Calculation of thermal load and impact factor analysis for hypersonic vehicle

Endothermal thermal protection system (TPS) and liquid N₂ heat sink were chosen to calculate the characteristics of thermal control system (TCS) in hypersonic vehicle. The methods of radiation balance and double lumped parameter were adopted to obtain the thermodynamic model of adiabatic layer and cabin air temperature. Therefore, aeroheating, adiabatic layer heat transfer and cabin air temperature were decoupled. On the basis of flight profile of X-34 hypersonic vehicle, the thermal load of avionics bay was calculated. Besides, the influence of adiabatic layer, cooling gas velocity and liquid N₂ amount on cabin air as well as the equipment temperature were analyzed. The results show that this method could get the response characteristics of heat transfer sections, which played an important part in the primary stage of hypersonic vehicle design.