Research On Integrated Flight/Propulsion Modeling And Control Method For Hypersonic Vehicles

The design of air-breathing hypersonic vehic les typically has a tightlyintegrated airframe and scramjet propulsion system, which include intricatecouplings between the aerodynamics and propulsion, the proplus ive efficience isaffected seriously by the flight state, on the other hand, the flight state is affected bythe engine. The great challenges are brought to the design of the guidance andcontrol system by the complex interplay. This paper take the scramjet-poweredhypersonic vehicles as research object, and the focus of the research is the modelingand control method for dealing with intricate couplings.Firstly, the coordinate system and their transform relationships are defined. Themotion equations are established based on the dynamic and kinematic characteristics,which lays the groundwrok for the successive research.Secondly, the integrated flight/propuls ion modeling method is studied. Theaerodynamic force and moment calculation method is derived with theoblique-shock/expansion theory, and the thrust and thrust moment calculationmethod is derived with the scramjet operational principle. On the basis of above all,the flight/propulsion coupling action mechanism is studied.Thirdly, the integrated flight/proplusion control method is studied. Thecontroller is designed for the couplings, which is also robust adaptive dealing withthe uncertainty.Finally, according to the requirements of the actual flight mission of thehypersonic vehicle, the six-DOF nonlinear vehicle modeling is simulated in severalsituations. The simulation results show that the controller can meet the requirementsof the stabilization and tracking performance.