Mathematical Problems in Engineering
Volume 2011 (2011), Article ID 145692, 18 pages
Research Article

Robust Design Optimization of an Aerospace Vehicle Prolusion System

School of Astronautics, Northwestern Polytechnical University (NWPU), 127-Youyi Xilu, Xi'an 710072, China

Received 20 June 2011; Accepted 14 September 2011

Academic Editor: Alex Elias-Zuniga

Copyright © 2011 Muhammad Aamir Raza and Wang Liang. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


This paper proposes a robust design optimization methodology under design uncertainties of an aerospace vehicle propulsion system. The approach consists of 3D geometric design coupled with complex internal ballistics, hybrid optimization, worst-case deviation, and efficient statistical approach. The uncertainties are propagated through worst-case deviation using first-order orthogonal design matrices. The robustness assessment is measured using the framework of mean-variance and percentile difference approach. A parametric sensitivity analysis is carried out to analyze the effects of design variables variation on performance parameters. A hybrid simulated annealing and pattern search approach is used as an optimizer. The results show the objective function of optimizing the mean performance and minimizing the variation of performance parameters in terms of thrust ratio and total impulse could be achieved while adhering to the system constraints.