Multidisciplinary design optimization applied to a sounding rocket

Abstract

Multidisciplinary design optimization (MDO) is an emerging discipline in aerospace engineering. In this paper, MDO is applied to RX-250-LPN- sounding rocket to optimize its performance. In the MDO of the referred vehicle, three fields have been considered - trajectory, propulsion and aerodynamics. A special design structure matrix is developed to assist data exchange among the fields. This design process uses response surface method (RSM) for multidisciplinary optimization of the rocket. RSM is applied to the design at two stages: propulsion model and the system level. In the propulsion model, RSM determines an approximate mathematical model of the engine output parameters as a function of design variables. At the system level, RSM fits a surface of objective
function versus design variables. Finally, an optimization method is applied to the response surface in the system level to find the best result. The application of the multidisciplinary design optimization procedure developed by us increased the accessible altitude (performance index) of the referred sounding rocket by 25%.