Design of thermal control system for high-altitude and high-speed unmanned vehicle

According to design of thermal control system for UAV (unmanned aerial vehicles), which is characterized by small flight time-consumption, high speed, and quick change in altitude, thermal analysis and calculation methods which can be applied to practice engineering were put forward. Hot atmosphere, standard atmosphere and cold atmosphere were referred to as design conditions. In virtue of referring temperature, hypersonic engineering prediction or CFD (computational fluid dynamics) numerical simulation, surface temperature of vehicle was attained and taken as outer boundary conditions of thermal analysis mathematical model. Structure thermal capacity influence of the transitional thermal load was analyzed, and boundary equation was set up and solved by finite difference method. According to flight feature and transitional thermal load value, scheme of temperature adjusting system of electronic equipment cabin was presented.