| Abstract: | In order to ensure the aerodynamic characteristics of hypersonic aircraft at low Mach num-ber , variable geometry inlet control for hypersonic aircraft is studied. The movable lip cover of varia-ble geometry inlet for hypersonic aircraft is a lip cover which can move forward and backward in thedirection of the incoming flow and achieve the maximum airflow capture of the aircraft and improvethe performance of the propulsion system. Based on the analysis of the working principle of the varia-ble geometry inlet ,the longitudinal model of the hypersonic aircraft using the combined propulsionsystem is established, the multi-model switching control strategy and feasible control methods are discussed. ''The simulation results show that compared with the fixed inlet, the hypersonic aircraft withvariable geometry inlet technology needs less fuel equivalent ratio at low Mach number , which en-sures the aerodynamic characteristics of the hypersonic aircraft at low Mach number. |
