sleeve structure.
[0010] Further, the vertical stabilizer is located in front of the horizontal stabilizer.
[0011] Further, when the counterweight of the pendulum is at the upper limit position, the rudder is in the same plane as the vertical tail; when the counterweight of the pendulum is at the lower limit position, the rudder deviates from the plane where the vertical tail is located.
[0012] Further, there are two counterweights, which are respectively placed on both side faces at the front end of the pendulum.
[0013] The utility model has the following advantages: Through a model airplane of the utility model, the adjustment of the deviation position of the rudder is realized through the cooperation of the swing rod and the pendulum, effectively realizing the precise positioning of the rudder. The device has a simple structure, low processing cost, and significantly improved adjustment effect. Description of the Drawings
[0014] Figure 1 It is the front view of a model airplane provided by some embodiments of the utility model.
[0015] Figure 2 It is the partial structure diagram of a model airplane provided by some embodiments of the utility model.
[0016] Figure 3 It is the three-dimensional view of a model airplane provided by some embodiments of the utility model.
[0017] Figure 4 It is the bottom view of a model airplane provided by some embodiments of the utility model.
[0018] In the figure, 1. Frame, 2. Pendulum, 3. Front limit screw, 4. Return spring, 5. Front pull rod, 6. Rear limit screw, 7. Swing rod, 8. Rear pull rod, 9. Driving rod, 10. Rudder, 11. Front hook, 12. Wing, 13. Rear hook, 14. Vertical tail, 15. Horizontal tail, 16. Snap A, 17. Snap B, 18. Rubber band member. Detailed Embodiments
[0019] The following specific embodiments illustrate the implementation manners of the utility model. Those skilled in the art can easily understand other advantages and effects of the utility model from the content disclosed in this specification. Obviously, the described embodiments are part of the embodiments of the utility model, rather than all of them. Based on the embodiments in the utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the utility model.
[0020] Embodiment 1
[0021] As Figures 1 to 4As shown in the figure, a model airplane in the first aspect of the present utility model includes a frame 1, a wing 12, a vertical stabilizer 14, and a horizontal stabilizer 15. The wing 12 is installed in the middle of the frame 1, and the vertical stabilizer 14 and the horizontal stabilizer 15 are installed at the front and rear of the tail of the frame 1. It is characterized in that it further includes a pendulum 2, a front pull rod 5, a swing rod 7, a rear pull rod 8, a drive rod 9, and a rudder 10. The front end of the frame 1 is hinged with the pendulum 2, and a counterweight is provided at the front end of the pendulum 2. The frame 1 is hinged with the swing rod 7 at the middle part below the wing 12, and a hook is provided at the lower end of the swing rod 7. The pendulum 2 is connected to the swing rod 7 through the front pull rod 5. The rudder 10 is rotatably arranged on the vertical stabilizer 14, and a drive rod 9 protrudes from the side of the rudder 10. The drive rod 9 is connected to the swing rod 7 through the rear pull rod 8.
[0022] The technical effects achieved by the above embodiments are as follows: Through a model airplane of this embodiment, the adjustment of the deviation position of the rudder is realized through the cooperation of the swing rod and the pendulum, effectively achieving the precise positioning of the rudder. The structure of this device is simple, the processing cost is low, and the adjustment effect is significantly improved.
[0023] Embodiment 2
[0024] As Figures 1 to 4 shown, a model airplane includes all the contents of Embodiment 1. In addition, a front limit screw 3 is provided at the position of the bottom surface of the frame 1 below the counterweight for limiting the lower limit position of the counterweight. During use, the adjustment of different height positions of the lower limit position of the counterweight is realized through the front limit screw 3 threadedly connected to the frame 1.
[0025] Optionally, the pendulum 2 is an arc-shaped bent structure, and the bent part is connected to the upper end of the frame 1 through a return spring 4.
[0026] Optionally, a rear limit screw 6 is provided at the position of the bottom surface of the frame 1 in front of the swing rod 7 for limiting the front limit position of the swing rod 7. During use, the adjustment of different front and rear positions of the front limit position of the swing rod 7 is realized through the rear limit screw 6 threadedly connected to the frame 1.
[0027] The technical effects achieved by the above embodiments are as follows: By setting the front limit screw 3, the adjustment of the lower limit position of the counterweight is realized; by setting the return spring 4, the reset of the pendulum 2 is realized; by setting the rear limit screw 6, the adjustment of the front limit position of the swing rod 7 is realized.
[0028] Embodiment 3
[0029] As Figures 1 to 4As shown in the figure, a model airplane includes all the contents of Embodiment 2. In addition, a front hook 11 and a rear hook 13 are sequentially arranged on the upper edge of the frame 1 from front to back. The wing 12 is located between the front hook 11 and the rear hook 13. The front end of the rubber band member 18 is hooked on the front hook 11, and the rear end is hooked on the rear hook 13, thereby pressing the wing 12 onto the frame 1.
[0030] The technical effects achieved by the above embodiment are as follows: By setting the front hook 11 and the rear hook 13 and fixing the wing 12 through the rubber band member 18, when the airplane collides and the wing 12 pops out protectively and separates from the fuselage, the rubber band member 18 is not easily lost.
[0031] Embodiment 4
[0032] As Figures 1 to 4 shown in the figure, a model airplane includes all the contents of Embodiment 3. In addition, the horizontal tail fin 15 is clamped to the tail of the frame 1 through a buckle A 16 and a buckle B 17.
[0033] Optionally, both the buckle A 16 and the buckle B 17 are of a square sleeve structure.
[0034] The technical effects achieved by the above embodiment are as follows: By installing the horizontal tail fin 15 with the buckle A 16 and the buckle B 17, the accuracy of the installation of the horizontal tail fin 15 is ensured.
[0035] Embodiment 5
[0036] As Figures 1 to 4 shown in the figure, a model airplane includes all the contents of Embodiment 4. In addition, the vertical tail fin 14 is located in front of the horizontal tail fin 15.
[0037] Optionally, when the counterweight of the pendulum 2 is at the upper limit position, the rudder 10 and the vertical tail fin 14 are in the same plane; when the counterweight of the pendulum 2 is at the lower limit position, the rudder 10 deviates from the plane where the vertical tail fin 14 is located.
[0038] Optionally, the counterweight is in two pieces and is respectively placed on both side faces of the front end of the pendulum 2.
[0039] The technical effects achieved by the above embodiment are as follows: By setting the counterweight in two pieces, the stability and accuracy of the movement of the pendulum 2 are ensured.
[0040] In the description of the present utility model, it should be understood that the orientation or positional relationship indicated by terms such as "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial direction", "radial direction", "circumferential direction", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present utility model.
[0041] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present utility model, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically and clearly defined.
[0042] In the present utility model, unless otherwise clearly specified and defined, terms such as "installation", "connection", "connection", "fixation", etc. should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements or the interaction relationship between two elements, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.
[0043] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "examples", "specific examples", or "some examples", etc. means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present utility model. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.
[0044] Although the embodiments of the present utility model have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as a limitation to the present utility model. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present utility model.
[0045] In the description of this specification, the descriptions referring to terms such as "Embodiment 1", "Embodiment 2", "example", "specific example", or "some examples", etc. mean that the specific methods, devices, or features described in connection with the embodiment or example are included in at least one embodiment or example of the present utility model. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, methods, devices, or features described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.
[0046] The above are only the preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.
Claims
1. A model airplane, comprising a frame (1), wings (12), a vertical tail (14) and a horizontal tail (15), wherein the wing (12) is installed in the middle of the frame (1), and the vertical tail (14) and the horizontal tail (15) are installed in the front and rear of the tail of the frame (1), characterized in that: The invention also comprises a pendulum (2), a front tie rod (5), a rocking rod (7), a rear tie rod (8), a driving rod (9) and a rudder (10); the front end of the frame (1) is hinged with the pendulum (2), the front end of the pendulum (2) is provided with a counterweight, the frame (1) is hinged with a rocking rod (7) at the middle part below the wing (12), the lower end of the rocking rod (7) is provided with a hook, the pendulum (2) is connected to the rocking rod (7) through the front tie rod (5), the rudder (10) is rotatably arranged on the vertical tail (14), the side of the rudder (10) is protruded with a driving rod (9), and the driving rod (9) and the rocking rod (7) are connected through the rear tie rod (8).
2. The model aircraft according to claim 1, characterized in that: A front limit screw (3) is provided on the bottom surface of the frame (1) at a position below the counterweight, and is used to limit the lower limit position of the counterweight.
3. The model aircraft according to claim 1, characterized in that: The pendulum (2) is an arc-shaped bent structure, and its bent portion is connected to the upper end of the frame (1) via a return spring (4).
4. The model aircraft according to claim 1, characterized in that: A rear limit screw (6) is provided on the bottom surface of the frame (1) at a position in front of the swing rod (7) for limiting the front limit position of the swing rod (7).
5. The model aircraft according to claim 1, characterized in that: The upper edge of the frame (1) is provided with a front hook (11) and a rear hook (13) in sequence from front to rear, the wing (12) is located between the front hook (11) and the rear hook (13), the front end of the elastic member (18) is hooked on the front hook (11), and the rear end is hooked on the rear hook (13), so that the wing (12) is pressed onto the frame (1).
6. The model aircraft according to claim 1, characterized in that: The horizontal tail (15) is clamped on the tail of the frame (1) through a clamp A (16) and a clamp B (17).
7. The model aircraft according to claim 6, characterized in that: Buckle A (16) and buckle B (17) are both square sleeve structures.
8. The model aircraft according to claim 1, characterized in that: The vertical tail (14) is located in front of the horizontal tail (15).
9. The model aircraft according to claim 1, characterized in that: When the counterweight of the pendulum (2) is located at the upper limit position, the rudder (10) and the vertical tail (14) are located in the same plane; when the counterweight of the pendulum (2) is located at the lower limit position, the rudder (10) deviates from the plane where the vertical tail (14) is located.
10. The model aircraft according to claim 1, characterized in that: The counterweight is composed of two pieces, which are respectively arranged on two side surfaces of the front end of the pendulum (2).