Research On Integrated Flight/Propulsion System Modeling And Control

Integrated Flight/Propulsion control technology which used to meet the performance requirements for advanced aircraft design is one of the key technologies of a new generation fighter.It takes the aircraft and propulsion system as a whole object to study and deal with coupling effects between them. The aircraft's closed-loop control system would turn out to be an much better integrated flight system by improving the performance of propulsion system or taking other measures to coordinate the flight control system and propulsion control system.In this paper, Integrated Flight/Propulsion System's Controller design and optimization control are studied; According to this dissertation's contents, three parts are as follows:First of all, the real-time model of aircraft is established for Integrated Flight/Propulsion system's simulation. the aircraft model with six degrees of freedom is established; based on the original engine nonlinear component level model, the fan and compressor model are constructed of which the guiding vane can be adjusted, then the nonlinear component level model are better realized; according to the coupling relationship between the two models, the Plane model and the engine model are combined into the Integrated Flight/Propulsion model,and then Steady-state trimming and dynamic simulated calculation verifications are carried out for the Integrated Flight/Propulsion system's model .Secondly,An Integrated Flight/Propulsion Controller is designed. As the design thread of Flight/Propulsion control system, ADRC decoupling method and ALQR method are respectively applied to design the Integrated Flight/Propulsion Controller, and simulation verifications are also carried out; In addition, a least square method to divide the flight envelope for some engine's intermediate state control is proposed to solve low fuel selection principle.Finally Integrated Flight/Propulsion optimization control is studied in the use of SQP optimization algorithm and LP optimization algorithm. Mechanism and algorithm realization of maximum thrust optimization mode and minimum fuel consumption optimization mode are elaborated; simulation verifications are carried out in consideration of the design scheme of flight/propulsion optimization control of maximum thrust optimization mode in accelerating and climbing mission and minimum fuel consumption optimization mode in cruise mission.