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Optimal design of launch vehicles is a complex multidisciplinary problem. The traditional way to optimize such vehicles is to decompose the problem into the different disciplines and to combine specific solvers and a global opti- mizer. This paper presents a new MDO method to optimize the configuration of an expendable launch vehicle and de- scribes the application of this method to the design optimization of a small liquid fueled multi-stage launch vehicle. The ob- jective is the payload mass maximization. The proposed bi-level method splits up the original MDO problem into the flight phases and optimizes concurrently the different stages of the launch vehicle. This transversal decomposition allows to re- duce the search domain at system-level because the optimization problem at this level is analog to a coordination one. Two formulations of the method are presented and the results are compared to the ones obtained by a standard MDO method.

Multidisciplinary Design Optimization of Multi-Stage Launch Vehicle using Flight Phases Decomposition