Optimization of Hypersonic Aircraft Fuel Thermal Management System Based on LQI-PSO

This paper addresses the challenges faced by the fuel thermal management system of hypersonic aircraft via a hybrid optimization strategy. The strategy aims to ensure that the fuel thermal management system meets heat dissipation requirements under different operating conditions. Establish four flow path first for the system. And then design optimal operating conditions for different flow paths and determine their boundary conditions. Third, determine flow paths according to different operating conditions, design the LQI-PSO algorithm, and optimize the system. The simulation shows that LQI-PSO optimization strategy significantly improves the stability of the fuel thermal management system. and the steady-state tracking error of the supply pipe fuel temperature is 0.6%, while the steady-state tracking error of the fuel temperature at the heat exchanger outlet is 1.69%.