A dual-mode hybrid aircraft battery thermal management system

Abstract

The disclosure provides a dual-mode hybrid aircraft battery thermal management system, including a battery pack, the battery pack includes a thermally conductive frame, a phase change component, at least one battery cell, and at least one heat pipe; fins are connected to the heat pipe; the heat pipe passes through the The phase change component is in contact with the phase change material in the phase change component; at least one cell installation slot and at least one heat pipe installation slot are provided on the heat conduction frame; each cell is correspondingly installed in a cell installation slot, and the electric The outer wall of the core is in contact with the inner wall of the cell installation groove; each heat pipe is correspondingly plugged into a heat pipe installation groove, and the outer wall of the heat pipe is in contact with the inner wall of the heat pipe installation groove. The battery thermal management system of this embodiment realizes the effective thermal management of the power battery through the phase change heat absorption of the phase change material and the air-cooled dual-mode thermal management scheme of the heat pipe connected to the fins, and can be applied to the power of the hybrid aircraft. on the battery.

Description

technical field [0001] The present disclosure relates to the field of battery heat management, and in particular to a battery pack and a dual-mode hybrid aircraft battery heat management system. Background technique [0002] When the power battery is working, it will release a lot of heat, and if the temperature is too high, the working efficiency of the battery will decrease or even fail to work normally. Therefore, it is usually necessary to design a corresponding heat dissipation system. At present, battery heat dissipation is mainly divided into air cooling and liquid cooling. Two, for electrical equipment with small power, air cooling can be used for heat dissipation, while for equipment with high power, air cooling is difficult to meet its heat dissipation requirements, and liquid cooling is usually required for heat dissipation, and liquid cooling needs to carry a large number of Cooling fluid, cooling motor, etc., resulting in a large weight. [0003] Since part of ...

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Problems solved by technology

[0004] First: Since the aircraft flies at high altitudes, it is different from the application environment of electric vehicles on the ground. The weight of the aircraft needs to be strictly controlled. Therefore, the weight of the power battery thermal management system is also strictly limited, and the liquid cooling system cannot be used;

[0005] Second: The air temperature is high when the aircraft is flying at low altitudes, and the power battery does not have a good cooling source, but due to weight restrictions, the refrigeration system cannot be used as a cooling source;

[0006] Third: Since the power battery of the aircraft often works under high-power and high-rate discharge conditions, it will generate high-power heat that needs to be dissipated, so it is impossible to dissipate the heat through the phase change material for a long time

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