Research On The Multidisciplinary Optimization Design Of The Wing Shape Of Suborbital Vehicle

As a new type of aircraft, the suborbital vehicle involved multiple disciplines. Theflight trajectory is strongly influenced by its aerodynamic characteristics of the wing. Itis an important task to design the shape of wing. The Multidisciplinary DesignOptimization was widely used in aerospace to solve the complex design problems. Thehigh precision analysis model and MDO can be integrated by the approximation modeltechnology which is an important research tool and working process of the aircraftMDO. In this paper, the advantages and disadvantages of each kind of model wasanalyzed, a method of approximation modeling based on adding points in the subspaceof DOE is proposed and applied in multidisciplinary design optimization of the wingshape.Firstly, the technology of aerodynamic analysis on wing shape is studied. A designmethod of CAD parametric modeling by Matlab and Pro/E on the wing shape ofsuborbital vehicle is proposed. The unstructured grids which is applied on CFD of wingis studied and it’s stypsis is validated.The aerodynamic capability of suborbital vehicleon landing is analyzed to make sure the angle of attack. The robotization of CAD andCFD is achieved based on the numerical analyze of the wing.Secondly, the Design of Experiments and approximation models are studied. Amethod of DOE based on adding points in the subspace is proposed and anapproximation modeling method based on the new DOE and Kriging is put forward.The advantage of this method is that the sample points will be increased which ispremised on precision. The convergency of model on prophase is improved. Themodeling method based on adding points in the subspace is applied on the aerodynamicheating of the stagnation point.Thirdly, the integrate technology of subject model is studied. The analyzesoftwares and the approximation modeling method based on adding points in thesubspace are integrated and applied on the approximation modeling of aerodynamicanalysis of wing. The aerodynamic optimization of wing shows that the approximationmodel is feasibility and high precision.Finally, Combined with trajectory, the quality of the wing structure and theaerodynamic capability of landing, the Collaborative Optimization is used to themultidisciplinary design optimization of wing shape of suborbital vehicle based on theIsight. The validity of the method of multidisciplinary design optimization on the wingshape is proved by the result.In the paper, the method of aerodynamic analysis on the wing shape of suborbitalvehicle, the technology of MDO and integration are studied. A method of approximationmodeling based on adding points in the subspace is proposed and applied on the aerodynamic heating of the stagnation point and the approximation modeling of wing. Itshows that the efficiency of modeling is improved. A basic processes and systemscheme of optimization design on the wing shape of suborbital vehicle which has somereference value for the wing design of suborbital vehicle is established.