Single-steering-engine model airplane speed brake device

Abstract

The utility model belongs to the technical field of speed reducing devices, and relates to a single-steering-engine model airplane speed reducing plate device which comprises a main wing, a concave cavity is formed in the middle of the main wing, an upper speed reducing plate and a lower speed reducing plate are rotationally connected to the end of the main wing, and a driving assembly is arranged in the middle of the concave cavity. When the single-steering-engine model airplane needs to be decelerated, the driving assembly can be used for separating the upper speed reducing plate and the lower speed reducing plate at the end of the main wing, then the upper speed reducing plate can be rotated upwards, the lower speed reducing plate can be rotated downwards, air resistance in the flying process of the single-steering-engine model airplane can be improved, and the speed reducing effect of the single-steering-engine model airplane is improved. And the purpose of quickly reducing the speed of the single-steering-engine model airplane can be achieved.

Description

Technical Field

[0001] This utility model belongs to the technical field of deceleration devices, and relates to a single servo motor model aircraft deceleration plate device. Background Technology

[0002] A single-servo model aircraft refers to a small aircraft model that uses only a single servo as the core actuator. Through mechanical linkages or transmission mechanisms, the servo's power is distributed to different control surfaces (such as elevators and rudders) to achieve basic flight attitude adjustments.

[0003] During the flight of a single servo model aircraft, if deceleration is required, the high speed of the motor can be reduced to the low speed of the output shaft through the multi-stage reduction gear set inside the servo, while increasing the torque. In this way, the power transmission efficiency and deceleration effect can be balanced through the gear ratio.

[0004] During use, it was found that existing single-servo model aircraft only have one speed brake deployed when decelerating and landing, resulting in relatively low drag and difficulty in effectively reducing the flight speed of single-servo model aircraft. Utility Model Content

[0005] The technical problem this invention aims to solve is that, during use, it has been found that existing single-servo model aircraft only have one speed brake deployed when decelerating and landing, resulting in relatively low drag and difficulty in effectively reducing the flight speed of the single-servo model aircraft.

[0006] The present invention relates to a single servo motor model aircraft speed brake device, comprising a main wing, a cavity formed in the middle of the main wing, an upper speed brake rotatably connected to the end of the main wing, a lower speed brake rotatably connected to the end of the main wing, and a drive assembly disposed in the middle of the cavity.

[0007] The drive assembly includes a rotating shaft, a connecting rudder arm, an upper connecting rod, and a lower connecting rod. The rotating shaft is rotatably connected to the center of the cavity, and the connecting rudder arm is rotatably connected to the center of the rotating shaft. The upper connecting rod is rotatably connected to the center of the upper part of the connecting rudder arm, and the lower connecting rod is rotatably connected to the center of the lower part of the connecting rudder arm. Support assemblies are provided at the ends of the upper and lower connecting rods.

[0008] The support assembly includes an upper speed reduction plate rudder arm and a lower speed reduction plate rudder arm. The upper speed reduction plate rudder arm is rotatably connected to the end of the upper connecting rod, and the end of the upper speed reduction plate rudder arm is fixedly connected to the upper speed reduction plate. The lower speed reduction plate rudder arm is rotatably connected to the end of the lower connecting rod, and the end of the lower speed reduction plate rudder arm is fixedly connected to the lower speed reduction plate.

[0009] The upper deceleration plate is wider than the lower deceleration plate, and the upper deceleration plate is located above the lower deceleration plate.

[0010] The upper and lower speed reducers are fixed with rubber sealing gaskets at their ends near the main wing.

[0011] Compared with the prior art, the beneficial effects of this utility model are: when it is necessary to decelerate a single servo model aircraft, the drive assembly can be used to separate the upper and lower speed brakes at the end of the main wing, so that the upper speed brake can be rotated upward and the lower speed brake can be rotated downward, thereby increasing the air resistance during the flight of the single servo model aircraft and achieving the purpose of rapidly decelerating the single servo model aircraft.

[0012] By rotating the pivot, and then through the action of the connecting rudder arm, the upper and lower connecting rods can be rotated. This force of rotating the connecting rudder arm can be transmitted to the support assembly. In turn, through the action of the support assembly, the upper and lower speed brakes can be rotated. Thus, when it is necessary to decelerate a single servo model aircraft, the upper and lower speed brakes can be opened or closed simultaneously. Attached Figure Description

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

[0014] Figure 2 This is a schematic diagram of the deceleration plate in the closed state in this utility model.

[0015] Figure 3 This is a rear view structural schematic diagram of the rotating shaft in this utility model.

[0016] Figure 4 This utility model Figure 2 Enlarged diagram of point A.

[0017] In the diagram: 1. Main wing; 2. Cavity; 3. Upper speed brake; 4. Lower speed brake; 5. Shaft; 6. Connecting rudder arm; 7. Upper connecting rod; 8. Lower connecting rod; 9. Upper speed brake rudder arm; 10. Lower speed brake rudder arm; 11. Rubber sealing gasket. Detailed Implementation

[0018] 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.

[0019] 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.

[0020] 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.

[0021] Example 1

[0022] like Figures 1-4 As shown, it includes a main wing 1, a cavity 2 is provided in the middle of the main wing 1, an upper speed reduction plate 3 is rotatably connected to the end of the main wing 1, a lower speed reduction plate 4 is rotatably connected to the end of the main wing 1, and a drive assembly is provided in the middle of the cavity 2.

[0023] When it is necessary to decelerate a single servo model aircraft, the drive assembly can be used to separate the upper speed brake 3 and the lower speed brake 4 at the end of the main wing 1. This allows the upper speed brake 3 to rotate upward and the lower speed brake 4 to rotate downward, thereby increasing the air resistance during the flight of the single servo model aircraft and achieving the purpose of rapidly decelerating the single servo model aircraft.

[0024] The drive assembly includes a rotating shaft 5, a connecting rudder arm 6, an upper connecting rod 7, and a lower connecting rod 8. The rotating shaft 5 is rotatably connected to the center of the cavity 2. The connecting rudder arm 6 is rotatably connected to the center of the rotating shaft 5. The upper connecting rod 7 is rotatably connected to the center of the upper part of the connecting rudder arm 6. The lower connecting rod 8 is rotatably connected to the center of the lower part of the connecting rudder arm 6. Support assemblies are provided at the ends of the upper connecting rod 7 and the lower connecting rod 8. The support assemblies are fixedly connected to the upper speed reduction plate 3 and the lower speed reduction plate 4, respectively.

[0025] When it is necessary to open the upper speed brake 3 and the lower speed brake 4, the rotating shaft 5 can be rotated. Then, through the action of the connecting rudder arm 6, the upper connecting rod 7 and the lower connecting rod 8 can be rotated. The force of the rotation of the connecting rudder arm 6 can be transmitted to the support assembly. Then, through the action of the support assembly, the upper speed brake 3 and the lower speed brake 4 can be rotated. Thus, when it is necessary to decelerate the single servo model aircraft, the upper speed brake 3 and the lower speed brake 4 can be opened or closed simultaneously.

[0026] The support assembly includes an upper speed reduction plate rudder arm 9 and a lower speed reduction plate rudder arm 10. The upper speed reduction plate rudder arm 9 is rotatably connected to the end of the upper connecting rod 7, and the end of the upper speed reduction plate rudder arm 9 is fixedly connected to the upper speed reduction plate 3. The lower speed reduction plate rudder arm 10 is rotatably connected to the end of the lower connecting rod 8, and the end of the lower speed reduction plate rudder arm 10 is fixedly connected to the lower speed reduction plate 4.

[0027] When the force of the rotation of the connecting rudder arm 6 is transmitted to the upper speed reduction plate 3 and the lower speed reduction plate 4 through the upper connecting rod 7, the upper speed reduction plate rudder arm 9 and the lower speed reduction plate rudder arm 10 can be used to rotate the upper speed reduction plate 3 and the lower speed reduction plate 4. In this way, when it is necessary to rotate the upper speed reduction plate 3 and the lower speed reduction plate 4, the damage caused to the middle of the upper speed reduction plate 3 and the lower speed reduction plate 4 by the ends of the upper connecting rod 7 and the lower connecting rod 8 can be reduced. At the same time, the upper speed reduction plate 3 and the lower speed reduction plate 4 can be rotated more easily.

[0028] Example 2

[0029] like Figures 1-4As shown, the upper speed reducer 3 is wider than the lower speed reducer 4, and the upper speed reducer 3 is located above the lower speed reducer 4.

[0030] The larger width of the upper speed reducer 3 makes it easier to install the lower speed reducer arm 10. This reduces the likelihood of the upper speed reducer arm 9 and the lower speed reducer arm 10 coming into contact with each other when the upper speed reducer 3 and the lower speed reducer 4 need to be opened, which would increase friction and make it difficult to rotate.

[0031] Example 3

[0032] like Figures 1-3 As shown, rubber sealing gaskets 11 are fixed to the ends of the upper speed reduction plate 3 and the lower speed reduction plate 4 near the main wing 1.

[0033] By using the rubber sealing gasket 11, the upper speed reduction plate 3 and the main wing 1 can be sealed after the upper speed reduction plate 3 and the lower speed reduction plate 4 are rotated open. This reduces the occurrence of air passing through the gap between the upper speed reduction plate 3 and the main wing 1, thus weakening the deceleration effect.

[0034] The descriptions of the orientation and relative positional relationships of the structure in this utility model, such as descriptions of front, back, left, right, up, and down, do not constitute a limitation on this utility model, but are merely for the convenience of description.

Claims

1. A single-rudder model airplane speed brake device, characterized in that: The utility model provides a kind of winged aircraft, including main wing (1), the main wing (1) middle part is provided with recess (2), the main wing (1) end is rotatably connected with upper speed reducer plate (3), the main wing (1) end is rotatably connected with lower speed reducer plate (4), the recess (2) middle part is provided with drive assembly.

2. A single-rudder model aircraft speed brake device according to claim 1, characterized in that: The drive assembly includes shaft (5), connecting rudder arm (6), upper connecting rod (7), lower connecting rod (8), the recess (2) middle part is rotatably connected with shaft (5), the shaft (5) middle part is rotatably connected with connecting rudder arm (6), the connecting rudder arm (6) upper middle part is rotatably connected with upper connecting rod (7), the connecting rudder arm (6) lower middle part is rotatably connected with lower connecting rod (8), the upper connecting rod (7) and lower connecting rod (8) end are provided with support assembly.

3. A single-rudder model aircraft speed brake device according to claim 2, characterized in that: The support assembly includes upper speed reducer plate rudder arm (9), lower speed reducer plate rudder arm (10), the upper connecting rod (7) end is rotatably connected with upper speed reducer plate rudder arm (9), the upper speed reducer plate rudder arm (9) end is fixedly connected with upper speed reducer plate (3), the lower connecting rod (8) end is rotatably connected with lower speed reducer plate rudder arm (10), and the lower speed reducer plate rudder arm (10) end is fixedly connected with lower speed reducer plate (4).

4. A single-rudder model aircraft speed brake device according to claim 1, characterized in that: The upper speed reducer plate (3) width is greater than the width of lower speed reducer plate (4), and the upper speed reducer plate (3) is located in the upper position of lower speed reducer plate (4).

5. A single-rudder model aircraft speed brake device according to claim 1, characterized in that: The upper speed reducer plate (3) and lower speed reducer plate (4) are fixed with rubber sealing gasket (11) close to the end of main wing (1).

Images