Integrated Modeling And Control For Tilt-Rotor Aircraft/Engine System

Different form helicopter and fixed-wing aircraft,the tilt-rotor aircrafts possess the properties of vertical takeoff and landing(VTOL),long-range voyage,so they are widely concerned today.As their propulsion system,turbo-shaft engines have the characteristics of powerful,hard to develop,etc.This dissertation focuses on the modeling of tilt-rotor aircraft and its turbo-shaft engine,and the integrated control of the overall system.First,the nonlinear mathematical model of the tilt-rotor aircraft was built.The components of the tilt-rotor aircraft was modeled including rotor system,wing,fuselage,horizontal tail and vertical tail.The rotor system was modeled based on blade element theory.The influences of the rotation of rotor and nacelle to the barycenter and inertia moment were taken into account.The flight dynamics model of the tilt-rotor aircraft was obtained by synthesizing each component together.The model can simulate the working state of the helicopter,tilting flight process and fixed-wing flight.The model of turbo-shaft engine was built too.The model includeds the sub-models of inlet,compressor,combustion,gas turbine,power turbine,nozzle and deceleration system.The power requirement and the pneumatic influence of the rotor were taken into account.The steady-state model was solved by Newton-Raphson algorithm,and the dynamic model was solved by single iteration algorithm.To solving the manipulation redundancy problem,the hybrid manipulation model of the tilt-rotor aircraft was built.The aircraft trim calculation was carried out at different flight speed under helicopter working state,tilting flight state and fixed-wing flight state.Compared with the results of GTRS and other literatures,the results show that the models of tilt-rotor aircraft and turbo-shaft engine built in this dissertation are in high accuracy and can be used as a basis for further studies.Last,the dynamic responses of aircraft and engine under different nacelle angles were studied and the results were analyzed qualitatively.The integrated control law of aircraft-engine was studied in helicopter state,tilting flight state and fixed-wing flight state.The research of this dissertation provides references for the modeling and control of the tilt-rotor aircrafts.