Aircraft Supersonic Inlet with Dual Control System

摘要

The paper deals with an aircraft supersonic inlet with mixed compression, which has a dual control system, based on the inner total pressure's ratio preservation. The authors have identified the inlet's gas-dynamic behavior, as well as the main control and controlled parameters. One has also built the system's mathematical model, based on system's non-linear motion equations; furthermore, one has established, based on some simplifying hypothesis, the system's linear non-dimensional model, useful for further studies, as well as for some similar inlets' modeling. A system description based on block diagram with transfer functions was also realized. Some simulations were also performed, concerning the system's time behavior (step response), for different cases of control possibilities.