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.0016a.svgz" name="5574436.fig.0016a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>Theoretical and actual velocity increment</td></tr><tr class="fig-image" id="b"><td><object data="https://static.hindawi.com/articles/ijae/volume-2021/5574436/figures/5574436.fig.0016b.svgz" name="5574436.fig.0016b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>Theoretical and actual velocity distribution ratio</td></tr></table>

<div>Velocity increment and velocity distribution ratio: (a) theoretical and actual velocity increment; (b) theoretical and actual velocity distribution ratio.</div>

International Journal of Aerospace Engineering

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Figure 16

Figure 16: Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle 