Design And Characteristic Simulation Of Thermoelectric Cooler System For Hypersonic Aircraft

The electronic equipment of hypersonic aircraft is facing more and more severe thermal environment challenge,and the electronic equipment is extremely sensitive to the working thermal environment temperature,so stabilizing the thermal environment of the electronic equipment is of great significance to ensure the operation of the equipment within its scope of application.Thermoelectric cooler technology has the advantages of small size,high efficiency and stable operation,and is widely used in aerospace technology,military,electronics and other fields.The application of thermoelectric cooler technology in the cooling of the chassis of airborne electronic equipment can provide a suitable working thermal environment for electronic equipment.Based on the basic theory of thermoelectric effect,the thermoelectric coupling theory model of thermoelectric cooler is established,and the importance of temperature correlation of material parameters to the accuracy of simulation results is analyzed.According to the actual working temperature of thermoelectric cooler,Bi₂Te₃ was selected as the material for thermoelectric cooler.By establishing the steady-state simulation and analysis model of thermoelectric cooler,the influences of input current,cold end load,hot end heat dissipation capacity and thermoelectric leg size on cold end temperature and refrigeration efficiency are obtained.The transient analysis results of thermoelectric cooler show that the response speed of cold end temperature is very fast,and the minimum value（supercooling effect）will be reached about 0.3s after the current is applied.The minimum value is greatly affected by the input current,cold end load and thermoelectric leg size.Through constructing the thermoelectric cooler system experimental platform to simulate the working condition of the practical application of thermoelectric cooler,thermoelectric cooling performance of the cooler are verified,respectively,under the condition of steady state and transient state to verify the input current,the cold end load of thermoelectric cooling capacity of the cooler,the influence of the speed of response,and simulated according to the experiment.Based on the thermal environment of the cabin of hypersonic aircraft and considering the operating environment and the input current range of the thermoelectric cooler,the input current,structure size and convection heat transfer coefficient of the thermoelectric cooler are optimized.