Detachable power modular electric rotor design

Abstract

The invention discloses a detachable power modular electric rotor wing, and relates to the field of design of multipurpose unmanned aerial vehicles. And the electric rotors and even groups of rotor fixing rod positioning holes are uniformly and symmetrically formed in the periphery of the machine body, so that plug-and-play connection is realized. The unmanned flying platform is formed by combining a plurality of modularized rotor wings and a machine body in a detachable connection mode, and a modularized battery, an electric adjusting system and the rotor wings form a whole to form a power system of the unmanned flying platform. The rotor wing fixing rod is of a cuboid box structure, one end of the rotor wing fixing rod can be connected with the positioning hole through a nut, and the other end of the rotor wing fixing rod is fixedly provided with a motor fixing groove; a motor with a proper size can be arranged in the motor fixing groove according to requirements, and a propeller is fixedly arranged on an output rotating shaft of the motor. According to the invention, more possibilities are provided for selection of rotor systems.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a detachable power modular electric rotor applied to a unmanned aerial vehicle, realizing a power modular multi-rotor unmanned aerial vehicle solution. Background Art

[0002] Rotary-wing UAVs are expanding their application areas due to their simple structure, strong maneuverability, and vertical take-off and landing. With the current major opportunities for the development of the low-altitude economy, UAVs will usher in a new upsurge in development, leading and driving the low-altitude economy to take off. Compared with traditional oil-powered UAVs, electric UAVs have the advantages of simple structure, low noise, low energy consumption, and environmental friendliness, and will have broader application prospects in the military and civilian fields.

[0003] Most of the existing multi-rotor UAVs are designed with the body and wings as one. In actual applications, it is usually necessary to select UAVs of different sizes and powers according to different work tasks, which increases the cost of purchasing the machines.

[0004] The existing design proposes to design the rotor independently, but it does not really achieve the electric rotor. The battery of the electric rotor is mostly installed in the fuselage. Even if the wing is modularly designed, it will inevitably need to change the line distribution when the wing is disassembled, which greatly increases the design and processing costs. In addition, since the current UAV power supply system is placed in the fuselage, the weight of the fuselage is increased, while the additional space of the fuselage is reduced. Especially for UAVs that need to carry loads, their load capacity is greatly reduced and the load space is occupied. Summary of the invention

[0005] In order to solve the above problems, the present invention proposes a detachable power modular electric rotor, which adopts a "plug and play" connection method between the electric rotor and the body, providing more possibilities for the selection of the rotor system.

[0006] The power modularized rotor UAV of the present invention comprises a power modularized rotor arm, a rotor connecting rod, an electric motor and a propeller.

[0007] The power modular rotor arm is a rectangular parallelepiped structure with a rectangular cross-section as a whole; the two opposite ends of the power modular rotor arm serve as the propeller mounting end and the arm connecting end respectively. Among them, a columnar channel is opened on the top surface of the propeller mounting end to fix the motor; the propeller is coaxially installed on the motor output shaft. A rotor connecting rod is coaxially installed at the center of the end surface of the arm connecting end; flanges are designed at both ends of the rotor connecting rod, and screws are used to fix the end flange of the rotor connecting rod to the end surface of the power modular rotor arm connecting end; the front flange of the rotor connecting rod is used to fix it to the main body of the drone by screws.

[0008] The interior of the powered modular rotor arm is designed with two chambers, namely the electric control system compartment and the battery compartment, which are used to install the electric control system and battery pack.

[0009] The advantages of the present invention are:

[0010] 1. The detachable power modular electric rotor of the present invention adopts a "plug and play" connection method with the body, which provides more possibilities for the selection of the rotor system. Users can choose drone bodies of different sizes according to the application scenarios, and then choose different numbers of motors and motors of different powers and blades of different sizes according to the weight of the body, so as to achieve one body corresponding to rotors of multiple powers.

[0011] 2. The detachable powered modular electric rotor of the present invention is assembled after optimizing the configuration of multiple monomers. The obtained unmanned aerial platform has the advantages of high lift-to-drag ratio, multi-function, good maintainability, etc., while also greatly reducing the cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is a schematic diagram of the overall structure of the detachable power modular electric rotor of the present invention;

[0013] Figure 2 This is a schematic diagram of the detachable power modular electric rotor electric adjustment system cabin of the present invention;

[0014] Figure 3 This is a schematic diagram of the detachable power modular electric rotor battery compartment of the present invention;

[0015] Figure 4 It is a schematic diagram of an unmanned aircraft configuration of a regular prism configuration using the detachable power modular electric rotor of the present invention;

[0016] Figure 5 It is a schematic diagram of a cross-configuration unmanned aircraft using the detachable power modular electric rotor of the present invention.

[0017] Figure 6 The figure is a schematic diagram of a fixed-wing unmanned aircraft configuration using the detachable power modular electric rotor of the present invention.

[0018] In the figure:

[0019] 1-Powered modular rotor arm 2-Rotor connecting rod 3-Electric motor

[0020] 4- Propeller 5- ESC system 6- Battery pack

[0021] 101- columnar channel 102- electric control system compartment 103- battery compartment

[0022] 104-openable and closable upper cover 105-openable and closable lower cover 106-heat dissipation hole DETAILED DESCRIPTION

[0023] The present invention is further described in detail below with reference to the accompanying drawings.

[0024] The detachable power modular electric rotor design of the present invention comprises a power modular rotor arm 1, a rotor connecting rod 2, an electric motor 3 and a propeller 4. Figure 1 shown.

[0025] The power modular rotor arm 1 is a rectangular parallelepiped structure with a rectangular cross section. The two opposite ends of the power modular rotor arm 1 serve as a propeller mounting end and an arm connection end, respectively.

[0026] Among them, a columnar channel 101 is opened on the top surface of the propeller installation end, and the axis of the columnar channel 101 intersects with the midline of the long direction of the top surface of the power rotor rotor arm 1. The columnar channel 101 is used for coaxial fixed installation of the motor 3, and the propeller 4 is coaxially installed on the output shaft of the motor 3. There can be one motor 3, and the output shaft can be set toward the top surface or bottom surface of the power modular rotor arm 1; there can also be two motors 3, and the output shafts are respectively set toward the top surface and bottom surface of the power modular rotor arm 1; the specific selection depends on the design scheme of the drone.

[0027] like Figure 2 , Figure 3 As shown, the interior of the power modular rotor arm 1 is designed with two chambers, namely the electric control system compartment 102 and the battery compartment 103, which are used to install the electric control system 5 and the battery pack 6; thereby achieving a modular design of the power system consisting of the circuit control system 5, the battery pack 6 and the electric motor 3, and is beneficial to reducing electromagnetic interference between the various parts, increasing the accuracy of the control module, and improving the performance of the aircraft.

[0028] The electric control cabin 102 is designed on the upper part of the power modular rotor arm 1, close to the position of the motor 3; the top surface of the electric control cabin 102 is equipped with an openable upper cover for sealing the electric control cabin 102; and after the openable upper cover 104 is closed, its surface and the top surface of the power modular rotor arm 1 form an integral plane. The battery compartment 103 is opened at the lower part of the power modular rotor arm 1, and the battery pack 6 is installed inside. Similarly, the bottom surface of the battery compartment 6 is equipped with an openable lower cover 105 for sealing the battery compartment 103; and after the openable lower cover 105 is closed, its surface and the bottom surface of the power modular rotor arm 1 form an integral plane. The electric control system 5 in the electric control cabin 102 is connected to the motor 3 through the wiring hole opened on the side wall of the electric control cabin 102; the electric control system 5 is connected to the battery pack 6 through the wiring hole opened on the bottom surface of the electric control cabin 102; at the same time, the signal line is connected to the flight control inside the body through the plug to achieve plug-and-play connection.

[0029] The battery pack includes a plurality of battery blocks connected in series in the battery compartment 103, and batteries of different powers and sizes can be replaced according to needs. A plurality of heat dissipation holes 106 are evenly spaced on the walls of both sides of the battery compartment 103 along the long direction of the power modular rotor arm 1, which can accelerate the heat dissipation capacity of the battery and reduce the battery power consumption, so as to avoid excessive power consumption caused by excessively high operating temperature of the battery.

[0030] The rotor connecting rod 2 is coaxially mounted at the center of the end face of the arm connection end. The rotor connecting rod 2 is a cylindrical rod with flanges at both ends, and is fixed by screws between the end flange of the rotor connecting rod 2 and the end face of the connection end of the power modular rotor arm 1. The front flange of the rotor connecting rod 2 is used to be fixed to the drone body by screws.

[0031] When the detachable power modular electric rotor of the above structure is applied to a UAV, the UAV body can be set into different shapes as needed. Two overall UAV configurations based on the detachable power modular electric rotor of the above structure are given below:

[0032] Configuration 1:

[0033] The UAV body is designed to have a regular prism structure or a cylindrical structure in cross section; mechanical arm connection positions are designed at equal angular intervals around the circumference, and a circle of threaded holes is opened at the mechanical arm connection positions, which are used to cooperate with the front end flange of the rotor connecting rod 2 of the power modular rotor arm 1 to connect the power modular rotor arm 1. In this way, the electric rotors can be installed at the connection positions at equal angular intervals around the UAV fuselage 1, so that the axis of the rotor connecting rod 2 in each electric rotor intersects at the center of the UAV body. The remaining arm connection positions are used as spare connection positions, and the number of electric rotors can be further expanded as needed. The electric rotors can also be disassembled as needed to reduce the number of electric rotors. Figure 4 As shown, a twelve-prism structure UAV body is shown, with six electric rotors evenly distributed around the circumference, which are respectively connected and fixed to the mechanical arm connection positions designed at the center position of the circumferential partition wall.

[0034] Configuration 2:

[0035] The UAV body adopts a cross-shaped structure, and the arm connection position is designed at the center of the four circumferential end faces. A circle of threaded holes is opened at the arm connection position for cooperating with the front end flange of the rotor connecting rod 2 of the power modular rotor arm 1 and fixing it with screws.

[0036] On the four circumferential branches of the cross-shaped UAV body, m groups of arm connection positions are further designed at equal intervals along the length of the branches. Each group of arm connection positions is located at corresponding positions on the left and right sides of the branch parts as spare connection holes, and electric rotors are added as needed.

[0037] Configuration three:

[0038] The UAV adopts a fixed-wing UAV, and multiple connectors are designed at equal intervals along the wing length direction under the wings on both sides, and the left and right positions of the connectors under the wings on both sides are symmetrical. An arm connection position is designed on the front and rear sides of each connector, and a circle of threaded holes is opened at the arm connection position, which is used to cooperate with the front end flange of the rotor connecting rod 2 of the power modular rotor arm 1 and fix it by screws. Thus, electric rotors can be installed on the front and rear sides of the connectors at corresponding positions on the wings on both sides to form a composite UAV, which maintains the advantages of fixed-wing flight speed, long flight distance, and high flight altitude, while combining the advantages of multi-rotor vertical take-off and landing. At the same time, multiple electric rotors can be selectively added according to different application environments.

[0039] In the above three configurations, an electric control system is installed in the electric control cabin 101 of the power modular rotor arm 1 of multiple electric rotors, which is connected to the flight control system inside the body, and the speed of the electric motor 3 is controlled by the flight control system.

[0040] The above three types of drones can increase or decrease the size and number of rotors according to the different weights of the drone body, different body structures, and different purposes of use. And the rotors can be installed in different positions according to needs, that is, the output shaft of the single motor 3 is selected to be upward or downward, or the output shafts of the dual motors 3 are selected to be set up one above and one below. At the same time, rotors with different powers or different blade diameters can be replaced. If the drone body is relatively light, or the load is small, a small number of electric rotors and electric rotors with smaller motor power, shorter propeller diameter, and smaller arm bearing capacity (small-sized electric rotors) can be used as power; when the drone body is relatively heavy, or the load is large, the small electric rotors can be removed and replaced with another set of rotors with larger motor power, longer propeller diameter, and larger arm bearing capacity (large-sized electric rotors), thereby truly realizing that one body corresponds to multiple rotors with different powers, while not increasing the weight of the fuselage, and not occupying the fuselage space, which can reduce the cost of production, and can also reduce the inconvenience caused by the need to purchase, store, and carry a large number of drones of different models when performing tasks. It can reduce production costs and also reduce the inconvenience caused by the need to purchase, store and carry a large number of drones of different models when performing tasks.

[0041] In the above three configurations of drones, in configuration one, the electric rotors at equal angular intervals in the circumferential direction can be replaced with smaller electric rotors; similarly, in configuration two, smaller electric rotors can be installed at the arm connection holes at the corresponding positions on the four branch parts ( Figure 4This is the case as shown); in configuration three, the electric rotors on the connectors at the corresponding positions on the left and right can be replaced with smaller electric rotors. As a result, large electric rotors can be installed on the drone to provide greater lift, which is suitable for application scenarios that require a larger load; at the same time, energy efficiency can be improved at low speeds; the small electric rotors installed on the drone provide the necessary lift during vertical takeoff and landing and hovering, and the flight state can be adjusted by controlling the attitude of the small rotors during flight to ensure flight stability and flexibility.

[0042] In summary, the detachable powered modular electric rotor of the present invention adopts an installation method of opening a threaded hole for connection, which makes the installation of the electric rotor simple, does not increase the weight of the whole machine, and has almost no effect on the aerodynamic performance of the whole machine, which is beneficial to energy saving of the UAV and improves its endurance.

[0043] Furthermore, since the designed rotor system has its own battery module, the operation of rewiring after replacing the rotor is eliminated, and the power system is truly modularized. At the same time, the battery and electric adjustment module are installed in the power modular rotor arm 1, which reduces the weight of the body and can increase other loads of the aircraft. Since the electric rotors are symmetrically distributed around the body, the center of gravity is on the propeller disc plane, and the torque formed by the resistance will cause the pitch angle of the multi-rotor drone to diverge, making the drone control more sensitive and more maneuverable, while reducing the resistance torque and making the aircraft more stable.

[0044] By proposing a modular power rotor system in the present invention, it is also possible to design unmanned aerial platforms of various structures under the inspiration of the three schemes proposed above, and add electric rotors of different sizes according to needs, truly realizing "plug and play" and greatly reducing manpower and material costs.

Claims

1. A detachable power modular electric rotor, characterized in that: It includes a powered modular rotor arm, rotor connecting rod, electric motor and propeller; The power modular rotor arm is a rectangular parallelepiped structure with a rectangular cross section as a whole; the two opposite ends of the power modular rotor arm serve as a propeller mounting end and an arm connection end respectively; The top surface of the propeller installation end is provided with a columnar channel to fix the motor; the propeller is coaxially installed on the motor output shaft; A rotor connecting rod is coaxially installed at the center of the end face of the arm connection end; flanges are designed at both ends of the rotor connecting rod, and the end flange of the rotor connecting rod is fixed to the end face of the power modular rotor arm connection end by screws; the front flange of the rotor connecting rod is used to fix it to the main body of the drone by screws; The interior of the powered modular rotor arm is designed with two chambers, namely the electric control system compartment and the battery compartment, which are used to install the electric control system and battery pack.

2. A detachable powered modular electric rotor as claimed in claim 1, characterized in that: There is one electric motor, and the output shaft faces the top surface or the bottom surface of the power modular rotorcraft arm.

3. A detachable powered modular electric rotor as claimed in claim 1, characterized in that: There are two electric motors, and the output shafts are respectively directed toward the top and bottom surfaces of the power modular rotorcraft arm.

4. A detachable powered modular electric rotor as claimed in claim 1, characterized in that: The electric control cabin is designed at the upper part of the power modular rotor arm, close to the motor; an openable and closable upper cover is installed on the top of the electric control cabin to achieve sealing of the electric control cabin; the battery cabin is opened at the lower part of the power modular rotor arm, and an openable and closable lower cover is installed on the bottom of the battery cabin to achieve sealing of the battery cabin; the electric control system in the electric control cabin is connected to the motor through the wiring holes opened on the side wall of the electric control cabin; the electric control system is connected to the battery pack through the wiring holes opened on the bottom of the electric control cabin; at the same time, the signal line is connected to the flight control inside the fuselage through a plug to achieve plug-and-play connection.

5. The detachable powered modular electric rotor as claimed in claim 1, characterized in that: The battery pack includes a plurality of battery blocks arranged in series in a battery compartment; a plurality of heat dissipation holes are arranged at equal intervals on the walls on both sides of the battery compartment along the arm length direction of the power modular rotorcraft.

6. The UAV with detachable power modular electric rotor as claimed in claim 1, characterized in that: According to the weight of the UAV body, choose electric rotors with different quantities, load-bearing capacities, motor powers, and propeller diameters for installation and replacement.

7. The UAV with detachable power modular electric rotor as claimed in claim 1, characterized in that: Electric rotors with different load-bearing capacities, motor powers, and propeller diameters are installed on the drone to provide lifts of different sizes. Large-sized electric rotors with large motor power and propeller diameters provide lift, while small-sized electric rotors with small motor power and propeller diameters assist in providing lift and adjusting flight attitude at the same time.

8. A UAV with detachable power modular electric rotor according to claim 1, characterized in that: The UAV body is designed with a cross-section of a regular prism structure or a cylindrical structure, and a mechanical arm connection position is designed at the center of each circumferential wall. A circle of threaded holes is opened at the mechanical arm connection position, which is used to cooperate with the front end flange of the rotor connecting rod of the power modular rotor arm to connect the power modular rotor arm; thus, the electric rotors are installed at connection positions at equal angles around the UAV fuselage, so that the axes of the rotor connecting rods in each electric rotor intersect at the center of the UAV body; the remaining arm connection positions are used as spare connection positions, and the number of electric rotors can be further expanded as needed.

9. A UAV with detachable power modular electric rotor according to claim 1, characterized in that: The UAV body adopts a cross-shaped structure, and arm connection positions are designed at the center positions of the four circumferential end faces. A circle of threaded holes is opened at the arm connection positions, which are used to cooperate with the front end flange of the rotor connecting rod of the power modular rotor arm and fix them through screws; on the four circumferential branches of the cross-shaped UAV body, m groups of arm connection positions are further designed at equal intervals along the long direction of the branches. Each group of arm connection positions is located at the corresponding positions on the left and right sides of the branch part as spare connection holes, and electric rotors are added as needed.

10. A UAV with detachable power modular electric rotor according to claim 1, characterized in that: The UAV adopts a fixed-wing UAV, and multiple connectors are designed at equal intervals under the wings on both sides along the wing length direction, and the left and right positions of the connectors under the wings on both sides are symmetrical; an arm connection position is designed on the front and rear sides of each connector, and a circle of threaded holes is opened at the arm connection position, which is used to cooperate with the front end flange of the rotor connecting rod of the power modular rotor arm and fix it by screws; thus, electric rotors are installed on the front and rear sides of the connectors at corresponding positions on the wings on both sides to form a composite UAV; electric rotors can be further added to multiple connectors as needed.

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