Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

<table class="figure-group"><tr class="fig-image" id="a"><td><object data="https://static.hindawi.com/articles/ijae/volume-2021/5574436/figures/5574436.fig.006a.svgz" name="5574436.fig.006a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>Chamber pressure</td></tr><tr class="fig-image" id="b"><td><object data="https://static.hindawi.com/articles/ijae/volume-2021/5574436/figures/5574436.fig.006b.svgz" name="5574436.fig.006b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>Thrust</td></tr></table>

<div>Experimental and predicted curves: (a) chamber pressure; (b) thrust.</div>

International Journal of Aerospace Engineering

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Figure 6

Figure 6: Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle 