Robust Design Optimization of an Aerospace Vehicle Prolusion System

<table class="table-group" width="800px"><tr class="fig-image" id="a"><td><img alt="145692.fig.006a" src="https://static.hindawi.com/articles/mpe/volume-2011/145692/figures/145692.fig.006a.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(a) </b>Average thrust ratio</td></tr></table></td></tr><tr class="fig-image" id="b"><td><img alt="145692.fig.006b" src="https://static.hindawi.com/articles/mpe/volume-2011/145692/figures/145692.fig.006b.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(b) </b>Total impulse</td></tr></table></td></tr><tr class="fig-image" id="c"><td><img alt="145692.fig.006c" src="https://static.hindawi.com/articles/mpe/volume-2011/145692/figures/145692.fig.006c.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(c) </b>Maximum boost pressure</td></tr></table></td></tr><tr class="fig-image" id="d"><td><img alt="145692.fig.006d" src="https://static.hindawi.com/articles/mpe/volume-2011/145692/figures/145692.fig.006d.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(d) </b>Propellant mass</td></tr></table></td></tr></table>

<table>Percentile difference plots of performance parameters.</table>

Mathematical Problems in Engineering

fig6

Figure 6

Figure 6: Robust Design Optimization of an Aerospace Vehicle Prolusion System 