Integrated Design Of Aerodynamic And Propulsion For Air-breathing Hypersonic Vehicle

Hypersonic vehicle is a research hotspot in the field of aerospace at home and abroad.The integrated aerodynamic propulsion design is an effective means to ensure the proper working conditions of the scramjet in the design state for the aspirated hypersonic vehicle.Due to its design characteristics,the waverider not only has the characteristics of high lift-to-drag ratio,but also has the characteristics of convenient integrated design.In the two-dimensional multistage compression design,shock waves converge at the lip of inlet,which is similar to the design of waverider,but it cannot satisfy the design of waverider in the three-dimensional case.On the basis of this,a design idea of combined waverider based on the combination of a compression forebody and a waverider has been proposed in this paper,and its performance has been calculated and verified by means of numerical simulation.On this basis,a hypersonic vehicle has been designed by combining it with other components,and its aerodynamic characteristics under cold flow state are calculated and analyzed by means of computational fluid dynamics(CFD).For two dimension and intensity of shock wave and shock wave angle design such as forebody have been verified,and combined with the type ? waverider design have been studied,and aimed at the problems in the process of the processing.In this paper,the hypersonic leading edge passivation problem has been studied,and a solution to the location disturbance of first stage compression shock wave caused by detached shock wave has been proposed.The problem of strong and weak shock waves has beeen studied and a complete three-dimensional hypersonic vehicle has been designed.Calculate and verified the ? waverider design,a forebody of the designed by this paper has been verified by porter,calculated the typical multistage compression forebody of liquidity,and calculated the combination of multistage compression and type ? waverider forebody performance.The aerodynamic characteristics and flow characteristics of the three dimensional hypersonic vehicle designed in this paper have been calculated and analyzed respectively with the change of Mach number and angle of attackThe thrust and flow characteristics of the super-combustion engine under different conditions have been calculated,and the influences of oil-gas ratio and Mach number on engine performance and flow have been analyzed.The performance of the forebody designed in this paper has been not obvious when the surface Angle is small,but it has been better when combined with single-stage compression and larger surface angle.In the case of three-dimensional design,the design performance has been reached the position with the best aerodynamic performance at an angle of attack of about 6 degrees.In the non-design state,the supersonic inlet has been prone to backflow,leading to a sharp increase in drag and the inlet does not start.Therefore,the supersonic inlet in the non-design state should be closed.And the oil-gas ratio has a great influence on the engine performance under design condition.