Research On Aerodynamic Configuration Design Technology Of Horizontal Takeoff And Landing Hypersonic Launch Vehicle

Hypersonic vehicle has become the hot research spot of the world,and a plurality of hypersonic demonstrator vehicle had succeeded in flight test.It is necessary to carry out research on aerodynamic configuration design of hypersonic vehicle in this context,develop practical design method and build up design system.This paper focuses on the practical design method of hypersonic vehicle aerodynamic configuration,and applies the design method to actual design of hypersonic vehicle aerodynamic configuration.Firstly,in view of shortage compression problem of traditional waverider,a new design method for multistage compression waverider configuration is presented,which is based on osculating cone theory.In this design method,tilting the zero incidence flow around a cone(Taylor-Maccoll flow)to approach generating flowfield of the second stage and following stage compression in second-order accuracy,then using streamline tracing to acquire streamline in every osculating planes to generate multistage compression waverider,which has multiple compressive ramps to conduct shock waves compression towards incoming flow,and whose shock waves intersect on the bottom section.Multistage compression cone-derived waverider and osculating cone waverider are obtained by applying this design method to traditional design of cone-derived and osculating cone waverider.The multistage compression waverider design method is verified by numerical simulation and wind tunnel test.To solve the problems of aerodynamic heating of sharp leading edge and low plot rate,study on leading edge passivation and expansion upper surface met exponential function is made.Secondly,Hypersonic vehicle put forward higher requirement on integrated design,including the integrated design of forebody/inlet and afterbody/nozzle.An integrated configuration is considered by combining multistage compression waverider and Busemann inlet based on study of them.But they can not be connected because of the singular point of Taylor-Maccoll flow,which can be solved by adding a transition section between them.It is concluded that the integrated configuration has superior compression capability by comparing with three-stage compression waverider in the same design condition.The afterbody/nozzle integrated configuration is optimized through the combination of genetic algorithms and numerical simulation.The design softwares of Busemann inlet and nozzle optimization are obtained through C#,which achieve visualization parameter input and design.Thirdly,with the developmental aerodynamic configuration design methods of hypersonic vehicle,horizontal takeoff and landing hypersonic launch vehicle powered by TBCC and hypersonic cruise vehicle powered by scramjet are obtained.Aerodynamic performance of launch vehicle in the condition of hypersonic cruise and low speed takeoff is studied by numerical simulation.Simulation results show that,in hypersonic design state,three-stage compression cone-derived waverider forebody can make full use of multistage compression waverider's pre-compression capability.The flow coefficient of two inlets' entrance are 3.316 and 3.402,the total pressure recovery coefficient are 66.882% and 61.168% after the compression of waverider forebody,which provides good flow condition for scramjet.Three-stage compression cone-derived waverider forebody and wing are major components to generate lift both in the condition of hypersonic cruise and low speed takeoff.Numerical simulation results of these two vehicles show that the aerodynamic configuration design methods have been successfully applied to the design of hypersonic vehicle which reaches the expectation and performance.Cruise vehicle is brought by launch vehicle to the cruising speed and cruising altitude,and then separates from the launch vehicle.Numerical simulation analysis of the configuration combined by the two vehicles has been done,research on separation scheme at separation point has also been made.The cruise vehicle separates from the launch vehicle in the form of rising by lift,because it is loaded on the launch vehicle's back.An estimation method of separating trajectory is developed by using cruise vehicle's steady calculation states.Two design principles of rising type separation are got by calculation and analysis of different separation schemes' trajectory: first,the vehicle must be longitudinal static stable at given position of gravity;second,the mass of cruise vehicle can not be higher than the maximum mass allowed at this gravity.Finally,the whole research technology is summarized,and the further development direction of these design technology is discussed.