Supersonic Inlet Control Design for Integrated Aero Propulsion during Supersonic Cruising State

抄録

In order to solve the supersonic inlet control problems during supersonic cruising state, an integrated model and inexact one-dimensional search algorithm are devised to design the inlet control law. An online inlet ramp angle mapping model is also proposed using recursive reduced least squares support vector regression and BP neural network methods. Finally, a proportional and integral (PI) controller is designed to control the inlet ramp. The simulation results indicated that an effective inlet ramp controller would greatly improve the engine installed performance and protect the engine from surge and other dangerous operations.