Electric aircraft and mechanical drive electromechanical coupling cycle power generation system

Abstract

The invention discloses an electric aircraft and mechanical transmission electromechanical coupling cycle power generation system which is characterized by comprising an electric aircraft, a propeller of the electric aircraft is connected with a double-shaft driving motor through a transmission mechanism, the double-shaft driving motor is connected with a gearbox, and the gearbox is connected with a generator set through a transfer case. Electric energy generated by the generator set is transmitted to the integrated controller through the rectifier, the integrated controller is connected with a storage battery of the electric aircraft in parallel, and the generator set and the storage battery supply power to the electric aircraft simultaneously. Rotation power of the propellers of the electric aircraft is transmitted to the generator set for power generation, the generator set and the storage battery supply power to the electric aircraft at the same time, the charging frequency of the storage battery is reduced, and the cruising ability of the electric aircraft is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of mechanical transmission electromechanical coupling of electric aircraft, in particular to an electric aircraft and a mechanical transmission electromechanical coupling cycle power generation system. Background Art

[0002] In the existing low-altitude aircraft technology, the radio and electrical control systems are relatively complete, and the flight system has good stability and flexibility, but the only drawback is that the battery life is poor. Since the drone is equipped with a multi-rotor structure, multiple drive motors work at the same time and the speed is above 8000 to 10000. The high speed and high power consumption of multiple motors cause the battery power to be consumed too quickly, resulting in a rapid decline in the battery voltage difference and a voltage drop. The endurance time is too short. Whether the ordinary agricultural drone is under heavy load or no-load flight, the battery power will be consumed very quickly. The endurance is basically within tens of minutes. If the drone sprays pesticides, fertilizers, and lifts goods for a long time, it can only replace the battery repeatedly to charge it back and forth. Due to the frequent charging and replacement of the battery, the power connector wears out and causes poor contact, and the battery life is seriously reduced, affecting the working efficiency of the drone. Therefore, civil drones cannot meet various use environments and flight conditions such as long distances. Summary of the invention

[0003] The purpose of the present invention is to provide an electric aircraft and a mechanical transmission electromechanical coupling cycle power generation system, which can improve the service life and endurance of the battery of the electric aircraft, and is easy to install and economical.

[0004] The technical solution of the present invention is: an electric aircraft mechanical transmission electromechanical coupling cycle power generation system, including an electric aircraft, the propeller of the electric aircraft is connected to a dual-axis drive motor through a transmission mechanism, the dual-axis drive motor is connected to a gearbox, the gearbox is connected to a generator set through a transfer case, the electric energy generated by the generator set is transmitted to an integrated controller through a rectifier, the integrated controller is simultaneously connected in parallel to the battery of the electric aircraft, and the generator set and the battery simultaneously supply power to the electric aircraft.

[0005] The integrated controller is connected to a power control box of the electric aircraft.

[0006] The transmission mechanism comprises a bevel gear transmission box and a transmission shaft, and the rotating shaft of the propeller is connected to the dual-shaft motor through the bevel gear transmission box and the transmission shaft.

[0007] The transfer case is a bevel gear synchronous transfer case, and the gearbox is connected to more than two generators via the bevel gear synchronous transfer case.

[0008] The transmission mechanism comprises a planetary gear transmission, the rotating shaft of the propeller is connected to a dual-shaft outer rotor motor assembly, and the dual-shaft outer rotor motor assembly is connected to a magnetically suspended coreless generator via a planetary gear transmission.

[0009] An electric aircraft comprises the above-mentioned electromechanical coupling cycle power generation system.

[0010] Electric aircraft include electric drones, electric manned helicopters or electric unmanned helicopters.

[0011] When the electric aircraft is an electric drone with four, six or eight support arms, the electromechanical coupling cycle power generation system is installed on the support arms at four symmetrical balance points.

[0012] Beneficial effects of the present invention: The present invention utilizes the rotational power of the propeller of the electric aircraft to transmit to the generator set to generate electricity. The generator set and the battery simultaneously supply power to the electric aircraft, reducing the number of times the battery is charged and improving the endurance of the electric aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a schematic diagram of one structure of the mechanical transmission electromechanical coupling cycle power generation system of the present invention; Figure 2 A circuit control schematic diagram of the mechanical transmission electromechanical coupling cycle power generation system of the present invention; Figure 3 Another circuit control schematic diagram of the mechanical transmission electromechanical coupling cycle power generation system of the present invention; Figure 4 Another structural schematic diagram of the mechanical transmission electromechanical coupling cycle power generation system of the present invention; Figure 5 This is a schematic diagram of the installation of the present invention on a multi-arm electric drone; Figure 6 The figure is a schematic diagram of the installation of the present invention on a helicopter. DETAILED DESCRIPTION

[0014] The present invention will be further described below in conjunction with the embodiments, but they are not intended to limit the present invention. Example

[0015] An electric aircraft mechanical transmission electromechanical coupling cycle power generation system, such as Figure 1-6 As shown, it includes an electric aircraft, the propeller of the electric aircraft is connected to a dual-axis drive motor through a transmission mechanism, the dual-axis drive motor is connected to a gearbox, the gearbox is connected to a generator set through a transfer case, the electric energy generated by the generator set is transmitted to an integrated controller through a rectifier, and the integrated controller is simultaneously connected in parallel to the battery of the electric aircraft, and the generator set and the battery simultaneously supply power to the electric aircraft.

[0016] The integrated controller is connected to a power control box of the electric aircraft.

[0017] The transmission mechanism comprises a bevel gear transmission box and a transmission shaft, and the rotating shaft of the propeller is connected to the dual-shaft motor through the bevel gear transmission box and the transmission shaft.

[0018] The transfer case is a bevel gear synchronous transfer case, and the gearbox is connected to more than two generators through the bevel gear synchronous transfer case. When the electric aircraft is an electric manned helicopter or an electric unmanned helicopter, multiple generators can be selected to form a generator set.

[0019] Its working principle is that when the battery provides power to drive the dual-axis drive motor into the working state, one end of the drive shaft of the dual-axis drive motor drives the propeller to fly through the bevel gear transmission box, and the other end of the drive shaft is connected to the gearbox, clutch, and then connected to the generator set for electromechanical coupling power generation. In this electromechanical coupling power generation system, due to the high speed of the drive motor, the maximum speed of the output shaft through the gearbox is determined by the maximum speed parameter of the generator. The maximum speed ratio of the gearbox output shaft, the bevel gear transfer case, and the generator set is 1:1:1. In order to make the dual-axis drive motor more reliable and intelligent speed control, the dual-axis drive motor parameters are designed as DC motors, and the voltage is designed to be 400v to 1000v. The voltage and power parameters are selected according to the actual situation. In the power generation system, its characteristic is that as long as the dual-axis drive motor is running, it can generate mechanical energy to drive the power generation system. This electromechanical coupling technology can be set up with three generators as one generator set, or it can be one. It can use a magnetic levitation generator with light volume and high power generation efficiency, and the power parameters of each generator are set consistently. It adopts a power supply control system with parallel connection of generator sets, and the power supply voltage is 380V. When the generator sets are connected in parallel to generate electricity, the DC power supply matched with the battery after rectification by the rectifier is input in parallel to the integrated controller. The integrated controller is connected to the power control box to provide power for the aircraft. The purpose of this mechanical transmission electromechanical coupling cycle power generation system is to add a set of generator secondary distribution power supply while the battery power is consumed, forming a dual power supply mode with the original battery. In order to effectively control the stability of current and voltage, the two input ends of the integrated controller are connected in parallel with capacitors and then connected to the generator rectifier power supply, and then connected to the battery, which can control the voltage generated by the high-speed operation of the drive motor to rapidly drop, referred to as the battery voltage drop. When the helicopter is ready to take off, the same voltage and current are generated at both ends of the integrated controller at the same time, and the voltage drop of the battery will not drop rapidly, which effectively controls the rapid consumption of battery power, resulting in frequent replacement of batteries and increased charging times, thus greatly improving their lifespan and endurance cycle capabilities. In the electromechanical coupling power generation system, when the drive motor sets the DC motor voltage to 400V to 1000V, the power generation parameters of the magnetic levitation generator set should be set to 220V to 380V AC voltage, specifically matching the corresponding generator set with the actual power used by the drive motor. Example

[0020] An electric aircraft comprises the above-mentioned electromechanical coupling cycle power generation system.

[0021] Electric aircraft include electric drones, electric manned helicopters or electric unmanned helicopters.

[0022] like Figure 5 As shown, when the electric aircraft is an electric drone with four, six or eight support arms, the electromechanical coupling cycle power generation system is installed on the support arms of four symmetrical balance points. In the electromechanical coupling cycle power generation system, the transmission mechanism includes a planetary gear transmission, the rotating shaft of the propeller is connected to the dual-axis outer rotor motor assembly, and the dual-axis outer rotor motor assembly is connected to the magnetic levitation coreless generator through the planetary gear transmission. According to the use requirements, a magnetic levitation coreless generator with light weight, low speed, light torque and high power generation is used, and the gears and housing of the planetary gear transmission are made of aluminum alloy and other materials to reduce weight.

[0023] When this system is used for multi-arm electric drones, multiple dual-axis drive motors with DC voltages of 55V to 96V or above can be set. The specific motor power parameters should be set according to the flight load and usage conditions. The generator voltage is set to 220V to 380V, and the corresponding voltage and power parameters are set according to the drone load and usage conditions. Two transmission shafts are set at the upper and lower ends of the dual-axis drive motor. Four mechanical transmission electromechanical coupling power generation systems are set at four symmetrical points based on the premise that the drone has four, six, or eight support arms. Specifically, an AC magnetic levitation generator with light volume and high power generation efficiency is selected in each power generation system. The upper transmission shaft of the dual-axis drive motor is connected to the propeller, and the lower transmission shaft is connected to the planetary gearbox and the magnetic levitation generator for power generation. In this power generation system, when the drone enters standby operation, the upper transmission shafts of the four dual-axis drive motors drive the propellers to work, and the lower transmission shafts are connected to each magnetic levitation generator through the gearbox to generate electricity. The electricity generated by the four generators is all connected in parallel to the rectifier. After the output end of the rectifier is connected to the capacitor and the output end of the battery is connected to the capacitor, the two are then connected in parallel with the integrated controller. The output end of the integrated controller is connected to the power control box to transmit the electric energy to each drive motor controller.

Claims

1. An electromechanical coupling cycle power generation system for an electric aircraft mechanical transmission, characterized in that: It includes an electric aircraft, whose propeller is connected to a dual-axis drive motor through a transmission mechanism, the dual-axis drive motor is connected to a gearbox, the gearbox is connected to a generator set through a transfer case, the electric energy generated by the generator set is transmitted to an integrated controller through a rectifier, the integrated controller is simultaneously connected in parallel to the battery of the electric aircraft, and the generator set and the battery simultaneously supply power to the electric aircraft.

2. The electric aircraft mechanical transmission electromechanical coupling cycle power generation system according to claim 1, characterized in that: The integrated controller is connected to a power control box of the electric aircraft.

3. The electric aircraft mechanical transmission electromechanical coupling cycle power generation system according to claim 1, characterized in that: The transmission mechanism comprises a bevel gear transmission box and a transmission shaft, and the rotating shaft of the propeller is connected to the dual-shaft motor through the bevel gear transmission box and the transmission shaft.

4. The electric aircraft mechanical transmission electromechanical coupling cycle power generation system according to claim 3, characterized in that: The transfer case is a bevel gear synchronous transfer case, and the gearbox is connected to more than two generators via the bevel gear synchronous transfer case.

5. The electric aircraft mechanical transmission electromechanical coupling cycle power generation system according to claim 1, characterized in that: The transmission mechanism comprises a planetary gear transmission, the rotating shaft of the propeller is connected to a dual-shaft outer rotor motor assembly, and the dual-shaft outer rotor motor assembly is connected to a magnetically suspended coreless generator via a planetary gear transmission.

6. An electric aircraft, characterized in that: A mechatronic coupled cycle power generation system comprising any one of claims 1 to 5.

7. An electric aircraft according to claim 6, characterized in that: Electric aircraft include electric drones, electric manned helicopters or electric unmanned helicopters.

8. The electric aircraft according to claim 7, characterized in that: When the electric aircraft is an electric drone with four, six or eight support arms, the electromechanical coupling cycle power generation system is installed on the support arms at four symmetrical balance points.

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