A single-motor coaxial power system for unmanned aerial vehicles (UAVs) and the UAV itself.

Abstract

This invention discloses a single-motor coaxial power system for unmanned aerial vehicles (UAVs), including a motor with a steel shaft that rotates with the motor's rotor. An upper rotor mount mechanism for fixing the upper blade is located at the upper end of the steel shaft. A lower rotor mount assembly is mounted on the steel shaft at the lower end of the upper rotor mount mechanism. The lower rotor mount assembly includes a transmission mechanism and a lower rotor mount mechanism for fixing the lower blade. The transmission mechanism is mounted on the upper end face of the motor's rotor. The lower rotor mount mechanism is rotatably connected to the steel shaft. When the motor's rotor rotates, the transmission mechanism drives the lower rotor mount mechanism to rotate around the steel shaft. This invention achieves consistent upper and lower rotor speeds and opposite rotation directions, realizing direct-drive coaxial operation with a single motor. Compared to non-direct-drive output coaxial operation, it is smaller and lighter. Compared to single-blade operation, it increases thrust, improves maneuverability, enhances the linearity of the model aircraft, and reduces energy consumption.

Description

Technical Field

[0001] This invention relates to the field of motor technology, specifically to a single-motor coaxial power system for unmanned aerial vehicles (UAVs) and the UAV itself. Background Technology

[0002] Coaxial dual-rotor drones are smaller than single-rotor helicopters because they do not require a tail rotor to provide balancing torque; compared to multi-rotor aircraft, in addition to being smaller, they also have higher energy efficiency, and therefore they are increasingly occupying an important position in various application fields such as aerial photography and aerial surveillance.

[0003] Most existing drones are non-direct drive coaxial outputs. To achieve coaxial operation, dual motors need to be installed, which results in a large size and weight. Summary of the Invention

[0004] The problem to be solved by this invention is to provide a single-motor coaxial power system and a drone, in which the upper and lower propellers rotate at the same speed and in opposite directions, realizing direct-drive coaxial operation of a single motor. Compared with non-direct-drive output coaxial operation, it is smaller in size and lighter in weight; compared with single propellers, it increases thrust, improves maneuverability, makes the model aircraft more linear, and consumes less energy.

[0005] The technical solution provided by the present invention to solve the above problems is: a single motor coaxial power system for unmanned aerial vehicles, including a motor, wherein a steel shaft that can rotate with the rotor of the motor is provided on the motor;

[0006] The upper end of the steel shaft is provided with an upper blade holder mechanism for fixing the upper blade; a lower blade holder assembly is installed on the steel shaft at the lower end of the upper blade holder mechanism.

[0007] The lower propeller mount assembly includes a transmission mechanism and a lower propeller mount mechanism for fixing the lower propeller blade. The transmission mechanism is installed on the upper end face of the motor rotor, and the lower propeller mount mechanism is rotatably connected to the steel shaft. When the motor rotor rotates, the transmission mechanism drives the lower propeller mount mechanism to rotate around the steel shaft.

[0008] Preferably, the upper propeller seat mechanism includes an upper propeller seat and an upper propeller blade pressure plate, wherein the upper propeller blade pressure plate and the upper propeller seat are mounted on the steel shaft from top to bottom and rotate with the steel shaft.

[0009] Preferably, the upper end of the steel shaft is provided with a nut that is threadedly connected to the steel shaft, and the lower end face of the nut is in contact with the upper end face of the upper blade pressure plate.

[0010] Preferably, the upper end surface of the upper propeller seat is knurled to form an uneven mounting contact surface.

[0011] Preferably, the lower propeller seat mechanism includes a lower propeller seat and a lower propeller blade pressure plate. The lower propeller blade pressure plate and the lower propeller seat are rotatably mounted on the steel shaft from top to bottom, and the lower propeller blade pressure plate and the lower propeller seat are connected by bolts.

[0012] Preferably, the lower propeller seat is provided with a receiving hole, a bearing is provided in the receiving hole, the steel shaft mates with the inner ring of the bearing, and a retaining groove is provided on the steel shaft above the bearing, and a retaining spring for limiting the bearing is installed in the retaining groove.

[0013] Preferably, the transmission mechanism is a planetary gear mechanism.

[0014] Preferably, the planetary gear mechanism includes an internal gear ring, a planet carrier, and a plurality of planetary gears. The internal gear ring is mounted on the lower propeller base, the planet carrier is mounted on the upper end face of the motor rotor, the planetary gears are mounted on the planet carrier, and the internal gear ring meshes with the planetary gears for transmission.

[0015] Preferably, the steel shaft is also fitted with a shim sleeve to limit the axial movement of the lower propeller seat.

[0016] The present invention also discloses an unmanned aerial vehicle (UAV), including a single-motor coaxial power system for UAVs as described in any of the preceding claims.

[0017] Compared with the prior art, the advantages of the present invention are: the upper and lower blades of the present invention rotate at the same speed and rotate in opposite directions, realizing direct drive coaxial operation of a single motor. Compared with non-direct drive output coaxial operation, it is smaller in size and lighter in weight; compared with single blades, it increases thrust, improves maneuverability, makes the model aircraft more linear, and consumes less energy. Attached Figure Description

[0018] The accompanying drawings, which are provided to further illustrate the invention and constitute a part of this invention, are illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention.

[0019] Figure 1 This is a three-dimensional structural schematic diagram of the present invention;

[0020] Figure 2 This is an exploded structural diagram of the present invention;

[0021] Figure 3 This is a cross-sectional view of the present invention;

[0022] Figure 4 yes Figure 3 Enlarged view of point A in the middle;

[0023] Figure 5 This is a schematic diagram of the fit between the lower planetary support and the planetary gear.

[0024] The attached diagram is labeled as follows: 1. Motor, 2. Cross mount, 3. Lower planetary support, 4. Lower propeller holder, 5. Upper propeller pressure plate, 6. Bolt, 7. Lower propeller pressure plate, 8. Upper propeller holder, 9. Steel shaft, 10. Nut, 11. Shim sleeve, 12. Bearing, 13. Upper planetary support, 14. Internal gear ring, 15. Planetary gear, 16. Snap ring, 17. Washer. Detailed Implementation

[0025] The following will describe in detail the implementation of the present invention with reference to the accompanying drawings and embodiments, so that the process of how the present invention uses technical means to solve technical problems and achieve technical effects can be fully understood and implemented accordingly.

[0026] In the description of this invention, it should be noted that the directional terms such as "center", "lateral", "longitudinal", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", and "counterclockwise" indicate the orientation and positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. They should not be construed as limiting the specific protection scope of this invention.

[0027] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features. Thus, the use of "first" and "second" to define a feature may explicitly or implicitly include one or more of that feature, and in the description of this invention, "a number" means two or more, unless otherwise explicitly specified.

[0028] In this invention, unless otherwise explicitly specified and limited, the terms "assembly," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can also refer to a mechanical connection; they can refer to a direct connection or a connection through an intermediate medium; or they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0029] Example 1

[0030] A single-motor coaxial power system for an unmanned aerial vehicle (UAV) includes a motor 1, on which a steel shaft 9 is provided that can rotate with the rotor of the motor 1;

[0031] The upper end of the steel shaft 9 is provided with an upper blade holder mechanism for fixing the upper blade; a lower blade holder assembly is installed on the steel shaft 9 at the lower end of the upper blade holder mechanism.

[0032] The lower propeller mount assembly includes a transmission mechanism and a lower propeller mount mechanism for fixing the lower propeller blade. The transmission mechanism is installed on the upper end face of the rotor of the motor 1. The lower propeller mount mechanism is rotatably connected to the steel shaft 9. When the rotor of the motor 1 rotates, it drives the lower propeller mount mechanism to rotate around the steel shaft 9 through the transmission mechanism.

[0033] The above solution enables the upper and lower propellers of the drone to rotate at the same speed and in opposite directions, achieving direct drive coaxial operation of a single motor. Compared with non-direct drive coaxial output, it is smaller and lighter. Compared with single propellers, it increases thrust, improves maneuverability, makes the model aircraft more linear, and consumes less energy.

[0034] Specifically, the upper propeller seat mechanism includes an upper propeller seat 8 and an upper propeller blade pressure plate 5. The upper propeller blade pressure plate 5 and the upper propeller seat 8 are mounted on the steel shaft 9 from top to bottom and rotate with the steel shaft 9.

[0035] In the above scheme, the lower propeller seat is fixed in the following way: multiple bolt holes are evenly distributed on the circumference of the lower propeller seat, and grommets are installed in the bolt holes. A chamfered groove is provided on the steel shaft at the position corresponding to the grommets. The lower propeller seat can be fixed to the steel shaft by screwing the grommets into the chamfered groove on the steel shaft.

[0036] The upper end of the steel shaft 9 is provided with a nut 10 that is threadedly connected to the steel shaft 9, and the lower end face of the nut 10 is in contact with the upper end face of the upper blade pressure plate 5.

[0037] In the above scheme, by tightening the nut, the nut presses the upper blade pressure plate downward, thereby pressing the upper blade tightly.

[0038] In order to increase the friction between the upper propeller seat and the upper propeller blade and prevent the upper propeller blade from rotating relative to the upper propeller seat when rotating, the upper end surface of the upper propeller seat 8 is knurled to form an uneven mounting contact surface.

[0039] In this embodiment, specifically, the lower propeller seat mechanism includes a lower propeller seat 4 and a lower propeller blade pressure plate 7. The lower propeller blade pressure plate 7 and the lower propeller seat 4 are rotatably mounted on the steel shaft 9 from top to bottom, and the lower propeller blade pressure plate 7 and the lower propeller seat 4 are connected by bolts 6.

[0040] Specifically, in order to increase the friction between the lower propeller base and the lower propeller blade and prevent the lower propeller blade from rotating relative to the lower propeller base when rotating, the upper end surface of the lower propeller base 8 is knurled to form an uneven mounting contact surface.

[0041] Furthermore, the installation method of the lower propeller seat is as follows: a receiving hole is provided on the lower propeller seat 4, and a bearing 12 is installed in the receiving hole. The steel shaft 9 mates with the inner ring of the bearing 12. A retaining groove is provided on the steel shaft 9 above the bearing 12, and a retaining spring 16 for limiting the bearing 12 is installed in the retaining groove. In order to prevent the retaining spring from directly contacting the bearing, a washer 17 is also provided between the retaining spring and the bearing.

[0042] Specifically, such as Figure 3 and Figure 5 As shown, the transmission mechanism is a planetary gear mechanism. More specifically, the planetary gear mechanism includes an internal gear ring 14, a planet carrier, and several planetary gears 15. The internal gear ring 14 is mounted on the lower propeller mount 4, the planet carrier is mounted on the upper end face of the rotor of the motor 1, and the planetary gears 15 are mounted on the planet carrier. The internal gear ring 14 meshes with the planetary gears 15 for transmission. It should be noted that, in order to ensure the stability of the planet carrier when rotating with the rotor, a bearing is also installed on the planet carrier. The bearing is fitted onto the steel shaft of the motor, and the rotational engagement between the planet carrier and the steel shaft is achieved through the bearing.

[0043] In the above scheme, when the motor rotor rotates, the planetary gears and the internal gear ring mesh, causing the rotor to rotate and the planetary gears to rotate, which in turn drives the internal gear ring to rotate. The internal gear ring then drives the lower propeller mount to rotate around the steel shaft. In this embodiment, the planetary gear mechanism does not have a sun gear. If the sun gear were fixed to the steel shaft, tooth breakage would occur. However, in this scheme, the planetary carrier is mounted on the motor rotor. The motor rotor drives the planetary carrier to rotate, and the planetary gears on the planetary carrier drive the internal gear ring to rotate, which in turn drives the lower propeller mount mechanism to rotate around the steel shaft. This results in a more stable transmission and prevents tooth breakage.

[0044] More specifically, the planetary carrier includes a lower planetary support 3 and an upper planetary support 13, which are connected together by bolts. The lower planetary support is installed on the upper end face of the motor.

[0045] In this embodiment, it should be noted that the steel shaft 9 is also fitted with a shim sleeve 11 to limit the axial movement of the lower propeller seat 4, such as... Figure 3 As shown, the upper end face of the shim sleeve contacts and positions the lower end face of the inner ring of the bearing.

[0046] In this embodiment, a cross mounting bracket 2 is also provided at the lower end of the motor, through which the power mechanism is installed as a whole.

[0047] Specifically, the upper propeller base mechanism is directly driven to rotate via a steel shaft, while the lower propeller base mechanism is driven to rotate via a rotor that drives a planetary gear mechanism.

[0048] The specific installation process is as follows:

[0049] S1. Install the shim ring onto the steel shaft to limit the axial movement of the lower propeller seat;

[0050] S2. Then install the planetary lower bracket onto the motor body using 3 screws;

[0051] S3. Install the planetary gears on the lower planetary support and insert the shims;

[0052] S4. Install the planetary support and bearing together;

[0053] S5. Connect the installed lower planetary support to the upper planetary support and fix them with screws to form a planetary gear set.

[0054] S6. Install the bearing into the bearing hole of the planetary support (to prevent the lower propeller seat from wobbling and to make the rotation smoother).

[0055] S7. The internal gear ring is installed in conjunction with the lower propeller seat, and radial rotation of the internal gear ring is prevented by 15 pins.

[0056] S8. Connect the bearing to the lower propeller seat (through the meshing of the planetary gear set and the internal gear ring, after the rotor rotates, it drives the internal gear ring to rotate, causing the upper propeller seat and the lower propeller seat to move relative to each other).

[0057] S9. Insert the shim and use the snap ring to place it into the slot on the motor steel shaft to fix the lower propeller seat (to prevent the lower propeller seat from moving axially).

[0058] S10. The lower blade pressure plate is bolted into the threaded hole of the lower blade seat to fix the lower blade.

[0059] S11. The upper propeller seat is fixed by inserting it into the beveled groove of the steel shaft with 4 nut screws.

[0060] S12. The upper blade pressure plate is locked onto the motor steel shaft by a nut to fix the upper blade.

[0061] Example 2

[0062] This embodiment discloses a drone, including a single-motor coaxial power system for drones as described in any one of the embodiments in 1 above.

[0063] It should be noted that the remaining structural components of the UAV in this embodiment are existing technologies, and those skilled in the art can design them as needed. Therefore, they will not be described in detail in this embodiment.

[0064] The above description only illustrates the preferred embodiments of the present invention and should not be construed as limiting the scope of the claims. The present invention is not limited to the above embodiments, and variations in its specific structure are permitted. All modifications made within the scope of the independent claims of this invention are also within the scope of protection of this invention.

Claims

1. A single-motor coaxial power system for an unmanned aerial vehicle (UAV), comprising a motor (1), wherein a steel shaft (9) is provided on the motor (1) and is capable of rotating with the rotor of the motor (1); characterized in that: The upper end of the steel shaft (9) is provided with an upper blade holder mechanism for fixing the upper blade; a lower blade holder assembly is installed on the steel shaft (9) at the lower end of the upper blade holder mechanism. The lower blade assembly includes a transmission mechanism and a lower blade mounting mechanism for fixing the lower blade. The transmission mechanism is installed on the upper end face of the rotor of the motor (1). The lower blade mounting mechanism is rotatably connected to the steel shaft (9). When the rotor of the motor (1) rotates, the lower blade mounting mechanism is driven to rotate around the steel shaft (9) through the transmission mechanism. The lower propeller seat mechanism includes a lower propeller seat (4) and a lower propeller blade pressure plate (7). The lower propeller blade pressure plate (7) and the lower propeller seat (4) are rotatably mounted on the steel shaft (9) from top to bottom. The lower propeller blade pressure plate (7) and the lower propeller seat (4) are connected by bolts (6). The lower propeller seat (4) is provided with a receiving hole, and a bearing (12) is provided in the receiving hole. The steel shaft (9) is engaged with the inner ring of the bearing (12). A slot is provided on the steel shaft (9) at the upper part of the bearing (12). A retaining ring (16) for limiting the bearing (12) is installed in the slot. The transmission mechanism is a planetary gear mechanism without a sun gear; The planetary gear mechanism includes an internal gear ring (14), a planet carrier, and several planetary gears (15). The internal gear ring (14) is mounted on the lower propeller base (4). The planet carrier is mounted on the upper end face of the rotor of the motor (1). The planetary gears (15) are mounted on the planet carrier. The internal gear ring (14) meshes with the planetary gears (15) for transmission. When the rotor of the motor (1) rotates, it drives the planetary carrier to rotate. When the planetary gear (15) and the internal gear ring (14) mesh, the rotor rotates and the planetary gear rotates, which in turn drives the internal gear ring (14) to rotate. Finally, the internal gear ring (14) drives the lower propeller seat (4) to rotate around the steel shaft (9).

2. The single-motor coaxial power system for a UAV according to claim 1, characterized in that: The upper propeller seat mechanism includes an upper propeller seat (8) and an upper propeller blade pressure plate (5). The upper propeller blade pressure plate (5) and the upper propeller seat (8) are mounted on the steel shaft (9) from top to bottom and rotate with the steel shaft (9).

3. The single-motor coaxial power system for a UAV according to claim 2, characterized in that: The upper end of the steel shaft (9) is provided with a nut (10) that is threadedly connected to the steel shaft (9), and the lower end face of the nut (10) is in contact with the upper end face of the upper blade pressure plate (5).

4. The single-motor coaxial power system for a UAV according to claim 2, characterized in that: The upper surface of the upper propeller seat (8) is knurled to form an uneven mounting contact surface.

5. The single-motor coaxial power system for a drone according to claim 1, characterized in that: The steel shaft (9) is also fitted with a shim sleeve (11) to limit the axial movement of the lower propeller seat (4).

6. An unmanned aerial vehicle (UAV), characterized in that: Including a single-motor coaxial power system for unmanned aerial vehicles as described in any one of claims 1-5.

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