A control structure for a model aircraft rudder
By designing a control structure in which a power mechanism drives two ailerons simultaneously in the model aircraft, the problem of increasing costs and weight of multiple drive systems in the prior art is solved, and lighter and more efficient flight control is achieved.
Patent Information
- Application Number
- CN202420654919.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-01
- Publication Date
- 2025-04-01
- Estimated Expiration
- 2034-04-01
AI Technical Summary
The existing model aircraft rudder surface control structure uses two independent drive systems, increasing component cost and overall weight.
A rudder surface control structure of model aircraft is designed, and two ailerons are driven simultaneously through a power mechanism, and a combination of driving end, power mechanism and driving rod mechanism is adopted to achieve the coordinated rotation of the two ailerons.
Saves the number of parts, reduces manufacturing costs and overall weight, while achieving flexible steering of the aircraft.
Smart Images
Figure CN222693989U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of model airplanes, and in particular relates to a control surface structure of a model airplane. Background Art
[0002] As the name suggests, an aviation model is a model aircraft made according to the appearance of an aircraft. It belongs to the aerospace model and is an unmanned aircraft for sports. The aircraft model has exceeded the narrow scope of research by aerospace scientists and has become a means of learning and exercise for aerospace and flight enthusiasts. When flying, the fixed-wing aircraft model controls the rotation of two ailerons to perform turning flight.
[0003] The commonly used control surface structure of model aircraft uses two drive systems to control the movement of two ailerons respectively. Although the control system can be directly installed on the control panel to reduce the weight to a certain extent, more drive components are used, which not only increases the cost of the components, but also increases the overall weight of the model aircraft. Utility Model Content
[0004] The purpose of the utility model is to provide a control structure for a model airplane rudder surface, which can not only save manufacturing costs, but also save the overall weight of the model airplane, so as to solve the problems raised in the above-mentioned background technology.
[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a rudder control structure for a model aircraft, comprising an outer shell and a mounting frame for mounting the outer shell, the mounting frame being sleeved on the middle part of the outer side of the outer shell, the top end of the outer shell being rotatably connected to a driving end head, the interior of the outer shell being provided with a power mechanism for driving the driving end head to rotate, a driving rod mechanism being symmetrically arranged on the driving end head, one end of the driving rod mechanism being rotatably connected to the driving end head, and the other end of the driving rod mechanism being rotatably connected to a connecting end head.
[0006] Furthermore, the shell includes a shell, both sides of the shell are fixedly connected with connecting ears, and the top of the shell is fixedly connected with a supporting end.
[0007] Furthermore, the mounting bracket includes a square sleeve sleeved on the outside of the shell, and both sides of the square sleeve are fixedly connected with supporting ears for supporting the connecting ears, and the bottom end of the supporting ears is provided with a threaded tube.
[0008] Furthermore, the driving end head includes a mounting tube, and a connecting plate is fixedly connected to the side wall of the mounting tube. There are four connecting plates, and the four connecting plates are symmetrically arranged in pairs. The surface of the connecting plate is provided with a first connecting hole for connecting the driving rod mechanism.
[0009] Furthermore, the power mechanism includes a forward and reverse motor and a reduction gearbox, and the forward and reverse motor and the reduction gearbox are fixedly connected inside the shell, the output shaft of the forward and reverse motor is fixedly connected to the input end of the reduction gearbox, the output end of the reduction gearbox is fixedly connected to a rotating shaft, the top of the rotating shaft is rotatably connected to the supporting end through a bearing, and the mounting tube is fixedly sleeved on the top of the rotating shaft.
[0010] Furthermore, the driving rod mechanism includes a connecting rod, both ends of which are integrally connected with Z-shaped end heads, one of which is rotatably connected inside a corresponding first connecting hole, and the other Z-shaped end is rotatably connected to the connecting end, and a U-shaped protrusion is provided on the connecting rod.
[0011] Furthermore, a second connection hole for rotationally cooperating with the Z-shaped end is provided on the top of the connection end.
[0012] Compared with the prior art, the utility model has the beneficial effect that when performing a steering operation, two ailerons are driven to move simultaneously by a power mechanism, thereby saving components, not only saving manufacturing costs, but also saving the overall weight of the model aircraft. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;
[0014] Figure 2 It is a top view of the utility model;
[0015] Figure 3 For this utility model Figure 2 Section view of plane AA.
[0016] In the accompanying drawings, the components represented by the reference numerals are listed as follows:
[0017] 1. Outer shell; 11. Shell; 12. Connecting ear; 13. Supporting end; 2. Mounting frame; 21. Square sleeve; 22. Supporting ear; 23. Threaded barrel; 3. Driving end; 31. Mounting barrel; 32. Connecting piece; 33. First connecting hole; 4. Power mechanism; 41. Forward and reverse motors; 42. Reducer; 43. Rotating shaft; 5. Driving rod mechanism; 51. Connecting rod; 52. Z-shaped end; 53. U-shaped protrusion; 6. Connecting end; 61. Second connecting hole. DETAILED DESCRIPTION
[0018] In order to make the purpose and advantages of the utility model more clear, the utility model is specifically described in combination with the following embodiments. It should be understood that the following text is only used to describe one or several specific implementations of the utility model, and does not strictly limit the protection scope of the specific request of the utility model.
[0019] like Figure 1 and 3 As shown, a control structure of a rudder surface of a model aircraft includes an outer shell 1 and a mounting frame 2 for mounting the outer shell 1, the mounting frame 2 is sleeved on the middle part of the outer side of the outer shell 1, the top end of the outer shell 1 is rotatably connected to a driving end head 3, the interior of the outer shell 1 is provided with a power mechanism 4 for driving the driving end head 3 to rotate, the driving end head 3 is symmetrically provided with a driving rod mechanism 5, one end of the driving rod mechanism 5 is rotatably connected to the driving end head 3, and the other end of the driving rod mechanism 5 is rotatably connected to a connecting end head 6.
[0020] According to the above structure, when in use, the driving end 3 is driven to rotate by the power mechanism 4, and two driving rod mechanisms 5 symmetrically arranged on the driving end 3 are pulled and pushed respectively. The connecting ends 6 at one end of the two driving rod mechanisms 5 are respectively fixedly installed on the two ailerons of the model aircraft, thereby pulling one aileron to rotate upward and pushing the other aileron to rotate downward, thereby realizing the turning flight of the aircraft. By driving the two ailerons to move at the same time through a power mechanism 4, components are saved, which not only saves manufacturing costs but also saves the overall weight of the model aircraft.
[0021] like Figure 1 and 3 As shown, the housing 1 includes a shell 11, both sides of the shell 11 are fixedly connected with connecting ears 12, the top of the shell 11 is fixedly connected with a supporting end 13, the mounting frame 2 includes a square sleeve 21 sleeved on the outside of the shell 11, both sides of the square sleeve 21 are fixedly connected with supporting ears 22 for supporting the connecting ears 12, and the bottom end of the supporting ear 22 is provided with a threaded tube 23.
[0022] According to the above structure, during installation, the mounting frame 2 is installed on the model aircraft, the shell 11 is inserted into the interior of the square sleeve 21, and then the connecting ear 12 and the supporting ear 22 are penetrated by screws to fix the connecting ear 12 and the supporting ear 22 together, so that the outer shell 1 is installed on the mounting frame 2, which is convenient for disassembly of the outer shell 1.
[0023] like Figure 2 and 3 As shown, the driving end head 3 includes a mounting cylinder 31, and a connecting plate 32 is fixedly connected to the side wall of the mounting cylinder 31. There are four connecting plates 32, and the four connecting plates 32 are symmetrically arranged in pairs. The surface of the connecting plate 32 is provided with a first connecting hole 33 for connecting the driving rod mechanism 5. The power mechanism 4 includes a forward and reverse motor 41 and a reduction box 42. The forward and reverse motor 41 and the reduction box 42 are both fixedly connected to the inside of the shell 11. The output shaft of the forward and reverse motor 41 is fixedly connected to the input end of the reduction box 42. The output end of the reduction box 42 is fixedly connected to a rotating shaft 43. The top of the rotating shaft 43 is rotatably connected to the supporting end 13 through a bearing. The mounting cylinder 31 is fixedly sleeved on the top of the rotating shaft 43.
[0024] According to the above structure, when turning, the forward and reverse motors 41 are started, and through the reduction transmission of the reduction box 42, the forward and reverse motors 41 drive the rotating shaft 43 to rotate at a low speed. After the rotating shaft 43 rotates, it drives the mounting tube 31 at the top of the rotating shaft 43 to rotate, and then drives the connecting plate 32 on the mounting tube 31 to rotate.
[0025] like Figure 1 and 2 As shown, the driving rod mechanism 5 includes a connecting rod 51, and both ends of the connecting rod 51 are integrally connected with Z-shaped ends 52, one of the Z-shaped ends 52 is rotatably connected inside the corresponding first connecting hole 33, and the other Z-shaped end 52 is rotatably connected to the connecting end 6, a U-shaped protrusion 53 is provided on the connecting rod 51, and a second connecting hole 61 for rotatably cooperating with the Z-shaped end 52 is opened on the top of the connecting end 6.
[0026] According to the above structure, after the installation tube 31 rotates, one of the connecting rods 51 is pushed and the other connecting rod 51 is pulled. The two connecting rods 51 push and pull the two connecting ends 6 respectively, thereby driving the two ailerons to rotate upward and downward respectively.
[0027] The working principle of the utility model is as follows: when in use, the driving end 3 is driven to rotate by the power mechanism 4, and two driving rod mechanisms 5 symmetrically arranged on the driving end 3 are pulled and pushed respectively, and the connecting ends 6 at one end of the two driving rod mechanisms 5 are respectively fixedly mounted on the two ailerons of the model aircraft, thereby pulling one aileron to rotate upward and pushing the other aileron to rotate downward, so as to realize the turning flight of the aircraft, and the two ailerons are driven to move at the same time by a power mechanism 4, which saves components, not only saves manufacturing costs, but also saves the overall weight of the model aircraft. When installing, the mounting frame 2 is installed on the model aircraft, the shell 11 is inserted into the interior of the square sleeve 21, and then Then, screws are passed through the connecting ear 12 and the supporting ear 22 to fix the connecting ear 12 and the supporting ear 22 together, so that the shell 1 is installed on the mounting frame 2, which is convenient for disassembling the shell 1. When turning, the forward and reverse motors 41 are started, and the forward and reverse motors 41 drive the rotating shaft 43 to rotate at a low speed through the reduction transmission of the reduction box 42. After the rotating shaft 43 rotates, it drives the mounting tube 31 at the top of the rotating shaft 43 to rotate, and then drives the connecting piece 32 on the mounting tube 31 to rotate. After the mounting tube 31 rotates, one of the connecting rods 51 is pushed and the other connecting rod 51 is pulled. The two connecting rods 51 push and pull the two connecting ends 6 respectively, thereby driving the two ailerons to rotate upward and downward respectively.
[0028] The above is only a preferred embodiment of the present invention. It should be noted that, for ordinary technicians in the technical field, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. The structures, devices and operating methods not specifically described and explained in the present invention shall be implemented according to the conventional means in the field unless otherwise specified and limited.
Claims
1. A control surface structure for a model aircraft, comprising a housing (1) and a mounting frame (2) for mounting the housing (1), characterized in that: The mounting frame (2) is sleeved on the middle part of the outer side of the housing (1); the top end of the housing (1) is rotatably connected to a driving end head (3); a power mechanism (4) for driving the driving end head (3) to rotate is arranged inside the housing (1); a driving rod mechanism (5) is symmetrically arranged on the driving end head (3); one end of the driving rod mechanism (5) is rotatably connected to the driving end head (3); and the other end of the driving rod mechanism (5) is rotatably connected to a connecting end head (6).
2. The control surface structure of a model aircraft according to claim 1, characterized in that: The housing (1) comprises a shell (11), both sides of the shell (11) are fixedly connected with connecting ears (12), and the top of the shell (11) is fixedly connected with a supporting end (13).
3. The control surface structure of a model aircraft according to claim 2, characterized in that: The mounting frame (2) comprises a square sleeve (21) sleeved on the outside of the housing (11), and support ears (22) for supporting the connecting ears (12) are fixedly connected to both sides of the square sleeve (21), and a threaded barrel (23) is provided at the bottom end of the support ear (22).
4. The control surface structure of a model aircraft according to claim 2, characterized in that: The driving end head (3) comprises a mounting tube (31), a side wall of the mounting tube (31) being fixedly connected to a connecting piece (32), four connecting pieces (32) being provided, the four connecting pieces (32) being symmetrically arranged in pairs, and a first connecting hole (33) for connecting to the driving rod mechanism (5) being provided on a surface of the connecting piece (32).
5. The control structure of the model aircraft rudder surface according to claim 4, characterized in that: The power mechanism (4) comprises a forward and reverse motor (41) and a reduction box (42); the forward and reverse motor (41) and the reduction box (42) are both fixedly connected inside the housing (11); the output shaft of the forward and reverse motor (41) is fixedly connected to the input end of the reduction box (42); the output end of the reduction box (42) is fixedly connected to a rotating shaft (43); the top of the rotating shaft (43) is rotatably connected to a support end (13) via a bearing; and the mounting cylinder (31) is fixedly sleeved on the top of the rotating shaft (43).
6. The control surface structure of a model aircraft according to claim 4, characterized in that: The driving rod mechanism (5) comprises a connecting rod (51), both ends of the connecting rod (51) being integrally connected with Z-shaped end heads (52), one of the Z-shaped end heads (52) being rotatably connected inside a corresponding first connecting hole (33), and the other Z-shaped end head (52) being rotatably connected to a connecting end head (6), and a U-shaped protrusion (53) being provided on the connecting rod (51).
7. The control structure of the model aircraft rudder surface according to claim 6, characterized in that: A second connection hole (61) for rotationally engaging with the Z-shaped end head (52) is provided at the top of the connection end head (6).