Simulation Research On Integrated Thermal Management Of Multi-electric Aircraft

With the development of aircraft multi-electricity,including electronic equipment,digitalization,intelligence and the integration of direct energy weapons,the heat load has increased rapidly;at the same time,the demand for combat radius of fighters has also increased,resulting in an increase in cruise speed.Brings a huge aerodynamic heat load;for fighter aircraft,the widely used and superior performance composite material structure will reduce the aircraft’s own heat dissipation capacity;for ram air heat sinks,excessive use will affect the aircraft’s stealth.Thermal management technology has become an increasingly severe challenge in aircraft design.The various systems of traditional aircraft are developed independently,and the ability to perform overall management analysis and optimization of heat is insufficient.Facing the increasing demand for integrated system optimization and full-cycle thermal management,this paper establishes a numerical model of the integrated thermal management system for multi-electric aircraft and performs overall performance analysis and optimization;then,through full-cycle transient calculations,the heat sink use to perform analysis,optimization and matching of the full flight profile.This article divides the integrated thermal management system into four working modes and introduces the system gas path and principle according to the multi-electric aircraft under different working conditions and states;then the main engine,power and thermal management of the integrated thermal management are introduced in detail.The system and fuel system are numerically modeled;the overall performance of the thermal management system is analyzed and optimized through the numerical model of the integrated thermal management system,and the thermal management system is calculated under the cooling mode cruise conditions including main engine thrust and ring Control cooling,power and other main parameters change with flight parameters;finally,based on the characteristic analysis of the system,this paper optimizes the bleed air volume coefficient and the shaft power extraction coefficient based on the multi-objective particle swarm optimization algorithm,so that the overall performance of the specific operating conditions Performance increased by 10.63%.This paper analyzes and calculates the heat generation,transformation and whereabouts of the aircraft under the entire typical flight profile.Through optimization of fuel flow and reasonable matching of heat sink,the utilization of heat sink of the integrated thermal management system is optimized.Perform heat sink matching analysis for different cruise Mach numbers.Through calculation,it is found that during the entire3000 s flight period,when the cruise Mach number is 1.6,fuel alone can provide sufficient heat sink;when the cruise Mach number reaches 1.8,it is necessary to match the fuel heat sink and the ram air heat sink.If the ram air is used at 2500 s,the thermal management needs can be well met.This paper also optimizes the fuel flow rate to increase the total utilization rate of the fuel heat sink by 23.5%.