Parametric Numerical Analysis Of Asymmetric Secondary Jet Thrust Vectoring Nozzle

With the development of space and aviation technology,the technology of aircraft has developed rapidly,especially the development of thrust vectoring device has reached a new technical height.Traditional Technology has been difficult to meet the requirements of the present,the new jet thrust vector technology began to enter people’s vision,through the application of practice,has been recognized by everyone,and gradually become a new technology with more development advantages.In the process of size design and simulation analysis of thrust vectoring nozzle,because of the more factors affecting nozzle and the larger data,there are many repetitive operations in the process of modeling and simulation analysis,which increase the workload of the analyst,wasted a lot of time.In this context,this paper improves the jet thrust vectoring nozzle and carries out the parametric design of asymmetric secondary jet thrust vectoring nozzle.In order to reduce the modeling cycle and simulation analysis cycle of asymmetric secondary jet thrust vectoring nozzle,save time and cost,save the time of repeated operation software,and reduce the professional difficulty.In this paper,based on CFD(Gambit and Fluent),the finite element analysis of the asymmetric secondary jet thrust vectoring nozzle was carried out.By using VB,the software Fluent was redeveloped to write the numerical simulation analysis system of the asymmetric secondary jet thrust vectoring nozzle.It enables designers to design and analyze the asymmetric secondary jet thrust vectoring nozzle simply and conveniently,thus effectively reducing the period of the simulation analysis of the asymmetric secondary jet thrust vectoring nozzle.First of all,the background call of the grid and boundary conditions set Gambit explanatory scripting Journal document.As well as grid checking,turbulence model selection,boundary condition setting and discrete method selection of Fluent script Journal document.Secondly,the object-oriented friendly,convenient and quick man-machine interface and Visual program are written in Visual Basic language for the convenience of the analysts.Finally,by changing the designed mach number,the nozzle drop pressure ratio(NPR),the secondary flow pressure ratio(SPR)and the position of the secondary jet port,the comparison of contours of static pressure,contours of velocity magnitude and contours of mach number was obtained.Then summarize the influence of each structural parameter and thrust vector angle.The results show that the design mach number,the nozzle pressure ratio(NPR),the secondary flow pressure ratio(SPR)and the position of the secondary jet port have different effects on the thrust vector angle.