A rotor head structure of a single-rotor flybarless unmanned helicopter

Abstract

The invention discloses a rotor head structure of a single-rotor flybarless unmanned helicopter, belonging to the technical field of unmanned aerial vehicles, and comprises a rotor seat, a rotor blade clamp assembly and a flapping damper. The rotor seat is located below the rotor blade clamp assembly, the flapping damper is located in the middle of the rotor seat, the front end surface of the rotor blade clamp assembly is provided with three evenly distributed transverse holes, the middle parts of the three transverse holes are provided with a pull button piece structure, the rotor blade clamp assembly comprises two blade clamps, a rotor transverse axis is provided between the two blade clamps, bearings are provided on the left and right sides of the rotor transverse axis, pull button pieces are fixedly connected on the left and right sides of the rotor transverse axis, a bearing spacer is provided on the inner side wall of the bearing, and a pressure cover is provided above the rotor transverse axis. The rotor structure is simplified in form, the number of parts is reduced, the structural weight is reduced, the structural parts can operate flexibly and stably with each other, and in addition to meeting the functions required for flight, the rigidity and weight of the parts are in a good state.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to a rotor head structure of a single-rotor flybarless unmanned helicopter. Background Art

[0002] The main features of traditional UAVs with ailerons are that the aircraft attitude is relatively stable and easy to operate, but they have very high requirements for design, installation and debugging. Most of the existing domestic UAVs use a flybarless structure, whose main features are simple structure, low requirements for assembly and debugging, and simpler and more efficient debugging methods.

[0003] The rotor parts of existing single-rotor flybarless UAVs are mostly hard-connected, which can only meet the needs of low-load UAVs. For aircraft with a load of 200 kg, this simple waving structure cannot meet the requirements of stable flight of the aircraft. Summary of the invention

[0004] The present invention provides a single-rotor flybarless unmanned helicopter rotor head structure, aiming to solve the problem that the rotor parts of existing single-rotor flybarless UAVs are mostly hard-connected and can only meet the needs of low-load UAVs. For aircraft with a load of 200 kg, this simple waving structure cannot meet the requirements of stable flight of the aircraft.

[0005] The present invention is achieved in this way. A rotor head structure of a single-rotor flybarless unmanned helicopter comprises a rotor seat, a rotor blade clamp assembly and a flapping damper. The rotor seat is located below the rotor blade clamp assembly, the flapping damper is located in the middle of the rotor seat, the front end surface of the rotor blade clamp assembly is provided with three evenly distributed transverse holes, the middle parts of the three transverse holes are provided with a button piece structure, the rotor blade clamp assembly comprises two blade clamps, a rotor transverse axis is provided between the two blade clamps, bearings are provided on the left and right sides of the rotor transverse axis, button pieces are fixedly connected on the left and right sides of the rotor transverse axis, a bearing spacer is provided on the inner side wall of the bearing, a pressure cover is provided above the rotor transverse axis, bearing mounting holes are provided on the opposite sides of the two blade clamps, the bearing and the bearing spacer are both located in the bearing mounting hole, and mounting holes are provided on the front end surfaces of the two blade clamps.

[0006] In order to facilitate the installation of the rotor transverse axis above the rotor seat, as a preferred single-rotor flybarless unmanned helicopter rotor head structure of the present invention, two evenly distributed longitudinal mounting holes are opened through the middle of the rotor transverse axis, and the shapes of the two sides of the rotor transverse axis are "cylindrical".

[0007] In order to change the hardness of the polyurethane to adjust the flapping function of the rotor, as a preferred single-rotor flybarless unmanned helicopter rotor head structure of the present invention, the flapping damping includes a polyurethane sleeve and a cylindrical pin, the outer wall of the cylindrical pin is fixedly connected to the inner wall of the polyurethane sleeve, and the front end face of the cylindrical pin is provided with a baffle.

[0008] In order to facilitate the fixed connection between the rotor transverse axis and the rotor seat, as a preferred single-rotor flybarless unmanned helicopter rotor head structure of the present invention, the front end surface of the rotor seat is sequentially penetrated with a propeller clamp mounting hole and a flapping damping mounting hole from top to bottom, and the inside of the propeller clamp mounting hole and the flapping damping mounting hole are both provided with a shouldered copper sleeve, and the flapping damper is located in the flapping damping mounting hole.

[0009] In order to make the structural parts operate flexibly and smoothly with each other, as a preferred single-rotor flybarless unmanned helicopter rotor head structure of the present invention, the button plate structure includes a nut and a first screw, and the nut and the first screw are respectively located on the front and rear sides of the propeller clamp, and the outer wall of the nut is movably connected with a button plate fixing sleeve A, and the outer wall of the first screw is movably connected with a button plate fixing sleeve B.

[0010] In order to facilitate the fixing of the rotor seat and to fix the main shaft to the unmanned aerial vehicle body, a preferred single-rotor flybarless unmanned helicopter rotor head structure of the present invention is that the lower end face of the rotor seat is fixedly connected to the main shaft, a rotor main shaft mounting hole is opened through the left side of the rotor seat, a deep hole is opened in the middle of the upper end face of the rotor seat, and the lower end face of the deep hole is connected to the upper end face of the rotor main shaft mounting hole.

[0011] In order to facilitate the fixing of the pressure cover, as a preferred single-rotor flybarless unmanned helicopter rotor head structure of the present invention, two evenly distributed threaded holes are opened on the front and rear sides of the upper end surface of the rotor seat, and the upper end surface of the pressure cover is provided with four second screws matching the threaded holes.

[0012] Compared with the prior art, the present invention has the following beneficial effects:

[0013] 1. The rotor head structure of the single-rotor flybarless unmanned helicopter comprises a rotor seat, a rotor blade clamp assembly and a flapping damper. The connection between the rotor blade clamp assembly and the rotor seat adopts a concave-convex matching method. The pull-button sheet structure connects the hole above the rotor transverse axis with the blade clamp mounting hole above the rotor seat. The flapping damper connects the hole below the rotor transverse axis with the flapping damper mounting hole below the rotor seat, making the structure simple and efficient. The structure is convenient for assembly and disassembly, easy to use and maintain, and reduces the cost of use. The flapping damper is mainly composed of a polyurethane sleeve and a connecting cylindrical pin. The flapping function of the rotor is adjusted by changing the hardness of the polyurethane to increase the service life. The rotor blade clamp assembly comprises a blade clamp, a rotor transverse axis, a pull-button sheet structure and a bearing. The assembly is mainly composed of a pull-button The plate structure is the center, and there are three holes on the rotor transverse axis that are distributed horizontally. There are two mounting holes in the middle of the rotor transverse axis that are distributed in a vertical row. The two sides are cylindrical. There is also a mounting hole on the propeller clamp, and there is a bearing mounting hole at the end. The three correspond to the pull button plate structure passing through the inside of the rotor transverse axis. The middle pull button plate structure corresponds to the mounting hole on the rotor transverse axis. After the cylinders on both sides of the rotor transverse axis are assembled with bearings, the propeller clamps on both sides are installed in turn. The propeller clamp and the pull button plate structure are fixed with two parts that match concave and convex to form a propeller clamp assembly, which improves the adaptability of the aircraft and the flight control equipment and improves the reliability of use. The rotor structure is simplified, the number of parts is reduced, and the structural quality is reduced, so that the structural parts can operate flexibly and smoothly with each other. In addition to meeting the functions required for flight, the rigidity and weight of its parts are in a good state.

[0014] 2. The rotor head structure of the single-rotor flybarless unmanned helicopter has two evenly distributed longitudinal mounting holes through the middle of the rotor transverse axis, so as to facilitate the installation of the rotor transverse axis above the rotor seat, and the two sides of the rotor transverse axis are designed to be "cylindrical" so as to facilitate the installation of bearings on the left and right sides of the rotor transverse axis. The outer wall of the cylindrical pin is fixedly connected to the inner wall of the polyurethane sleeve, and the swinging function of the rotor is adjusted by changing the hardness of the polyurethane;

[0015] 3. The rotor head structure of this single-rotor flybarless unmanned helicopter is provided by sequentially penetrating a propeller clamp mounting hole and a flapping damping mounting hole from top to bottom on the front end surface of the rotor seat, and the propeller clamp mounting hole is provided. The pull button piece structure corresponds to the mounting hole in the middle of the rotor transverse axis and the propeller clamp mounting hole, so as to facilitate the fixed connection between the rotor transverse axis and the rotor seat, ensure that the structural parts of the rotor propeller clamp assembly can operate flexibly and stably with each other, and meet the flight requirements. Shouldered copper sleeves are provided inside the propeller clamp mounting hole and the flapping damping mounting hole, and the shouldered copper sleeves have wear-resistant properties, thereby increasing the service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a front view of a rotor head structure of a single-rotor, flybarless, unmanned helicopter of the present invention;

[0017] Figure 2This is a structural diagram of a rotor head structure of a single-rotor, flybarless, unmanned helicopter of the present invention;

[0018] Figure 3 This is an appearance diagram of the rotor base of the present invention;

[0019] Figure 4 This is an appearance diagram of the swing damping of the present invention;

[0020] Figure 5 It is a structural diagram of the rotor blade clamp assembly of the present invention;

[0021] Figure 6 This is an appearance diagram of the rotor blade clamp assembly of the present invention.

[0022] In the figure: 1. rotor seat; 101. main shaft; 102. rotor main shaft mounting hole; 103. propeller clamp mounting hole; 104. flapping damping mounting hole; 105. shouldered copper sleeve; 106. deep hole; 107. threaded hole; 2. flapping damping; 201. polyurethane sleeve; 202. cylindrical pin; 203. baffle; 3. rotor propeller clamp assembly; 301. propeller clamp; 302. rotor transverse axis; 3021. button piece; 3022. longitudinal mounting hole; 303. button piece structure; 3031. nut; 3032. button piece fixing sleeve A; 3033. button piece fixing sleeve B; 3034. first screw; 304. bearing; 3041. bearing spacer; 4. pressure cover; 401. second screw. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention 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 invention and are not intended to limit the present invention.

[0024] In the description of the present invention, it should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention 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, and therefore cannot be understood as limiting the present invention. In addition, in the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined.

[0025] See also Figure 1-6The present invention provides a technical solution: a rotor head structure of a single-rotor unmanned helicopter without ailerons, comprising a rotor seat 1, a rotor blade clamp assembly 3 and a flapping damper 2, wherein the rotor seat 1 is located below the rotor blade clamp assembly 3, the flapping damper 2 is located in the middle of the rotor seat 1, the front end surface of the rotor blade clamp assembly 3 is provided with three evenly distributed transverse holes, the middle of the three transverse holes are all provided with a button sheet structure 303, the rotor blade clamp assembly 3 includes two blade clamps 301, and a The rotor transverse axis 302 has bearings 304 on both sides thereof, and knob pieces 3021 are fixedly connected to both sides thereof. The inner wall of the bearing 304 is provided with a bearing spacer 3041, and a pressure cover 4 is provided above the rotor transverse axis 302. Bearing mounting holes are provided on the opposite sides of the two propeller clamps 301, and the bearing 304 and the bearing spacer 3041 are both located in the bearing mounting holes, and mounting holes are provided on the front end surfaces of the two propeller clamps 301.

[0026] In this embodiment: the rotor head structure of a single-rotor flybarless unmanned helicopter includes a rotor seat 1, a rotor blade clamp assembly 3 and a flapping damper 2. The connection between the rotor blade clamp assembly 3 and the rotor seat 1 adopts a concave-convex matching method. The button plate structure 303 connects the hole above the rotor transverse axis 302 with the blade clamp mounting hole 103 above the rotor seat 1. The flapping damper 2 connects the hole below the rotor transverse axis 302 with the flapping damper mounting hole 104 below the rotor seat 1, so that the structure is simple and efficient, and its structure is convenient for assembly and disassembly, easy to use and maintain, and reduces the cost of use. The flapping damper 2 is mainly composed of a polyurethane sleeve 201 and a connecting cylindrical pin 202. The flapping function of the rotor is adjusted by changing the hardness of the polyurethane to improve the service life. The rotor blade clamp assembly 3 includes a blade clamp 301, a rotor transverse axis 302, a button plate structure 303 and a bearing 304. The assembly is mainly composed of a button plate structure 30 3 is the center, and there are three holes on the rotor transverse axis 302 that are distributed horizontally. There are two mounting holes in the middle of the rotor transverse axis 302 that are distributed in a vertical row. The two sides are cylindrical. There is also a mounting hole on the propeller clamp 301, and a bearing mounting hole at the end. The three are correspondingly passed through the inside of the rotor transverse axis 302 by a pull button sheet structure 303. The middle pull button sheet structure 303 corresponds to the mounting hole on the rotor transverse axis 302. After the cylinders on both sides of the rotor transverse axis 302 are equipped with bearings 304, the propeller clamps 301 on both sides are installed respectively in turn. The propeller clamp 301 and the pull button sheet structure 303 are fixed with two parts of concave and convex matching to form a propeller clamp assembly, which improves the adaptability of the aircraft and the flight control equipment and improves the reliability of use. The rotor structure is simplified, the number of parts is reduced, and the structural quality is reduced, so that the structural parts can operate flexibly and stably with each other. In addition to meeting the functions required for flight, the rigidity and weight of its parts are in a good state.

[0027] As a technical optimization solution of the present invention, two evenly distributed longitudinal mounting holes 3022 are provided through the middle of the rotor transverse axis 302, and the shapes of the two sides of the rotor transverse axis 302 are "cylindrical".

[0028] In this embodiment: by opening two evenly distributed longitudinal mounting holes 3022 through the middle of the rotor transverse axis 302, it is convenient to install the rotor transverse axis 302 above the rotor seat 1, and the two sides of the rotor transverse axis 302 are designed to be "cylindrical" in shape, so that the bearings 304 can be easily installed on the left and right sides of the rotor transverse axis 302.

[0029] As a technical optimization solution of the present invention, the flapping damper 2 includes a polyurethane sleeve 201 and a cylindrical pin 202 , the outer wall of the cylindrical pin 202 is fixedly connected to the inner wall of the polyurethane sleeve 201 , and a baffle 203 is provided on the front end surface of the cylindrical pin 202 .

[0030] In this embodiment: the flapping damper 2 includes a polyurethane sleeve 201 and a cylindrical pin 202, and the flapping function of the rotor is adjusted by changing the hardness of the polyurethane.

[0031] As a technical optimization solution of the present invention, the front end surface of the rotor seat 1 is sequentially penetrated with a propeller clamp mounting hole 103 and a flapping damper mounting hole 104 from top to bottom, and the inside of the propeller clamp mounting hole 103 and the flapping damper mounting hole 104 are both provided with a shouldered copper sleeve 105, and the flapping damper 2 is located in the flapping damper mounting hole 104.

[0032] In this embodiment: by sequentially penetrating a propeller clamp mounting hole 103 and a flapping damping mounting hole 104 from top to bottom on the front end surface of the rotor seat 1, a propeller clamp mounting hole 103 is provided, and a button sheet structure 303 corresponds to the mounting hole in the middle of the rotor transverse axis 302 and the propeller clamp mounting hole 103, so as to facilitate fixed connection between the rotor transverse axis 302 and the rotor seat 1, thereby ensuring that the structural parts of the rotor propeller clamp assembly 3 can operate flexibly and stably with each other to meet flight requirements, and shouldered copper sleeves 105 are provided inside the propeller clamp mounting hole 103 and the flapping damping mounting hole 104, and the shouldered copper sleeves 105 have wear-resistant properties, thereby increasing service life.

[0033] As a technical optimization solution of the present invention, the button piece structure 303 includes a nut 3031 and a first screw 3034. The nut 3031 and the first screw 3034 are respectively located on the front and rear sides of the paddle clamp 301. The outer wall of the nut 3031 is movably connected with a button piece fixing sleeve A3032, and the outer wall of the first screw 3034 is movably connected with a button piece fixing sleeve B3033.

[0034] In this embodiment: the button piece structure 303 includes a nut 3031, a first screw 3034, a button piece fixing sleeve A3032 and a button piece fixing sleeve B3033. The button piece structure 303 corresponds to the mounting hole in the middle of the rotor transverse axis 302. After the cylindrical bearings 304 on both sides of the rotor transverse axis 302 are assembled, the propeller clamps 301 on both sides are installed respectively. The propeller clamps 301 and the button piece structure 303 are fixed with two parts that match concave and convex to form a propeller clamp assembly, so that the structural parts can operate flexibly and smoothly with each other.

[0035] As a technical optimization scheme of the present invention, the lower end face of the rotor seat 1 is fixedly connected to the main shaft 101, a rotor main shaft mounting hole 102 is opened through the left side of the rotor seat 1, a deep hole 106 is opened in the middle of the upper end face of the rotor seat 1, and the lower end face of the deep hole 106 is connected to the upper end face of the rotor main shaft mounting hole 102.

[0036] In this embodiment, the main shaft 101 is fixedly connected to the lower end surface of the rotor seat 1, thereby facilitating the fixing of the rotor seat 1, so that the main shaft 101 is fixedly connected to the drone body.

[0037] As a technical optimization solution of the present invention, two evenly distributed threaded holes 107 are provided on both the front and rear sides of the upper end surface of the rotor seat 1, and the upper end surface of the pressure cover 4 is provided with four second screws 401 matching the threaded holes 107.

[0038] In this embodiment: by setting four second screws 401 matching the threaded holes 107 on the upper end surface of the pressure cover 4, the pressure cover 4 is placed above the rotor horizontal axis 302, and the second screws 401 are rotated into the threaded holes 107, so as to facilitate fixing the pressure cover 4.

[0039] Working principle: First, the connection between the rotor blade clamp assembly 3 and the rotor seat 1 adopts a concave-convex matching method. The button plate structure 303 connects the hole on the rotor transverse axis 302 with the blade clamp mounting hole 103 on the rotor seat 1, and the flapping damper 2 connects the hole below the rotor transverse axis 302 with the flapping damper mounting hole 104 below the rotor seat 1, so that the structure is simple and efficient, and its structure is convenient for assembly and disassembly, easy to use and maintain, and reduces the cost of use. The flapping damper 2 is mainly composed of a polyurethane sleeve 201 and a connecting cylindrical pin 202. The flapping function of the rotor is adjusted by changing the hardness of the polyurethane to improve the service life. The rotor blade clamp assembly 3 includes a blade clamp 301, a rotor transverse axis 302, a button plate structure 303 and a bearing 304. The assembly is mainly centered on the button plate structure 303, and there are three holes on the rotor transverse axis 302. The rotor shaft 302 is laterally distributed with two mounting holes arranged in a vertical row in the middle, and the two sides are cylindrical. There is also a mounting hole on the propeller clamp 301, and a bearing mounting hole at the end. The three are correspondingly passed through the inside of the rotor shaft 302 by a pull button piece structure 303, and the middle pull button piece structure 303 corresponds to the mounting hole on the rotor shaft 302. After the cylindrical bearings 304 are assembled on both sides of the rotor shaft 302, the propeller clamps 301 on both sides are installed respectively. The propeller clamp 301 and the pull button piece structure 303 are fixed with two parts of concave and convex matching to form a propeller clamp assembly, which improves the adaptability of the aircraft and the flight control equipment and improves the reliability of use. The rotor structure is simplified, the number of parts is reduced, and the structural quality is reduced, so that the structural parts can operate flexibly and smoothly with each other. In addition to meeting the functions required for flight, the rigidity and weight of its parts are in a good state.

[0040] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A rotor head structure of a single-rotor flybarless unmanned helicopter, comprising a rotor seat (1), a rotor blade clamp assembly (3) and a flapping damper (2), wherein the rotor seat (1) is located below the rotor blade clamp assembly (3), and the flapping damper (2) is located in the middle of the rotor seat (1), characterized in that: The front end surface of the rotor blade clamp assembly (3) is provided with three evenly distributed transverse holes, and the middle parts of the three transverse holes are provided with a button plate structure (303). The rotor blade clamp assembly (3) comprises two blade clamps (301), a rotor transverse axis (302) is provided between the two blade clamps (301), bearings (304) are provided on the left and right sides of the rotor transverse axis (302), and button plates (3021) are fixedly connected to the left and right sides of the rotor transverse axis (302), a bearing spacer (3041) is provided on the inner side wall of the bearing (304), and a pressure cover (4) is provided above the rotor transverse axis (302), and bearing mounting holes are provided on the opposite sides of the two blade clamps (301), and the bearing (304) and the bearing spacer (3041) are both located in the bearing mounting hole, and mounting holes are provided on the front end surfaces of the two blade clamps (301); The flapping damper (2) comprises a polyurethane sleeve (201) and a cylindrical pin (202), the outer wall of the cylindrical pin (202) is fixedly connected to the inner wall of the polyurethane sleeve (201), and the front end surface of the cylindrical pin (202) is provided with a baffle (203); A propeller clamp mounting hole (103) and a flapping damper mounting hole (104) are sequentially penetrated through the front end surface of the rotor seat (1) from top to bottom, and a shouldered copper sleeve (105) is provided inside the propeller clamp mounting hole (103) and the flapping damper mounting hole (104), and the flapping damper (2) is located in the flapping damper mounting hole (104).

2. The rotor head structure of a single-rotor flybarless unmanned helicopter according to claim 1, characterized in that: Two evenly distributed longitudinal mounting holes (3022) are provided through the middle of the rotor transverse axis (302), and the shapes of the two sides of the rotor transverse axis (302) are cylindrical.

3. The rotor head structure of a single-rotor flybarless unmanned helicopter according to claim 1, characterized in that: The button plate structure (303) comprises a nut (3031) and a first screw (3034), wherein the nut (3031) and the first screw (3034) are respectively located at the front and rear sides of the paddle clamp (301), and the outer side wall of the nut (3031) is movably connected to a button plate fixing sleeve A (3032), and the outer side wall of the first screw (3034) is movably connected to a button plate fixing sleeve B (3033).

4. The rotor head structure of a single-rotor flybarless unmanned helicopter according to claim 1, characterized in that: The lower end surface of the rotor seat (1) is fixedly connected to a main shaft (101); a rotor main shaft mounting hole (102) is provided through the left side of the rotor seat (1); a deep hole (106) is provided in the middle of the upper end surface of the rotor seat (1); and the lower end surface of the deep hole (106) is connected to the upper end surface of the rotor main shaft mounting hole (102).

5. The rotor head structure of a single-rotor flybarless unmanned helicopter according to claim 1, characterized in that: Two evenly distributed threaded holes (107) are provided on both the front and rear sides of the upper end surface of the rotor seat (1), and four second screws (401) matching the threaded holes (107) are provided on the upper end surface of the gland (4).

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