Control Law for the Air Inlet of a High Supersonic Velocity Aerial Vehicle

This paper aims to determine a control law for a supersonic air inlet, consisting of its spike positioning with respect to the flight Mach number, keeping in sight the necessity of a suitable parameters' distribution into engine's combustion chamber. Inlet's optimal architecture was determined (using an algorithm regarding the maximization of the total pressure recovery), based on planar geometry principles. Based the optimal geometry of the inlet, its flow rate characteristic and its control law were calculated and graphically represented. Possible control system architecture was also studied and evaluated from its quality point of view, by performing some simulations.