Inlet/Engine Integrated Multivariable Control Method

Aiming at the problem that the flow between inlet and engine is difficult to match at high angle of attack in subsonic maneuvering flight，resulting in large thrust loss of propulsion system，a multivariable inlet/en⁃ gine integrated control method is proposed. Based on the inlet/engine integration model，the common working equation of inlet/engine with auxiliary inlet valve is derived，and the common working principle is analyzed. The common working point position of inlet and engine is selected as the inlet feedback quantity and extended to the state quantity to ensure the flow matching between inlet and engine. In order to suppress the instantaneous loss of thrust caused by angle of attack and other factors，the inlet restriction protection link is added to the control loop to modify the control command，and the inlet/engine multivariable controller is designed based on H2/H∞ algo⁃ rithm. The full digital simulation verification experiments have been carried out on the engine nonlinear compo⁃ nent level model. The simulation results show that compared with the conventional inlet open-loop control struc⁃ ture，the proposed inlet/engine integrated multivariable control has good dynamic performance and less thrust loss under the change of angle of attack. © 2023 Journal of Propulsion Technology. All rights reserved.