INVENT Surrogate Modeling and Optimization of Transient Thermal Responses

Abstract

A methodology is presented for optimization of transient thermal responses of an “Energy Optimized Aircraft” modeling and simulation environment. The increasing challenges of aircraft thermal management and complex systems integration require knowledge about transient thermal loads early in the design cycle. A previously developed “Tip-to-Tail” aircraft thermal model provides this capability, but it is difficult to efficiently optimize the aircraft design directly. A surrogate modeling approach is chosen based on its ability to rapidly predict subsystem temperatures over a mission. The aircraft thermal management system is then designed to minimize exceedance of the temperature limit. Nomenclature limit1 MSE = mean squared error of liquid-cooled avionics temperatures greater than or equal to the limit limit2 MSE = mean squared error of liquid-cooled avionics temperatures greater than the limit sp MSE = mean squared error of liquid-cooled avionics temperatures from the setpoint i T