An automated approach to multidisciplinary system design optimization of small solid propellant launch vehicles

Current methodology for multidisciplinary conceptual design optimization of expendable launch vehicles necessitates evaluation of a large number of different combinations. With existing codes, performance evaluation of all design combinations becomes very time consuming and restricts design space. Up to now, a commonly used solution to this problem has been the creation of approximation models such as, quadratic response surface equations and surrogating these models in automated design optimization cycle. However, the design space of multi-stages launch vehicles is highly nonlinear and cannot be adequately modeled by response surface approximation. In this paper, a fully automated approach for multidisciplinary system design optimization of small solid propellant launch vehicles is presented to improve design performance and reduce design cycle. Required codes were developed in homogenous environment.