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-preview.hindawi.com/articles/ijae/volume-2021/5574436/figures/5574436.fig.007a.svgz" name="5574436.fig.007a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>1-chamber HRM</td></tr><tr class="fig-image" id="b"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/5574436/figures/5574436.fig.007b.svgz" name="5574436.fig.007b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>4-chamber HRM</td></tr></table>

<div>Different types of HRM in the 1st/2nd stage of SLV: (a) 1-chamber HRM; (b) 4-chamber HRM.</div>

International Journal of Aerospace Engineering

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Figure 7

Figure 7: Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle 