Multi-shaft target aircraft aileron control mechanism

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By designing a multi-axis target machine aileron control mechanism in the target machine and using a umbrella gear to achieve synchronous driving of the aileron, the problem of high cost of servo in the existing target machine is solved, and the effect of simplification of structure and cost reduction is achieved.

CN222438688UActive Publication Date: 2025-02-07HAINAN TIANKUN INVESTMENT PARTNERSHIP (LLP)

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Patent Information

Application Number: CN202421339912.7
Authority / Receiving Office: CN · China
Patent Type: Utility models(China)
Current Assignee / Owner
Filing Date: 2024-06-13
Publication Date: 2025-02-07
Estimated Expiration: 2034-06-13

AI Technical Summary

Technical Problem

The servo components in the existing target machines are costly and have complex structures, resulting in high manufacturing costs.

Method used

A multi-axis target machine aileron control mechanism is designed, and the rotation transmission of the servo output is realized through three bevel gears (first bevel gear, second bevel gear, and third bevel gear), and the first aileron and The second aileron reduces the number of servos and simplifies the structure.

Benefits of technology

This design reduces the number of servo machines used in the target machine, simplifies the structure, reduces manufacturing costs, while improving adaptability and commissioning ease.

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Abstract

The utility model relates to the technical field of target drones, in particular to a multi-shaft target drone aileron control mechanism which comprises a first wing, a second wing, a first aileron, a second aileron, a steering engine, a first shaft system and a second shaft system. The three bevel gears are adopted, rotation output by the steering engine is transmitted to the first shaft system and the second shaft system, then the first aileron and the second aileron are synchronously and reversely driven to rotate, the first shaft system or the second shaft system composed of the first rotating shaft, the second rotating shaft and the universal joint is adopted, and therefore the rotating speed is increased. The structure can adapt to the shape structure of a first wing or a second wing, by adopting the first shaft section, the second shaft section and the coupling sleeve used for separating / combining the first shaft section and the second shaft section, the first aileron and the second aileron can be conveniently debugged to be in the normal position, and it is further guaranteed that the first aileron and the second aileron synchronously and reversely rotate; the number of steering engines used in the target drone can be reduced, the structure of the target drone is simplified, and the manufacturing cost of the target drone is reduced.

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Description

Technical Field

[0001] The utility model relates to the technical field of target drones, in particular to an aileron control mechanism for a multi-axis target drone. Background Art

[0002] Target drones are a common and necessary means of training. At the same time, they are also consumable products. They are also developing towards low cost and simplification.

[0003] The servo component is a key component in the cost structure of the target drone. At the same time, since the production of the target drone itself is difficult and the production process is complicated, the cost of the servo used in the target drone is relatively high.

[0004] At present, most target drones still use two groups of steering gears to independently control two aileron control surfaces, which has the problem of high manufacturing cost. Therefore, the utility model provides a novel aileron control mechanism for a multi-axis target drone. Summary of the invention

[0005] The utility model aims to solve the shortcomings in the prior art and proposes a multi-axis target drone aileron control mechanism.

[0006] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0007] The aileron control mechanism of a multi-axis target drone comprises:

[0008] A first wing, wherein a first aileron is rotatably mounted at the tail of the first wing and close to the outer side;

[0009] A second wing, wherein a second aileron is rotatably mounted at the tail of the second wing and close to the outer side;

[0010] A steering gear, wherein the steering gear is fixedly mounted on the body of the target drone, and a first bevel gear is fixedly mounted on the output end of the steering gear;

[0011] A first shaft system, wherein the first shaft system is rotatably mounted with the first wing, a first end of the first shaft system is fixedly connected with the first aileron, and a second bevel gear is fixedly mounted on the second end of the first shaft system;

[0012] A second shaft system, wherein the second shaft system is rotatably mounted with the second wing, a first end of the second shaft system is fixedly connected with the second aileron, and a third bevel gear is fixedly mounted on the second end of the second shaft system;

[0013] The first bevel gear is meshed with the second bevel gear and the third bevel gear for transmission.

[0014] As a further description of the above technical solution:

[0015] The first shaft system includes: a first rotating shaft and a second rotating shaft. The first rotating shaft and the second rotating shaft are both rotatably mounted with the first wing, and one end of the first rotating shaft is connected to one end of the second rotating shaft through a universal joint transmission.

[0016] As a further description of the above technical solution:

[0017] The first aileron is connected to the first wing via a connecting ear, and a special-shaped plug is fixedly connected to one end of the second rotating shaft away from the universal joint, the special-shaped plug is inserted into the side of the first aileron, and the rotation center of the first aileron relative to the first wing coincides with the rotation center of the second rotating shaft.

[0018] As a further description of the above technical solution:

[0019] The second rotating shaft comprises: a first shaft section, a second shaft section and a coupling sleeve for coupling / discoviating the first shaft section and the second shaft section.

[0020] As a further description of the above technical solution:

[0021] The end of the first shaft segment is fixedly connected to a first polygonal segment, the first polygonal segment and the end of the first shaft segment form a step, the coupling sleeve is sleeved on the first polygonal segment, and an elastic sleeve is fixedly connected to one end of the coupling sleeve close to the step, the side of the second shaft segment is fixedly connected to a second polygonal segment, the second shaft segment is slidably connected to the coupling sleeve, and a polygonal hole corresponding to the second polygonal segment is opened on the inner side of the coupling sleeve.

[0022] As a further description of the above technical solution:

[0023] The transmission ratio of the first bevel gear to the second bevel gear is the same as the transmission ratio of the first bevel gear to the third bevel gear.

[0024] The utility model has the following beneficial effects:

[0025] 1. Compared with the prior art, the aileron control mechanism of the multi-axis target drone adopts three bevel gears (first bevel gear, second bevel gear, third bevel gear) to transmit the rotation output by the servo to the first axis system and the second axis system, thereby synchronously and reversely driving the first aileron and the second aileron to rotate. The application of this structure to the target drone can reduce the number of servos used in the target drone, simplify the structure of the target drone, and reduce the manufacturing cost of the target drone.

[0026] 2. Compared with the prior art, the aileron control mechanism of the multi-axis target drone can adapt to the shape structure of the first wing or the second wing by adopting a first axis system or a second axis system composed of a first rotating shaft, a second rotating shaft and a universal joint. The universal joint changes the transmission direction and can be adjusted according to the specific shape of the target drone, which has better practicality.

[0027] 3. Compared with the prior art, the aileron control mechanism of the multi-axis target drone adopts the first shaft section, the second shaft section and the coupling sleeve for clutching / engaging the first shaft section and the second shaft section, so as to facilitate the debugging of the first aileron and the second aileron in the positive position, and further ensure the synchronous and opposite rotation of the first aileron and the second aileron. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a three-dimensional schematic diagram of the utility model;

[0029] Figure 2 It is a three-dimensional schematic diagram of the first wing part of the utility model;

[0030] Figure 3 for Figure 2 A partial enlarged view in the middle;

[0031] Figure 4 It is a 1 / 4 cutaway stereoscopic view of the coupling sleeve position of the second rotating shaft of the utility model.

[0032] Legend:

[0033] 1. First wing; 2. Second wing; 3. First aileron; 4. Second aileron; 5. Servo; 6. First bevel gear; 7. First shaft system; 701. First rotating shaft; 702. Second rotating shaft; 7023. First shaft section; 7023a. First polygonal section; 7021. Second shaft section; 7021a. Second polygonal section; 7022. Coupling sleeve; 7022a. Elastic sleeve; 702b. Special-shaped plug; 703. Universal joint; 8. Second shaft system; 9. Second bevel gear; 10. Third bevel gear; 11. Connecting ear. DETAILED DESCRIPTION

[0034] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0035] Reference Figure 1-Figure 4 The multi-axis target drone aileron control mechanism provided by the utility model comprises: a first wing 1, a second wing 2, a first aileron 3, a second aileron 4, a steering gear 5, a first axis system 7, and a second axis system 8.

[0036] Like a traditional target drone, a first wing 1 and a second wing 2 are symmetrically mounted on both sides of the target drone, a servo 5 is fixedly mounted on the body of the target drone, the servo 5 is located between the first wing 1 and the second wing 2, a first aileron 3 is rotatably mounted at the tail of the first wing 1 and close to the outside, and a second aileron 4 is rotatably mounted at the tail of the second wing 2 and close to the outside.

[0037] In the utility model, a first bevel gear 6 is fixedly installed at the output end of the steering gear 5 , and a first shaft system 7 and a second shaft system 8 are designed.

[0038] The first shaft system 7 is rotatably mounted on the first wing 1, and the first end of the first shaft system 7 is fixedly connected to the first aileron 3, the second end of the first shaft system 7 is fixedly mounted with the second bevel gear 9, the second shaft system 8 is rotatably mounted on the second wing 2, and the first end of the second shaft system 8 is fixedly connected to the second aileron 4, the second end of the second shaft system 8 is fixedly mounted with the third bevel gear 10, and the first bevel gear 6 is meshed with the second bevel gear 9 and the third bevel gear 10 for transmission at the same time.

[0039] The rotating shaft of the first bevel gear 6 can be arranged vertically, and the rotating shafts of the second bevel gear 9 and the third bevel gear 10 can be arranged horizontally. The first bevel gear 6 and the second bevel gear 9 and the third bevel gear 10 are all at 90°. The first bevel gear 6 is directly driven by the steering gear 5 to rotate, and then the second bevel gear 9 and the third bevel gear 10 are synchronously driven to rotate. The second bevel gear 9 and the third bevel gear 10 are located on both sides of the first bevel gear 6, so that the second bevel gear 9 and the third bevel gear 10 rotate in opposite directions, driving the first shaft system 7 and the second shaft system 8 to rotate synchronously in opposite directions, and then driving the first aileron 3 and the second aileron 4 to rotate in opposite directions.

[0040] In this embodiment, the first axis system 7 and the second axis system 8 have the same structure, and their specific installation positions have been described above. The detailed structure of the first axis system 7 is described below, and the detailed structure of the second axis system 8 can obviously be understood.

[0041] In one embodiment, the first shaft system 7 includes: a first rotating shaft 701 and a second rotating shaft 702. The first rotating shaft 701 and the second rotating shaft 702 are both rotatably mounted with the first wing 1, and one end of the first rotating shaft 701 is transmission-connected with one end of the second rotating shaft 702 via a universal joint 703.

[0042] The rotation transmission between the first rotating shaft 701 and the second rotating shaft 702 can be realized by relying on the universal joint 703 , and the axes of the first rotating shaft 701 and the second rotating shaft 702 are not required to coincide, so that the structure of the first wing 1 can be adapted.

[0043] In one embodiment, if Figure 3 As shown, the first aileron 3 is connected to the first wing 1 through a connecting ear 11, and one end of the second rotating shaft 702 away from the universal joint 703 is fixedly connected with a special-shaped plug 702b, and the special-shaped plug 702b is inserted into the side of the first aileron 3. The special-shaped plug 702b has a non-circular cross-section and can well transmit rotation. The rotation center of the first aileron 3 relative to the first wing 1 coincides with the rotation center of the second rotating shaft 702, so that the second rotating shaft 702 drives the first aileron 3 to rotate.

[0044] In one embodiment, if Figure 4 As shown, the second rotating shaft 702 includes: a first shaft segment 7023 , a second shaft segment 7021 , and a coupling sleeve 7022 for coupling / discoving the first shaft segment 7023 and the second shaft segment 7021 .

[0045] Specifically, the end of the first shaft segment 7023 is fixedly connected to the first polygonal segment 7023a, the first polygonal segment 7023a and the end of the first shaft segment 7023 form a step, the coupling sleeve 7022 is sleeved on the first polygonal segment 7023a, and the end of the coupling sleeve 7022 close to the step is fixedly connected to the elastic sleeve 7022a, the side of the second shaft segment 7021 is fixedly connected to the second polygonal segment 7021a, the second shaft segment 7021 is slidably connected to the coupling sleeve 7022, and a polygonal hole corresponding to the second polygonal segment 7022a is opened on the inner side of the coupling sleeve 7022.

[0046] It is necessary to ensure that the first aileron 3 and the second aileron 4 rotate synchronously in opposite directions. Therefore, the relative positions of the first aileron 3 and the second aileron 4 should be adjusted during installation and debugging, such as Figure 1 As shown in FIG, the first aileron 3 and the second aileron 4 are both in the upright position.

[0047] Debugging process: the servo 5 drives the first shaft system 7 and the second shaft system 8 to rotate, so that the first aileron 3 and the second aileron 4 rotate. First, ensure that the first aileron 3 is in the normal position, and then manually operate the coupling sleeve 7022 to make the coupling sleeve 7022 squeeze the elastic sleeve 7022a. At this time, the polygonal hole inside the coupling sleeve 7022 is separated from the second polygonal segment 7021a; the servo 5 still drives the first shaft system 7 and the second shaft system 8 to rotate, but because the polygonal hole inside the coupling sleeve 7022 is separated from the second polygonal segment 7021a, the rotation of the first shaft system 7 cannot be transmitted to the first aileron 3. At this time, it can only drive the second aileron 4 to rotate. After the second aileron 4 rotates to the normal position, release the coupling sleeve 7022, and the coupling sleeve 7022 automatically returns to its original position under the action of the elastic sleeve 7022a.

[0048] In one embodiment, the transmission ratio between the first bevel gear 6 and the second bevel gear 9 is the same as the transmission ratio between the first bevel gear 6 and the third bevel gear 10, so that the second bevel gear 9 and the third bevel gear 10 rotate in the same manner.

[0049] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. Aileron control mechanism for a multi-axis target drone, including: A first wing (1), a first aileron (3) being rotatably mounted at the tail of the first wing (1) and close to the outer side; A second wing (2), a second aileron (4) being rotatably mounted at the tail of the second wing (2) and close to the outer side; It is characterized by further comprising: A steering gear (5), the steering gear (5) being fixedly mounted on a body of the target drone, and a first bevel gear (6) being fixedly mounted on an output end of the steering gear (5); A first shaft system (7), the first shaft system (7) being rotatably mounted on the first wing (1), and a first end of the first shaft system (7) being fixedly connected to the first aileron (3), and a second bevel gear (9) being fixedly mounted on a second end of the first shaft system (7); a second shaft system (8), the second shaft system (8) being rotatably mounted on the second wing (2), a first end of the second shaft system (8) being fixedly connected to the second aileron (4), and a third bevel gear (10) being fixedly mounted on the second end of the second shaft system (8); The first bevel gear (6) is meshed with the second bevel gear (9) and the third bevel gear (10) for transmission.

2. The multi-axis target drone aileron control mechanism according to claim 1, characterized in that: The first shaft system (7) comprises: a first rotating shaft (701) and a second rotating shaft (702); the first rotating shaft (701) and the second rotating shaft (702) are both rotatably mounted on the first wing (1); and one end of the first rotating shaft (701) is transmission-connected to one end of the second rotating shaft (702) via a universal joint (703).

3. The multi-axis target drone aileron control mechanism according to claim 2, characterized in that: The first aileron (3) is connected to the first wing (1) via a connecting ear (11), and an end of the second rotating shaft (702) away from the universal joint (703) is fixedly connected to a special-shaped plug (702b), the special-shaped plug (702b) is inserted into the side of the first aileron (3), and the rotation center of the first aileron (3) relative to the first wing (1) coincides with the rotation center of the second rotating shaft (702).

4. The multi-axis target drone aileron control mechanism according to claim 3, characterized in that: The second rotating shaft (702) comprises: a first shaft section (7023), a second shaft section (7021), and a coupling sleeve (7022) used for coupling / discoving the first shaft section (7023) and the second shaft section (7021).

5. The multi-axis target drone aileron control mechanism according to claim 4, characterized in that: The end of the first shaft segment (7023) is fixedly connected to a first polygonal segment (7023a), the first polygonal segment (7023a) and the end of the first shaft segment (7023) form a step, the coupling sleeve (7022) is sleeved on the first polygonal segment (7023a), and an end of the coupling sleeve (7022) close to the step is fixedly connected to an elastic sleeve (7022a), the side of the second shaft segment (7021) is fixedly connected to a second polygonal segment (7021a), the second shaft segment (7021) is slidably connected to the coupling sleeve (7022), and a polygonal hole corresponding to the second polygonal segment (7021a) is opened on the inner side of the coupling sleeve (7022).

6. The multi-axis target drone aileron control mechanism according to claim 1, characterized in that: The transmission ratio between the first bevel gear (6) and the second bevel gear (9) is the same as the transmission ratio between the first bevel gear (6) and the third bevel gear (10).