Research On Control Technology Of Turbojet Engine With Thrust Vectoring And Application

In this thesis, digital control system of Micro-turbojet engine with vectoring nozzle is studied,The working mechanism of micro-turbojet engine, control programs, control law, simulation platform,the implementation of digital control system and the engine used in the UAV system applications arediscussed. Firstly, based on the study of the engine working process, the component level all-variablemodel is established, in order to verify the model, digital simulation is researched, through it, engineperformance parameters affected by the nozzle deflection is analyzed. Then to meet the controlobjectives of the engine, considering the limitations of the environment of working process of theengine, the control laws are designed, and improved particle swarm algorithm is used to optimize theparameters of PID controller, the control law is confirmed through digital simulation. Toward to thegoals for the nozzle control, implementing agencies are selected, control method is designed. Themodel reference adaptive control method is introduced, Digital controller of Micro-turbojet enginewith vectoring nozzle is finished, including software and hardware design. Finally, the engine is usedin a UAV, and the semi-physical simulation test is designed. The simulation needs are analyzed, theoverall program design of simulation platform, hardware components and software are designed. TheUAV model with the thrust changed is established, the control law is designed according tocorresponding control loop. The viability of the Micro-turbojet engine with Vectoring nozzle used inUAV is confirmed by semi-physical simulation.With the broader outlook of micro-turbojet engine with vectoring nozzle, the results of this thesisare beneficial to control this type engine and its application on the UAV.