Study Of The Performance Of Micro Thermoelectric Conversion System For Aircraft

The aircraft in supersonic flight will bear a lot of aerodynamic heat energy.In this paper,the utilization of aerodynamic heat is taken as the research background,and the thermoelectric structure is used to convert the aerodynamic heat into the electric energy that can be used by the electronic equipment with small power consumption.Because the thermoelectric conversion is directly affected by the temperature environment,phase change temperature control structure is used to provide a stable temperature environment.In this paper,the mathematical model of micro thermoelectric conversion system is established,the expression of output power and conversion efficiency of thermoelectric conversion is derived,and the relationship between thermal conductivity of temperature control structure and power output of thermoelectric power generation module is calculated by programming.The finite element analysis software is used to study the parameters that affect the output power and conversion efficiency of the thermoelectric power generation module,including the three-dimensional structure size of the PN junction,the temperature environment of the power generation structure,etc.In order to provide a stable temperature environment,the thermal performance of temperature control structure in thermoelectric conversion system is studied.Through the establishment of the experimental platform of the micro thermoelectric conversion system,the thermoelectric conversion system experiments are carried out in different thermal environments,and the simulation results are compared and verified.Based on a certain supersonic vehicle,a micro thermoelectric conversion system is designed,which can work continuously and efficiently in the working cycle.Its main structure is about 40*40*15mm~3,and it can generate the maximum energy of 6k J in 1000s under ideal condition.