A power system integrating a split liquid-cooled heat dissipation module and its aircraft

Abstract

The invention discloses a power system integrating a split type liquid-cooling heat dissipation module, comprising a stator and a rotor; and a liquid-cooling system; the stator is provided with at least one liquid-cooling head; the liquid-cooling system comprises a liquid inlet pipe, The liquid outlet pipe, the driving pump and the cold discharge, the liquid inlet pipe is connected with the liquid inlet of the liquid cooling head, the liquid outlet pipe is connected with the liquid outlet of the liquid cooling head, and the liquid inlet pipe is far away from the liquid cooling head. One end and the end of the liquid outlet pipe away from the liquid cooling head are both connected to the cold row, and the driving pump is used to drive the cooling liquid in the cold row from the cold row through the liquid inlet pipe to the liquid cooling head and then through the liquid outlet pipe. Back to the cold row. The liquid passing through the liquid cooling system and the liquid cooling head of the present invention takes the heat from the inside of the motor to the cold exhaust placed in the propeller wake or outside the fuselage, and the cold exhaust is arranged in the propeller wake and passes through the high-speed wake of the propeller or the engine. The high-speed airflow outside the body exchanges heat with the cold exhaust to take away the heat.

Description

technical field [0001] The invention relates to the technical field of electric motors, in particular to a power system integrating split liquid cooling and heat dissipation modules and an aircraft thereof. Background technique [0002] The outer rotor brushless motor has large torque, high speed, low power consumption and low noise. Therefore, electric aircraft usually use external rotor brushless motors. Compared with aircraft powered by thermal engines, electric aircraft have less noise, are more concealed during military reconnaissance, and have higher survivability and mission success rate. Electric aircraft can be used in various fields such as military reconnaissance, environmental monitoring, emergency rescue and disaster relief. [0003] The existing external rotor brushless motors have the following problems: [0004] 1. The power density of the motor is getting bigger and bigger, and the heat dissipation problem is getting more and more serious; [0005] 2. Fo...

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Problems solved by technology

[0004] 1. The power density of the motor is getting bigger and bigger, and the heat dissipation problem is getting more and more serious;

[0005] 2. For the outer rotor brushless motor, there is already a design of adding a liquid cooling cavity inside the motor for heat dissipation, but the liquid cooling cavity is integrated with the stator, and is limited by the processing method. There is no inside the liquid cooling cavity Optimized Design Runner Features

[0006] 3. The current liquid cooling solution is mostly one-in and one-out flow channels. If large-diameter pipes are used, the space where the inlet and outlet are placed at the bottom of the motor is narrow and easy to interfere

If small-diameter inlet and outlet pipes are used, the flow rate must be very fast in order to ensure sufficient coolant flow. For liquid-cooled chambers without internal optimized flow channels, excessively fast flow rates will increase flow resistance and interfere with the flow of coolant. Heat transfer effect

[0007] 4. As the power of the motor driver increases, pure air cooling cannot meet the demand. The motor driver is more likely than the motor to reduce its lifespan or even be damaged due to excessive temperature.

[0008] 5. The current liquid cooling cycle heat dissipation scheme itself has no ability to regulate and control, and cannot be adjusted in real time according to the temperature of the power system itself and the atmospheric environment

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