A model of thermal management system (TMS) for hypersonic aircraft was designed based on single phase fluid circuit. Corresponding thermal control strategy and heat sink allocation model were presented for improving the cooling ability of heat sinks and solving the problem of lacking cold source. The thermal control strategy was implemented based on the algorithms of system identification and heat load forecast

and the thermal control model which aimed for overcoming the control delay caused by thermal inertia was optimized by adding an energy balance model and thermal feedback. Moreover

the heat sink allocation model based on heat sink cooling capacity evaluation and heat load matching was designed for higher usage of cooling source. Furthermore

MATLAB/Simulink was employed for testing TMS model and control strategy. Simulation work shows that: TMS model can meet the cooling requirement of hypersonic aircraft; current control model of smaller overshoot and higher decay rate is better than thermal feedback control model; the heat sink allocation model can obviously save cooling source in whole fly profile

further utilize various heat sinks more sufficient.