Aerodynamic Configuration Parameterization And Optimization Of Hypersonic Gliding Vehicle

Hypersonic flight vehicle has become the focused area of frontier research in aerospace field and it is unveiled gradually along with the test flight of several types of aircrafts.The parameterization and optimization of aircraft are of great importance during conceptual design stage.Class/Shape Function Transformation approach is a kind of accurate parametric method,which has been widely used in the parameterization and optimization work of 2-D airfoil,3-D wings,as well as multi-stage composite aircraft.This work made an improvement based on the study of traditional parametric method.The parametric accuracy of 2-D airfoil has been enhanced while the application range of 3-D parametric method has also been expanded.Based on the construction of surrogate model and the adoption of hybrid optimization strategy,this work obtained outstanding airfoil and conceptual configurations of hypersonic gliding vehicle.Traditional Class/Shape Function Transformation approach has bad accuracy in the two ends of airfoil when it was utilized in airfoil parameterization.This paper decreased the the maximum parametric error by changing the sampling method from linear function to tangent function.Numeric method has been used in the aerodynamic analysis of airfoil,and the grid independency has been analyzed.Based on NACA 0012,this paper established surrogate model and used MIGA and NLPQL optimization method to carry out airfoil design.The result shows that the polynomial based response-surface model is suitable to replace the original physical model with high accuracy.Besides,when the NLPQL method is combined with MIGA,the optimization result is better than these methods using separately.The Class/Shape Function Transformation approach is developed in three dimensional spaces.Traditional method only cared about the coupling item thus the edge of the described surface is limited on the XOY plane.This paper introduced an independent item in the normal direction so that the location of the surface's edge can also be controlled and the parametric range is enlarged.This paper applied three-dimensional parametric method to the modeling of hypersonic gliding vehicle with engineering method analyzing the aerodynamic performance.Finally,multi-objective optimization method is employed in the configuration design.It was founded that the Pareto front of the optimization result based on the refined parametric method is in front of the Pareto front based on the original three-dimensional CST method,which means that the refined method can find configurations with better performance than the original one.One of the configurations on the Pareto front has been analyzed and its aerodynamic performance has been studied by both panel method and CFD method.The results show that the obtained configuration owns outstanding aerodynamic properties.Hypersonic gliding vehicle may experience different airspaces as well as different speed environments.Based on the design theory of waverider,this paper put out with a novel design approach of gliding vehicle,which is accommodated in a wide range of speed.The parametric method employed in ascender line design makes it possible to control the overall configuration of the vehicle designed.Numerical results show that this kind of aircrafts own good wave-ride properties in the designed speed range.The aerodynamic performance of them makes a balance by comparing with the waveriders designed in the two ultimate speeds.Therefore,this kind of vehicles is worth referring in aircraft design.The simplified trajectory property analysis also shows that this kind of vehicles is suitable for long-distance attacking and tactical defense penetration.