Analysis of a Hybrid Rocket Burn Using Generalized Compressible Flow

<p>The analysis of square ports in a hybrid rocket is simple when compared to other complicated port geometries such as a wagon wheel configuration. In the present work, fuel grains with several ports in a hybrid rocket engine are analyzed by transforming the ports into equivalent square ports. As an example, the internal ballistics of a hybrid rocket with circular ports is analyzed by transforming it to an equivalent solid grain with square ports having the same amount of solid fuel and burn time. The results obtained are similar to that of circular port but with a slight decrease in oxidizer to fuel (O/F) ratio and decrease in web thickness. The volumetric efficiencies for different number of square ports are determined assuming a constant mass of solid fuel. The variation of the flow properties along the axial length of the port are calculated using a generalized one-dimensional compressible flow analysis. The combined effects of wall mass injection and heat addition are taken into account.</p>

Name thesis:degree_name

Master of Science in Aerospace Engineering

Level thesis:degree_level

Thesis - Open Access

Discipline thesis:degree_discipline

Aerospace Engineering

Year

2015

Author dc:creator

• Uddanti, Naveen Sri

• hybrid rockets
• compressible flow
• Aerospace Engineering

Repository record dc:identifier

https://commons.erau.edu/edt/285

OAI identifier oai:identifier

oai:commons.erau.edu:edt-1284