Thermal control device for external bearing cylinder aircraft battery pack

Abstract

The invention provides an outer bearing cylinder aircraft storage battery thermal control device which comprises a storage battery, an outer bearing cylinder and an instrument mounting plate, and also comprises an embedded heat pipe and a heat expanding plate, wherein the embedded heat pipe is connected with the instrument mounting plate and arranged on the bottom side of the storage battery, and the embedded heat pipe is used for warming the storage battery; the heat expanding plate is arranged on the instrument mounting plate and is used for gathering the heat of the storage battery and relieving heat dissipation; and the storage battery is connected with the instrument mounting plate by virtue of the heat expanding plate. The outer bearing cylinder aircraft storage battery thermal control device provided by the invention also comprises a temperature-controlled thermistor and an electric heater, wherein the temperature-controlled thermistor and the electric heater are pasted on the surface of the storage battery. According to the outer bearing cylinder aircraft storage battery thermal control device, the electric heater and the thermistor are arranged, so that the precise temperature control of a lithium-ion storage battery is realized.

Description

technical field [0001] The invention relates to a thermal control design of a spacecraft, in particular to a thermal control device for a lithium-ion storage battery pack of a bearing cylinder aircraft. Background technique [0002] The test target orbit of a certain type of aircraft needs to be able to adapt to the change of the descending node local time 6:30±30min and the orbit altitude of 500-800km. Large changes in orbital conditions lead to large changes in the heat flow conditions outside the aircraft. At the same time, the changeable operating modes of the aircraft cause large changes in the heat consumption of the entire aircraft. This requires the thermal control design of the aircraft to have high adaptability. The aircraft adopts a complex external load-bearing cylinder structure, and a single unit with high power consumption and high mass such as the power system power controller cannot be directly installed on the heat dissipation surface for temperature contro...

AI Technical Summary

Problems solved by technology

The structure of the outer bearing cylinder cannot directly install a single machine, and the thin-walled skin cannot be installed with heat pipes, and its own heat dissipation capacity is also small (the thin-walled skin is made of 5A90 aluminum-lithium alloy material, and its thermal conductivity at 20°C is 47.5W / (m·°C ); the thermal conductivity of the conventional heat expansion plate aluminum alloy 2A120 at 20°C is 183W / (m·°C)), this method cannot be applied to the aircraft with a complex configuration of the outer load-bearing cylinder structure, and the compensation power consumption is relatively high (conventional Satellite battery packs are generally equipped with three heaters, each with 30W, the aircraft battery pack is equipped with three heaters, two with 15W, and the third with 20W)

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