Paddle clamp mechanism adaptive to thickness of paddle and model airplane

Abstract

The utility model relates to a paddle clamp mechanism adaptive to the thickness of a paddle and a model airplane. The paddle clamp mechanism comprises a motor rotor, the paddle and a paddle clamp, the motor rotor and the paddle clamp are installed on a motor rotating shaft so as to rotate along with the motor rotating shaft, the paddle clamp is located on one side of the motor rotor, the position of the paddle clamp can be adjusted so that the distance between the paddle clamp and the motor rotor can be adjusted, a plurality of shaft rods are connected between the paddle clamp and the motor rotor, each shaft rod is provided with a paddle, and each paddle is clamped by the motor rotor and the paddle. And the blades are uniformly distributed around the motor rotating shaft as the center. According to the improved paddle clamp mechanism, the motor rotor is matched with the paddle clamp, the distance between the paddle clamp and the motor rotor is controlled by adjusting the position of the paddle clamp, and the paddle clamp mechanism can be compatible with paddles with different thicknesses. In addition, the blade clamp is limited on the motor rotating shaft through the compression spring positioning nut, and the blade clamp is high in stability and not prone to loosening. Meanwhile, the polytetrafluoroethylene gaskets are adopted to reduce friction force of the blades to facilitate opening and closing.

Description

Technical Field

[0001] The utility model relates to the technical field of model aircraft, especially the blade mounting method of model aircraft. Background Art

[0002] The blades on a model aircraft rotate under the control of a motor to achieve flight. Currently, the common blades are fixedly installed through upper and lower blade clips. This installation method is relatively rigid and usually can only install blades of a single thickness, so its applicability is not strong. Therefore, there is room for improvement in the blade installation of existing model aircraft. Summary of the Utility Model

[0003] The technical problem solved by the present disclosure is to provide an improved blade mounting mechanism and a model aircraft with such a mechanism.

[0004] The technical solution adopted by the utility model to solve its technical problems is: a blade clip mechanism adapted to the blade thickness, the blade clip mechanism includes a motor rotor, a blade, and a blade clip; the motor rotor and the blade clip are both installed on a motor rotating shaft and rotate therewith. The blade clip is located on one side of the motor rotor, and its position is adjustable to achieve the adjustment of the distance between it and the motor rotor. A plurality of shaft rods are connected between the blade clip and the motor rotor, and each shaft rod is installed with a blade. Each blade is clamped by the motor rotor and the blade clip and is evenly distributed around the motor rotating shaft.

[0005] For a blade clip mechanism adapted to the blade thickness as described above, the blade clip is provided with a central hole, which is passed through the motor rotating shaft through the central hole and is located outside the motor rotor. The motor rotating shaft is provided with an external thread, and a positioning nut is engaged with the external thread to abut against the outside of the blade clip. An elastic member is arranged between the motor rotor and the blade clip to generate a thrust on the blade clip.

[0006] For a blade clip mechanism adapted to the blade thickness as described above, the elastic member is a compression spring, and the compression spring is sleeved on the motor rotating shaft.

[0007] For a blade clip mechanism adapted to the blade thickness as described above, the blade clip is provided with three supporting feet, and each supporting foot is connected to the motor rotor by a shaft rod.

[0008] For a blade clip mechanism adapted to the blade thickness as described above, each blade can rotate along the corresponding shaft rod to realize the opening and closing of each blade.

[0009] For a blade clip mechanism adapted to the blade thickness as described above, gaskets are arranged between each blade and the motor rotor and the blade clip.

[0010] A paddle clip mechanism adapted to the thickness of the paddle as described above, wherein the gasket is made of polytetrafluoroethylene.

[0011] A model aircraft, which adopts the paddle clip mechanism as described in any one of the preceding items.

[0012] Advantages of the present disclosure: The improved paddle clip mechanism uses the cooperation of the motor rotor and the paddle clip to realize the installation of the paddle, and the installation position of the paddle clip can be selected to achieve the spacing between it and the motor rotor, so that the paddle clip mechanism can install paddles of different thicknesses, and the overall applicability is stronger. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Some specific embodiments of the present invention will be described in detail below in an exemplary and non-limiting manner. The same reference numerals in the drawings denote the same or similar components or parts. Those skilled in the art should understand that these drawings are not necessarily drawn to scale.

[0014] In the drawings:

[0015] Figure 1 is a schematic diagram of the paddle clip mechanism of the present invention (in the folded and closed state);

[0016] Figure 2 is an exploded view of the paddle clip mechanism of the present invention;

[0017] The reference numerals in the figure are explained as follows:

[0018] 1. Motor rotating shaft; 100. External thread; 2. Motor rotor; 200. Through hole; 3. Paddle clip; 300. Middle hole; 301. Support leg; 4. Paddle; 5. Shaft rod; 6. Locking nut; 7. Compression spring. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0019] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention.

[0020] Based on the described embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the scope of protection of the present invention. Unless otherwise defined, the technical terms or scientific terms used in the present disclosure shall have the ordinary meanings understood by those of ordinary skill in the art to which the present invention belongs.

[0021] As used in this disclosure, terms such as "first", "second" and the like do not denote any order, quantity or importance, but are merely used to distinguish different components. Similarly, terms such as "a", "an" or "the" do not denote a quantity limitation, but rather indicate the presence of at least one. Words such as "comprising" or "including" mean that the elements or items appearing before this word cover the elements or items listed after this word and their equivalents, without excluding other elements or items. Words such as "connected" or "coupled" are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. Words such as "upper", "lower", "left" and "right" are only used to indicate relative positional relationships, and when the absolute position of the object being described changes, the relative positional relationship may also change accordingly.

[0022] Refer to the attached Figure 1-2 , which shows a blade clamp mechanism adapted to the blade thickness. The blade clamp mechanism includes a motor rotor 2, a blade 4, and a blade clamp 3. The motor rotor 2 and the blade clamp 3 are both mounted on a motor shaft 1 and rotate therewith. The blade clamp 3 is located on one side of the motor rotor 2, and its position is adjustable to adjust the distance between it and the motor rotor 2. A plurality of shaft rods 5 are connected between the blade clamp 3 and the motor rotor 2. The blades 4 are mounted on each of the shaft rods 5. Each of the blades 4 is held by the motor rotor 2 and the blade clamp 3 and is evenly distributed around the motor shaft 1.

[0023] The blade 4 of the model aircraft is driven by a motor, and the output of the motor is realized by the motor shaft 1. In this embodiment, the motor rotor is fixedly mounted on the motor shaft 1, and the blade clamp 3 is also mounted on the motor shaft 1 at an appropriate position. The distance between the motor rotor 2 and the blade clamp 3 is adapted to the thickness of the blade 4 to be installed. A hole is provided at the inner end of the blade 4, and the shaft rod 5 between the motor rotor 2 and the blade clamp 3 passes through the hole at the inner end of the blade 4, and the blade 4 is clamped by the two.

[0024] There are various solutions to adjust the position of the blade clamp 3 on the motor shaft 1 to control the distance between it and the motor rotor 2. For example, there are positions with a preset interval on the motor shaft 1 that can cooperate with the blade clamp 3 for fixation. Usually, the blade clamp 3 can be moved to a selected position and then fixed with the help of other parts. The blade clamp 3 can also be adjusted in a stepless manner, and the adjustment of the distance is more precise. For example, the blade clamp 3 is connected to the motor shaft 1 through a threaded structure to adjust the distance after the blade clamp 3 and the motor rotor 2. The blade clamp 3 can be screwed along the thread to different positions to adjust the distance between it and the motor rotor 2.

[0025] In some embodiments, the blade clamp 3 is provided with a central hole 300, which is passed through the motor shaft 1 through the central hole 300 and is located on the outside of the motor rotor 2. The motor shaft 1 is provided with an external thread 100, and a positioning nut 6 cooperates with the external thread 100 to abut against the outside of the blade clamp 3. An elastic member is arranged between the motor rotor 2 and the blade clamp 3 to generate thrust on the blade clamp 3.

[0026] The motor rotor 2 can be processed by using existing materials, and the installation position of the shaft 5 can be set on it. Compared with the motor rotor 2, the blade clamp 3 is at the end away from the motor, and a middle hole 300 is set in the middle position, and the blade clamp 3 is inserted into the motor shaft 1 through the middle hole 300. An external thread 100 is set at the outer end of the motor shaft 1, and a positioning nut 6 with a threaded hole axially passing through is screwed along the external thread 100 until it abuts against the outer side of the blade clamp 3, while the inner side of the blade clamp 3 has a thrust from the elastic member. The two components are clamped and matched, so that the blade clamp 3 can be stabilized in a suitable position to reduce the probability of loosening.

[0027] In some embodiments, the elastic member is a compression spring 7, and the compression spring 7 is sleeved on the motor shaft 1. The compression spring 7 generates thrust on the blade clamp 3 with the motor rotor 2 as the fulcrum, and cooperates with the positioning nut 6 to strengthen the stability of the blade clamp 3 and prevent it from loosening.

[0028] In some embodiments, the blade clamp 3 is provided with three legs 301, and a shaft 5 is connected between each leg 301 and the motor rotor 2. A common aircraft mold has three blades 4, so the blade clamp 3 is provided with three legs 301, and a shaft 5 is respectively connected between each leg 301 and the motor rotor 2, and a blade 4 is installed on each shaft 5. Specifically, the shaft 5 can be a screw, which is screwed and fixed with the through hole 200 on the motor rotor 2 through a threaded structure, and then the blade 4 is installed on the shaft 5, and then the hole position on the leg 301 of the blade clamp 3 is tightly matched with the shaft 5.

[0029] In some embodiments, each blade 4 can rotate along the corresponding shaft 5 to open and close each blade 4. When working, the motor drives the blade 4 to rotate, and the blade 4 will be unfolded under the action of centrifugal force. When not in use, the blade 4 can be manually closed to reduce the occupied space.

[0030] Usually, a gasket is arranged between each of the blades 4 and the motor rotor 2 and the blade clamp 3, which is beneficial to the stability of the installation of the blades 4. Preferably, the gasket is made of polytetrafluoroethylene, which has a small friction force and is beneficial to the opening and closing of the blades 4.

[0031] Provided is an aircraft model, the aircraft model adopts a propeller clamp mechanism as described in any of the preceding items.

[0032] In summary, the improved paddle clip mechanism uses the motor rotor 2 and the paddle blade clip 3 in cooperation, and controls the distance between the paddle blade clip 3 and the motor rotor 2 by adjusting the position of the paddle blade clip 3, which can be compatible with paddle blades 4 of different thicknesses. In addition, the paddle blade clip 3 is restricted on the motor rotating shaft 1 by the compression spring 7 and the positioning nut 6, and has strong stability and is not easy to loosen. At the same time, a polytetrafluoroethylene gasket is used to reduce the friction of the paddle blade 4, facilitating its opening and closing.

[0033] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various changes, combinations and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the scope of the claims of the present invention.

Claims

1. A blade clamp mechanism adapted to the thickness of a blade, characterized by: The propeller clamp mechanism comprises a motor rotor, a propeller blade, and a propeller blade clamp; The motor rotor and the blade clamp are both installed on a motor shaft to rotate with it. The blade clamp is located on one side of the motor rotor, and its position is adjustable to achieve adjustment of the spacing between the blade clamp and the motor rotor. A plurality of shafts are connected between the blade clamp and the motor rotor, and the blades are installed on each of the shafts. Each blade is held by the motor rotor and the blade clamp, and is evenly distributed around the motor shaft as the center.

2. The blade clamp mechanism adapted to blade thickness according to claim 1, characterized in that: The blade clamp is provided with a central hole, through which it is passed through the motor shaft and is located on the outside of the motor rotor. The motor shaft is provided with an external thread, and a positioning nut cooperates with the external thread to abut against the outside of the blade clamp. An elastic member is arranged between the motor rotor and the blade clamp to generate thrust for the blade clamp.

3. The blade clamp mechanism adapted to blade thickness as claimed in claim 2, characterized in that: The elastic member is a compression spring, and the compression spring is sleeved on the motor shaft.

4. The blade clamp mechanism adapted to blade thickness as claimed in claim 3, characterized in that: The blade clamp is provided with three legs, and a shaft is connected between each leg and the motor rotor.

5. The blade clamp mechanism adapted to blade thickness as claimed in claim 4, characterized in that: Each of the blades can rotate along the corresponding shaft to achieve the opening and closing of each of the blades.

6. The blade clamp mechanism adapted to the thickness of the blade as claimed in claim 5, characterized in that: A gasket is arranged between each of the blades, the motor rotor and the blade clamp.

7. The blade clamp mechanism adapted to the thickness of the blade according to claim 6, characterized in that: The material of the gasket is polytetrafluoroethylene.

8. Model airplane, characterized by: The model airplane adopts the propeller clamp mechanism as described in any one of claims 1-7.

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