# A General Integrated Method for Design Analysis and Optimization of Missile Structure
## 1 Introduction  
The research and manufacture of missile weapon system is a complicated systematic project, which involves many technical fields and departments. From the stage of design to mass production, it needs to undergo the processes of feasibility demonstration, program demonstration, preliminary design, sample design, design typification [1]. Generally speaking, the conceptual design of missile mainly relies on the personnel experience of engineering technicians, which is an iterative process that requires a serious amount of time and energy to obtain an optimal scheme, and the typical duration for a conceptual design activity is approximately a few months. Hence, realizing the rapid conceptual design of missiles will have extremely vital significance to improve the design efficiency of the missile, and shorten the production cycle. UG is a high-end software product for engineering solutions that includes CAD/CAE/CAM modules. Meanwhile, the UG system provides powerful secondary tools of UG/OPEN API, Menu Script and UISTyler development to customize user interface and application programs as needed. [PERSON] [2] presented a design tool, which was for the combustion chamber preliminary design, driven by the EXCEL database and generated by the UG software. [PERSON] et al. [3] developed an automated3D modeling program based on the UG secondary development technology, which has improved the modeling efficiency. [PERSON] et al. [4] used the technology of UG/KF secondary development for the automatic modeling of the wind turbine blades, and the aerodynamic characteristics of the impeller were analyzed by the Fluent software. Moreover, [PERSON] et al. [5] implemented the parametric modeling of the blended-wing-body underwater glider structure by using UG secondary development technology and studied its structural performance with ANSYS. Therefore, UG is considered as an excellent tool that can realize the integration of modeling and simulation. Meanwhile, airfoils have been parameterized in a wide variety of ways. Among them, CST is considered to be a more effective method, which can represent the different types of geometries in a generic way with fewer parameters. [PERSON] and [PERSON] [6] proposed a parameterization method that based on class and shape transformation functions, which has the advantages of high precision and fewer variables. The CST method is a powerful and versatile means to describe complex aeronautical shapes ranging from 2D airfoils to 3D geometries of aircraft using analytical functions. Since it has been introduced, this parameterization method has been the subject of several studies [7]. [PERSON] of the University of Michigan studied the characteristics of CST parameterization and found that the ill-conditioning of parameterization when fitting airfoil with high-order Bernstein polynomials [8]. [PERSON] et al. proposed a parameterization method that used a combination of Bernstein polynomials and B-splines to allow for both the local and global control of a shape, which is an extension to the Class-Shape-Transformation Method [9].Currently, for 3D wing geometries, the CST methodology is being widely used to drive aerodynamic optimization problems by using a full potential panel code, where the Euler solver being used for 2D airfoil optimizations [10; 11; 12; 13]. Moreover, in terms of structural optimization, plenty of research has been made, and various optimization strategies have been proposed. Presently, the surrogate model technique is promising due to the excellent computational accuracy and efficiency, especially for the practical engineering system with complex mapping functions [14; 15; 16; 17]. The existing surrogate models, for instance the Polynomial Regression, Radial Basis Functions, Kriging models, Support Vector Regression, and Polynomial chaos expansion, have their limitations. Therefore, the proposal of a high-efficiency and straightforward surrogate model will be beneficial for improving the efficiency and accuracy of computational response.